Attachment Schedule S document SAT-LOI-20080910-00183

Attachment Schedule S document

This document pretains to SAT-LOI-20080910-00183 for Letter of Intent on a Satellite Space Stations filing.

IBFS_SATLOI2008091000183_694915

BSSNET119W

CONTENTS
Section Page

1 - GENERAL SYSTEM DESCRIPTION......................................................................................4
2 - SPACE SYSTEM OPERATING CHARACTERISTICS ..........................................................5
2.1 FREQUENCY AND POLARIZATION PLAN ......................................................5
2.2 COMMUNICATIONS PAYLOAD ........................................................................7
2.2.1 Uplink/Downlink Interconnection and Frequency
Translation..................................................................................................7
2.2.2 Transponder Channel Characteristics.........................................................7
2.2.2 Transponder Channel Characteristics.........................................................8
2.2.3 Transmit Beams and Antennas .......................................................................9
2.2.3.1 CONUS+ Beam ..............................................................................9
2.2.3.2 Spot Beams .....................................................................................9
2.3 TELEMETRY, TRACKING & COMMAND, TT&C ..........................................12
3 - SERVICES ...............................................................................................................................14
4 - LINK ANALYSIS....................................................................................................................14
5 - EARTH STATIONS.................................................................................................................15
6 - SATELLITE ORBIT CHARACTERISTICS...........................................................................15
7 - POWER FLUX DENSITY.......................................................................................................15
8 - PHYSICAL CHARACTERISTICS OF THE SPACE STATION...........................................17
9 - SPACECRAFT BUS SUBSYSTEM........................................................................................17
10 - COMMON CARRIER STATUS ...........................................................................................18
11 - SCHEDULE ...........................................................................................................................18
12 - INTERFERENCE ANALYSIS ..............................................................................................18
13 - ORBITAL DEBRIS MITIGATION.......................................................................................19
13.1 ORBITAL DEBRIS AND ORBITAL STORAGE....................................................19
13.2 SPACECRAFT HARDWARE DESIGN..................................................................20
13.3 LIMITATION ON RELEASE OF ORBITAL DEBRIS DURING
NORMAL OPERATIONS AND FROM COLLISIONS WITH
SMALL DEBRIS OR METEOROIDS .................................................................22
13.5 MINIMIZING ACCIDENTAL EXPLOSIONS ........................................................22
13.6 SATELLITE COLLISIONS WITH LARGE OBJECTS..........................................23
14 - CONCLUSION ......................................................................................................................26
1 - GENERAL SYSTEM DESCRIPTION .........................................................................4

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BSSNET119W
(Earth-to-Space). The Telemetry, Tracking and Control (“TT&C”) functions will

also be provided at the edges of these same frequency bands.

The BSSNET119W satellite is capable of supporting 10 "17/24"

uplink/downlink transponders (5 LHCP and 5 RHCP) providing coverage via a

"CONUS+" national beam and 16 downlink/uplink transponders (8 LHCP and 8

RHCP) providing coverage via 53 spot beams. The national coverage beam is

designed to provide coverage to all 50 states (CONUS, Alaska and Hawaii). The

spot beams also provide local/regional programming to this area as well as the

Netherlands Antilles, Puerto Rico, and U.S. Virgin Islands. Working in

conjunction with SPECTRUM FIVE's Ku BSS satellite to be launched at 119°

W.L., the national beams provide additional capacity for improved HDTV

programming delivery, and the spot beams carry HD local-into-local

programming material into new service areas not served by the Ku BSS system.

All national programming material will be aggregated and uplinked from the

SPECTRUM FIVE broadcast center in Los Angeles, CA, while regional/local

programming material will be uplinked at six selected broadcast sites.

The available 4

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00 MHz of spectrum in CONUS on both uplink and downlink will be

channelized into 26 channels of 24 MHz nominal bandwidth each, with 29.16

MHz spacing between co-polar channel center frequencies, and with the cross-

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17.7 GHz downlink band. All of these channels are to be uplinked from the

national broadcast center in Southern California.

