Product Description

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Exhibit 1 – WRT-2100 Product Description CPN 815-3695-001 Rockwell Collins, Inc. - Proprietary Information Page 1-1

Exhibit 1 – WRT-2100 Product Description TABLE OF CONTENTS 1.1 System Overview .................................................................................................... 1-3 1.2 System Components ............................................................................................... 1-4 1.3 Aircraft Installation................................................................................................... 1-6 1.4 Operation of Controls .............................................................................................. 1-7 1.5 Equipment Specifications....................................................................................... 1-10 1.6 Receiver-Transmitter............................................................................................. 1-12 1.7 Source (A3A1) ...................................................................................................... 1-14 1.8 Driver Module (A3) ................................................................................................ 1-18 1.9 PA Module (A4) .................................................................................................... 1-18 1.10 Power Multiplier Module (A5) ............................................................................. 1-18 1.11 Duplexer/Monitor(A6) ........................................................................................ 1-19 1.12 Limiter/Preamplifier (A18) .................................................................................. 1-19 st 1.13 Mixer/1 IF Module (A7) .................................................................................... 1-20 1.14 Second IF Module (A8)...................................................................................... 1-20 1.15 Sampler Card (A31) .......................................................................................... 1-20 1.16 DSP Card (A32) ................................................................................................ 1-20 1.17 CPU Card (A34)................................................................................................ 1-21 1.18 I/O Card (A33) .................................................................................................. 1-21 1.19 Low Voltage Power Supply (A2) ......................................................................... 1-21 1.20 Rear Interconnect Module (A1) .......................................................................... 1-21 1.21 Front Panel....................................................................................................... 1-21 1.22 WRT-2100 Oscillators and Critical Frequencies................................................... 1-22 LIST OF FIGURES Figure 1-1. WRT-2100 System Components ........................................................................ 1-5 Figure 1-2. Typical WXR-2100 Aircraft Installation................................................................ 1-6 Figure 1-3. WCP-702 Dual Control Panel............................................................................. 1-7 Figure 1-4. WRT-2100 Receiver-Transmitter Simplified Block Diagram................................ 1-12 Figure 1-5. WRT-2100 RF Section Block Diagram.............................................................. 1-13 Figure 1-6. Source Module (A3A1) .................................................................................... 1-14 LIST OF TABLES Table 1-1. DDS Source Frequencies ................................................................................. 1-16 Table 1-2. WRT-2100 Oscillators and Critical Frequencies.................................................. 1-22 CPN 815-3695-001 Rockwell Collins, Inc. - Proprietary Information Page 1-2

1.1 System Overview The WRT-2100 MultiScan Weather Radar Receiver/Transmitter is an updated version of the Rockwell Collins WRT-701X Air Transport Weather Radar that has been in commercial service for over 20 years. The WRT-2100 is capable of Weather detection out to 320 nautical miles, Ground Mapping, Turbulence detection and Forward-Looking Windshear detection. In addition the WRT-2100 incorporates a new automatic operating mode called MultiScan. The purpose of MultiScan is to provide automatic superior weather hazard detection with an essentially clutter-free display to enable rapid pilot interpretation of weather hazards without the workload required for manual adjustment of the tilt control. Therefore, it is intended that the flight crew may turn on the MultiScan radar in AUTO mode prior to takeoff and fly the entire flight without use of the controls or adjustment of the radar. At the same time, however, if conditions warrant, all controls normally associated with radar operation - MODE, GAIN, and TILT, can be manually adjusted independently by the flight crew to enable a detailed assessment of the weather hazard or terrain situation. MultiScan operates by automatically scanning the antenna over multiple tilt settings while saving the individual scan data in memory. This internal memory data is continually refreshed and corrected for aircraft motion. The display to the flight crew is a composite of multiple scans which have been processed to remove ground clutter and provide an optimal display for weather detection. MultiScan utilizes advanced multiple beam ground clutter suppression techniques which allow the radar beams to be optimized for superior long and short range weather detection while at the same time eliminating clutter from the screen. These techniques enable rapid, unambiguous weather hazard interpretation without the workload associated with excessive tilt management. Ground clutter can be switched in or out of the display by using the Ground Clutter Suppression (GCS) switch. The Windshear Detection feature automatically activates during the takeoff and landing phases of flight to scan the region ahead of the aircraft for microburst windshear hazards. If a windshear event is detected, the radar provides both Aural and Visual warning alerts to the flight crew. This feature can provide up to 60 seconds of advanced warning of a windshear encounter enabling the flight crew to either reject a takeoff or execute a go-around on approach to avoid the windshear hazard. CPN 815-3695-001 Rockwell Collins, Inc. - Proprietary Information Page 1-3

1.2 System Components The WXR-2100 system consists of the following components: Equipment Part Number Description WRT-2100 822-1710-0xx (Boeing) Receiver/Transmitter 822-1710-2xx (Airbus) WMA-701X 622-5135-8xx (Single) Antenna Pedestal WMA-702X 622-5136-8xx (Dual) WFA-701 X 622-6137-601 Antenna Flatplate WCP-701 622-5129-8xx (Single) Control Panel WCP-702 622-5130-8xx (Dual) CPN 815-3695-001 Rockwell Collins, Inc. - Proprietary Information Page 1-4

WFA-701X Flatplate Antenna WRT-2100 Receiver / Transmitter WMA-701X Antenna Pedestal WCP-701 Control Panel Figure 1-1. WRT-2100 System Components CPN 815-3695-001 Rockwell Collins, Inc. - Proprietary Information Page 1-5

