System Specifications

0258-EX-ST-2003 Text Documents

Advanced Navigation & Positioning Corp.

2003-09-30ELS_63123

System Design Specification – Milestone #29 ANPC

ENGINEERING CHANGE ORDER RECORD
SYSTEM SPECIFICATION

Document No. 010-00057 – REV -

REVISION
ISSUE DATE REVISION DESCRIPTION ECO #
LEVEL
- 06/30/03 INITIAL RELEASE 1739

Document No. 010-00057 - Rev - 2

System Design Specification – Milestone #29 ANPC

3-5.1 Maintenance Interface Unit (MIU) .................................................................................................26
3-5.2 Oscilloscope....................................................................................................................................27
3-5.3 Monitor ...........................................................................................................................................28
3-5.4 Keyboard.........................................................................................................................................28
3-5.5 Interface Control .............................................................................................................................28
3-6 Central Processing Units.................................................................................................................28
3-6.1 CPU 1..............................................................................................................................................28
3-6.2 CPU2...............................................................................................................................................29
3-6.3 Memory...........................................................................................................................................29
3-6.4 Motherboard....................................................................................................................................29
3-6.5 Operating System............................................................................................................................29
3-6.6 Peripherals.......................................................................................................................................29
3-6.7 Hard Drive ......................................................................................................................................29
3-6.8 Floppy Drive ...................................................................................................................................29
3-6.9 CD-ROM Drive ..............................................................................................................................29
3-6.10 Network Adapter.............................................................................................................................29
3-6.11 Input / Output..................................................................................................................................29
3-6.12 Mounting.........................................................................................................................................30
3-7 Local Area Network........................................................................................................................30
3-7.1 Network Topology ..........................................................................................................................30
3-7.2 Main Switch ....................................................................................................................................30
3-7.3 Remote Control Unit (RCU) Hub ...................................................................................................30
3-7.4 Interconnectivity .............................................................................................................................30
3-8 Remote Control Unit (RCU) ...........................................................................................................30
3-8.1 Central Processing Unit (CPU) .......................................................................................................30
3-8.2 Memory...........................................................................................................................................30
3-8.3 Motherboard....................................................................................................................................30
3-8.4 Operating System............................................................................................................................30
3-8.5 Peripherals.......................................................................................................................................30
3-8.6 Hard Drive ......................................................................................................................................31
3-8.7 Floppy Drive ...................................................................................................................................31
3-8.8 CD-ROM Drive ..............................................................................................................................31
3-8.9 Network Adapter.............................................................................................................................31
3-8.10 Input / Output..................................................................................................................................31
3-9 Power Requirements .......................................................................................................................31
3-9.1 Power Input.....................................................................................................................................31
3-9.2 Uninterruptible Power Supply/Battery Pack ...................................................................................31
3-9.3 Interface Control .............................................................................................................................31
3-10 Uplink Assembly ............................................................................................................................32
3-10.1 Guidance Transmitter Unit (GTU)..................................................................................................32
3-10.2 RF Output – Glide Slope.................................................................................................................32
3-10.3 Monitor Functions...........................................................................................................................33
3-10.4 Uplink Antennas .............................................................................................................................33
3-10.5 Glide Slope Transmission ...............................................................................................................34
3-10.6 Interface Control .............................................................................................................................35
3-10.7 Placement/Polarization....................................................................................................................35
3-10.8 Monitoring ......................................................................................................................................35
3-11 Interrogation Assembly...................................................................................................................35
3-11.1 Antennas .........................................................................................................................................36
3-11.2 Interrogation Rate and Switching....................................................................................................37
3-11.3 Interrogation Transmitters...............................................................................................................38
3-11.4 Interface Control .............................................................................................................................39
3-11.5 Placement........................................................................................................................................39
3-12 Azimuth Sensor Assembly (ASA) ..................................................................................................39
3-12.1 Antennas .........................................................................................................................................39
3-12.2 Antenna Mounting ..........................................................................................................................39

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System Design Specification – Milestone #29 ANPC

3-12.3 Antenna Placement .........................................................................................................................39
3-12.4 Angle of Arrival Sensor ..................................................................................................................39
3-12.5 Health Monitors ..............................................................................................................................45
3-12.6 Interface Control .............................................................................................................................46
3-12.7 Placement........................................................................................................................................46
3-13 Elevation Sensor Assembly (ESA) .................................................................................................46
3-13.1 Antennas .........................................................................................................................................46
3-13.2 Antenna Mounting ..........................................................................................................................46
3-13.3 Antenna Separation/Placement .......................................................................................................46
3-13.4 Angle of Arrival Sensor ..................................................................................................................46
3-13.5 Interface Control .............................................................................................................................47
3-13.6 Switching ........................................................................................................................................47
3-14 Built in Test Equipment (BITE)......................................................................................................47
3-14.1 Antennas .........................................................................................................................................47
3-14.2 Built In Test Equipment (BITE) Generator.....................................................................................47
3-14.3 Interface Control .............................................................................................................................48
3-15 Environment....................................................................................................................................48
3-15.1 Temperature ....................................................................................................................................48
3-15.2 Humidity .........................................................................................................................................48
3-15.3 Wind................................................................................................................................................49
3-15.4 Ice....................................................................................................................................................49
3-15.5 Altitude ...........................................................................................................................................49
3-15.6 Vibration .........................................................................................................................................49
3-15.7 Shock ..............................................................................................................................................49
3-15.8 Environmental Control Unit............................................................................................................49
3-16 System Siting ..................................................................................................................................50
3-16.1 Siting Procedure..............................................................................................................................50
3-16.2 Terrain Gradient Requirements.......................................................................................................54
3-17 Error Budget....................................................................................................................................54
3-17.1 Main Runway Error Budget ............................................................................................................54
3-17.2 Reciprocal Runway Error Budget ...................................................................................................55
3-18 Critical and Sensitive Areas ............................................................................................................56
3-18.1 Main Runway Service Critical Area ...............................................................................................58
3-18.2 Reciprocal Runway Service Critical Area ......................................................................................60
SECTION 4 Software Specifications Rhino II ....................................................................................................62
4-1 Software Configuration Items .........................................................................................................62
4-2 Base CPU1/CPU2 Software Configuration Items Description .......................................................62
4-2.1 System Manager Process ................................................................................................................64
4-2.2 Network Communications Processes ..............................................................................................64
4-2.3 Signal Processing Process...............................................................................................................64
4-2.4 Uplink Process ................................................................................................................................66
4-2.5 RCU Manager Process ....................................................................................................................66
4-2.6 Log Manager Process......................................................................................................................66
4-2.7 Maintenance Interface Manager Process.........................................................................................66
4-2.8 Sensor Software Configuration Items Description..........................................................................66
4-2.9 Remote Control Unit Software Configuration Items Description ...................................................66
4-2.10 Maintenance Interface Software Configuration Items Description.................................................67
SECTION 5 Safety ..............................................................................................................................................68
5-1 HERO..............................................................................................................................................68
5-2 HERP ..............................................................................................................................................68
SECTION 6 Maintainability................................................................................................................................69
6-1 Mean Time To Repair (MTTR) ......................................................................................................69
6-1.1 Maximum Repair Time (MMAX) ..................................................................................................69
6-1.2 Scheduled Maintenance ..................................................................................................................69

Document No. 010-00057 - Rev - 5

System Design Specification – Milestone #29 ANPC

6-1.3 Periodicity .......................................................................................................................................69
6-2 Level of Maintainability..................................................................................................................69
6-3 Special Tools and Test Equipment..................................................................................................69
6-3.1 Equipment Handling .......................................................................................................................69
6-3.2 Cable and Wire Marking.................................................................................................................69
6-3.3 Cable Connections and Cable Slack ...............................................................................................69
6-3.4 Panels, Handles and Fastener Standard...........................................................................................69
6-3.5 Wire and Pin Designations..............................................................................................................69
6-3.6 CaNDI Markings.............................................................................................................................70
6-3.7 Name Plate Data .............................................................................................................................70
6-4 Safety Warning Labels....................................................................................................................70
6-5 Human Engineering ........................................................................................................................70
6-6 Weather Proofing and Air Flow Filtering .......................................................................................70
6-7 Built In Test Equipment (BITE) .....................................................................................................70
6-8 Re-Certification Requirements........................................................................................................70
SECTION 7 Materials And Processes .................................................................................................................71
7-1 Hazardous Materials Utilized..........................................................................................................71
7-1.1 Paint Used/Required .......................................................................................................................71
7-1.2 Flammability Of Materials..............................................................................................................71
7-2 Recycled Vice Virgin Materials......................................................................................................71
SECTION 8 Logistics..........................................................................................................................................72
8-1 Maintenance Concept......................................................................................................................72
8-1.1 On Line ...........................................................................................................................................72
8-1.2 Off Line...........................................................................................................................................72
8-2 Overhaul Periods/Hours..................................................................................................................72
8-3 Tools And Test Equipment .............................................................................................................72
8-4 Dimensions .....................................................................................................................................72
8-4.1 Weights ...........................................................................................................................................72
8-4.2 Appearances....................................................................................................................................72
8-4.3 Workmanship..................................................................................................................................72
SECTION 9 Methods Of Verification .................................................................................................................73
9-1 Analysis ..........................................................................................................................................73
9-2 Demonstration.................................................................................................................................73
9-3 Examination ....................................................................................................................................73
9-3.1 Functional tests ...............................................................................................................................73
9-4 No formal testing will be associated with the Technical Demonstration. .......................................73
9-4.1 Methods of Verification ..................................................................................................................73
9-5 Classes of Verifications ..................................................................................................................73
9-6 Inspections and tests........................................................................................................................73
9-6.1 Visual inspections ...........................................................................................................................73
9-6.2 Functional tests ...............................................................................................................................73
9-7 Requirement/Verification Cross-Reference Matrix ........................................................................73
SECTION 10 GLOSSARY ...................................................................................................................................93
SECTION 11 ACRONYMS AND ABBREVIATIONS .......................................................................................94

Document No. 010-00057 - Rev - 6

System Design Specification – Milestone #29 ANPC

Table 1 Secondary Tracking Coverage Volume Requirements ...............................................................................16
Table 2 Secondary Tracking Accuracy Requirements.............................................................................................16
Table 3 Guidance Coverage Volume Requirements ................................................................................................18
Table 4 Reciprocal Runway Guidance Accuracy Requirements .............................................................................21
Table 5 Localizer Antenna Specifications ...............................................................................................................33
Table 6 Localizer Transmit Antenna Characteristics...............................................................................................34
Table 7 Glide Slope Antenna Specifications ...........................................................................................................34
Table 8 Glide Slope Transmit Characteristics .........................................................................................................35
Table 9 Interrogator Uni directional Antenna Specifications ..................................................................................36
Table 10 Interrogator Omni-directional Antenna Specifications .............................................................................37
Table 11 Interrogation Pattern per Second...............................................................................................................37
Table 12 Interrogations and Suppression Pairing ....................................................................................................38
Table 13 ASA Antenna Specifications ....................................................................................................................39
Table 14 Low Input Phase Control ..........................................................................................................................40
Table 15 Log Accuracy............................................................................................................................................42
Table 16 ESA Antenna Specifications.....................................................................................................................46
Table 17 Main Runway ASA Error Budget.............................................................................................................55
Table 18 Main Runway ESA Error Budget .............................................................................................................55
Table 19 Reciprocal Runway ASA Error Budget ....................................................................................................55
Table 20 Reciprocal Runway ESA Error Budget ....................................................................................................56
Table 21 Secondary Tracking Error Budget ............................................................................................................56
Table 22 The Five Software Configuration Items....................................................................................................62
Table 23 Requirement/Verification Cross-Reference Matrix ..................................................................................74

Document No. 010-00057 - Rev - 8

System Design Specification – Milestone #29 ANPC

Under guidance from Headquarters of Marine Corps and Marine Corps Warfighting Laboratory, ANPC is
augmenting the capabilities of the Rhino system resulting in the Rhino II. A Cooperative Agreement has been
established to fund this development, which is being managed by Naval Air Warfare Center Aircraft Division
(NAWCAD).

The government expressed interest in a Rhino-type system that is augmented to provide 360o tracking, provide
guidance to reciprocal runways, and track multiple aircraft on final approach. Rhino II shall display aircraft position
and guidance information on up to 5 monitors serving one approach controller and four GCA controllers. Secondary
Tracking shall provide position and transponder information on all Cooperating Aircraft up to a 20-mile radius of
airspace centered on the Rhino II site.

Document No. 010-00057 - Rev - 10

System Design Specification – Milestone #29 ANPC

1-3 Applicable Documents

1-3.1 Government Documents
The following documents of the exact issue shown form a part of this specification to the extent specified herein. In
the event of conflict between the documents referenced herein and the contents of this specification, the contents of
this specification shall be considered a superseding requirement

Code of Federal Regulations, Title 14, Aeronautics and Space, Parts 140 to 199; 1993 edition.

Code of Federal Regulations, Title 47 Telecommunications, Part 15 Radio Frequency Devices, United States Federal
Communications Commission, October 1991.

Code of Federal Regulations, Title 47 Telecommunications, Part 87 Aviation Services, United States Federal
Communications Commission, October 1990.

Code of Federal Regulations, Title 14 Federal Aviation Regulations, Part 171: Non-Federal Navigation Facilities,
September 1992.

Federal Aviation Administration Specification, G-2100F, the Electronic Equipment, General Requirements
Specification, December 06, 1993.

Mil-Std-461C, Electromagnetic Emission and Susceptibility Requirements for the Control of Electromagnetic
Interference, August 4, 1986.

Mil- Std-810E, Environmental Test Methods and Engineering Guidelines, Revised February 9, 1990.

Mil-HDBK-454, General Guidelines for Electronic Equipment, Guideline 1, Safety Design Criteria, April 28, 1995.

Mil-Std-1366C, Transportability Criteria, February 27, 1992.

Mil-F-14072, Military Specification Finishes for Ground Based Electronic Equipment, October 4, 1990.

Mil-P-9503B, Paint, rubber and rigid and air supported radome, September 30, 1986.

Mil-Std-808, Finish, materials and processes for corrosive prevention and control in support equipment, July 18,
1996.