The upper portion of the 24.75

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-25.15 GHz uplink band is also re-used multiple times through

transmissions from a number of carefully located and geographically separated

regional aggregation broadcast sites, ( sites S1 to S7). The transmissions from

each of these regional broadcast sites will carry a unique mix of HD regional/local

broadcast programming information and other new services provided by the

BSSNET119W satellite. These uplink transmissions will be connected to the

appropriate downlink spot beams as detailed in Table 2-1 and Appendix A, Table

A-1.

2.2.2 Transponder Channel Characteristics

The maximum receive antenna gain, receive system noise temperature,

and maximum G/T of the BSSNET119 satellite are all specified in the

accompanying Schedule S. BSSNET119W employs 1m diameter uplink receive

antennas with a maximum gain of 47.0 dB and a receive G/T pf 17.5 dBoK. Note

that the G/T will decrease, dB-for-dB, from the maximum as the uplink location

moves away from beam peak. BSSNET119W will employ input multiplexer

(“IMUX”) and output multiplexer ("OMUX") filters to limit the bandwidth of

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antenna system will cover CONUS+Alaska+Hawaii and will be capable of

transmitting across the frequency band 17.3-17.7 GHz using LCP and RCP. The

peak transmit gain of 37.7dB, and the antenna gain contour in GXT format, are

given in the accompanying Schedule S. The gain contour for CONUS+ beam is

also graphically depicted in Figure 2-1 below.

2.2.3.2 Spot Beams

BSSNET119W employs four 2.8x3.5m spot beams antennas to provide

maximum spot beam interference reduction, a critical parameter in the

performance of these antenna systems. Peak antenna gain is 46.5 dB including

antenna losses after the TWTA. Locations of the downlink spot beams are

shown in Table 2-5.

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SPECTRUM FIVE will use the BSSNET119W satellite to retransmit digital

video and audio entertainment, educational and informational programming to

subscribers throughout the United States, including Alaska, Hawaii, and the

Netherlands Antilles.

4 - LINK ANALYSIS

Representative communications link budgets for the BSSNET119W

satellite are shown in Appendix A as Tables A-1 to A-8. There is one link budget

for a city in each of the CONUS downlink power flux density (“PFD”) regions

defined by the Commission’s rules, and one for a non-CONUS region (Alaska or

Hawaii), as well as the same four cities operating with the spot beam

transponder. SPECTRUM FIVE is applying for an orbital location that is not offset

from the FCC "Appendix F grid", and requests that it be allowed to operate at full

power with full protection according to the Commissions' rules. These budgets

include an entry for adjacent satellite interference (“ASI”) from neighboring 17/24

GHz BSS satellites nominally spaced at -8.0º, -4.0º, +4.0º, and +8.0º relative to

BSSNET119W.

The link analysis performed using a 45 cm earth station antenna shows

that availability numbers for the spot beam operation exceeds 99.7% across

CONUS, and exceeds 99.5% for the national beams when operating the link with

a high spectral efficiency modulation scheme (8PSK, Rate 2/3). This includes the

effects of adjacent satellites operating at maximum power at the four locations

discussed above.

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5 - EARTH STATIONS

There are three types of earth stations to be used with the

BSSNET119W satellite: subscriber terminals with small antennas (45-65cm),

large feeder-link stations using for uplinking the video content (13m), and a

large TT&C station antenna (7m). Subscriber terminals for reception outside

CONUS may need to be somewhat larger, typically 1 meter. The characteristics

of these three terminal types are summarized in the attached Schedule S.

6 - SATELLITE ORBIT CHARACTERISTICS

The BSSNET119W satellite will be maintained in geosynchronous orbit at

the 119º W.L. orbital location with a maximum North-South drift of ± 0.05°, and a

maximum East-West station keeping of ± 0.05.