1.3 Aircraft Installation The following figure illustrates a typical aircraft installation. The WRT-2100 Receiver-Transmitter is the heart of the radar system. The Receiver/Transmitter produces transmitted output pulses which are radiated through the antenna, it receives and processes the resulting return signals from weather and ground targets and provides a serial digital bus output used to generate a cockpit display of weather and ground targets. The WRT-2100 provides antenna elevation and scan commands to the antenna pedestal, receives and processes the control signals from the cockpit control panels and provides all interfaces to other aircraft systems. The WRT-2100 utilizes multiple sources of aircraft data including Air Data, Aircraft Attitude, Radio Altitude, and numerous discrete inputs. The radar display for the flight crew is generally the Electronic Flight Instruments (EFIS) NAV display. A stand-alone radar indicator is utilized in some older installations. Range selection of the radar display is generally controlled from the EFIS NAV display control panel or radar indicator if installed. RADAR CONTROL UNITS WCP-701 429 429 453 DISPLAY CONTROL CONTROL 453 DISPLAY BUS BUS BUS BUS AUDIO INHIBIT INPUT AUDIO (FROM RWS) PROG PINS AUDIO INHIBIT OUTPUT (TO GPWS) RADOME ANTENNA PEDESTAL FLATPLATE AURAL ANTENNA ANNUNCIATOR SCAN-ELEV DRIVE SCAN-ELEV FEEDBK WRT-2100 Tx-Rx RF FEED RECEIVER/ WARN ANNUNCIATOR TRANSMITTER UNIT CAUTION ANNUNCIATOR 115 VAC (SW) WINDSHEAR FAIL ANNUNCIATOR WFA-701X WMA-701X SIDE SIDESIDE SIDE SIDE SIDE #1 #2 #1 #2 #1 #2 RADIO QUALIFIER A GEAR AIR- 115 VAC ALTIMETER DISCRETES DOWN GRND 400 HZ POWER AUTO INPUT TURN-ON TAS QUALIFIER B AIRCRAFT ARINC 429 (FROM TAS DISCRETES ATTITUDE GROUND COMPUTER) SPEED DRIFT ANGLE Figure 1-2. Typical WXR-2100 Aircraft Installation CPN 815-3695-001 Rockwell Collins, Inc. - Proprietary Information Page 1-6

1.4 Operation of Controls The WRT-2100 is a full function weather radar system intended for air transport category aircraft. It is capable of fully automatic operation utilizing the MultiScan AUTO mode or operating in manual mode with full pilot control of Mode, Range and Tilt. The figure below illustrates a typical dual control panel. Figure 1-3. WCP-702 Dual Control Panel The following paragraphs describe the various operating modes. The following describes the operation of each control during AUTOMATIC MultiScan operation. AUTO The MultiScan AUTO button switches between MANUAL mode and MultiScan AUTOMATIC mode. The AUTO button is a latching alternate action mechanism. When the AUTO button is depressed, both sides are in MultiScan AUTOMATIC mode. When the AUTO button is in the out position, both sides are in manual and all controls function as described in the Manual Operation section. S1/2 (Dual Control Only) This switch selects between System 1 and System 2 in a dual installation. The button is an alternate action latching design. The out position selects System 1, the depressed position selects System 2. (Note: Primary power is applied to the system through the EFIS “WXR” button on the EFIS control panel) CPN 815-3695-001 Rockwell Collins, Inc. - Proprietary Information Page 1-7

TEST The TEST button is used to activate a Self TEST of the radar system. When TEST is selected, both sides are in test. During non-windshear operation, a full self test will be performed including a test pattern on the display, test of the aural and visual windshear alerts as well as the windshear fail indication. At the conclusion of the test sequence, the tilt value displayed will indicate any faults of external data sources required for windshear operation. A list of tilt codes representing external faults is provided in the equipment installation manual. Radar LRU faults are displayed in the normal locations on the display. If TEST is selected while the windshear qualifiers are active, the system will continue operating in windshear mode. The system will perform a “silent” self test with a test pattern being displayed but no aural or visual windshear annunciations. If the qualifiers become active during the test sequence, the system will enter windshear mode canceling the full test sequence and reverting to the “silent” test described above. MODE Selections Four mode selections are available for the both Captain’s and First Officers positions. These are TFR, WX, WX+T and MAP. These are latching buttons such that pressing one releases any other that had been selected. TFR (Transfer) The TFR button allows the Captain or First Officer to select all of the control settings from the opposite side. Therefore, if the First Officer presses the TFR button, the First Officer’s radar control settings and display will be slaved to the Captain’s settings. Conversely, if the Captain presses the TFR button, all control settings and display will be slaved to the First Officer’s side. This function works for both AUTO and Manual modes of operation. During Manual operation, the TFR includes slaving of the TILT value selected on the opposite side. WX Weather Mode enables display of weather targets without turbulence information. If GCS is enabled, the Weather display will be essentially free of ground clutter enabling rapid and accurate interpretation of weather hazards. Path Attenuation Compensation (PAC) and PAC Alert features are active to provide compensation for attenuation due to intervening rainfall and to alert the crew when the compensation limits have been exceeded. WX_T Weather Plus Turbulence Mode enables display of weather targets with turbulence information overlaid on the display. Turbulence will be displayed out to 40 nautical miles for all selected ranges. If GCS is enabled, the Weather plus Turbulence display will be essentially free of ground clutter enabling rapid and accurate interpretation of weather hazards. Path Attenuation Compensation (PAC) and PAC Alert features are active to provide compensation for attenuation due to intervening rainfall and to alert the crew when the compensation limits have been exceeded. MAP Map mode enables display of all radar echoes including terrain and weather information. The STC range correction is adjusted for terrain characteristics instead of weather. This mode enables identification of terrain features such as mountains, coastlines, bodies of water etc. No turbulence information is displayed. PAC and PAC Alert are not active in MAP mode. CPN 815-3695-001 Rockwell Collins, Inc. - Proprietary Information Page 1-8

