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`REPLACEMENT PAGE
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`REVISED: December 8, 1995
`
`Copyright@ 1996 by
`AERONAUTICAL RADIO, INC.
`2551 Riva Road
`
`Annapolis, Maryland 21401-7465 USA
`
`;
`
`AVIATION SATELLI'I'E COMMUNICATION SYSTEM
`
`PART 1
`
`AIRCRAFT INSTALLATION PROVISIONS
`
`Published: January 25, 1996
`
`Prepared by the Airlines Electronic Engineering Committee
`
`Characteristic 741
`
`Adopted by the Airlines Electronic Engineering Committee: October 9, 1986
`
`Characteristic 741-1
`
`Adopted by the Airlines Electronic Engineering Committee: September 22, 1988
`
`Characteristic 741-2
`
`Adopted by the Airlines Electronic Engineering Committee: August 30, 1990
`
`Characteristic 741-3
`
`Adopted by the Airlines Electronic Engineering Committee: November 6-8, 1990
`
`Characteristic 741-4
`
`Adopted by the Airlines Electronic Engineering Committee: October 8-10, 1991
`
`Characteristic 741-5
`
`Adopted by the Airlines Electronic Engineering Committee: October 19', 1993
`
`Characteristic 741-6
`Characteristic 741-7
`
`Adopted by the Airlines Electronic Engineering Committee: October 50, 1994
`Adopted by the Airlines Electronic Engineering Committee: October 31, 1995
`
`BOEING
`BOEING
`Ex. 1039, p. 3
`Ex. 1039, p. 3
`
`'
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`I
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`I
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`'
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`'
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`

`
`FOREWORD
`
`Activities of AERONAUTICAL RADIO, INC. (ARINC)
`
`and the
`
`Purpose of ARINC Characteristics
`
`Aeronautical Radio, Inc. is a corporation in which the United States scheduled airlines
`are the principal stockholders. Other stockholders include a variety of other air transport
`companies, aircraft manufacturers and non—U.S. airlines.
`'
`
`Activities of ARINC include the operation of an extensive system of domestic and
`overseas aeronautical land radio stations, the fulfillment of systems requirements to accomplish
`ground and airborne compatibility, the allocation and assignment of frequencies to meet those
`needs, the coordination incident to standard airborne communications and electronics systems
`and the exchange of technical information. ARINC sponsors the Airlines Electronic Engineering
`Committee (AEEC), composed of airline technical personnel. The AEEC formulates standards
`for electronic equipment and systems for the airlines.
`The establishment of Equipment
`Characteristics is a principal function of this Committee.
`
`An ARINC Equipment Characteristic is finalized after investigation and coordination with
`the airlines who have a requirement or anticipate a requirement, with other aircraft operators,
`with the Military services having similar requirements, and with the equipment manufacturers.
`It is released as an ARINC Equipment Characteristic only when the interested airline companies
`are in general agreement. Such a release does not commit any airline or ARINC to purchase
`equipment so described nor does it establish or indicate recognition of the existence of an
`operational reqliirement for such equipment, nor does it constitute endorsement of any
`manufacturer’s product designed or built to meet the Characteristic. An ARINC Characteristic
`has a twofold purpose, which is:
`
`(1)
`
`(2)
`
`To indicate to the prospective manufacturers of airline electronic equipment the
`considered opinion -of the airline technical people, coordinated on an industry
`basis, concerning requisites of new equipment, and
`
`in the
`To charmel new equipment designs in a direction which can result
`maximum possible standardization of those physical and electrical characteristics
`which influence interchangeability of equipment without seriously hampering
`engineering initiative.