Federal Aviation Administration Advisory Circular, Change 4 to Airport Design 150/5300-13, November 10, 1994

Document No. 010-00057 - Rev - 11

System Design Specification – Milestone #29 ANPC

1-3.2 Non-Government Documents
The following documents of the exact issue shown form a part of this specification to the extent specified herein. In
the event of conflict between the documents referenced herein and the contents of this specification, the contents of
this specification shall be considered a superseding requirement.

International Standards and Recommended Practices and Procedures for Air Navigation Services: Aeronautical
Telecommunications, Annex 10 to the Convention on International Civil Aviation; Volume I, Part I - Equipment and
Systems; International Civil Aviation Organization; Fourth Edition of Volume I - April 1985.

International Standards and Recommended Practices: Aerodromes, Annex 14 to the Convention on International
Civil Aviation; Volume I-- Aerodrome Design and Operations; International Civil Aviation Organization; First
Edition -- July 1990.

ANPC. Rhino II Software Development Plan, Document No. 010-00006-B.

ANPC. System Specification for the Transponder Landing System, Document No. 010-00007-D.

ANPC Letter to AND-520 entitled “Preliminary Design for Rhino II Level B Design Assurance”, February 5, 1997.
International Standards and Recommended Practices and Procedures for Air Navigation Services: Aeronautical
Telecommunications, Annex 10 to the Convention on International Civil Aviation; Volume I, Part I -- Equipment
and Systems; International Civil Aviation Organization; Fourth Edition of Volume I, April,1985.

International Standards and Recommended Practices: Aerodromes, Annex 14 to the Convention on International
Civil Aviation; Volume I -- Aerodromes Design and Operations; International Civil Aviation Organization; First
Edition, July, 1990.

Software Considerations in Airborne Systems and Equipment Certification, Document No. RTCA/DO-178B,
December 1, 1992.

Certification Considerations for Highly Integrated or Complex Aircraft Systems, ARP 4754, Systems Integration
Requirements Task Group, Society of Automotive Engineers, 1996.

Guidelines and Methods for Conducting the Safety Assessment Process on Civil Airborne Systems and Equipment,
ARP 4761, S-18 Committee, Society of Automotive Engineering, 1996.

1-4 Order Of Precedence
In the event of a conflict between text of this specification and any references cited herein, the text of this
specification takes precedence. Nothing in this specification however supercedes applicable laws and regulations,
unless a specific exception has been obtained.

Document No. 010-00057 - Rev - 12

System Design Specification – Milestone #29 ANPC

Built-in-Test Aircraft UHF/VHF Uplink
Equipment
(BITE) Interrogator
1090 MHz
1030 MHz
BITE
Generator

1090 MHz RF RF
Switch Switch
Azimuth Sensor Elevation
Assembly (ASA) Sensor
Assembly
Interrog
(ESA)
Transmitter

Interrog
Sensor RF Sensor Transmitter
Switch
Network
Panel CPU1
GTU
CPU2

Display Hub Display MIU

Keyboard
Display Display Display
Monitor
Remote Control Unit (RCU) Equipment Rack

Figure 1 Rhino II Block Diagram

2-3.1 Transponder Interrogation
A transponder interrogation signal shall be transmitted to the landing aircraft at a periodic rate. The transponder
interrogation signal shall be equivalent to that which would be produced by a secondary surveillance radar system
with Mode A/C capabilities as specified in the International Civil Aviation Organization (ICAO) publication
Convention on International Civil Aviation Annex 10.

2-3.1.1 Interrogation Volume
The interrogation volume differs between Secondary Track, Main Runway, and Reciprocal Runway functions and is
described individually.

2-3.1.2 Interrogation Radiated Power
The radiated power of the interrogation transmission shall be ≥ -86 dBW/m2 (peak power) throughout the
interrogation volume. The radiated amplitude of P3 shall be within 1 dB of the radiated amplitude of P1 at any point
throughout the interrogation volume. The radiated amplitude of P2 shall allow transponder interrogation within the
coverage volume.

Document No. 010-00057 - Rev - 14

System Design Specification – Milestone #29 ANPC

2-3.2 Secondary Tracking

2-3.2.1 Service Volume
The system shall track all cooperative targets that are in line of sight of the antennas and within the coverage
volume. The secondary tracking coverage volume shall at least encompass the regions illustrated in Figure 2 and 3
and as listed in Table 1.

20 nm

Main approach

System
Footprint

Figure 2 Secondary Tracking Service Volume in Azimuth

10,000 ft

20 nm

System
Footprint

Figure 3 Secondary Tracking Service Volume in Elevation

Document No. 010-00057 - Rev - 15

System Design Specification – Milestone #29 ANPC

Table 1 Secondary Tracking Coverage Volume Requirements

Parameter Requirements
Azimuth Omni-directional surrounding the system
Altitude 0° to 90° from horizontal
Range Touchdown to 20 nm
Maximum Coverage Altitude 10,000 Feet

2-3.2.1.1 Service Volume Transition Zones
Tracks of aircraft position shall be upgraded from secondary to approach tracking or downgraded from approach to
secondary tracking within the transition zone depicted in Figure 4.

SECONDARY
TRANSITION ZONE TRACKING
~5° WIDE

RUNWAY

APPROACH 10° 10° APPROACH
TRACKING COURSE LINE TRACKING
& &
GUIDANCE 10° 10° GUIDANCE

SECONDARY
TRACKING

Figure 4 Coverage Volume Relationship And Transitional Zones

2-3.2.2 Accuracy
The distance and azimuth accuracy requirements are indicated for the system in Table 2 and shall meet or exceed
ICAO Annex 10 Volume 1 section 3.2 (Surveillance Radar Element). The accuracy requirements for secondary
tracking are indicated in Table 2.

Table 2 Secondary Tracking Accuracy Requirements

Parameter Requirements
Azimuth Within 2 degrees of true position, 2 sigma
Altitude ±100 ft of true aircraft altitude (within Mode C spec)
Range Within 5% of aircraft range or 490', whichever is greater

Document No. 010-00057 - Rev - 16

System Design Specification – Milestone #29 ANPC

2-3.2.2.1 Azimuth Accuracy
The indication of position in azimuth shall be within plus or minus 2 degrees of true position. It shall be possible to
resolve the positions of two aircraft, which are at 4 degrees of azimuth of one another.

2-3.2.2.2 Range Accuracy
The error in range indications shall not exceed 5 per cent of the true range, or 150 meters, whichever is greater. It
shall be possible to resolve the positions of two aircraft that are separated by a distance of 1 per cent of the true
distance from the point of observation or 230 meter, whichever is the greater.

2-3.2.3 Tracking
The Rhino II shall utilize a Kalman filter algorithm to estimate the horizontal position of all aircraft replying to
interrogations described herein.

2-3.2.4 Monitoring
BITE functions shall be able to detect failure conditions that would result in secondary track errors beyond
permissible limits.

2-3.3 Main Runway Service

2-3.3.1 Service Volume
The ILS guidance coverage volume shall at least encompass the area illustrated in Figures 5 and 6 and indicated in
Table 3.

18 nm

Point C

10o Approach Direction

10o

Figure 5 Main Runway Localizer Coverage in Azimuth

Document No. 010-00057 - Rev - 17

System Design Specification – Milestone #29 ANPC

Approach Direction

10,000 ft
Threshold

7.0o
0.75o

18 nm

Figure 6 Main Runway Localizer Coverage in Elevation

Table 3 Guidance Coverage Volume Requirements

Parameter Requirements
Azimuth ±10 degrees on either side of approach centerline
Altitude 1 degree to 7 degrees above horizontal
Range Touchdown to 18 nm
Decision Height 200 feet

2-3.3.2 Accuracy

2-3.3.2.1 Localizer Course Alignment
The mean course line shall not deviate from the runway centerline by more than ± 35 ft. or the linear equivalent of
0.3 degree (0.015 DDM), whichever is less.

2-3.3.2.2 Localizer Displacement Sensitivity
The nominal displacement sensitivity shall correspond to a DDM of 0.155 at angular displacements of 3.0 degrees ±
0.5 degrees on both sides of the center course line. The increase of DDM shall be substantially linear with respect to
angular displacement from the course line (where DDM is zero) to an angle on either side of the course line where
the DDM is 0.180. From that angle to ± 35 degrees, the DDM shall not be less than 0.180 as illustrated in Figure 7.

Document No. 010-00057 - Rev - 18

System Design Specification – Milestone #29 ANPC

DDM > 0.180
DDM = 0.180

Localizer Apparent
Emanation Point
DDM = 0.155

35o
Linear Change
6o + 1o
DDM = 0.00

35o

DDM = 0.155

DDM = 0.180
DDM > 0.180

Figure 7 DDM and Displacement Sensitivity

2-3.3.2.3 Localizer Course Structure
Structure in the course line shall not have amplitudes that exceed the following:

Outer limit of coverage to ILS point A - 0.031 DDM (0.6 deg)
Decreasing at a linear rate from 0.031 DDM (0.6 deg) at point A to 0.015 DDM (0.3 deg) at ILS point B
ILS point B to ILS point C - 0.015 DDM (0.3 deg)

2-3.3.3 Interrogation Requirements
The Rhino II shall provide an interrogation rate of 10Hz within the Main Runway Service volume described above
in Figures 5 and 6.

2-3.3.4 Tracking
The Rhino II shall accomplish the aircraft tracking function by using transponder reply measurements of the time-
of-arrival and angle-of-arrival.

2-3.3.5 Guidance
A localizer signal shall be transmitted to the landing aircraft corresponding to the most recent guidance correction
computed by the system. The localizer shall be equivalent to that which would be produced by a standard VHF
localizer as specified in ICAO Annex 10, paragraph 3.1.3 and specified below, with the exception that these signal
properties shall apply at the position of the tracked aircraft only.

2-3.3.6 Monitoring
BITE functions shall be able to detect failure conditions that would result in Main Runway Service errors beyond
permissible limits.

Document No. 010-00057 - Rev - 19

System Design Specification – Milestone #29 ANPC

2-3.4 Reciprocal Runway Service

2-3.4.1 Service Volume
Reciprocal Runway Service volume is illustrated in Figures 8 and 9.

6 nm

Point C

10o Approach Direction

10o

Figure 8 Reciprocal Runway Localizer Coverage in Azimuth

Approach Direction

10,000 ft
Threshold

7.0o
0.75o

6 nm

Figure 9 Reciprocal Runway Localizer Coverage in Elevation

2-3.4.2 Accuracy
The accuracy requirements for both the VHF/UHF and GCA guidance are listed in Table 4

Document No. 010-00057 - Rev - 20

System Design Specification – Milestone #29 ANPC

Table 4 Reciprocal Runway Guidance Accuracy Requirements

Parameter Requirements
Azimuth ±15 ft from centerline, or ±0.3°, whichever is greater
Altitude 0.3 degrees
Range ±250 ft
Decision Height 300 feet

2-3.4.3 Glide Slope Displacement Sensitivity
The nominal displacement sensitivity shall correspond to a DDM of 0.0875 at angular displacements of 0.35
degrees ± 0.07 degrees above and below the glide path. The angular displacement sensitivity shall be maintained
as symmetrical as practicable and within ± 25% of the nominal.
The increase of DDM shall be linear with respect to angular displacement from the glide path (where DDM is zero)
to an angle on either side of the glide path where the DDM is 0.220. From that angle to edges of the glide slope
coverage volume, the DDM shall not be less than 0.220 as illustrated in Figure 10.

DDM = 0.220
DDM > 0.220
DDM = 0.0875

Linear DDM = 0.00
Change
0.70o + .14o DDM = 0.0875

DDM = 0.220

DDM > 0.220

Touchdown 0.75o Glideslope 7.0o

Figure 10 Glide Slope Displacement Sensitivity

2-3.4.4 Interrogation Requirements
The Rhino II shall provide an interrogation rate of 10 Hz within the Reciprocal Runway Service volume described
above in Figures 8 and 9.

2-3.4.5 Tracking
The Rhino II shall utilize a Kalman filter algorithm to estimate the horizontal position of all aircraft replying to
interrogations described herein.

Document No. 010-00057 - Rev - 21

System Design Specification – Milestone #29 ANPC

2-3.4.6 Guidance
The glide slope signal shall be equivalent to that which would be produced by a standard UHF glide path system as
specified in ICAO Annex 10, paragraph 3.1.5 and specified below, with the exception that these signal properties
shall apply at the position of the tracked aircraft only.

2-3.4.7 Monitoring
BITE functions shall be able to detect failure conditions that would result in Reciprocal Runway service errors
beyond permissible limits.

2-4 Capability Interface
The system shall switch from Main Runway end to Reciprocal Runway end, or vice versa, within 5 minutes. The
mechanism for switching runway ends shall not include any rotating, moving, or re-installing any of the antenna
arrays.

2-5 Logistics /Transportation

2-5.1 Rhino II Vehicle
An M1097 HMMWV shall be used as the Rhino II system prime mover. The operational characteristics of the
M1097 HMMWV shall not be degraded by the integration/addition of system hardware. The Rhino II shall support
transport of 2 persons in the HMMWV vehicle. No persons shall be permitted to occupy the Rhino II shelter or
trailer during transport operations.

2-5.2 Rhino II Shelter
The M1097 HMMWV Shelter shall provide housing for critical elements of the Rhino II system. The shelter when
installed shall conform to the size requirements in Sub-section 2-6.4.

2-5.3 Rhino II Trailer
An M1101 high mobility trailer (HMT) or equivalent (including commercial options) shall be used to transport
Rhino II elements.

2-5.4 Rhino II Highway Transport
The Rhino II vehicle including the towed trailer shall meet all highway regulations for transportation on highways
across the United States. The Rhino II shall also be capable of traversing terrain with a slope gradient of 40 percent.
The Rhino II vehicle in its ground transport configuration shall not exceed the following outside dimensions:

Height 13.1 feet
Length 35.0 feet
Width 8.0 feet

2-5.5 Rhino II Aircraft Transport
The Rhino II shall be transportable via military aircraft on a single C-130, a C-141, or a C-5A. The vehicle and
trailer shall have the necessary tie downs for transport. Weight and center of gravity shall be clearly marked for the
transport configuration. Rhino II components shall withstand air transportation up to 50,000 feet above sea level
(unpressurized). The Rhino II vehicle in its air transport configuration shall not exceed the following outside
dimensions:

Height 8.5 feet
Length 35.0 feet
Width 8.0 feet

2-5.6 Rhino II Transport Configurations
The dimensions for a single vehicle provided in MIL-STD-1366 shall be used for guidance for ground and air
shipment. Component disassembly may be utilized to accommodate overhead clearances during system transport.