7 - POWER FLUX DENSITY
The allowable PFD levels in the 17.3-17.7 GHz band are defined in

Section 25.208(w) of the Commission’s rules on a regional basis for all

conditions, including clear sky, and for all methods of modulation as:

In the region of the contiguous United States, located south of 38º North
Latitude and east of 100º West Longitude: -115 dBW/m2/MHz;

In the region of the contiguous United States, located north of 38º North
Latitude and east of 100º West Longitude: -118 dBW/m2/MHz;

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In the region of the contiguous United States, located west of 100º
West Longitude: -121 dBW/m2/MHz; and

For all regions outside of the contiguous United States including Alaska
and Hawaii: -115 dBW/m2/MHz.

As discussed in Section 2.2.2 above, the maximum downlink EIRP for

BSSNET119W will be 61.4dBW/24 MHz channel. The maximum power flux

density/MHz on the Earth’s surface from this emission is calculated as follows:

Peak PSD (dBW/MHz) = EIRP(dB) - Spreading Loss (dB) - BW

Factor(dB)

where Bandwidth Factor (dB) = 10(log(24) for a 24 MHz transponder. The

atmospheric loss (which is always present as a link attenuation) provides an

additional margin for this calculation.

For the maximum EIRP of 61.4 dBW discussed earlier, PSD = +61.4-
162.6 (dB/

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m2) – 10log(24) = -115.0 dBW/m2/MHz. The atmospheric loss in the South

Florida area where this maximum occurs is at least 0.35 dB, providing additional

margin This bandwidth allocation applies to the QPSK modulation mode, For

the 8PSK modulation mode, the PSD would be -115.3 dBW/m2/MHz maximum

minus the atmospheric loss.

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As discussed in Section 2.2.3.1 above, the downlink national beam
antenna gain pattern for BSSNET119W shows (1) that the antenna gain north of
38º North latitude and east of 100º W.L. is at least 3 dB below peak gain, and (2)
that the antenna gain west of 100º W.L. is at least 6 dB below peak gain. As a
result, the maximum PFD for the CONUS+ beam on the earth’s surface complies
with Section 25.208(w) for the national beams in each of the applicable regions
defined in the Commission’s rules. For the spot beams, the peak EIRP of each
spot beam is adjusted to remain below the appropriate PSD limit depending on
what region the beam is in, and cannot exceed -115 dBW/m2/MHz anywhere
outside CONUS for the spot beams as well.

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8 - PHYSICAL CHARACTERISTICS OF THE SPACE STATION

SPECTRUM FIVE has not yet settled upon exact specifications for the physical
characteristics of the satellite as it has not yet contracted for the construction of
the BSNET119W satellite Accordingly, the payload envelope has been estimated
to allow more than one spacecraft currently available with extensive heritage and
fully qualified

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t

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technology to serve as the design platform. SPECTRUM FIVE anticipates that
the key spacecraft characteristics for BSNET119W are as summarized in the
appropriate sections of the accompanying Schedule S.

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9 - SPACECRAFT BUS SUBSYSTEM

As discussed

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above, SPECTRUM FIVE has not yet contracted with a manufacturer for

the construction of the BSSNET119W satellite and does not wish to show a

preference by providing data specific to any one manufacturer. As such, it is

difficult to discuss any specific characteristics of what may comprise the

spacecraft bus subsystem beyond that already specified in the accompanying

Schedule S.

SPECTRUM FIVE will provide the Commission with full spacecraft

physical characteristics once a final spacecraft provider has been selected

and a final satellite design has been adopted.

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10 - COMMON CARRIER STATUS

SPECTRUM FIVE intends to operate the BSNET119W satellite on a non-
broadcast, non-common carrier basis, as it anticipates

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. SPECTRUM FIVE may sell and/or lease a portion of its capacity on a

non-common carrier basis for complementary business purposes.