TILT The TILT control is active only during MANUAL operation and allows the flight crew to adjust the antenna tilt for the best display. Each side, the Captain and First Officer may independently adjust the tilt controls. During MultiScan AUTOMATIC operation, the TILT controls are not active since the antenna tilt settings are managed automatically by the MultiScan function. Note: During MultiScan AUTOMATIC operation, the display bus contains the tilt settings representing the display information being transmitted to the flight crew. Therefore, it is highly recommended to display the TILT values during MultiScan AUTOMATIC operation. The 453 Display Bus Bit-15 is enabled during MultiScan to indicate automatic control of the antenna. GAIN The GAIN control allows manual adjustment of the radar sensitivity for more detailed assessment of weather conditions. The Calibrated (CAL) position, sets the radar sensitivity to the standard calibrated reflectivity levels and is the recommended position for normal operation. If desired, the radar GAIN may be adjusted to increase sensitivity by rotating clockwise from CAL or the sensitivity may be decreased by rotating counterclockwise from CAL. The GAIN control settings and the corresponding sensitivity changes are contained in the following table. CPN 815-3695-001 Rockwell Collins, Inc. - Proprietary Information Page 1-9

1.5 Equipment Specifications Characteristic Specification FAA TSO -C63c dated August 18, 1983 Size 8MCU Weight Less than 30 lb. Power Requirement 115 V ac, 400 Hz Less than 5 amps Transmitted Output Power 150 Watts (+51.8dBm) nominal Frequency X-band, 9327.064 MHz - 9338.876 MHz ± 2 MHz Channels 64 Channels, 187.5KHz Spacing Pulse Length 2.0, 6.0, 20.0 microseconds Pulse Repetition Rate 900 pulses per second in WX, WX+T, Map modes 3000 pulses per second in Windshear mode. Duty Factor 0.06 Receiver IF Bandwidths 10 MHz, 1MHz, First IF Center Frequency 166.765 MHz Second IF Center Frequency 13.9 MHz MDS: –124 dBm nominal STC (Dynamic) optimized for range and pulse width Environmental DO-160D Category Temperature/Altitude Cat A2 -15ºC to +70ºC Operating, 15,000 ft. Temperature Variation Cat C - Vary from -15ºC to +70ºC @2ºC rate Humidity Cat A – 48 Hours Non Operating Shock Cat B - Operational, Crash safety Vibration Cat S – Random Curve C, 1hr per axis, 4.12 grms Explosion N/A Waterproofness N/A Fluid Susceptability N/A Sand and Dust N/A Fungus Resistance N/A Salt Spray N/A Magnetic Effect Cat A– 0.3 to 1.0 meters for 1 degree deflection Power Input Cat E Voltage Spike Cat A – 600 Volt Peak Audio Frequency Susceptibility Cat E –AC input power Induced Susceptibility Cat C – Interference free operation Radio Frequency Susceptibility Cat R Electromagnetic Interference Cat M – Power Lines/Intct Cable-2MHz-6GHz, . Lightning Induced Transient Susceptibility Cat E3 Lightning Direct Effects Boeing D6-16050-4C Multiple Burst, Single Stroke Icing N/A CPN 815-3695-001 Rockwell Collins, Inc. - Proprietary Information Page 1-10

Characteristic Specification Electrostatic Discharge Cat A Cooling Forced Air per Arinc 600 or Fan in R/T Mount Antenna Flatplate Phased Array, 28 Inches Wide X 26.5 Inches, High Half-height waveguide broadside radiators, Milled / Beamwidth Brazed Construction Gain 3.85 º 34.5 dB Data Bus Format Display Data output ARINC 453 Control data input ARINC 429 External data inputs ARINC 429 Stabilization Digital High speed ARINC 429 Analog 3-wire synchro Selectable Modes TEST (test) MAP (ground mapping) WX (normal weather) WX+T (weather with turbulence detection) TURB (turbulence only) MultiScan AUTO Special Features GCS (ground clutter suppression) TFR (Transfer control to opposite side) PAC (Path Attenuation Compensation) MultiScan - Overflight Protection Gain Control Variable above and below CAL CAL – Calibrated, Above CAL +4, +8, +16 dB Below CAL -2,-4, -6, -8, -12, -14 dB Tilt Control -15 to +15 degrees. Selectable Ranges (nmi) 5 to 320 nmi in 5 nmi increments (Aircraft Configuration Dependent) CPN 815-3695-001 Rockwell Collins, Inc. - Proprietary Information Page 1-11