Document No. 010-00057 - Rev - 22

System Design Specification – Milestone #29 ANPC

Track shall consist of small dots displayed at the positions of the aircraft over the last 20 seconds. The “trail of dots”
gives the controller a visual indication of aircraft velocity. A heading vector indicating the predicted flight path of
the aircraft shall be displayed at the current position.

3-1.8.2 Guidance Track
The aircraft position shall be indicated by a crosshair display. Beside the crosshair, the transponder code and aircraft
MSL altitude shall be displayed. The altitude shall be displayed with three digits in units of 100 feet, i.e., 030 for
3000 feet, 292 for 29,200 feet, etc. The track history shall consist of small dots displayed at the positions of the
aircraft over the last 20 seconds. The “trail of dots” gives the controller a visual indication of aircraft velocity. A
heading vector indicating the predicted flight path of the aircraft shall be displayed at the current position.

3-1.9 Tooltips
On mouse-over of any particular aircraft, a “tool tip” shall appear that displays the aircraft’s transponder code range
in nautical miles to touchdown, ground speed, MSL altitude, and heading.

3-2 Lighting System Requirements

3-2.1 Shelter
Adequate adjustable illumination shall be provided to allow for operator monitor observations, the reading of maps
and small print as well as adequate illumination for maintenance activities.

3-2.2 Blackout Lighting
Blackout lighting requirements are to be determined.

3-2.3 Obstruction
Obstruction lighting shall be provided according to Federal Aviation Administration Regulations.

3-3 Communication System

3-3.1 Air to Ground
Air to Ground Communication Systems are to be determined.

3-3.2 Intercom
Intercom Systems are to be determined.

3-4 Calibration/Installation
A calibration procedure shall provide sufficient truth and system track data to compensate for sensor measurement
errors and terrain-induced multipath errors.

3-4.1 Truth Data
The truth data shall be provided by an optical tracking system. The truth data shall be compared with the system
track data to result in site-dependent, error compensation information.

3-4.2 Interface
An RF data link shall be used to connect the optical tracking system to the MIU.

3-5 Maintenance Interface Assembly

3-5.1 Maintenance Interface Unit (MIU)

3-5.1.1 CPU
The MIU shall have an Intel or AMD x86 processor with a minimum speed of 2.0 GHz.

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3-5.1.2 Memory
The MIU shall have a minimum of 512 MB of RAM and be compatible with the motherboard.

3-5.1.3 Motherboard
The MIU motherboard shall be compatible with the CPU and Hard Drive, and will contain a minimum of three PCI
interface slots.

3-5.1.4 Operating System
The MIU shall run Windows XP Professional.

3-5.1.5 Peripheral Configuration
All peripherals shall be compatible with Windows XP Professional.

3-5.1.6 Hard Drive
The MIU shall have a minimum hard drive capacity of 120 GB.

3-5.1.7 Floppy Drive
The MIU shall have one (1) 3.5-inch floppy drive accessible from the front panel.

3-5.1.8 CD-ROM Drive
The MIU shall have one CD-ROM drive accessible from the front panel.

3-5.1.9 Network Adapter
The MIU network adapter shall be a 10/100 MBPS Ethernet Network Adapter with a RJ-45 port.

3-5.1.10 Input / Output
The MIU shall have the following I/O: connections:

One (1) PS/2 keyboard port
One (1) PS/2 mouse port
One (1) VGA monitor port
One (1) bi-directional parallel port
One (1) RS-232 serial port
Two (2) external USB 2.0 ports

All connections shall be computer standard with appropriate securing mechanisms.

3-5.1.11 Input Power Electrical Requirements
The MIU shall run with 120 VAC ± 10%, 47 to 63 Hz single-phase power input.

3-5.1.12 Mean Time Between Failure
The MIU shall have a MTBF of greater than 100,000 hours @ 25 degrees Centigrade.

3-5.1.13 Physical Design
Provisions shall be made for the MIU to have a maximum depth of 25 inches and for mounting into a standard 19-
inch equipment rack.

3-5.2 Oscilloscope
Provisions shall be made for the mounting of an Oscilloscope into a standard 19-inch equipment rack.

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3-5.3 Monitor
The monitor shall have the performance capability of VGA or greater performance and be compatible with the video
adapter in the MIU CRT display. The monitor shall be mounted in a standard 19-inch equipment rack.

3-5.4 Keyboard
The keyboard shall be an ASCII standard keyboard mounted in a standard 19-inch equipment rack. Cabling shall
meet or exceed the current Mil Specification.

3-5.5 Interface Control

3-5.5.1 MIU to Network Panel
The MIU shall connect to the Network Panel by:

One (1) PS2 mouse cable
One (1) PS2 keyboard cable
One (1) VGA cable
One (1) Ethernet Cable

3-5.5.2 Monitor to Network Panel
The monitor shall connect to the Network panel by one (1) VGA cable.

3-5.5.3 Keyboard to Network Panel
The Keyboard shall connect to the Network Panel by:

One (1) PS2 mouse cable
One (1) PS2 keyboard cable

3-6 Central Processing Units

3-6.1 CPU 1
This section specifies the hardware and operating system requirements for CPU1.

3-6.1.1 CPU
CPU1 shall have an Intel or AMD x86 processor with a minimum speed of 2.0 GHz.

3-6.1.2 Memory
CPU1 shall have a minimum 256 MB of RAM.

3-6.1.3 Motherboard
The CPU1 motherboard shall provide a minimum of one ISA and three PCI interface slots.

3-6.1.4 Operating System
CPU1 shall run QNX version 4.25.

3-6.1.5 Peripherals
All peripherals shall be compatible with QNX 4.25.

3-6.1.6 Hard Drive
CPU1 shall have a minimum hard drive capacity of 20 GB.

3-6.1.7 Floppy Drive
CPU1 shall have one (1) 3.5-inch floppy drive accessible from the front panel.

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3-6.1.8 CD-ROM Drive
CPU1 shall have one CD-ROM drive accessible from the front panel.

3-6.1.9 Network Adapter
The CPU1 network adapter shall be a 10/100 MBPS Ethernet Network Adapter with a RJ-45 port.

3-6.1.10 Input / Output
CPU1 shall have at a minimum the following I/O connections:

One (1) PS/2 keyboard port
One (1) PS/2 mouse port
One (1) VGA monitor port
One (1) bi-directional parallel port
One (1) RS-232 serial port

3-6.1.11 Mounting
Provisions shall be made for the mounting of CPU 1 into a standard 19-inch rack.

3-6.2 CPU2
This section specifies the hardware and operating system requirements for CPU2.

3-6.2.1 CPU
CPU2 shall have an Intel or AMD x86 processor with a minimum speed of 2.0 GHz.

3-6.3 Memory
CPU2 shall have a minimum of 512 MB of RAM.

3-6.4 Motherboard
The CPU2 motherboard shall provide a minimum of three PCI interface slots.

3-6.5 Operating System
CPU2 shall run Windows NT 4.0 with Service Pack 5 or later.

3-6.6 Peripherals
All peripherals shall be compatible with Windows NT 4.0 Service Pack 5.

3-6.7 Hard Drive
CPU2 shall have a minimum hard drive capacity of 120 GB.

3-6.8 Floppy Drive
CPU2 shall have one (1) 3.5” floppy drive accessible from the front panel.

3-6.9 CD-ROM Drive
CPU2 shall have one CD-ROM drive accessible from the front panel.

3-6.10 Network Adapter
The CPU2 network adapter shall be a 10/100 MBPS Ethernet Network Adapter with a RJ-45 port.

3-6.11 Input / Output
CPU2 shall have at a minimum the following I/O connections:

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One (1) PS/2 keyboard port
One (1) PS/2 mouse port
One (1) VGA monitor port
One (1) bi-directional parallel port
One (1) RS-232 serial port

3-6.12 Mounting
Provisions shall be made for the mounting of CPU2 into a standard 19-inch equipment rack.

3-7 Local Area Network
A single 100 Mbps Ethernet LAN shall be used for network communications between computers.

3-7.1 Network Topology
The Ethernet LAN shall consist of the following components: a main Ethernet switch; a remote RCU switch;
computers connected to the switches; and cabling to connect the computers and switches. (Note that there is a
distinction between an Ethernet hub and an Ethernet switch. A hub is a repeater that indiscriminately broadcasts
messages to all connected nodes; a switch is a repeater that selectively re-distributes messages based on hardware
MAC address.) The system shall use switches, not hubs.

3-7.2 Main Switch
The main Ethernet switch shall provide a minimum of eight (8) 10/100 RJ-45 ports and a minimum of two (2)
10/100 fiber ports. At least one of the eight RJ-45 ports, or an additional RJ-45 port, shall allow a link connection to
the RCU Ethernet switch.

3-7.3 Remote Control Unit (RCU) Hub
The RCU Ethernet switch shall provide a minimum of eight (8) 10/100 RJ-45 ports. At least one of the eight RJ-45
ports, or an additional RJ-45 port, shall allow an uplink connection to the main Ethernet switch.

3-7.4 Interconnectivity
The MIU, CPU1 and CPU2 shall be connected to the main Ethernet switch using CAT-5 RJ-45 cabling. The sensors
shall be connected to the main Ethernet switch using 100 Mbps fiber. A CAT-5 cable shall be used to connect the
main Ethernet switch to the RCU Ethernet switch.

3-8 Remote Control Unit (RCU)
This section specifies the hardware and operating system requirements for the RCU. The RCU should be a laptop
computer.

3-8.1 Central Processing Unit (CPU)
The RCU shall have an Intel or AMD x86 processor with a minimum speed of 800 MHz.

3-8.2 Memory
The RCU shall have a minimum 512 MB of RAM.

3-8.3 Motherboard
The RCU shall be a laptop computer.

3-8.4 Operating System
The RCU shall run Windows 2000 or Windows XP.

3-8.5 Peripherals
All peripherals shall be compatible with Windows 2000 or Windows XP, as appropriate.

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3-8.6 Hard Drive
The RCU shall have a minimum hard drive capacity of 20 GB.

3-8.7 Floppy Drive
The RCU does not need a floppy drive.

3-8.8 CD-ROM Drive
The RCU shall have one CD-ROM drive.

3-8.9 Network Adapter
The RCU network adapter shall be a 10/100 Mbps Ethernet Network Adapter with an RJ-45 port.

3-8.10 Input / Output
The RCU shall have at a minimum the following I/O connections:

One (1) PS/2 keyboard port
One (1) PS/2 mouse port
One (1) VGA monitor port

3-9 Power Requirements

3-9.1 Power Input
The input power to the system shall be 240 VAC ± 10%, 47 to 63 HZ single-phase power.

3-9.2 Uninterruptible Power Supply/Battery Pack

3-9.2.1 Primary Input Power
The input power of the UPS shall be 240 VAC ± 10%, 47 to 63 HZ single-phase power.

3-9.2.2 Output Power
The output of the UPS shall be a minimum of 3 KVA at 120 VAC ±5%, 60 ± 2Hz.

3-9.2.3 Mean Time Between Failure
The MTBF of the UPS shall be greater than 50,000 hours @ 25 degrees Centigrade.

3-9.2.4 Battery Hold-Up Time
The battery pack shall provide a minimum of 20 minutes of operation at full load @ 25 degrees Centigrade.

3-9.3 Interface Control

3-9.3.1 Signal Entry Panel to UPS/Battery
The signal entry panel shall provide an external power source for the UPS.

3-9.3.2 UPS to shelter power
The UPS shall provide sufficient output power for shelter lighting and auxiliary power outlets for ancillary
equipment.

3-9.3.3 UPS to rack power
The UPS shall provide sufficient power for all rack-mounted components.

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3-10 Uplink Assembly
The Uplink Assembly shall consist of a Guidance Transmitter Unit, two sets of Uplink Antennas, and a
Main/Reciprocal Service RF Switch.

3-10.1 Guidance Transmitter Unit (GTU)
The GTU shall receive and measure samples of the transmitted GS and Loc signals and provide signal measurement
data to the CPUs via the control interfaces. The Monitor functions within the GTU shall be able to be tuned for
sample input levels between 20 and 50 dB below the transmitter output power levels. The measurement isolation
shall be such that when calculating DDM from carrier, 90 and 150 Hz tones, the maximum error shall be less than
.001 DDM.

3-10.1.1 RF Output – Localizer

3-10.1.2 Localizer Output Power
The carrier output power of the localizer signal shall be 24 dBm ± 2 dB into a 50 Ω load.

3-10.1.3 Localizer Carrier Frequency
The localizer shall operate in the band 108.10 MHz to 111.95 MHz. The localizer carrier frequency shall be
controllable via the computer interface to any of the allowable frequencies. See Table 12 for specific frequencies
authorized within this band. All specifications defined herein shall be met at any allowable output frequency. The
frequency variation of the carrier shall not exceed ± 0.002 %.

3-10.1.4 Localizer Carrier Modulation
When enabled, the localizer carrier shall be AM modulated, double side band, un-suppressed carrier with
modulation tones at 90 and 150 Hz. Guidance commands are conveyed by changing the relative % modulation
(difference of depth of modulation DDM) of these tones, without changing the sum of depth of modulation (SDM).

3-10.1.5 Localizer Depth of Modulation
With a transmitted Difference of Depth of Modulation (DDM) of 0.000, the depth of carrier modulation for each of
the 90 Hz and 150 Hz tones shall be within the limits of 18 and 22%. The Sum of Depth of Modulation (SDM) of
localizer modulation tones shall 40 ± 1 %. This SDM limit shall be met with DDM in the range of –0.180 to +0.180.