`-
`
`BOEWG
`BOEING
`Ex. 1039, p. 4
`Ex.1039,p.4
`
`

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`
`ARINC CHARACTERISTIC 741 PART 1
`TABLE OF CONTENTS
`
`SUBJECT
`
`INTRODUCTION AND DESCRIPTION
`
`Purpose of this Characteristic
`Relationship of this Document to ARINC Characteristics
`597 and 724
`
`'
`
`PAGE
`
`hlbl
`
`Function of Equipment
`Airborne Avionics Configurations
`Unit Description
`Satellite Data Unit (SDU)
`Radio Frequency Unit (RFU)
`RF Distribution Units
`
`Splitter
`Combiner
`High Power Relay (HPR)
`Diplexer/Low Noise Amplifier (LNA)
`High Power Amplifier (HPA)
`Low Gain Antenna (DGA)
`High Gain Antenna (I-IGA)
`Dual Side Mounted I-IGA
`
`-
`
`Single Top Mounted HGA
`Keyhole Antennas
`Antenna Control Unit (ACU)
`Beam Steering Unit (BSU)
`System Performance
`Transmitter Equipment Performance
`Receiver Equipment Performance
`Interchangeability
`Regulatory Approval
`
`INTERCHANGEABILITY STANDARDS
`Introduction
`Form Factors, Connectors and Index Pin Coding
`Satellite Data Unit (SDU)
`SDU Size
`Connectors
`Form Factor
`
`Radio Frequency Unit
`RFU Size
`Connectors
`Form Factor
`
`RFU Power Output
`Harmonics, Discrete, Spurious and Noise
`RFU Linearity
`Noise Figure
`Radio Frequency Distribution Units (RFDU)
`Splitter Connectors
`Combiner Connectors
`High Power Relay {I-IPR)
`HPR Preferred Connectors
`
`Diplexer/LNA
`Diplexer/LNA VSWR
`Noise Figure/Gain
`Diplexer/LNA: Antenna Port to LNA Output Port
`Type A - For Protection of GPS Only
`Type B - For Protection of GPS, GLONASS
`and TFTS
`'
`Reserved
`LNA Output Power -
`Diplexer/LNA Connectors
`Diplexer/LNA Form Factors
`Diplexer/LNA 0n1'Off Control
`High Power Amplifier (I-IPA)
`
`
`
`
`
`000000000000-J--J-JD'\O\O\U\O\O\O\O\G\O\UlUlU|UIUIUILhUlLnUlUIUIUI-P-hLDbJl~)l\Jl~JI\Jl\JbJbJt\ll\JI~JbJ!Ql\JhJh||—|b—thdh—s»a
`
`”
`
`ifi
`
`BOEWG
`BOEING
`Ex. 1039, p. 5
`Ex.1039,p.5
`
`

`
`
`ARINC CI-IARACTERISTIC 1741 PART 1
`TABLE OF CONTENTS
`
`E:
`
`SUBJECT
`
`PAGE
`
`Harmonics, Discrete, Spurious and Noise
`Noise Figure
`VSWR
`I-IPA Connectors
`Form Factor
`
`HPA Muting and Carriers Off Level
`Coaxial Cable losses
`Loss Between RFU and HPA
`Total Loss Between HPA and Antenna
`
`Cable Loss Between Antenna and Diplexer/LNA
`Loss Between LNA and RFU
`Loss Between SDU and RPU
`
`Antenna System Specification
`Antenna Coverage Volumes
`Ideal Antenna Coverage Volume
`Achieved Antenna Coverage Volume
`High Gain Antenna CI-IGA) Receive System
`Frequency of Operation
`Polarization
`Axial Ratio
`Receive System Figure of Merit (G/T)
`Steering Angle
`Steering Control
`Overload Capability
`Receive Antenna VSWR
`Discrimination
`
`Phase Discontinuity
`High Gain Antenna (I-IGA) Transmit System
`Frequency of Operation
`Polarization
`Axial Ratio
`Steering Angle
`Steering Control
`Transmit Antenna VSWR
`Output Power Capability
`Discrimination
`I-IGA Connectors and Form Factor
`Beam Steering Unit (BSU)
`Beam Steering Unit Connectors
`BSU Size and Form Factor
`
`Antenna Control Unit (ACU)
`Phase Discontinuity
`L-Band System Physical Isolation
`Antenna Intermodulation
`Antenna Intermodulation in SATCOM
`Receive Band
`Antenna Intermodulation Products Which Fall
`in the GNSS Band
`
`Low Gain Antenna (IJGA) Receive System
`Frequency of Operation
`Polarization
`Axial Ratio
`
`Receive System Figure of Merit (G/T)
`Overload Capability
`Receive Antenna VSWR
`
`Low Gain Antenna (LGA) Transmit System
`Frequency of Operation
`Polarization
`Axial Ratio
`Transmit Antenna VSWR
`
`Output Power Capability
`LGA Form Factor
`L-Band System Physical Isolation
`
`iv
`
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`
`BOEWG
`BOEING
`Ex. 1039, p. 6
`Ex.1039,p.6
`
`
`
`
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`
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`
`1
`2
`3
`4
`5
`6
`7
`3
`
`91
`
`0
`10
`10
`
`I-d|—l)—lJI-Ili-sew-..I-5IN)?"