1.6 Receiver-Transmitter The WRT-2100 is an upgraded version of the existing WRT-701X. The WRT-2100 Receiver/Transmitter design includes a new Source module, a new Sampler and a new Digital Signal Processor (DSP) to implement MultiScan capability. The new frequency source module is based on a Direct Digital Synthesis (DDS) design which enables the selection of 64 channels. The Sampler and DSP are upgraded to provide additional computational throughput needed for the advanced MultiScan algorithms. Figure 1-4 is a simplified block diagram showing the relationship of the various modules within the R/T unit. New modules for the WRT-2100 are outlined in bold red. The remainder of the modules are identical to the standard WRT-701X which has been in airline service for many years. The RF Section is outlined in blue. Figures 1-4, 1-5, and 1-6 will be used for the following discussion of module functions. LIMITER MIXER RCVR - I SECOND IF PREAMP FIRST IF (A8) RCVR - Q (A18) (A7) SAMPLER DSP 1st 2nd 3rd New STC LO LO LO A31 A32 Modules for AGC WRT-2100 RF RETURN SOURCE 453 DISPLAY BUSES A3A1 TUNING ANTENNA COMMANDS FEED ANTENNA INTERFACES DUPLEXER DRVR SOURCE MONITOR (A6) TX TRIGGERS CONTROL FREQ LOOP REFERENCE DRIVER PROCESSOR DIGITAL ATTITUDE INPUTS FREQ LOOP PHASE DET A3 FREQ LOOP MONITOR (A34) CONTROL BUSES DIGITAL AIR DATA INPUTS POWER MONITOR TX POWER OUTPUT POW ER RF Section MULTIPLIER PA DRIVE AMP HAZARD BUS (A5) (A4) W/S AUDIO OUTPUTS W/S WARN-CAUTION DIG ATTITUDE INPUT / OUTPUT CARD W/S FAIL (INOP) BITE P/S QUALIFIER INPUTS LOW VOLTAGE 115VAC KEEP-ALIVE (A33) POW ER SUPPLY BITE P/S AUTO-ON AIRCRAFT DISCRETE INPUTS (A2) (A35) HAZARD BUS 115VAC 115VAC 28VDC ON/ R/T ANALOG PROG 400 HZ 400 HZ SWTCH OFF ENABLE RADIO PINS SWTCH ALTITUDE Figure 1-4. WRT-2100 Receiver-Transmitter Simplified Block Diagram CPN 815-3695-001 Rockwell Collins, Inc. - Proprietary Information Page 1-12

Driver A3 Duplexer/Monitor A6 Pwr Mon 499-509 mV @ 50 dBm 300-335 mV @ 47 dBm Source Prepulse Monitor A6A1 A3A1 Ref Chan Trig Tuning Commands Freq Loop Ref 19.5-21.3 Rcv 3rd LO from dBm 13.9 MHZ A31 Sampler Ref Chan x12 Switch Rcv 2nd LO 152.87 MHZ Freq Loop Loop Error A3A5 Rcvr 1st LO Drive TX Drive Tx Gated Drvr Trig Bias Trig 777.25 MHZ Modulator P.A. A4 Multiplier A5 778.24 MHZ Buffer Ckt Ckt 160 W (nominal) 9327.06 MHZ G=-0.35 dB max. Pulse Pulsed -9338.88 MHZ 2 115 W Multiplier PA Drive Bandpass Pulse Ckt Drive P.A. 800 W x3 x4 Filter 3 150 W (nominal) 9327.06 MHZ -9338.88 MHZ Receiver Tx Test 1st LO Drive Noise_Trig 763.36 MHZ Preamplifier A18 Lim_Bias_Trig 764.34 MHZ Noise LNA Limiter Diode G=-0.60 dB max. Mixer Waveguide A7 LO AMP 1st LO A7A1 9160.32 MHZ 9172.08 MHZ x12 + + 2 3 1st. IF Amp AGC 166.8 MHZ 2nd. IF A8 13.9 MHZ A7A2 STC I + - Q 10.5+1.0 dBm Rcv 2nd LO 152.87 MHZ To A31 Sampler 5.0+ 2.0 dBm Rcv 3rd LO 13.9 MHZ STC Gain Control AGC Gain Control from Sampler Figure 1-5. WRT-2100 RF Section Block Diagram CPN 815-3695-001 Rev - Rockwell Collins - Proprietary Information Page 1-13

1.7 Source (A3A1) The Source Module (A3A1) is located as a subassembly of the A3 Driver module and is the primary frequency generating assembly within the Receiver/Transmitter unit. It provides the following outputs. Transmit Channel output to the Driver 777.25 MHz - 778.24 MHz, st RCVR 1 LO Drive 763.36 MHz - 764.34 MHz nd RCVR 2 LO Drive 152.87 MHz rd RCVR 3 LO Drive 13.9 MHz st The Transmit Channel output and Receiver 1 LO output are later multiplied by 12 for the on- channel transmit / receive functions. The Source module also contains a PIC 16F873 microcontroller to control the DDS frequency selections. OSC X2 X4 Rcvr 1st LO Drive 90.33 MHZ 180.66 MHZ 722.64 MHZ 763.36 MHZ 764 - 777.9 764.34 MHZ MHZ R/T CHANNEL Splitter Tx Drive R/T Switch 777.25 MHZ 778.24 MHZ DDS 2 41.35 MHZ RT 40.707 MHZ SWITCH - 41.691 MHZ 2ND L.O 152.87 MHZ 54.604 MHZ -55.589 MHZ DDS 1 DIVIDE BY 2 3RD L.O. 13.9 MHZ 27.8 MHZ 13.9 MHZ PIC Processor Serial Tuning 160 MHZ Commands from PIC 16F873 XTAL OS C A31 Sampler Decoding and frequency Determining Software Prepulse from Prepulse A31 Sampler Figure 1-6. Source Module (A3A1) CPN 815-3695-001 Rev - Rockwell Collins - Proprietary Information Page 1-14