3-10.1.6 Localizer Modulation Control Resolution and Accuracy
The DDM of localizer modulation tones shall be controllable in DDM steps not larger than 0.0004 DDM. The
accuracy of localizer DDM shall be within 0.002 DDM for any DDM setting between –0.180 to +0.180 DDM.

3-10.2 RF Output – Glide Slope

3-10.2.1 Glide Slope Output Power
The carrier output power of the Glide Slope signal shall be 34 dBm ±2dB into a 50 Ω load.

3-10.2.2 Glide Slope Frequency
The glide slope transmission shall operate in the band 329.15 MHz to 335.00 MHz. The glide slope carrier
frequency shall be set to the frequency paired with the commanded localizer frequency. See Paragraph 3.4 for
specific frequency pairings. All specifications defined herein shall be met at any allowable output frequency. The
frequency variation of the carrier shall not exceed ± 0.002%.

3-10.2.3 Glide Slope Carrier Modulation
When enabled, the glide slope carrier shall be AM modulated, double side-band, un-suppressed carrier with
modulation tones at 90 and 150 Hz. Guidance commands are conveyed by changing the relative % modulation
(difference of depth of modulation DDM) of these tones, without changing the sum of depth of modulation (SDM).

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3-10.2.4 Glide Slope Depth of Modulation
With a transmitted Difference of Depth of Modulation (DDM) of 0.000, the depth of carrier modulation for each of
the 90 Hz and 150 Hz tones shall be within the limits of 38 and 42%. The Sum of Depth of Modulation (SDM) of
glide slope modulation tones shall 80 ± 1 %. This SDM limit shall be met with DDM in the range of -0.220 to
+0.220.

3-10.2.5 Glide Slope Modulation Control Resolution and Accuracy
The DDM of glide slope modulation tones shall be controllable in DDM steps not larger than 0.0005 DDM. The
accuracy of glide slope DDM shall be within 0.002 DDM for any DDM setting between –0.220 to +0220 DDM.

3-10.3 Monitor Functions

3-10.3.1 DDM Monitors
The GTU shall provide monitor data, via the CPU interfaces, so that the CPUs can monitor transmitted signal
modulation characteristics.

3-10.3.1.1 DDM Monitor Resolution
The RF monitor elements shall provide measurements of the carrier, 90 Hz, 150 Hz, and tone freq. band (loc only)
power levels. The measurement resolution shall be such that when calculating DDM from carrier, 90 and 150 Hz
tones, the bit error shall be less than .0005 DDM.

3-10.3.1.2 DDM Monitor Accuracy
The measurement isolation shall be such that when calculating DDM from carrier, 90 and 150 Hz tones, the
maximum error shall be less than .001 DDM.

3-10.4 Uplink Antennas
The localizer uplink antenna of the Uplink Antenna Assembly shall operate between 108-118 MHz and the glide
slope uplink antenna will operate between 328.6-335.4 MHz. FCC licensing is required to operate at this frequency.
There shall be two (2) identical sets of uplink antennas, one set established for Main Runway Service, the other set
established for Reciprocal Runway Service.

3-10.4.1 Localizer Antenna
The localizer antenna specifications shall be as indicated in Table 5.

Table 5 Localizer Antenna Specifications

Antenna Parameter Antenna Performance

Type Uni-directional
Polarization Horizontal
Gain, Main beam 7 dB/iso
Horizontal field pattern The radiation pattern in the horizontal plan has lobe not more than 80 degrees
wide at the half power points.

3-10.4.1.1 Localizer Antenna Power
The antenna EIRP output power level for the Localizer signal shall be 30 dBm (1.0 watts).

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3-10.4.1.2 Localizer Transmission
The requirements for the localizer transmission shall be:

Minimum field strength of –107 dBW/m2 on glide path between 10 nm from threshold and the point 200’
above threshold.
Minimum field strength of –114 dBW/m2 elsewhere in the coverage volume.
Receivable 2000’ above threshold at the ranges specified or 1000’ above the highest point, whichever is
higher (based on ICAO Annex 10 3.1.3.3.1). Using the maximum service volume range of 18 nm and
2000’ yields an elevation angle of 1.0°.

The lowest antenna gain occurs at the point 18 nm from threshold, 35 degrees azimuth off bore-site (off the
approach centerline), and at 0.75° elevation. The localizer transmit antenna characteristics are as summarized in
Table 6.

Table 6 Localizer Transmit Antenna Characteristics

Quantity Value
Transmitter Power (dBm) 24±2
Cable Loss (dB) 2
Peak Antenna Gain on Bore sight (dBi) +7
Antenna Gain at 35° azimuth (dBi) +3
Minimum EIRP at 35° azimuth (dBm) 23 (.2 watt)
Peak EIRP (dBm) 31

3-10.4.2 Glide Slope Antenna
The localizer antenna specifications shall be as indicated in Table 7.

Table 7 Glide Slope Antenna Specifications

Antenna Parameter Antenna Performance

Type Uni-directional
Polarization Horizontal
Gain, Main beam 7 dB/iso
Horizontal field pattern The radiation pattern in the horizontal plan has lobe not more than 80 degrees
wide at the half power points.

3-10.4.2.1 Glide Slope Antenna Power
The antenna EIRP output power level for the Glide Slope signal shall be 40 dBm (10.0 watts).

3-10.5 Glide Slope Transmission
The requirement for the glide slope transmission shall be minimum field strength of –95 dBW/m2 throughout the
glide slope coverage volume. The lowest antenna gain occurs at the point 10 nm, 8° azimuth off bore site (off the
approach centerline), and 0.75° elevations. The glide slope transmit antenna characteristics shall be as summarized
in Table 8.

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Table 8 Glide Slope Transmit Characteristics

Quantity Value

Transmitter Power (dBm) 34±2 (32 – 36)
Cable Loss (dB) 2
Peak Antenna Gain on Bore sight (dBi) +7
Antenna Gain at 35° azimuth (dBi) +6
EIRP at 35° azimuth (dBm) 36 (4.0 watts)
Peak EIRP (dBm) 41

3-10.6 Interface Control
Two parallel interface ports on the Modulation Generator board provide control and status access to both the Rhino
II base CPUs. The CPU interfaces are used to enable transmitter outputs, control the Difference of Depth of
Modulation (DDM) between the 90 and 150 Hz side tones, set the carrier frequency, and enable ID tones (localizer
only). Monitor and transmitter status data is available for the CPUs to read back.

As a key system safety component, the interface section includes compare logic which is used to verify that digital
control signals from the two CPUs match each other and are updated at a regular rate (updates at > 5 Hz). If a
mismatch or slow update rate are detected, this compare function disables the transmitter and provides diagnostic
status information to the CPUs.

3-10.7 Placement/Polarization
The emissions from the localizer shall be horizontally polarized. The vertically polarized component of the radiation
on the course line shall not exceed that which corresponds to a DDM error of .016 when an aircraft is positioned on
the course line and is on a roll attitude of 20 degrees from the horizontal. The emission from the glide path
equipment shall be horizontally polarized.

3-10.7.1 Antenna Clear Zone
No part of the assembly, or any structural elements that are part of the assembly may be placed within the signal
transmit path area of the mounted antenna. Therefore the area ± 55 degrees azimuth of the antenna bore-site shall be
kept clear of structural elements.

3-10.8 Monitoring
The GTU shall receive and measure samples of the transmitted GS and Loc signals and provide signal measurement
data to the CPUs via the control interfaces. The Monitor functions within the GTU shall be able to be tuned for
sample input levels between 20 and 50 dB below the transmitter output power levels. The measurement isolation
shall be such that when calculating DDM from carrier, 90 and 150 Hz tones, the maximum error shall be less than
.001 DDM.

3-11 Interrogation Assembly
There shall be five antennas, referred to as Front, Back, Left, Right and Center as indicated in Figure 10. The
antenna pattern in azimuth shall be as shown in Figure 11.

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Approach Direction

90o

Left

Omni-directional

Back Front
180o 0o

Right

270o

Figure 11 Front, Back, Left and Right Antenna Orientation

3-11.1 Antennas
There shall be five antennas, referred to as Front, Back, Left, Right, and Center Antenna.

3-11.1.1 Interrogator Uni directional Antenna Specifications
The Front, Back, Left, and Right Interrogation Antennas shall be all Uni-directional antennas, and shall function as
per the specifications in Table 9.

Table 9 Interrogator Uni directional Antenna Specifications

Antenna Parameter Antenna Performance

Azimuth coverage Uni-directional
Polarization Vertical
Gain, Main beam 9 dB/iso, main horizontal beam
Main beam elevation peak 10°±0.1° above the horizon
Vertical field pattern The radiation pattern in the vertical plan has lobe not more than
12 degrees wide at the half power points.
Horizontal field pattern The radiation pattern in the vertical plan has lobe not more than
90 degrees wide at the half power points.

3-11.1.2 Interrogator Omni-directional Antenna Specifications
The Center Antenna shall function as per the specifications in Table 10.

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Table 10 Interrogator Omni-directional Antenna Specifications

Antenna Parameter Antenna Performance

Azimuth coverage Omni-directional
Polarization RHCP
Gain, Main beam 6 dB/iso, main beam
Main beam elevation peak 90°±2° above the horizon
Vertical field pattern The radiation pattern in the vertical plan has a lobe not more
than 120 degrees wide at the half power points.

3-11.1.3 Antenna Mounting
The antennas shall be mounted with the main beams of the Front, Left, Back, and Right antennas at 0°, 90°, 180°,
and 270°, respectively, with 0° parallel to runway centerline and positive angles are counter clockwise. The Front
antenna shall be within ±5° of the desired orientation, and the other 3 antennas shall be within ±1° of their position
with respect to the Front antenna.

The Center antenna shall be mounted at the intersection of the lines between the Front / Back and the Left / Right
antennas.

The installation tolerance for antenna position with respect to vertical shall be ≤ 0.5 degrees. Assembly stability
shall be such that vertical level is maintained to the installation level ± 1.0 degrees.

3-11.2 Interrogation Rate and Switching
A nominal 10 Hz interrogation rate shall be utilized with system guidance tracks updated at a 5 Hz rate to maintain
the required accuracy. The surveillance tracks shall use a nominal 2 Hz interrogation rate. Since the Front antenna is
used to interrogate guidance and surveillance tracks and the other 4 antennas are used to interrogate surveillance
tracks, the interrogation rate shall be ≥ 18 Hz.

Therefore, the interrogation pattern per second shall be as indicated in Table 11:

Table 11 Interrogation Pattern per Second

Interrogation # Antenna

1 Front
2 Left
3 Front
4 Back
5 Front
6 Right
7 Front
8 Center
9 Front
10 Front
11 Left
12 Front
13 Back
14 Front
15 Right
16 Front
17 Center
18 Front

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Interrogations and suppression timing shall provide that when either FRONT, BACK, LEFT or RIGHT interrogation
uni-directional antenna is selected, and omni-directional broadcast side lobe suppression signal will be transmitted
from the CENTER antenna. The uni-directional antenna power output shall be tuned using attenuation, such that
side lobe suppression is provided beyond /-45 degrees off the bore site of the uni-directional. When CENTER
antenna is selected no suppression pulse shall be transmitted. Interrogations and suppression pairing is listed in
Table 12.

Table 12 Interrogations and Suppression Pairing

Interrogation Suppression

Front Center
Left Center
Back Center
Right Center
Center None

3-11.3 Interrogation Transmitters
A transponder interrogation signal shall be transmitted to the landing aircraft at a periodic rate. The transponder
interrogation signal is intended to be equivalent to that which would be produced by a secondary surveillance radar
system with Mode A/C capabilities as specified in the International Civil Aviation Organization (ICAO) publication
Convention on International Civil Aviation Annex 10. Coverage shall be equal or greater than the service area
described in Sub-Section 2-3.2.1, 2-3.3.1 and 2-3.4.1.

3-11.3.1 Interrogation Frequency
The carrier frequency of the interrogation transmission shall be 1030 MHz ± 0.2 MHz. The carrier frequencies of
each of the interrogation pulse transmissions shall not differ from each other by more than 0.2 MHz.

3-11.3.2 Interrogation Polarization
Interrogation transmissions shall be vertically polarized.

3-11.3.3 Interrogation Pulse Timing
The interrogation shall consist of transmitted pulses designated P1 and P3 identifying mode of interrogation and a
control pulse P2, which shall under certain conditions be transmitted. Transmission of P2 is following P1
transmission time and before P3 transmission time to provide side lobe suppression to targets outside area of interest.

The duration of pulses P1, P2, and P3 shall be 0.8 ± 0.1 µs
The rise time of pulses P1, P2, and P3 shall be between 0.05 and 0.1 µs.
The decay time of pulses P1, P2, and P3 shall be between 0.05 and 0.2 µs.
The interval between P1 and P3 shall be 8 ± 0.2 µs to provide mode A interrogation only
The interval between P1 and P3 shall be 21 ± 0.2 µs to provide mode C interrogation only
The interval between P1 and P2 shall be 2.0 ± 0.15 µs.

3-11.3.4 Interrogation Volume
The interrogation volume depends on the Secondary Track (Figures 2 and 3), Main Runway (Figures 5, and 6)
Reciprocal Runway (Figures 8 and 9) functions.

3-11.3.5 Interrogation Radiated Power
The radiated power of the interrogation transmission shall be ≥ -86 dBW/m2 (peak power) throughout the
interrogation volume. The radiated amplitude of P3 shall be within 1 dB of the radiated amplitude of P1 at any point

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throughout the interrogation volume. The radiated amplitude of P2 shall allow transponder interrogation within the
coverage volume.

3-11.4 Interface Control
The connection between the base station and the Interrogation assembly shall be a Radio Frequency cable.

3-11.5 Placement
The Interrogation assembly must be able to interrogate the entire service volume. To minimize signal interference,
the signal transmit path needs to be kept clear of structural elements. Therefore, the assembly, or any structural
elements that are part of the assembly shall not be within the top and bottom of the antenna.

3-12 Azimuth Sensor Assembly (ASA)

3-12.1 Antennas
There shall be three antennas referred to as the reference, low, and high antennas. The antenna pattern shall be omni-
directional in azimuth. The antenna pattern in elevation shall be as shown in Table 13, with the exception that the
Relative Voltage above 20° shall be above 0.5.