11 - SCHEDULE

SPECTRUM FIVE will contract for, begin construction of, and launch

and operate BSNET119W in accordance with the milestones specified in Section

25.164(a) of the Commission’s rules.

12 - INTERFERENCE ANALYSIS

The Commission has established coordination thresholds for earth station off-
axis EIRP density and spacecraft PFD in Sections 25.223 and 25.208,
respectively. In order to achieve maximum compatibility between diverse
networks, the Commission has established coordination thresholds for earth
station off-axis EIRP density and spacecraft PFD in Sections 25.223 and 25.208,
respectively. In order to achieve maximum compatibility between diverse
networks, the Commission has established coordination thresholds for earth
station off-axis EIRP density and spacecraft PFD in Sections 25.223 and 25.208,
respectively.

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n order to achieve maximum compatibility between diverse networks, the
Commission has established coordination thresholds for earth station off-axis
EIRP density and spacecraft PFD in Sections 25.223 and 25.208, respectively.

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SPECTRUM FIVE has assumed for the purposes of this application regional
maximum downlink PFD values from neighboring systems consistent with Section
25.208(w), maximum feeder link earth station off-axis transmit power density
consistent with Section 25.223, and receive earth station compliance with
Section 25.224 (

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Recommendation ITU-R BO.1213). The interference analyses that are

included in this application were performed in conjunction with the end-to-end

link performance analyses. Abbreviated link budgets are presented in Tables A-

1 through A-8 in Appendix A, i.e. one budget for each of the PFD regions

defined in Section 25.208(w). In each case, the analysis includes the effects of

adjacent satellite interference from satellites nominally located at -8.0º, -4.0º,

+4.0,º and +8.0º relative to BSSNET119W in evaluating whether the system

accommodates the various data rates at acceptable C/(N+I) thresholds.

Additionally, adjacent satellite interference was calculated assuming 0.05°

station-keeping of the interfering satellites. Tables A-1 to A-8 of Appendix A

demonstrate that the BSSNET119W satellite design described in this application

is compatible with the aforementioned transmission parameters and interference

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environment. Accordingly, the proposed 17/24 GHz BSS satellite would operate

successfully in such an environment.

13 - ORBITAL DEBRIS MITIGATION

13.1 ORBITAL DEBRIS AND ORBITAL STORAGE

This section is consistent with the requirements specified in the FCC’s Second

Report & Order, IB Docket 02-54, Released June 21, 2004, Part 25.114 of the

FCC Rules and Public Notice DA –2698 “Disclosure of Orbital Debris Mitigation

Plans, Including Amendment of Pending Applications”.

Spectrum Five’s spacecraft procurement will be initiated during 2008, and have a

construction contract in one year after license award. The new spacecraft,

BSSNET119W, a Satellite Operations Center, SOC, Network Operations, Center,

NOC and feederlink earth stations will be fully defined by specifications,

statement of work, test plans and contract. These documents will contain the

FCC requirements and objectives described in the Orbital Debris Second Report

and Order. In addition, design reviews will include consideration of these

requirements and how they will be specifically implemented by the manufacturer

and by the SOC operator, including a requirement to cooperate and exchange

vital information with the operator, including a requirement to cooperate and

exchange vital information with the SOCs of neighboring satellites.

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13.2 SPACECRAFT HARDWARE DESIGN

The Spectrum Five satellites will not be a source of debris either during

the launch, drift or operating mode; no debris is planned to be released. All

separation and deployment mechanisms, and any other potential source of

debris will be retained by the spacecraft or launch vehicle. The spacecraft TT&C

system, vital for orbit raising, will be extremely rugged with regard to meteoroids

smaller than 1 cm, by virtue of its redundancy, shielding, separation of

components and physical characteristics. Omni-directional antennas are

mounted on opposite sides of the spacecraft. These antennas, each providing

greater than hemispherical coverage patterns are extremely rugged and capable

of providing adequate coverage even if struck and bent or otherwise damaged by

a small or medium sized particle. Either omni-directional antenna, for either

command or telemetry, is sufficient to enable orbit raising. The command

receivers and decoders and telemetry encoders and transmitters will be located

within a shielded area and will be totally redundant and physically separated. A

single rugged thruster and shielded propellant tank provide the energy for orbit

raising. Otherwise, there are no single points of failure in the system. Spectrum