The Source Module contains three elements that determine the frequency of operation. A 90.33 MHz crystal oscillator, a Direct Digital Synthesizer (DDS 1) tuned to a fixed 27.8 MHz and a second DDS 2 with variable output frequencies between 40.707 MHz and 41.691 MHz depending on the operating channel. The second DDS will be referred to as the ‘41 MHz DDS’ for ease of discussion recognizing that it’s frequency changes with channel. The 90.33 MHz oscillator is multiplied by two to get 180.66 MHz, which is used as a clock for the DDS ICs. One of the DDS IC outputs is 27.8 MHz and is mixed with the 180.66 MHz to produce nd rd 152.87 MHz for the 2 LO. The 27.8 MHz signal is divided by two to produce the 13.9 MHz 3 LO. The 180.66 MHz is multiplied by four to produce 722.64 MHz. When the R/T is in receive mode the 722.64 MHz is mixed with the output of the second DDS output at 41MHz to produce st the 764Mhz, the 1 LO frequency. The 13.9 MHz is mixed with the 41MHz to produce 55MHz, which when the R/T is in transmit is mixed with the 722MHz to produce the 777MHz transmit channel frequency. (Note: The 777 MHz transmit channel frequency is subsequently multiplied by twelve by the Multiplier module to achieve the 9.33GHz transmit output frequency.) The output frequency range is 763.36 MHz - 764.34 MHz in Receive mode and 777.25 MHz - 778.24 MHz in Transmit mode. The transmitter frequency is controlled by a tuning word sent serially from the A31 Sampler to the PIC processor located within the Source module. The PIC processor is a single chip microcontroller which receives tuning commands from the A31 Sampler, then sends the appropriate hexadecimal tuning commands to the DDS chips via the serial connection between the PIC and the DDSs. The PIC processor contains an on-chip 16MHz oscillator used for a clock. nd rd The 27MHz DDS output, the 2 LO, and 3 LO do not change frequency with channel number and are constant. The following table contains the DDS Frequencies and channel assignments. It should be noted that the Tx Drive output of the Source module is multiplied by 12 later in the transmit chain to produce the 9327.06 MHz - 9338.88 MHz transmitter output frequency. CPN 815-3695-001 Rev - Rockwell Collins - Proprietary Information Page 1-15

Table 1-1. DDS Source Frequencies DDS Source Frequencies Crystal Oscillator 90331394 Crystal times 2 180662788 Crystal times 8 722651152 27MHz DDS 27794275.0769 3rd LO 13897137.5385 2nd LO 152868512.9231 1st IF 166765650.4615 2nd IF 13897137.5385 DDS CH Hex Value 42MHz Freq. 55MHZ Freq. REC Freq. 1st LO ÷12) TX Freq. (÷ ÷12) (÷ (Hz) (Hz) (Hz) (Hz) (Hz) 0 39AE9B47D4AE 40707036 54604173.54 763358188 9160298256 777255325.5 1 39B4464B150E 40722661 54619798.54 763373813 9160485756 777270950.5 2 39B9F14E556F 40738286 54635423.54 763389438 9160673256 777286575.5 3 39BF9C5195D0 40753911 54651048.54 763405063 9160860756 777302200.5 4 39C54754D631 40769536 54666673.54 763420688 9161048256 777317825.5 5 39CAF2581691 40785161 54682298.54 763436313 9161235756 777333450.5 6 39D09D5B56F2 40800786 54697923.54 763451938 9161423256 777349075.5 7 39D6485E9753 40816411 54713548.54 763467563 9161610756 777364700.5 8 39DBF361D7B3 40832036 54729173.54 763483188 9161798256 777380325.5 9 39E19E651814 40847661 54744798.54 763498813 9161985756 777395950.5 10 39E749685875 40863286 54760423.54 763514438 9162173256 777411575.5 11 39ECF46B98D6 40878911 54776048.54 763530063 9162360756 777427200.5 12 39F29F6ED936 40894536 54791673.54 763545688 9162548256 777442825.5 13 39F84A721997 40910161 54807298.54 763561313 9162735756 777458450.5 14 39FDF57559F8 40925786 54822923.54 763576938 9162923256 777474075.5 15 3A03A0789A58 40941411 54838548.54 763592563 9163110756 777489700.5 16 3A094B7BDAB9 40957036 54854173.54 763608188 9163298256 777505325.5 17 3A0EF67F1B1A 40972661 54869798.54 763623813 9163485756 777520950.5 18 3A14A1825B7B 40988286 54885423.54 763639438 9163673256 777536575.5 19 3A1A4C859BDB 41003911 54901048.54 763655063 9163860756 777552200.5 20 3A1FF788DC3C 41019536 54916673.54 763670688 9164048256 777567825.5 21 3A25A28C1C9D 41035161 54932298.54 763686313 9164235756 777583450.5 22 3A2B4D8F5CFD 41050786 54947923.54 763701938 9164423256 777599075.5 23 3A30F8929D5E 41066411 54963548.54 763717563 9164610756 777614700.5 24 3A36A395DDBF 41082036 54979173.54 763733188 9164798256 777630325.5 25 3A3C4E991E20 41097661 54994798.54 763748813 9164985756 777645950.5 26 3A41F99C5E80 41113286 55010423.54 763764438 9165173256 777661575.5 CPN 815-3695-001 Rev - Rockwell Collins - Proprietary Information Page 1-16