Table 13 ASA Antenna Specifications

Antenna Parameter Antenna Performance

Azimuth coverage Omni-directional
Polarization Vertical
Gain, Main beam 12 dB/iso, main horizontal beam
Main beam elevation peak 7°±0.1° above the horizon
Vertical field pattern The radiation pattern in the vertical plan has a lobe not more than 6 degrees
wide at the half power points.

3-12.2 Antenna Mounting
The antennas shall be mounted such that the low and the high antennas are between the reference antenna and the
Elevation Sensor Assembly. The assembly shall provide mounting surfaces such that the three antennas can be
mounted such that their base mounting plate heights are between 2.5 and 4 feet above ground level. The installation
tolerance for antenna position with respect to vertical shall be ≤ 1.0 degree. The installation tolerance for horizontal
level of the antennas is <1.0 degree. Assembly stability shall be such that horizontal level is maintained to the
installation level ± 0.5 degrees.

3-12.3 Antenna Placement
To meet the accuracy and initialization requirements of the error budget, the lateral spacing of the antennas shall be
as follows:

The distance from the Reference antenna phase center to Low Resolution antenna phase center shall be
30.0 inches ± 0.1 inch
The distance from the Reference antenna phase center to High Resolution antenna phase center shall be
120.0 inches ± 0.1 inch.
The antennas shall be aligned to be within ±2.0° of being perpendicular with respect to centerline.

3-12.4 Angle of Arrival Sensor

3-12.4.1 Performance
The proposed sensor specifications below shall be the basis for the ANPC sensor design.

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3-12.4.1.1 Radio Frequency Inputs
The AOA Sensor Assembly shall have four RF inputs. For each of these inputs, the following signal characteristics
and specifications apply.

3-12.4.1.2 Dynamic Range
The AOA Sensor shall meet the performance specifications defined herein with an input RF Operating power range
of -80 dBm to -20 dBm.

3-12.4.1.3 Input Power
The AOA Sensor instantaneous input power level without causing damage to the assembly shall be greater than or
equal to +15 dBm.

3-12.4.1.4 VSWR
The VSWR of each AOA Sensor input shall be 1.5:1 MAX into 50 ohms.

3-12.4.2 RF Path Controls

3-12.4.2.1 RF Distribution Path Control
The AOA Sensor shall provide the capability to switch signals from the High, Medium, and Low RF inputs to either
or both of the sensor A and C measurement output paths. The paths shall reflect the control signal settings and all
performance requirements shall be met within 100 us of a change in the commanded path control values.

3-12.4.2.2 Low Input Phase Control
The AOA Sensor shall provide the capability to select the amount of phase shift in the Low input indicated in Table
14. The low path phase shall reflect the control signal settings and all performance requirements shall be met within
100 us of a change in the commanded phase control values. Phase change of the Low path signal, measured at either
IF output A or C, relative to the phase with no phase shift commanded, shall be controllable to the following values
(electrical degrees):

Table 14 Low Input Phase Control

Phase Change + Degree - Degree

45 15 15
90 5 5
135 20 20
180 10 10
225 25 25
270 15 15
315 30 30

3-12.4.2.3 High Input Phase Control
The AOA Sensor shall provide the capability to select the amount of phase shift in the High input. The high path
phase shall reflect the control signal settings and all performance requirements shall be met within 100 us of a
change in the CPU commanded phase control values. Phase change of the High path signal, measured at either IF
output A or C, relative to the phase with no phase shift commanded, shall be controllable to 45 + 5 / - 20 electrical
degrees.

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3-12.4.4.9 Log Accuracy
For an input range of –80 dBm to –20 dBm, the log accuracy shall be ± 2.0 dB. This accuracy is defined as the
errors as compared to a fixed slope of 25 mV/dB over this power range, the operational temperature range, and
frequency range. The fixed slope line of 25 mV/dB is defined in Table 15 below. The fixed slope line may be offset
over temperature within the range defined below, but must remain fixed over frequency at each specific temperature.

Table 15 Log Accuracy

Input Power (dBm ± 2 dB) Output Voltage (Volts)

No Signal < 0.100
-73 0.625 ± 0.1
-63 0.875 ± 0.1
-53 1.125 ± 0.1
-43 1.375 ± 0.1
-33 1.625 ± 0.1
-23 1.875 ± 0.1

3-12.4.4.10 Channel to Channel Matching
Given equal IF input power, the log video outputs for the Low, Medium, and High inputs shall be within ± 75 mV of
the log video output for the Reference input.

3-12.4.4.11 Channel to Channel Isolation
When an input is applied to any one input, the log video output of the other two channels shall be a minimum of 625
mV (25 dB) below the output of the channel with the applied signal.

3-12.4.4.12 Signal to Noise Ratio
With input signals above –70 dBm, the signal to noise ratio shall be a minimum of 325 mV (13 dB).

3-12.4.5 Selectivity
Selectivity specifications shall be met for any RF input, output, distribution switch, and phase shifter setting.

3-12.4.5.1 Pass Band
Within the 1090 ± 8 MHz input band, there shall be a maximum power delta of ± 25 mV (± 1 dB). Between 8 and
12 MHz from center frequency, the output power shall be within 2 dB of the average power through the ± 8 MHz
pass band.

3-12.4.5.2 Image Frequency Rejection
Rejection of inputs in the band of 1405 MHz ± 12 MHz shall be such that the measured output shall be a minimum
of 30 dB below the input image power level.

3-12.4.5.3 Out of Band
Sensor out of band rejection shall be, at a minimum, as diagrammed in Figure 12.

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3-12.4.23 Frequency to Voltage Conversion
The AOA Sensor output level shall change at a rate of 90 mV per MHz through the input frequency range..

3-12.4.24 Slope
The AOA Sensor frequency measurement shall increase as the input frequency decreases.

3-12.4.25 Center Frequency Accuracy
With a sensor input of 1090.0 MHz, the voltage output shall be -225 mV ± 180 mV.

3-12.4.26 Through the Band Accuracy
The maximum frequency error for any input frequency or power level shall be 180 mV from the ideal 90 mV / MHz
ideal line, through the measured voltage point for an input at 1090 MHz.

3-12.4.27 Delay to Stable Output
The AOA Sensor frequency measurement shall be stable within 50 ns of any change to the input frequency.

3-12.5 Health Monitors
The Sensor shall provide health monitor data to the computer interface to allow system diagnostics of the Sensor.
These health monitors shall include, but not be limited to the following.

3-12.5.1 Sensor Temperature
A 12-bit digital data field shall represent internal sensor temperature. Temperature data range shall be –50 to + 359
degrees C; LSB = 0.1 degree C; and 0 deg C at 500 counts.

3-12.5.2 DC Voltage Monitors
All Sensor DC voltages shall be measured and provided to the computer interface. A voltage measurement
resolution of less than 10 mV shall be used in all cases.

3-12.5.3 AC Input Power
The performance specifications defined herein shall be met when the AC input power voltage is 120 VAC ±10% at
an input frequency in the range of 47 to 63 Hz. Circuit breaker protection internal to the AOA Sensor is required.

3-12.5.4 Mean Time Between Failure
The AOA Sensor shall be designed to meet a MTBF of greater than 40,000 hrs.

3-12.5.5 Electromagnetic Compatibility (EMC)

3-12.5.6 Electromagnetic Radiation

3-12.5.7 Conducted Limits
Conducted emissions shall comply with the limit specified in 47 CFR Chapter 1 (1-0-1-94), Part 15 paragraph
15.107 or the equivalent European Directives to this requirement, EN50081-1.

3-12.5.8 Radiated Limits
Radiated emissions shall comply with the limit specified in 47CFR Chapter 1 (10-1-94), Part 15 paragraph
15.109(b) or the equivalent European Directives to this requirement, EN50081-1.

3-12.5.9 Electromagnetic Susceptibility
The AOA Sensor shall comply with European Directives EN61000-4-3, EN61000-4-4, and EN61000-4-5. Testing
shall be performed with the sub-system(s) Operating, in a stand-alone mode, or in a system mode when housed in
the enclosure used in normal operation.

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3-12.6 Interface Control
The connection between the base station and the ASA sensor shall be an integrated fiber / optic power cable.

3-12.7 Placement
The ASA assembly must be able to measure phase for a primary approach and a reciprocal approach. To minimize
signal interference, the signal receive path needs to be kept clear of structural elements. Therefore, no part of the
assembly, or any structural elements that are part of the assembly shall be placed within ±55 degrees of the bore
sight of the runway and above the base plate of the antenna towards either end of the runway.

3-13 Elevation Sensor Assembly (ESA)

3-13.1 Antennas
There shall be four antennas referred to as the reference, low, medium, and high antennas. The antenna pattern shall
be omni-directional in azimuth for all antennas. The antenna pattern in elevation for the high and the low antennas
shall be as indicated in Table 16, with the exception that the Relative Voltage above 10° shall be above 0.5.

Table 16 ESA Antenna Specifications

Antenna Parameter Antenna Performance

Azimuth coverage Omni-directional
Polarization Vertical
Gain, Main beam 9 dB/iso, main horizontal beam
Main beam elevation peak 10°±0.1° above the horizon
Vertical field pattern The radiation pattern in the vertical plan has a lobe not more than 12 degrees
wide at the half power points.

3-13.2 Antenna Mounting
The antennas shall be mounted in stacked pairs with the high antenna above the medium in one pair and the low
antenna above the reference in another pair. The low/reference antenna pair shall be the pair closest to runway
threshold. The base plate of the lower antenna in each pair shall be 1 – 2 feet above ground. The installation
tolerance for antenna position with respect to vertical shall be ≤ 0.5 degree. Assembly stability shall be such that
vertical level is maintained to the installation level ± 0.2 degrees. The ESA Assembly shall be required to measure
phase for a primary approach and a reciprocal approach. To minimize signal interference, the signal receive path
needs to be kept clear of structural elements. Therefore, the assembly, or any structural elements that are part of the
assembly within ±55 degrees of the bore sight and above the base plate of the antenna towards either end of the
runway shall be minimized.

3-13.2.1 Antenna Stability - Short Duration
Structure stability shall be that vertical plumb is maintained to the installation level ± 2.0 degrees during short
duration movements of the antennas due to wind gust conditions. The position shall not exceed the 0.2 degree
stability requirement for more than 3 seconds.

3-13.3 Antenna Separation/Placement
To meet the accuracy and initialization requirements of the error budget, the separation between the lower and upper
antenna base plates of the antenna pairs shall be 5.5 ± 0.083 feet (1 inch). The two pairs of antennas shall be aligned
parallel to runway centerline within ± 1 degree. The separation of the antenna pairs shall be 300 to 350 feet.

3-13.4 Angle of Arrival Sensor
Refer to Sub-Section 3-12.4 as the ASA and the ESA shall utilize the same model sensor.

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3-13.5 Interface Control
The connection between the base station and the ESA sensor shall be an integrated fiber / optic power cable.

3-13.6 Switching
The ESA shall have the capability to switch the RF antenna inputs as follows:

Reference and Medium
High and Low
The time required to complete the switch shall be less than 5 seconds

3-14 Built in Test Equipment (BITE)

3-14.1 Antennas

3-14.1.1 Antenna Performance
Antenna shall perform according to uni-direction antenna specifications as found in Table 9.

3-14.1.2 Antenna Mounting Vertical Height / Plumb
The assembly shall provide mounting surfaces such that the mounted antenna phase center can be placed between
the heights of 2.5 and 4 feet above ground level. The installation tolerance for antenna position with respect to
vertical shall be ≤ 1.0 deg.

3-14.1.3 Antenna Stability
The assembly stability shall be such that the antenna base location remains within ± 0.1 inches of its installation
location, and vertical plumb is maintained to the installation level ± 0.2 degrees.

3-14.1.4 Antenna Position Maintenance
Maintenance shall be required to maintain installation position settings for periods greater than 24 hours. Use of
special tools to perform any position maintenance should be avoided. Design shall be done in a manner that
minimizes the need for a regular position maintenance activity.

3-14.1.5 Provisions for Harness Tie Downs
The assembly shall include provisions for tying down harnesses that are routed from the BITE transmitter to each of
the other mounted items. The design should allow for strain relief near the harness termination points, ability to
weather proof harness ends, and assist in routing water paths away from the harness terminations.

3-14.2 Built In Test Equipment (BITE) Generator

3-14.2.1 Radio Frequency (RF) Output
The output frequency of BITE signal shall be 1090 MHz ± 50ppm during all of the operating conditions specified
herein. The peak pulse output power of the 1090 MHz signal shall be 40 dBm -0dB + 2dB into a 50 ohm load.

3-14.2.1.1 Spectral Purity
The BITE Generator intentional radiation outputs shall pass and be licensed per FCC Part 87 for all outputs. All
outputs shall meet these FCC requirements with a FCC Emission designation of 6MM1D.

3-14.2.1.2 Radio Frequency Output Voltage Standing Wave Ratio
The output VSWR for the RF Output port shall be < 1.5:1.

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3-14.2.1.3 RF Output Rise / Fall Time
For all output signal pulses, the rise time of the output RF pulse, measured from the 10% point to the 90% point
shall be 75 ns ± 15 ns. For all output signal pulses, the fall time of the output RF pulse, measured from the 10%
point to the 90% point shall be between 75 ns and 200 ns.

3-14.2.1.4 RF Output Pulse Width
The pulse width of the output RF pulse, measured from the 90% point of the rising edge to the 90% point of the
falling edge shall be within 5 % of the pulse width of the Transmit Gate input control signal, measured from the
90% point of the rising edge to the 90% point of the falling edge.

3-14.2.1.5 RF Output Delay - Multiple Pulses
For any single output signal, modulated with multiple pulses within a 25 us time frame, the output delay shall be the
same as the transmit gate delay ± 10.0 ns. Delay is measured at the rising edge 50% points of the Tx gate and output
pulse.

3-14.2.1.6 RF Output Jitter - Rising Edge
For any single output signal the output jitter with respect to the transmit gate input shall be < 2.0 ns (2 sigma). Jitter
is measured at the rising edge 50% points of the output relative to the 50% point of the transmit gate input.