Five will continue to review these aspects of on-orbit operations with the

spacecraft manufacturer and will make such adjustments and improvements as

appropriate to assure that its spacecraft will not become sources of debris during

operations or become derelicts in space due to a collision with a small, medium

or large object. To

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accomplish these and the following objectives Spectrum five plans to incorporate

the material of this document into its satellite Technical Specifications, Statement

of Work and Test Plans. The Statement of Work will include provisions to review

orbit debris mitigation as part of PDR and CDR and to incorporate its

requirements, as appropriate, into its Test Plan, including a formal Failure Mode

Verification Analysis, FMVA, for orbital debris mitigation involving particularly the

TT&C, propulsion and energy systems.

At the appropriate time, Spectrum Five intends to contract with an appropriate

agency which can supply information regarding large orbital debris that may pose

a threat to Spectrum Five’s satellites. With the situation as described in this

paragraph, only normal station-keeping regimens are necessary to avoid

collisions. Frequency and physical coordination during orbital drift cannot be

undertaken until license authorization and until the spacecraft and launch vehicle

manufacturers are selected and a Launch Plan, launch vehicle and launch

scenario developed. No pre-operational orbits requiring STA authority are now

anticipated.

13.3 LIMITATION ON RELEASE OF ORBITAL DEBRIS DURING

NORMAL OPERATIONS AND FROM COLLISIONS WITH SMALL DEBRIS OR

METEOROIDS. Spectrum Five has assessed the likelihood of the release of

debris during normal operations and, based on the present design, believes that

there will not be any planned release of debris during normal operations of the
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Spectrum Five satellites. The spacecraft will be designed with full redundancy

for all active components, with shielding where appropriate. Location of critical

components will minimize exposure to small debris or meteoroids that might

cause catastrophic failure of the spacecraft control system or prevent orbital

storage at the end of spacecraft life. Spectrum Five will continue to review these

aspects of on-orbit operations with the spacecraft manufacturer and will make

such adjustments and improvements as appropriate to assure that the spacecraft

is not the source of debris during operations or becomes derelict in space due to

collision with a small object. The following items are those which will be

embodied in the procurement, launch and operational documents.

13.5 MINIMIZING ACCIDENTAL EXPLOSIONS

Spectrum Five will contract for a spacecraft design that limits the

probability of accidental explosions that might fragment the satellite during and

after completion of mission operations. All batteries and fuel tanks will be

monitored for pressure and temperature. Excessive battery charging or

discharging will be limited by a monitoring and control system which will

automatically limit the possibility of fragmentation. Corrective action, if not

automatically undertaken, will be immediately undertaken by the SOC to avoid

destruction and fragmentation. Thruster temperatures, impulse and thrust

duration are carefully monitored; any thruster may be turned off via redundant

valves. Consequently, there is no possibility of explosion during the operating

mission.

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All TWTAs will be outgassed prior to post-mission disposal. After post-

mission disposal all residual fuel is will be consumed, all fuel latch valves will be

placed in an “open” position and any pressurized system will be vented.

Spacecraft battery trickle charge and all automatic battery charging sequences

will be disabled.

Consequently, via its spacecraft documentation, design reviews, FMVA,

test plans and testing, Spectrum Five will assess and limit the possibility of

accidental explosions during mission operations and assure that all stored energy

at the end of the spacecraft’s mission operation will be removed.