DDS Source Frequencies DDS CH Hex Value 42MHz Freq. 55MHZ Freq. REC Freq. 1st LO ÷12) TX Freq. (÷ ÷12) (÷ (Hz) (Hz) (Hz) (Hz) (Hz) 27 3A47A49F9EE1 41128911 55026048.54 763780063 9165360756 777677200.5 28 3A4D4FA2DF42 41144536 55041673.54 763795688 9165548256 777692825.5 29 3A52FAA61FA2 41160161 55057298.54 763811313 9165735756 777708450.5 30 3A58A5A96003 41175786 55072923.54 763826938 9165923256 777724075.5 31 3A5E50ACA064 41191411 55088548.54 763842563 9166110756 777739700.5 32 3A63FBAFE0C5 41207036 55104173.54 763858188 9166298256 777755325.5 33 3A69A6B32125 41222661 55119798.54 763873813 9166485756 777770950.5 34 3A6F51B66186 41238286 55135423.54 763889438 9166673256 777786575.5 35 3A74FCB9A1E7 41253911 55151048.54 763905063 9166860756 777802200.5 36 3A7AA7BCE247 41269536 55166673.54 763920688 9167048256 777817825.5 37 3A8052C022A8 41285161 55182298.54 763936313 9167235756 777833450.5 38 3A85FDC36309 41300786 55197923.54 763951938 9167423256 777849075.5 39 3A8BA8C6A36A 41316411 55213548.54 763967563 9167610756 777864700.5 40 3A9153C9E3CA 41332036 55229173.54 763983188 9167798256 777880325.5 41 3A96FECD242B 41347661 55244798.54 763998813 9167985756 777895950.5 42 3A9CA9D0648C 41363286 55260423.54 764014438 9168173256 777911575.5 43 3AA254D3A4EC 41378911 55276048.54 764030063 9168360756 777927200.5 44 3AA7FFD6E54D 41394536 55291673.54 764045688 9168548256 777942825.5 45 3AADAADA25AE 41410161 55307298.54 764061313 9168735756 777958450.5 46 3AB355DD660F 41425786 55322923.54 764076938 9168923256 777974075.5 47 3AB900E0A66F 41441411 55338548.54 764092563 9169110756 777989700.5 48 3ABEABE3E6D0 41457036 55354173.54 764108188 9169298256 778005325.5 49 3AC456E72731 41472661 55369798.54 764123813 9169485756 778020950.5 50 3ACA01EA6791 41488286 55385423.54 764139438 9169673256 778036575.5 51 3ACFACEDA7F2 41503911 55401048.54 764155063 9169860756 778052200.5 52 3AD557F0E853 41519536 55416673.54 764170688 9170048256 778067825.5 53 3ADB02F428B4 41535161 55432298.54 764186313 9170235756 778083450.5 54 3AE0ADF76914 41550786 55447923.54 764201938 9170423256 778099075.5 55 3AE658FAA975 41566411 55463548.54 764217563 9170610756 778114700.5 56 3AEC03FDE9D6 41582036 55479173.54 764233188 9170798256 778130325.5 57 3AF1AF012A36 41597661 55494798.54 764248813 9170985756 778145950.5 58 3AF75A046A97 41613286 55510423.54 764264438 9171173256 778161575.5 59 3AFD0507AAF8 41628911 55526048.54 764280063 9171360756 778177200.5 60 3B02B00AEB59 41644536 55541673.54 764295688 9171548256 778192825.5 61 3B085B0E2BB9 41660161 55557298.54 764311313 9171735756 778208450.5 62 3B0E06116C1A 41675786 55572923.54 764326938 9171923256 778224075.5 63 3B13B114AC7B 41691411 55588548.54 764342563 9172110756 778239700.5 CPN 815-3695-001 Rev - Rockwell Collins - Proprietary Information Page 1-17

1.8 Driver Module (A3) The Driver Module contains two major sections; the Source Module (A3A1) described above and the Driver which amplifies the signal used to drive the PA Module. The driver contains pulse amplifier circuits to drive the PA, a frequency control loop, and a reference circuit. The driver receives the 777.25 MHz - 778.24 MHz Tx Drive output from the Source Module (at approximately 30 mW) and amplifies this to approximately 115 Watts which is then used to drive the PA Module (A4). The driver output is modulated by a rectangular “prepulse”. The reference channel provides a separate 777.25 MHz - 778.24 MHz signal to the Duplexer/Monitor (A6) which is multiplied by 12 and used as a phase reference for the transmitted output pulse. The frequency control loop receives a phase detector output signal from the Duplexer/Monitor (A6) module which indicates a phase error between the reference channel and the transmitter output frequency. This phase detector “error” signal is passed through a ‘frequency loop’ amplifier which then provides a correction signal to a phase shifter in the Driver transmit frequency path. This frequency control loop is intended to cancel out phase shift during the transmit pulse induced by heating effects in the PA and Multiplier devices. 1.9 PA Module (A4) The Power Amplifier receives the approximately 115 watt pulsed output from the Driver and amplifies it to an 800 Watt pulsed signal to drive the Power Multiplier (A5). The PA module contains a bipolar first stage which amplifies the signal to approximately 180 watts. This signal is fed to a hybrid splitter that sends the signal to two parallel bipolar power devices. The outputs from these two devices are combined with a hybrid combiner to produce an approximately 800 watt output over the frequency 777.25 MHz - 778.24 MHz. The PA module receives a +66 Volt unregulated DC input from the A2 Power Supply module. The +66 volt power is regulated to approximately +42VDC which charges large storage capacitors to supply the power amplifier devices during the transmit pulses. The DC Input to the PA devices during the transmit pulse is 42VDC at approximately 60 amperes. The PA module contains a circulator at the output to provide isolation between the PA and Multiplier Modules. 1.10 Power Multiplier Module (A5) The Power Multiplier module (A5) multiplies the 800 watt 777.25 MHz - 778.24 MHz drive signal from the PA to produce a single 9327.06 MHz - 9338.88 MHz output at a nominal 150 watts. This signal is then applied to the Duplexer/Monitor (A6) and directed to the antenna as the Transmitted output signal. The Power Multiplier contains X3 and X4 passive diode multiplication stages. The X3 multiplier diode is reverse biased by a -220 volt bias signal from the Multiplier Bias board to act as a non-linear reactance. The 777.25 MHz - 778.24 MHz drive signal is applied to the X3 diode through a microstrip matching network which produces harmonic outputs. The third harmonic of the drive signal is filtered through a microstrip-coupled line filter to produce a 2332.75 MHz - 2334.72 MHz signal which is fed to the X4 stage through a tunable coaxial line filter. The filter is tuned by a coaxial slider which is tuned to optimize the bandpass around 2333 MHz. CPN 815-3695-001 Rev - Rockwell Collins - Proprietary Information Page 1-18