3-14.2.1.7 RF Output Protection
The BITE Generator shall not be damaged if the RF Output port is left in either a open circuit or short circuit
condition while operation is attempted.

3-14.2.1.8 Duty Cycle Protection
The BITE Generator shall safely operate (no damage) regardless of the input control states. If duty cycle protection
is required, the protection circuitry shall be as flexible as possible in allowing input pulse control options while
maintaining operation safe to the transmitter.

3-14.3 Interface Control

3-14.3.1 BITE Generator to Antenna
The RF Output Connector shall be RF cabling.

3-14.3.2 CPU1 to BITE Generator
The connection between CPU1 and the BITE generator shall be an integrated fiber optic / power cable.

3-15 Environment

3-15.1 Temperature

3-15.1.1 Internal to Shelter
All components internal to the shelter shall operate within –10 degrees Centigrade to +50 degrees Centigrade. All
components internal to the shelter shall withstand storage within –50 degrees Centigrade to +70 degrees Centigrade.

3-15.1.2 External to Shelter
All components internal to the shelter shall operate within –10 degrees Centigrade to +50 degrees Centigrade. All
components internal to the shelter shall withstand storage within –50 degrees Centigrade to +70degrees Centigrade.

3-15.2 Humidity
All components external to the shelter shall operate within 5 to 100% relative humidity. All components internal to
the shelter shall operate within 30 to 80% relative humidity. Above 40 degrees Centigrade, the relative humidity
shall be based on a dew point of 40 degrees Centigrade.

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3-15.3 Wind
All components external to the shelter shall be capable of withstanding wind to 100 mph without permanent
deformation or change that would impact upon critical performance parameters.

3-15.4 Ice
All components external to the shelter shall be operable with ½” of heavy ice accumulation during storage and
operation.

3-15.5 Altitude
All components shall operate within 0 to 12,000 feet above sea level. All components shall be able to withstand 0 to
50,000 feet above sea level.

3-15.6 Vibration
No component will be exposed to a significant amount of vibration during normal operation. Under non-operating
circumstances, components shall not suffer damage or degraded performance when exposed to the following Power
Spectral Density (PSD) vibration spectrum with 3 axis inputs as graphed in Figure 13.

0.03

0.025

0.02

0.015

0.01

0.005

0
1 10 100 1000
Frequency (Hz)

Figure 13 Vibration Spectrum

3-15.7 Shock
No component shall be exposed to shock during normal operation. All components shall meet or exceed non-
operating shock in accordance with Per MIL-STD-810E method 516.4 procedure VI.

3-15.8 Environmental Control Unit
The ECU shall maintain the shelter contents within the temperature and humidity ranges prescribed in sections
3.14.1 and 3.14.2, respectively.

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3-16 System Siting

3-16.1 Siting Procedure

3-16.1.1 ESA Siting
The center of the ESA array shall be less than 360 feet (110 m) from runway centerline and 330-360 feet behind
touchdown. The ESA center is the point midway between the two elevation antenna assemblies that are separated on
a runway parallel line as illustrated in Figure 14.

Touchdown

360 ft

330 ft 360 ft

ESA ESA
Center

Figure 14 Elevation Sensor Assembly Siting

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3-16.1.2 ASA Siting
The center of the ASA array shall be within ±5 degrees of one of the ESA antenna pairs with respect to a line
perpendicular to runway centerline and intersecting the appropriate ESA antenna. The distance from the center of
the ASA array to the line running through both ESA antenna pairs shall be greater than 165 feet (50 m). The center
of the ASA array shall be less than 200 feet (60 m) from runway centerline. Refer to Figure 15.

200 ft

5o
5o

ESA 165 ft

5o

5o

Figure 15 Azimuth Sensor Assembly Siting

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3-16.1.3 Built In Test Equipment Antenna Siting
The BITE antenna shall be within 10 feet of the ESA Center as shown in Figure 16.

10 ft

10 ft ESA ESA
Center

Figure 16 Built In Test Equipment Antenna Siting

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3-16.1.4 Interrogation Assembly Siting
The Interrogation Assembly shall be between 80 to 100 feet from the line through the ESA antenna pairs, towards
runway centerline. Refer to Figure 17.

ASA

80 ft
ESA

100 ft

Figure 17 Interrogator Antenna Siting

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Table 17 Main Runway ASA Error Budget

Quantity Amount
Sensor Measurement 0.22
Critical Area 0.05°
Multipath 0.05°
Margin 0.03°
Total Measurement Error 0.240°
GDOP due to Siting 0.002°
Uplink 0.058°
Total Error 0.3°

Table 18 Main Runway ESA Error Budget

Quantity Amount
Sensor Measurement 0.146
Critical Area 0.075°
Multipath 0.08°
Margin 0.023°
Total Measurement Error 0.184°
GDOP due to Siting 0.009°
Uplink 0.032
Total Error 0.225

3-17.2 Reciprocal Runway Error Budget
The system shall have a Reciprocal Runway error budget as detailed in Tables 19 and 20.

Table 19 Reciprocal Runway ASA Error Budget

Quantity Amount
Sensor Measurement 0.22
Critical Area 0.05°
Multipath 0.05°
Margin 0.03°
Total Measurement Error 0.240°
GDOP due to Siting 0.002°
Uplink 0.058°
Total Error 0.3°

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area boundaries for vehicles that exceed the sensitive area dimensions but are smaller than a Boeing 727. If there
will be vehicles larger than a Boeing 727 outside the sensitive area there shall be a reassessment of the critical and
sensitive areas with an anticipated expansion of either or both. The Rhino II critical and sensitive areas are a result
of compiling all sub unit critical and sensitive areas, these sub-unit requirements are found below.

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Major functions this SCI shall perform in common with Base CPU2 include:

Aircraft tracking and guidance
Command of the guidance transmitter
Integrity Monitoring
Data logging
Network communications

The top-level architecture of the Base CPU1 SCI shall be as shown in Figure 27 and for Base CPU2 in Figure 28.
Each Base process is described below in the context of the Computer Software Components (CSCs) comprising it.
All processes are common to both SCIs; one description is given and any differences in operation between CPU1
and CPU2 are discussed.

Figure 27 Base CPU1 Architecture

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4-2.3.8 Steer
The Steer CSC shall compute corrections to provide to the aircraft via the Uplink process. It shall use track
information computed by Track Processing and approach information for the selected approach to calculate the
corrections.

4-2.4 Uplink Process
The Uplink process shall provide command and control of the guidance transmitter. Uplink computes DDM values
based on corrections provided by Steer in Signal Processing and sends these to the transmitter for modulation on
desired ILS frequencies for glide slope and localizer. It also performs integrity monitoring of the uplink and shall
provide this status back to System Manager for action. The Uplink process is identical on both CPU1 and CPU2.

4-2.5 RCU Manager Process
The RCU Manager process shall be comprised of a single CSC that establishes and maintains application-to-
application communications with the RCU process running on the RCU CPU. The RCU Manager receives the RCU
operator-entered approach selection and transponder code as part of the start approach message and also receives
abort request messages from the RCU and forwards them to System Manager. It also shall provide the RCU process
with system mode and alarm information as well as track information for RCU recording and approach replay. The
RCU Manager is also responsible for detecting failure of the RCU communication link and generating an alert or
alarm, depending on system mode. The RCU Manager process is identical on both CPU1 and CPU2 except that
system mode and track data are sent to the RCU process from RCU Manager on CPU1 only.

4-2.6 Log Manager Process
The Log Manager process shall be comprised of a single CSC that receives disk-logging requests from local
application processes and performs the disk file output. File recording includes BIT log file data and error/event
messages. The Log Manager process shall be identical on both CPU1 and CPU2.

4-2.7 Maintenance Interface Manager Process
The Maintenance Interface Manager process shall be comprised of a single CSC that establishes and maintains
application-to-application communications with the MI process running on the MIU CPU. The Maintenance
Interface Manager receives the Rhino II Technician-entered system commands and controls to view system status,
stop or start the system for maintenance activities, or enter calibration data during installation or repair. It also shall
provide the Maintenance Interface process with system mode and alarm information. The Maintenance Interface
Manager process shall be identical on both CPU1 and CPU2.

4-2.8 Sensor Software Configuration Items Description
The Sensor SCI shall be comprised of the Sensor process, which is a single CSC, and the Network Communication
processes described in Section 3.3.1.2. The Sensor process’ primary purpose is to interface with the sensor
acquisition hardware. This includes receiving sensor setup data from the Base CPU1 and sending this setup
information to the Phase Acquisition Card (PAC). It also performs the read of the PAC data once an acquisition is
complete and sends the data in to both Base CPUs, and reads sensor hardware health data from the PAC.

4-2.9 Remote Control Unit Software Configuration Items Description
The RCU SCI shall be comprised of the RCU process (a single CSC) and the Network Communications processes
(Section 3.3.1.2). The RCU process shall provide the Rhino II Operator interface to the system for the following
operator functions:

Transponder Code Entry (Code of aircraft desiring Rhino II approach)
Enter/Abort commands for approach start/stop
Alarm/Alert/System mode monitoring to determine Rhino II general health and availability

The RCU SCI communicates with the Base CPUs using UDP/IP and the network via PPP utility for Windows-NT
across a physical serial link connected to Base CPU2 or by a physical Ethernet connection. The RCU CSC records
track data received from the Base CPU1 for later approach replay by the optional Approach Replay tool. The RCU
also maintains the communication link with the Base CPUs via a “ping” message.

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4-2.10 Maintenance Interface Software Configuration Items Description
The Maintenance Interface SCI shall be comprised of the Maintenance Interface process (a single CSC) and the
Network Communications processes (Section 3.3.1.2). It shall provide the Rhino II Technician, ANPC installer, and
ANPC engineering an interface to the Rhino II. Rhino II Technician functions which are conducted through this
interface include:

Entry/maintenance of Integrity Monitoring Limits information
Review equipment status/alarm status
System control and control of data recording (with proper authorization)
Manual control of Built-In-Test schedule, start, stop

In addition, the Maintenance Interface process allows for review and maintenance of ANPC entered calibration data
and the ANPC installer access to tools used during installation and calibration. All Maintenance Interface functions
will be password protected and provide for file security.

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SECTION 5 Safety

5-1 HERO
The Frequencies and power levels utilized by this system are the identical to those currently existing on military air
facilities.

5-2 HERP
The Frequencies and power levels utilized by this system are the identical to those currently existing on military air
facilities.

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SECTION 6 Maintainability

6-1 Mean Time To Repair (MTTR)
To be determined

6-1.1 Maximum Repair Time (MMAX)
To be determined

6-1.2 Scheduled Maintenance
To be determined

6-1.3 Periodicity
To be determined

6-1.3.1 Daily
Reserved for later use.

6-1.3.2 Weekly
Reserved for later use.

6-1.3.3 Monthly
Reserved for later use.

6-1.3.4 Quarterly
Reserved for later use.

6-1.3.5 Annually
Reserved for later use.

6-2 Level of Maintainability
To be determined

6-3 Special Tools and Test Equipment
To be determined

6-3.1 Equipment Handling
To be determined

6-3.2 Cable and Wire Marking
To be determined

6-3.3 Cable Connections and Cable Slack
To be determined

6-3.4 Panels, Handles and Fastener Standard
To be determined

6-3.5 Wire and Pin Designations
To be determined

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6-3.6 CaNDI Markings
To be determined

6-3.7 Name Plate Data
To be determined

6-4 Safety Warning Labels
To be determined

6-5 Human Engineering
To be determined

6-6 Weather Proofing and Air Flow Filtering
To be determined

6-7 Built In Test Equipment (BITE)
To be determined

6-7.1.1 Power Monitoring
To be determined

6-7.1.2 Over Temperature, Humidity Sensors/Alarms
To be determined

6-8 Re-Certification Requirements
To be determined

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SECTION 7 Materials And Processes

7-1 Hazardous Materials Utilized
To be determined

7-1.1 Paint Used/Required
To be determined

7-1.2 Flammability Of Materials
To be determined

7-2 Recycled Vice Virgin Materials
To be determined

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SECTION 8 Logistics

8-1 Maintenance Concept

8-1.1 On Line
To be determined

8-1.2 Off Line
To be determined

8-2 Overhaul Periods/Hours
To be determined

8-3 Tools And Test Equipment
To be determined

8-4 Dimensions

8-4.1 Weights
To be determined

8-4.2 Appearances
To be determined

8-4.3 Workmanship
To be determined

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SECTION 9 Methods Of Verification

9-1 Analysis
Analysis will be performed verifying data derived from developmental research as well as comparison from data
developed during the Building and certification process of Transponder Landing System (TLStm).

9-2 Demonstration
Rhino II will be installed and aircraft approach demonstrations will be performed while using independent means of
verifying Rhino II range coarse line and glide slope accuracy in the VHF/UHF ILS and GCA method of operation to
the accuracies stated in Milestone 29. Range course, and altitude accuracy will be measured by independent means
to verify accuracies as stated in Milestone 29 in the secondary track method of operation.

9-3 Examination
The visual inspection shall consist of visual verification of the measurements and standards established in Milestone
29.

9-3.1 Functional tests
Functional tests shall include the verification and validation of design documentation and shall include the
verification of the modes and methods of operation, as well basic BITE function and fault isolation.

9-4 No formal testing will be associated with the Technical Demonstration.

9-4.1 Methods of Verification
The following methods shall be utilized to accomplish the verification of requirements:

(1) Analysis
(2) Demonstrations
(3) Examinations
(4) No Formal Testing will be associated with this Demonstration.

9-5 Classes of Verifications
The trainer shall be subject to the verification classes listed below. Under each verification class, the trainer will be
subject to inspections and tests as specified below:

(A) In-process inspections
(B) Incremental development inspections
(C) Technical Demonstration

9-6 Inspections and tests
Rhino II shall be subject to no inspections or test for this evolution.

9-6.1 Visual inspections
The visual inspection shall consist of verification of siting measurements and equipment placement.

9-6.2 Functional tests
Functional tests shall include the verification and validation of design documentation and shall include the following
test sequence:

9-7 Requirement/Verification Cross-Reference Matrix
Requirement/Verification Cross-Reference Matrix is Table 23.