13.6 SATELLITE COLLISIONS WITH LARGE OBJECTS

Spectrum Five has considered the possibility of its spacecraft becoming a

source of debris by collisions with large debris other than spacecraft. Extensive

damage may be done, perhaps rendering it inoperative with respect to its

communications mission yet enabling the TT&C and propulsion systems to

function sufficiently to permit the achievement of a parking orbit. This capability

is due to the inherent ruggedness, shielding and redundancy of the TT&C and

propulsion system. The preservation of this capability will be emphasized in

Spectrum Five’s procurement documents, design reviews, test plans and FMVA,

as described above. Through these methods, Spectrum Five intends to limit the

probability of its spacecraft becoming a source of debris by collisions with large

debris or other operational space stations.

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This section is consistent with the requirements specified in the FCC’s Second

Report & Order, IB Docket 02-54, Released June 21, 2004, Part 25.114 of the

FCC Rules and Public Notice DA –2698 “Disclosure of Orbital Debris Mitigation

Plans, Including Amendment of Pending Applications”. Spectrum Five’s

spacecraft procurement will be initiated during 2008/2009, with the objective of

selecting a spacecraft manufacturer by the end of 2009. The new spacecraft,

BSSNET119W, , a Satellite Operations Center, SOC, a Network Operations

Center, NOC and feederlink earth stations will be fully defined by specifications,

statement of work, test plans and contract. These documents will contain the

FCC requirements and objectives described in the Orbital Debris Second Report

and Order. In addition, design reviews will include consideration of these

requirements and how they will be specifically implemented by the manufacturer

and by the SOC operator, including a requirement to cooperate and exchange

vital information with the operator, including a requirement to cooperate and

exchange vital information with the SOCs of neighboring satellites.

SPECTRUM FIVE will limit the amount of debris released in a planned

manner during normal operations. BSSNET119W will not be a source of debris

during launch, drift, or operating mode, as SPECTRUM FIVE does not intend to

release debris during the planned course of operations of the satellite.

SPECTRUM FIVE will also consider the possibility of BSSNET119W becoming a
source of debris by collisions with small debris or meteoroids that could cause loss

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of control of the spacecraft and prevent post-mission disposal. As such,
SPECTRUM FIVE will take steps to address this possibility by incorporating
redundancy, shielding, separation of components, and other physical
characteristics into the satellite’s design. For example, omni-directional antennas
will be mounted on opposite sides of the spacecraft, and either will be sufficient
to support orbit raising. The command receivers and decoders, telemetry
encoders and transmitters, and the bus control electronics will be fully redundant,
physically separated, and located within a shielded area to minimize the
probability of the spacecraft becoming a source of debris due to a collision.
SPECTRUM FIVE will continue to review these aspects of on-orbit operations
with the spacecraft manufacturer and will make such adjustments and
improvements as appropriate to assure that its spacecraft will not become a
source of debris during operations or become derelict in space due to a collision.

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Safe Flight Profiles

SPECTRUM FIVE will assess and limit the probability of BSSNET119W
becoming a source of debris by collisions with large debris or other operational
space stations through detailed and conscientious mission planning. In addition to
reviewing the existing on-orbit operational satellites near 119° W.L. (Direct-7S
and Echostar-7 are currrently operating from 119° W.L.) SPECTRUM FIVE has
also reviewed the list of licensed systems and systems that are under
consideration by the Commission near (within +-0.2°)

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the nominal 119° W.L. orbital location it has requested. In addition, in order to
address non-U.S. licensed systems, SPECTRUM FIVE has reviewed the list of
satellite networks in the vicinity of 119° W.L. for which a request for coordination
has been submitted to the ITU. Only those networks that are operating, or are
planned to be operating, within ± 0.4

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° have been taken into account in this review.

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As a consequence of this review, it has been determined that aside from US DBS
satellites operating at 118.8° W.L., 119.0° W.L., and 119.2° W.L.,

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Document Created: 2009-02-05 12:08:38
Document Modified: 2009-02-05 12:08:38

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