The slider cavity directs the 2333 MHz signal to the X4 multiplier diode mounted in a waveguide cavity structure. The fourth harmonic of the 2332.75 MHz - 2334.72 MHz signal is tuned for optimum peak power output with a tunable waveguide idler structure. The 9327.06 MHz - 9338.88 MHz output signal is then passed through a 3-pole waveguide filter to reject higher harmonics. The output power from the Multiplier A5 is nominally 160 watts peak. The output pulse widths range between 2 and 20 microseconds. The bias voltage to the X3 and X4 multiplier diodes is switched on and off by the transmit trigger signal from the A31 Sampler. This bias switching allows the PA power to reach maximum before the multiplier is switched on to produce fast transmitter output pulse rise and fall times. The output of the Power Multiplier is applied to the transmitter input port of the Duplexer/Monitor. 1.11 Duplexer/Monitor(A6) The Duplexer/Monitor (A6) performs three functions; 1)couples the transmitter output of the A5 Power Multiplier to the Antenna, 2) directs the antenna input signal to the receiver Limiter/Preamplifier (A18), and 3) provides a monitor of the transmitter output power and phase. The Duplexer/Monitor couples the transmitter output to the antenna through a 4-port circulator. The circulator also functions to match the impedance of the transmitter output. The 4-port circulator also couples received energy from the antenna port to the receiver Limiter/Preamplifier input. The fourth port of the circulator is terminated into a load resistor. The Duplexer/Monitor function includes a microstrip coupler and detector to sample the transmitted power output. This detected output is used to monitor transmitter power output. The monitor function also contains a phase detector function which compares the transmitted output frequency to an on-channel reference signal. The phase detector output is fed back to the frequency loop amplifier in the A3 Driver module and is used to correct the phase of the transmitter output. The phase detector reference is derived from the A3 Driver 777.25 MHz - 778.24 MHz Reference output which is multiplied by twelve in the Duplexer/Monitor to produce the on-channel reference to the phase detector. The X12 reference multiplier is a passive varacter diode with a stripline filter. 1.12 Limiter/Preamplifier (A18) The Limiter/Preamplifier (A18) contains a limiter section to protect the input of the receiver and a preamplifier to amplify the received signal. The Limiter/Preamplifier also contains a noise diode assembly which is used during test mode to test the receiver noise figure and STC gain response. The limiter section consists of a three stage microstrip diode limiter. During transmit operation, the diodes are forward biased by a +5V dc bias source to provide a low impedance shunt to ground for RF energy. This limiter prevents damage to the receiver front-end from reflected transmit energy caused by high VSWR conditions at the antenna or transmitter leakage through the duplexer. The limiter also contains a self-bias detector to apply limiting in case of high energy received from another radar or RF source during receive time. The Preamplifier consists of a two stage FET preamplifier. Each stage contributes approximately 9.5dB of gain at 9333 MHz. The overall gain is +18 dB minimum with a 3dB noise figure. Gate and drain bias for the FET amplifiers is generated on the preamplifier bias circuit board. CPN 815-3695-001 Rev - Rockwell Collins - Proprietary Information Page 1-19

1.13 Mixer/1st IF Module (A7) st st The Mixer/1 IF Module (A7) contains a X12 LO Multiplier, Mixer, and 1 IF Amplifier. The st 763.36 MHz - 764.34 MHz 1 LO Drive signal from the Source Module (A3A1) is applied to a buffer amplifier and a X12 diode multiplier/filter. The output from the X12 multiplier is the st st 9160.32 MHz - 9172.08 MHz 1 LO signal which is applied to a waveguide mixer. This 1 LO st signal is mixed with the incoming radar signal from the preamplifier to produce the 1 IF signal at st st 166.8 MHz. This received 1 IF signal is amplified by the 1 IF Amplifier and passed to the Second IF Module (A8). 1.14 Second IF Module (A8) The Second IF (A8) contains an amplifier, Mixer, 13.9MHz Gain Stages, AGC and STC gain control inputs and a Quadrature Detector. st The 166.8 MHz received signal from the 1 IF is filtered and applied to a mixer amplifier in the nd Second IF. This signal is mixed with the 152.87MH 2 LO signal from the Source Module (A3A1). The resulting 13.9MHz third IF signal is amplified and passed through AGC and STC controlled gain stages. The Automatic Gain Control (AGC) is controlled to set the noise floor of the receiver. The Sensitivity Time Control (STC) is a fast bin-to-bin gain control function to maintain the return signal at a normalized level 10 dB below saturation. The AGC and STC functions are controlled by the Sampler (A31). The amplified 13.9 MHz Second IF signal is power divided into two signals that are mixed with a third local oscillator (Third LO) signal, developed by Source (A3A1) to produce the I (In phase) and Q (Quadrature phase) RETURN signals. The I and Q signals are applied to the Sampler (A31). 1.15 Sampler Card (A31) The I and Q RETURN signals are applied to the digital weather data processing portion of the R/T. The Sampler Card contains three TMS320C44 Digital Signal Processor chips. These operate from a 40 MHz crystal oscillator clock located on the circuit card. The Sampler converts the I and Q RETURN signals to digital and originates the STC (Sensitivity Time Control) and AGC feedback signals used in the Second IF. The sampler (DSP00) also provides timing and receive/transmitter control pulses to the receiver-transmitter section of the unit. Digital signal processors DSP01 and DSP02 on the sampler board are currently not used (they will be used for Enhanced turbulence detection capability). The Sampler also controls the Noise Diode in the Limiter/Preamplifier module (A18) to perform the receiver self test functions. 1.16 DSP Card (A32) The digital information is then passed to the DSP circuit card. The DSP circuit card contains 5 digital signal processors, which perform different functions in processing the returned signals, including formatting the digitized data for the display. The DSP card contains three Texas Instruments TMS320VC33 DSP chips and two Analog Devices 21065L DSP chips. The two Analog Devices ADSP21065L processors (DSP M and DSP M’) are dedicated to the MultiScan function. These processors perform the computational task of intelligently merging multiple weather sweep data sets. They also perform the rotation and translation function necessary to provide a display image that is coordinated with aircraft movement. DSP3 is responsible for sending the weather data to the display on the 453 bus. The 453 display bus drivers are located on the CPU board. CPN 815-3695-001 Rev - Rockwell Collins - Proprietary Information Page 1-20