Document No. 010-00057 - Rev - 73

Rhino II Rhino II Specification

Table 23 Requirement/Verification Cross-Reference Matrix

Table 23 Requirement/Verification Cross-Reference Matrix

VERIFICATION METHOD VERIFICATION CLASS
N/A - NOT APPLICABLE A – IN-PROCESS INSPECTIONS
1 – ANALYSIS B – INCREMENTAL DEVELOPMENT INSPECTIONS
2 – DEMONSTRATION C – TECHNICAL DEMONSTRATION
3 – EXAMINATION
4 – NO TESTING WILL BE ASSOCIATED WITH THIS DEMONSTRATION

REQUIREMENT VERIFICATION METHOD VERIFICATION CLASS SECTION 4
N/A 1 2 3 4 A B C D E VERIFICATION

SECTION 1 SCOPE X
1-1 Introduction X
1-2 System Overview X
1-3 Applicable
X
Documents
1-3.1 Government
X
Documents
1-3.2
Non-Government X
Documents
1-4 Order Of
X
Precedence
SECTION 2 Rhino II
PERFORMANCE X
REQUIREMENTS
2-1 System Definition X X X
2-2 Modes and States X X
2-2.1 OFF Mode X
2-2.2 STANDBY
X
Mode
2-2.3 TEST Mode X X
2-2.4 ON Mode X X
2-3 System Functions X
2-3.1 Transponder
X
Interrogation
2-3.1.1 Interrogation
X
Volume
2-3.1.2 Interrogation
X X
Radiated Power
2-3.2 Secondary
X
Tracking
2-3.2.1 Service
X X
Volume
2-3.2.1.1 Service
Volume Transition X
Zones

Document No. 010-00057 - Rev - 74

Rhino II Rhino II Specification

Table 23 Requirement/Verification Cross-Reference Matrix

VERIFICATION METHOD VERIFICATION CLASS
N/A - NOT APPLICABLE A – IN-PROCESS INSPECTIONS
1 – ANALYSIS B – INCREMENTAL DEVELOPMENT INSPECTIONS
2 – DEMONSTRATION C – TECHNICAL DEMONSTRATION
3 – EXAMINATION
4 – NO TESTING WILL BE ASSOCIATED WITH THIS DEMONSTRATION

REQUIREMENT VERIFICATION METHOD VERIFICATION CLASS SECTION 4
N/A 1 2 3 4 A B C D E VERIFICATION

2-3.2.2 Accuracy X X
2-3.2.2.1 Azimuth
X X X
Accuracy
2-3.2.2.2 Range
X X
Accuracy
2-3.2.3 Tracking X X
2-3.2.4 Monitoring X X
2-3.3 Main Runway
X X
Service
2-3.3.1 Service
X X X
Volume
2-3.3.2 Accuracy X X X
2-3.3.2.1 Localizer
X X X
Course Alignment
2-3.3.2.2 Localizer
Displacement X X X
Sensitivity
2-3.3.2.3 Localizer
X X X
Course Structure
2-3.3.3 Interrogation
X X
Requirements
2-3.3.4 Tracking X X
2-3.3.5 Guidance X X
2-3.3.6 Monitoring X X
2-3.4 Reciprocal
X
Runway Service
2-3.4.1 Service
X X
Volume
2-3.4.2 Accuracy X X X
2-3.4.3 Glide Slope
Displacement X X X
Sensitivity
2-3.4.4 Interrogation
X X
Requirements
2-3.4.5 Tracking X X
2-3.4.6 Guidance X X X
2-3.4.7 Monitoring X X
2-4 Capability
X X
Interface

Document No. 010-00057 - Rev - 75

Rhino II Rhino II Specification

Table 23 Requirement/Verification Cross-Reference Matrix

VERIFICATION METHOD VERIFICATION CLASS
N/A - NOT APPLICABLE A – IN-PROCESS INSPECTIONS
1 – ANALYSIS B – INCREMENTAL DEVELOPMENT INSPECTIONS
2 – DEMONSTRATION C – TECHNICAL DEMONSTRATION
3 – EXAMINATION
4 – NO TESTING WILL BE ASSOCIATED WITH THIS DEMONSTRATION

REQUIREMENT VERIFICATION METHOD VERIFICATION CLASS SECTION 4
N/A 1 2 3 4 A B C D E VERIFICATION
3-1.5 Secondary Track
X X X
View
3-1.5.1 Range Rings X X X
3-1.5.2 Approach X X X
3-1.5.3 Compass Rose X X X
3-1.5.4 Service
X X X
Volume
3-1.6 GCA View X X X
3-1.6.1 Range
X X X
Indicators
3-1.6.2 Approach X X X
3-1.7 Controls X X X
3-1.7.1 Function
X X X
Control
3-1.7.2 Acquisition
X X X
Control
3-1.8 Track Display X X X
3-1.8.1 Secondary
X X X
Track Function Tracks
3-1.8.2 Guidance
X X X
Track
3-1.9 Tooltips X X X
3-2 Lighting System
X
Requirements
3-2.1 Shelter X
3-2.2 Blackout
X
Lighting
3-2.3 Obstruction X
3-3 Communication
X
System
3-3.1 Air to Ground X
3-3.2 Intercom X
3-4 Calibration /
X X
Installation
3-4.1 Truth Data X X
3-4.2 Interface X X
3-5 Maintenance
X
Interface Assembly

Document No. 010-00057 - Rev - 77

Rhino II Rhino II Specification

Table 23 Requirement/Verification Cross-Reference Matrix

VERIFICATION METHOD VERIFICATION CLASS
N/A - NOT APPLICABLE A – IN-PROCESS INSPECTIONS
1 – ANALYSIS B – INCREMENTAL DEVELOPMENT INSPECTIONS
2 – DEMONSTRATION C – TECHNICAL DEMONSTRATION
3 – EXAMINATION
4 – NO TESTING WILL BE ASSOCIATED WITH THIS DEMONSTRATION

REQUIREMENT VERIFICATION METHOD VERIFICATION CLASS SECTION 4
N/A 1 2 3 4 A B C D E VERIFICATION
3-5.1 Maintenance
X
Interface Unit (MIU)
3-5.1.1 CPU X
3-5.1.2 Memory X
3-5.1.3 Motherboard X
3-5.1.4 Operating
X
System
3-5.1.5 Peripheral
X
Configuration
3-5.1.6 Hard Drive X
3-5.1.7 Floppy Drive X
3-5.1.8 CD-ROM
X
Drive
3-5.1.9 Network
X
Adapter
3-5.1.10 Input / Output X
3-5.1.11 Input Power
Electrical X
Requirements
3-5.1.12 Mean Time
X
Between Failure
3-5.1.13 Physical
X
Design
3-5.2 Oscilloscope X
3-5.3 Monitor X
3-5.4 Keyboard X
3-5.5 Interface Control X
3-5.5.1 MIU to
X
Network Panel
3-5.5.2 Monitor to
X
Network Panel
3-5.5.3 Keyboard to
X
Network Panel
3-6 Central Processing
X
Units
3-6.1 CPU 1 X
3-6.1.1 CPU X
3-6.1.2 Memory X

Document No. 010-00057 - Rev - 78

Rhino II Rhino II Specification

Table 23 Requirement/Verification Cross-Reference Matrix

VERIFICATION METHOD VERIFICATION CLASS
N/A - NOT APPLICABLE A – IN-PROCESS INSPECTIONS
1 – ANALYSIS B – INCREMENTAL DEVELOPMENT INSPECTIONS
2 – DEMONSTRATION C – TECHNICAL DEMONSTRATION
3 – EXAMINATION
4 – NO TESTING WILL BE ASSOCIATED WITH THIS DEMONSTRATION

REQUIREMENT VERIFICATION METHOD VERIFICATION CLASS SECTION 4
N/A 1 2 3 4 A B C D E VERIFICATION

3-6.1.3 Motherboard X
3-6.1.4 Operating
X
System
3-6.1.5 Peripherals X
3-6.1.6 Hard Drive X
3-6.1.7 Floppy Drive X
3-6.1.8 CD-ROM
X
Drive
3-6.1.9 Network
X
Adapter
3-6.1.10 Input / Output X
3-6.1.11 Mounting X
3-6.2 CPU2 X
3-6.2.1 CPU X
3-6.3 Memory X
3-6.4 Motherboard X
3-6.5 Operating
X
System
3-6.6 Peripherals X
3-6.7 Hard Drive X
3-6.8 Floppy Drive X
3-6.9 CD-ROM Drive X
3-6.10 Network
X
Adapter
3-6.11 Input / Output X
3-6.12 Mounting X
3-7 Local Area
X
Network
3-7.1 Network
X
Topology
3-7.2 Main Switch X
3-7.3 Remote Control
X
Unit (RCU) Hub
3-7.4 Interconnectivity X
3-8 Remote Control
X
Unit (RCU)

Document No. 010-00057 - Rev - 79

Rhino II Rhino II Specification

Table 23 Requirement/Verification Cross-Reference Matrix

VERIFICATION METHOD VERIFICATION CLASS
N/A - NOT APPLICABLE A – IN-PROCESS INSPECTIONS
1 – ANALYSIS B – INCREMENTAL DEVELOPMENT INSPECTIONS
2 – DEMONSTRATION C – TECHNICAL DEMONSTRATION
3 – EXAMINATION
4 – NO TESTING WILL BE ASSOCIATED WITH THIS DEMONSTRATION

REQUIREMENT VERIFICATION METHOD VERIFICATION CLASS SECTION 4
N/A 1 2 3 4 A B C D E VERIFICATION
3-8.1 Central
X
Processing Unit (CPU)
3-8.2 Memory X
3-8.3 Motherboard X
3-8.4 Operating
X
System
3-8.5 Peripherals X
3-8.6 Hard Drive X
3-8.7 Floppy Drive X
3-8.8 CD-ROM Drive X
3-8.9 Network
X
Adapter
3-8.10 Input / Output X
3-9 Power
X
Requirements
3-9.1 Power Input X
3-9.2 Uninterruptible
Power Supply/Battery X
Pack
3-9.2.1 Primary Input
X
Power
3-9.2.2 Output Power X
3-9.2.3 Mean Time
X
Between Failure
3-9.2.4 Battery Hold-
X
Up Time
3-9.3 Interface Control X
3-9.3.1 Signal Entry
X
Panel to UPS/Battery
3-9.3.2 UPS to shelter
X
power
3-9.3.3 UPS to rack
X
power
3-10 Uplink Assembly X
3-10.1 Guidance
Transmitter Unit X
(GTU)
3-10.1.1 RF Output –
X
Localizer

Document No. 010-00057 - Rev - 80

Rhino II Rhino II Specification

Table 23 Requirement/Verification Cross-Reference Matrix

VERIFICATION METHOD VERIFICATION CLASS
N/A - NOT APPLICABLE A – IN-PROCESS INSPECTIONS
1 – ANALYSIS B – INCREMENTAL DEVELOPMENT INSPECTIONS
2 – DEMONSTRATION C – TECHNICAL DEMONSTRATION
3 – EXAMINATION
4 – NO TESTING WILL BE ASSOCIATED WITH THIS DEMONSTRATION

REQUIREMENT VERIFICATION METHOD VERIFICATION CLASS SECTION 4
N/A 1 2 3 4 A B C D E VERIFICATION
3-10.1.2 Localizer
X
Output Power
3-10.1.3 Localizer
X
Carrier Frequency
3-10.1.4 Localizer
X
Carrier Modulation
3-10.1.5 Localizer
X
Depth of Modulation
3-10.1.6 Localizer
Modulation Control
X
Resolution and
Accuracy
3-10.2 RF Output –
X
Glide Slope
3-10.2.1 Glide Slope
X
Output Power
3-10.2.2 Glide Slope
X
Frequency
3-10.2.3 Glide Slope
X
Carrier Modulation
3-10.2.4 Glide Slope
X
Depth of Modulation
3-10.2.5 Glide Slope
Modulation Control
X
Resolution and
Accuracy
3-10.3 Monitor
X
Functions
3-10.3.1 DDM
X
Monitors
3-10.3.1.1 DDM
X
Monitor Resolution
3-10.3.1.2 DDM
X
Monitor Accuracy
3-10.4 Uplink
X
Antennas
3-10.4.1 Localizer
X
Antenna
3-10.4.1.1 Localizer
X
Antenna Power
3-10.4.1.2 Localizer
X
Transmission

Document No. 010-00057 - Rev - 81

Rhino II Rhino II Specification

Table 23 Requirement/Verification Cross-Reference Matrix

VERIFICATION METHOD VERIFICATION CLASS
N/A - NOT APPLICABLE A – IN-PROCESS INSPECTIONS
1 – ANALYSIS B – INCREMENTAL DEVELOPMENT INSPECTIONS
2 – DEMONSTRATION C – TECHNICAL DEMONSTRATION
3 – EXAMINATION
4 – NO TESTING WILL BE ASSOCIATED WITH THIS DEMONSTRATION

REQUIREMENT VERIFICATION METHOD VERIFICATION CLASS SECTION 4
N/A 1 2 3 4 A B C D E VERIFICATION
3-10.4.2 Glide Slope
X
Antenna
3-10.4.2.1 Glide Slope
X
Antenna Power
3-10.5 Glide Slope
X
Transmission
3-10.6 Interface
X
Control
3-10.7
X
Placement/Polarization
3-10.7.1 Antenna
X
Clear Zone
3-10.8 Monitoring X
3-11 Interrogation
X
Assembly
3-11.1 Antennas X X
3-11.1.1 Interrogator
Uni directional
X X X
Antenna
Specifications
3-11.1.2 Interrogator
Omni-directional
X X X
Antenna
Specifications
3-11.1.3 Antenna
X X
Mounting
3-11.2 Interrogation
X X
Rate and Switching
3-11.3 Interrogation
X X
Transmitters
3-11.3.1 Interrogation
X X
Frequency
3-11.3.2 Interrogation
X X
Polarization
3-11.3.3 Interrogation
X
Pulse Timing
3-11.3.4 Interrogation
X
Volume
3-11.3.5 Interrogation
X
Radiated Power

Document No. 010-00057 - Rev - 82

Rhino II Rhino II Specification

Table 23 Requirement/Verification Cross-Reference Matrix

VERIFICATION METHOD VERIFICATION CLASS
N/A - NOT APPLICABLE A – IN-PROCESS INSPECTIONS
1 – ANALYSIS B – INCREMENTAL DEVELOPMENT INSPECTIONS
2 – DEMONSTRATION C – TECHNICAL DEMONSTRATION
3 – EXAMINATION
4 – NO TESTING WILL BE ASSOCIATED WITH THIS DEMONSTRATION

REQUIREMENT VERIFICATION METHOD VERIFICATION CLASS SECTION 4
N/A 1 2 3 4 A B C D E VERIFICATION
3-11.4 Interface
X X
Control
3-11.5 Placement X X
3-12 Azimuth Sensor
X
Assembly (ASA)
3-12.1 Antennas X X X
3-12.2 Antenna
X X
Mounting
3-12.3 Antenna
X X
Placement
3-12.4 Angle of
X
Arrival Sensor
3-12.4.1 Performance X X X X
3-12.4.1.1 RF Inputs X X
3-12.4.1.2 Dynamic
X X X X
Range
3-12.4.1.3 Input Power X X X X
3-12.4.1.4 VSWR X X X X
3-12.4.2 RF Path
X
Controls
3-12.4.2.1 RF
Distribution Path X X
Control
3-12.4.2.2 Low Input
X X
Phase Control
3-12.4.2.3 High Input
X X
Phase Control
3-12.4.3 Acquisition
X
Control
3-12.4.3.1 Sensor
X X
Acquisition Enable
3-12.4.3.2 Start Signal X X
3-12.4.3.3 Acquisition
X X
Window Duration
3-12.4.4 Sensor CPU X X
3-12.4.4.1 CPU X X
3-12.4.4.2 RAM
X X
Memory

Document No. 010-00057 - Rev - 83

Rhino II Rhino II Specification

Table 23 Requirement/Verification Cross-Reference Matrix

VERIFICATION METHOD VERIFICATION CLASS
N/A - NOT APPLICABLE A – IN-PROCESS INSPECTIONS
1 – ANALYSIS B – INCREMENTAL DEVELOPMENT INSPECTIONS
2 – DEMONSTRATION C – TECHNICAL DEMONSTRATION
3 – EXAMINATION
4 – NO TESTING WILL BE ASSOCIATED WITH THIS DEMONSTRATION

REQUIREMENT VERIFICATION METHOD VERIFICATION CLASS SECTION 4
N/A 1 2 3 4 A B C D E VERIFICATION
3-12.4.4.3 Non-
X X
volatile Memory
3-12.4.4.4 Ethernet
X X
Interface
3-12.4.4.5 Amplitude
Measurement X X
Performance
3-12.4.4.6 Digital
Amplitude X X
Measurement Output
3-12.4.4.7 Amplitude
X X
Measurement Rate
3-12.4.4.8 Log Slope X X
3-12.4.4.9 Log
X
Accuracy
3-12.4.4.10 Channel to
X X
Channel Matching
3-12.4.4.11 Channel to
X X
Channel Isolation
3-12.4.4.12 Signal to
X X X X
Noise Ratio
3-12.4.5 Selectivity X X X X
3-12.4.5.1 Pass Band X X X X
3-12.4.5.2 Image
X X X X
Frequency Rejection
3-12.4.5.3 Out of Band X X X X
3-12.4.6 Delay Time X X X X
3-12.4.7 Delay Jitter X X X X
3-12.4.8 Amplitude
X X X X
Jitter
3-12.4.9 Phase
X X X X
Measurements
3-12.4.10 Digital
Phase Measurement X X X X
Output
3-12.4.11 Phase
X X X X
Measurement Rate
3-12.4.12 Phase
Stability – Amplitude X X X X
Variation

Document No. 010-00057 - Rev - 84

Rhino II Rhino II Specification

Table 23 Requirement/Verification Cross-Reference Matrix

VERIFICATION METHOD VERIFICATION CLASS
N/A - NOT APPLICABLE A – IN-PROCESS INSPECTIONS
1 – ANALYSIS B – INCREMENTAL DEVELOPMENT INSPECTIONS
2 – DEMONSTRATION C – TECHNICAL DEMONSTRATION
3 – EXAMINATION
4 – NO TESTING WILL BE ASSOCIATED WITH THIS DEMONSTRATION

REQUIREMENT VERIFICATION METHOD VERIFICATION CLASS SECTION 4
N/A 1 2 3 4 A B C D E VERIFICATION
3-12.4.13 Phase
Stability – Frequency
X
and Dynamic
Balanced Power
3-12.4.14 Phase
Stability – Frequency
X X X X
and Dynamic
Balanced Low Power
3-12.4.15 Phase
Stability – Delta X X X X
Power
3-12.4.16 Phase
X X X X
Polarity
3-12.4.17 Delta Phase X X X X
3-12.4.18 Delay to
X X X X
Stable Output
3-12.4.19 Phase Jitter X X X X
3-12.4.20 Frequency
Measurement X X X X
Performance
3-12.4.21 Digital
Frequency X X X X
Measurement Output
3-12.4.22 Frequency
X X X X
Measurement Rate
3-12.4.23 Frequency
X X X X
to Voltage Conversion
3-12.4.24 Slope X X X X
3-12.4.25 Center
X X X X
Frequency Accuracy
3-12.4.26 Through the
X X X X
Band Accuracy
3-12.4.27 Delay to
X X X X
Stable Output
3-12.5 Health
X X X X
Monitors
3-12.5.1 Sensor
X X X X
Temperature
3-12.5.2 DC Voltage
X X X X
Monitors

Document No. 010-00057 - Rev - 85

Rhino II Rhino II Specification

Table 23 Requirement/Verification Cross-Reference Matrix

VERIFICATION METHOD VERIFICATION CLASS
N/A - NOT APPLICABLE A – IN-PROCESS INSPECTIONS
1 – ANALYSIS B – INCREMENTAL DEVELOPMENT INSPECTIONS
2 – DEMONSTRATION C – TECHNICAL DEMONSTRATION
3 – EXAMINATION
4 – NO TESTING WILL BE ASSOCIATED WITH THIS DEMONSTRATION

REQUIREMENT VERIFICATION METHOD VERIFICATION CLASS SECTION 4
N/A 1 2 3 4 A B C D E VERIFICATION
3-12.5.3 AC Input
X X
Power
3-12.5.4 Mean Time
X X
Between Failure
3-12.5.5
Electromagnetic X
Compatibility (EMC)
3-12.5.6
Electromagnetic X
Radiation
3-12.5.7 Conducted
X X
Limits
3-12.5.8 Radiated
X X
Limits
3-12.5.9
Electromagnetic X X
Susceptibility
3-12.6 Interface
X X
Control
3-12.7 Placement X X
3-13 Elevation Sensor
X
Assembly (ESA)
3-13.1 Antennas X X X
3-13.2 Antenna
X X
Mounting
3-13.2.1 Antenna
Stability - Short X X
Duration
3-13.3 Antenna
X X
Separation/Placement
3-13.4 Angle of
X X X X
Arrival Sensor
3-13.5 Interface
X X
Control
3-13.6 Switching X
3-14 Build in Test
X
Equipment (BITE)
3-14.1 Antennas X X
3-14.1.1 Antenna
X X
Performance

Document No. 010-00057 - Rev - 86

Rhino II Rhino II Specification

Table 23 Requirement/Verification Cross-Reference Matrix

VERIFICATION METHOD VERIFICATION CLASS
N/A - NOT APPLICABLE A – IN-PROCESS INSPECTIONS
1 – ANALYSIS B – INCREMENTAL DEVELOPMENT INSPECTIONS
2 – DEMONSTRATION C – TECHNICAL DEMONSTRATION
3 – EXAMINATION
4 – NO TESTING WILL BE ASSOCIATED WITH THIS DEMONSTRATION

REQUIREMENT VERIFICATION METHOD VERIFICATION CLASS SECTION 4
N/A 1 2 3 4 A B C D E VERIFICATION
3-14.1.2 Antenna
Mounting Vertical X X
Height / Plumb
3-14.1.3 Antenna
X X
Stability
3-14.1.4 Antenna
X
Position Maintenance
3-14.1.5 Provisions for
X X X
Harness Tie Downs
3-14.2 Build In Test
Equipment (BITE) X
Generator
3-14.2.1 Radio
Frequency (RF) X X X X
Output
3-14.2.1.1 Spectral
X X
Purity
3-14.2.1.2 Radio
Frequency Output
X X X X
Voltage Standing
Wave Ratio
3-14.2.1.3 RF Output
X X X X
Rise / Fall Time
3-14.2.1.4 RF Output
X X X X
Pulse Width
3-14.2.1.5 RF Output
Delay - Multiple X X X X
Pulses
3-14.2.1.6 RF Output
X X X X
Jitter - Rising Edge
3-14.2.1.7 RF Output
X X X X
Protection
3-14.2.1.8 Duty Cycle
X X X X
Protection
3-14.3 Interface
X
Control
3-14.3.1 BITE
X X
Generator to Antenna
3-14.3.2 CPU1 to
X X
BITE Generator
3-15 Environment X

Document No. 010-00057 - Rev - 87

Rhino II Rhino II Specification

Table 23 Requirement/Verification Cross-Reference Matrix

VERIFICATION METHOD VERIFICATION CLASS
N/A - NOT APPLICABLE A – IN-PROCESS INSPECTIONS
1 – ANALYSIS B – INCREMENTAL DEVELOPMENT INSPECTIONS
2 – DEMONSTRATION C – TECHNICAL DEMONSTRATION
3 – EXAMINATION
4 – NO TESTING WILL BE ASSOCIATED WITH THIS DEMONSTRATION

REQUIREMENT VERIFICATION METHOD VERIFICATION CLASS SECTION 4
N/A 1 2 3 4 A B C D E VERIFICATION

4-2.3.7 Track Monitor X X
4-2.3.8 Steer X X
4-2.4 Uplink Process X X
4-2.5 RCU Manager
X X
Process
4-2.6 Log Manager
X X
Process
4-2.7 Maintenance
Interface Manager X X
Process
4-2.8 Sensor Software
Configuration Items X X
Description
4-2.9 Remote Control
Unit Software
X X
Configuration Items
Description
4-2.10 Maintenance
Interface Software
X X
Configuration Items
Description
SECTION 5 Safety X
5-1 HERO X
5-2 HERP X
SECTION 6
X
Maintainability
6-1 Mean Time To
X
Repair (MTTR)
6-1.1 Maximum
X
Repair Time (MMAX)
6-1.2 Scheduled
X
Maintenance
6-1.3 Periodicity X
6-1.3.1 Daily X
6-1.3.2 Weekly X
6-1.3.3 Monthly X
6-1.3.4 Quarterly X
6-1.3.5 Annually X

Document No. 010-00057 - Rev - 90

Rhino II Rhino II Specification

Table 23 Requirement/Verification Cross-Reference Matrix

VERIFICATION METHOD VERIFICATION CLASS
N/A - NOT APPLICABLE A – IN-PROCESS INSPECTIONS
1 – ANALYSIS B – INCREMENTAL DEVELOPMENT INSPECTIONS
2 – DEMONSTRATION C – TECHNICAL DEMONSTRATION
3 – EXAMINATION
4 – NO TESTING WILL BE ASSOCIATED WITH THIS DEMONSTRATION

REQUIREMENT VERIFICATION METHOD VERIFICATION CLASS SECTION 4
N/A 1 2 3 4 A B C D E VERIFICATION
6-2 Level Of
X
Maintainability
6-3 Special Tools And
X
Test Equipment
6-3.1 Equipment
X
Handling
6-3.2 Cable And Wire
X
Marking
6-3.3 Cable
Connections And X
Cable Slack
6-3.4 Panels, Handles
X
And Fastener Standard
6-3.5 Wire And Pin
X
Designations
6-3.6 CaNDI
X
Markings
6-3.7 Name Plate Data X
6-4 Safety Warning
X
Labels
6-5 Human
X
Engineering
6-6 Weather Proofing
And Air Flow X
Filtering
6-7 Built In Test
X
Equipment (BITE)
6-7.1.1 Power
X
Monitoring
6-7.1.2 Over
Temperature,
X
Humidity
Sensors/Alarms
6-8 Re-Certification
X
Requirements
SECTION 7
Materials And X
Processes
7-1 Hazardous
X
Materials Utilized
7-1.1 Paint
X
Used/Required

Document No. 010-00057 - Rev - 91

Rhino II Rhino II Specification

Table 23 Requirement/Verification Cross-Reference Matrix

VERIFICATION METHOD VERIFICATION CLASS
N/A - NOT APPLICABLE A – IN-PROCESS INSPECTIONS
1 – ANALYSIS B – INCREMENTAL DEVELOPMENT INSPECTIONS
2 – DEMONSTRATION C – TECHNICAL DEMONSTRATION
3 – EXAMINATION
4 – NO TESTING WILL BE ASSOCIATED WITH THIS DEMONSTRATION

REQUIREMENT VERIFICATION METHOD VERIFICATION CLASS SECTION 4
N/A 1 2 3 4 A B C D E VERIFICATION
7-1.2 Flammability Of
X
Materials
7-2 Recycled Vice
X
Virgin Materials
SECTION 8 Logistics X
8-1 Maintenance
X
Concept
8-1.1 On Line X
8-1.2 Off Line X
8-2 Overhaul
X
Periods/Hours
8-3 Tools And Test
X
Equipment
8-4 Dimensions X
8-4.1 Weights X
8-4.2 Appearances X
8-4.3 Workmanship X
SECTION 9 Methods
X
Of Verification
9-1 Analysis X
9-2 Demonstration X
9-3 Examination X
9-3.1 Functional Tests X
9-3.2 Methods of
X
Verification
9-4 Classes of
X
Verifications
9-5 Inspections and
X
Tests
9-5.1 Visual
X
Inspections
9-5.2 Functional Tests X
9-5.2.1 Computer
X
System Tests
9-5.2.2 Electrical Tests X

Document No. 010-00057 - Rev - 92

Document Created: 2003-09-30 10:16:26
Document Modified: 2003-09-30 10:16:26

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