Two crystal controlled oscillators are located on the DSP circuit card to provide clock signals for the DSP chips. The TMS320C44 DSPs utilize a 30 MHz clock oscillator and the ADSP21065L DSPs utilize a 12 MHz clock oscillator. The ADSP21065L DSPs contain an internal X5 clock multiplier to run internally at 60 MHz. 1.17 CPU Card (A34) The control Processor (CPU) manages virtually all of the radar system operation. The CPU receives and decodes all aircraft data inputs, receives control commands from the cockpit control panel, manages the processing modes of the Sampler and DSP modules. The CPU also performs the antenna scanning and attitude stabilization functions. The CPU manages the internal test and monitoring functions. The CPU is an Intel 80196 processor running at 16 MHz. The CPU communicates with DSP1 through a dual port memory. The interface to the I/O card is through a bi-directional latch. The CPU utilizes a 16 MHz crystal controlled clock oscillator. 1.18 I/O Card (A33) The I/O Card (A33) contains interfaces to various aircraft data sources including synchro attitude, synchro airspeed and heading, along with several Arinc 429 data sources. The CPU communicates with the I/O card through a bi-directional latch. An Intel 8031 BITE processor is also located on the I/O card. This processor stores detected faults in non-volatile memory and interfaces with the aircraft on-board maintenance systems. The BITE processor utilizes a 12 MHz crystal oscillator for a clock. 1.19 Low Voltage Power Supply (A2) The Low Voltage Power Supply operates from the 115VAC 400Hz aircraft power bus and provides the power to all of the internal cards and modules. The power supply also supplies power to the external control panel, waveguide switch (dual installation) and antenna pedestal. All of the power lines that come into or leave the WRT-2100 have the appropriate filtering and isolation to meet EMI requirements. 1.20 Rear Interconnect Module (A1) The rear interconnect module provides the interconnect wiring between the WRT-2100 rear connector and the power supply, circuit cards and modules contained within the WRT-2100. 1.21 Front Panel The front panel contains a 15 pin Cannon ‘D’ test connector which provides an interface to an RS-232 terminal such as a laptop PC. The RS-232 interface is used for test and diagnostic purposes and is not connected to the aircraft. Functions available through the RS-232 interface include Programming of the CPU and DSP code, internal fault diagnostics, monitoring of external aircraft inputs and parameters, control of specialized test modes, and downloading of internally stored windshear events captured in flash memory. The front panel also includes a BNC Reference Output for locking an RF signal generator to the transmit/receive frequency during bench test. CPN 815-3695-001 Rev - Rockwell Collins - Proprietary Information Page 1-21

1.22 WRT-2100 Oscillators and Critical Frequencies The following table lists the oscillators contained within the R/T unit and critical frequencies. Table 1-2. WRT-2100 Oscillators and Critical Frequencies Function Frequency KHz/MHz (A33) Universal I/O ARINC 429 Bus High 100.0 kHz (A33) Universal I/O ARINC 453 Bus 1.0 MHz (A33) Universal I/O UART Clock 2.0 MHz (A33) Universal I/O Clock 12.0 MHz (A33) BITE Processor Clock 12.0 MHz (A34) Main CPU Clock 16.0 MHz (A34) Processor UART Clock 2.0 MHz (A32) DSP – DSP1,DSP2,DSP3 Clock 12.0 MHz (A32) DSP - ARIES ARINC 429 High Speed UART 20.0 MHz (A32) DSP – DSP1,DSP2,DSP3 Data Bus 30.0 MHz (A32) DSP – DSPM, DSPM2 (SHARC) Clock 30.0 MHz (A32) DSP – DSPM, DSPM2 Data Bus 60.0 MHz (A31) Sampler DSP00, DSP01,DSP02 Data Bus 20.0 MHz (A31) Sampler – DPS00,DSP01,DSP02 Clock 40.0 MHz (A3) Source - PIC 16F873 Microcontroller Clock 16.0 MHz (A3) Source XTAL Oscillator 90.331394 MHz (A3) Source – DDS1 27.794275 MHz (A3) Source – DDS2 40.707036 - MHz 41.691411 MHz rd (A3) Source - 3 LO Drive 13.897137 MHz nd (A3) Source - 2 LO Drive 152.868512 MHz st (A3) Source - 1 LO Drive 763.358188 MHz 764.342563 MHz (A3) Source - Tx Drive 777.255325 MHz 778.239700 MHz (A5) Multiplier Tx Output / Rx RCV Frequency 9327.0639 - MHz 9338.8764 MHz st (A7) 1 IF Frequency 166.765650 MHz nd (A8) 2 IF Frequency 13.897137 MHz CPN 815-3695-001 Rev - Rockwell Collins - Proprietary Information Page 1-22


Document Created: 2002-03-21 14:37:38
Document Modified: 2002-03-21 14:37:38
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