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`1
`l
`1
`
`5
`
`"
`
`REPLACEMENT PAGE
`
`M
`
`REVISED: December 8, 1995
`
`ITEM
`
`2.3.6
`2.4
`2.5
`2.5.1
`2.5.2
`2.6
`2.7
`2.8
`2.8.1
`2.8.2
`2.8.3
`2.8.4
`2.8.5
`2.9
`2.10
`2.10.1
`2.10.2
`
`2.10.3
`2.HL3.1
`2.10.3.2
`2.10.3.3
`2.10.3.4
`2.10.3.5
`
`Af|j!fACHMENTS
`
`'
`
`-
`
`I-1
`1—1A
`1-2
`1-3
`1-3A
`
`1-4
`1-4-A
`1-4B
`1-4C
`
`I-5
`1-5A
`1-5B
`1-5C
`1-6
`1-6A
`1-6B
`1-6C
`1-715;
`1—?B
`1-7C
`1-7D
`1-8
`1—9A
`
`1-9B
`
`1-10
`1-10A
`1-10B
`
`ARINC CI-IARACTERISTIC 74!, PART 1
`TABLE OF CONTENTS
`SUBJECT
`
`Antenna Positioning Data
`Standard Interwiring
`Power Circuitry
`Primary Power Input
`Power Control Circuitry
`System Functions and Signal Characteristics
`Environmental Conditions
`Cooling
`SDU
`Radio Frequency Unit (RFU)
`High Power Amplifier (I-IPA)
`Antenna Control Unit (ACU)
`Beam Steering Unit (BSU)
`Grounding and Bonding
`System ATE Design
`General
`Unit Identification
`
`Built—In Test Equipment (BITE)
`Euirzrnquay
`Fault Monitor
`Self-Test Initiation
`Monitor Memory Output
`Use of Automatic Test Equipment
`
`-
`
`General Configuration Overview
`Sample Dual SATCOM Installation
`Antenna Configurations
`Standard Interwiring
`2MCU Beam Steering Unit Size 1 Connector
`Pin Assignments
`Notes Applicable to Standard Interwiring
`Steering Inhibit and HPA Mute Signal Characteristics
`BSU/I-IPR Wiring Diagrams
`System Configuration Pins Definition and
`Interpretation
`-
`SDU Form Factor
`SDU Top Plug Connector Layout
`SDU Middle Plug Connector Layout
`SDU Bottom Plug Connector Layout
`RFU Form Factor
`RFU Top Plug Connector Layout
`RFU Midde Plug Connector layout
`RFU Bottom Plug Connector Layout
`Beam Steering Unit (BSU) "Alternate A"
`Beam Steering Unit (BSU) "Alternate B"
`Beam Steering Unit (BSU) "Alternate C"
`2MCU Beam Steering Unit (BSU) Rear Connector
`Configuration
`Antenna Coverage
`Type A - Diplexer/LNA Form Factor for
`Protection of GPS Only
`Type B - Diplexer/LNA Form Factor for
`Protection of GPS, GLONASS, and TFI‘S
`HPA Form Factor
`HPA Top Plug Connector layout
`HPA Middle Plug Connector Layout
`
`v
`
`I
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`
`I
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`|
`
`I
`
`I
`
`I
`
`PAGE
`
`14
`14
`15
`15
`15
`15
`15
`15
`15
`15
`15
`16
`16
`16
`16
`16
`16
`
`16
`17
`17
`17
`17
`17
`
`V
`
`'
`
`19
`20
`21-28
`-29-45
`
`46
`4'7-53
`54
`55
`
`56-61
`62
`63
`64
`65
`66
`67
`68
`69
`70
`71
`'72
`
`73
`74-77
`
`78
`
`79
`80
`81
`82
`
`BOEING
`BOEING
`Ex. 1039, p. 7
`Ex.1039,p.7
`
`

`
`REPLACEMENT PAGE
`
`REVISED: December 8, 1995
`
`ITEM
`
`1—10C
`1—11A
`
`1—11B
`
`1-11C
`1-11D
`1-11E
`
`1-11F
`1-11G-1
`
`1—11G-2
`1-11G-3
`1-11G-4
`1-11G-5
`1-111-I-1
`
`1-111-I-2
`1-11H-3
`1-IIH4
`
`1-1 II
`
`1-111-1
`
`1-12A
`1-12B
`I-12C
`
`1-13
`2
`
`3
`
`4
`
`APPENDIX
`
`1
`2
`
`ARINC CQAEACTELIIETIC 741, PART 1
`TABLE OF CONTENTS
`
`SUBJECT
`
`'
`
`PAGE
`
`HPA Bottom Plug Connector Layout
`High Gain Antenna Form Factor "Confonnal Phased Array
`Antenna 19.55 X 22.36 Inches"
`High Gain Antenna Form Factor “Conformal Phased Array
`Antenna 16 X 32 Inches
`Top Mounted Low-Profile Array -12 dBic (Side View)
`Top Mounted Low-Profile Array -12 dBic (Top View)
`Closeup View of the Coaxial Interface Top Mounted
`Low-Profile Array -12 dBic
`Blade Antenna High Gain Footprint
`Interface Control Drawing for 747 Fuselage-Mounted
`Mechanically-Steered I-Iigh~Gain Anenna Subsystem
`Radome Outline
`Top View
`Stringer Locations
`Doubler Outline
`Interface Control Drawing for 747 Vertical Stabilizer
`Mechanically-Steered High-Gain Antenna Subsystem
`Tail Fin Installation - ‘1'4‘7SP
`Tail Fin Installation - 747-200 and 300
`Side View
`
`High Gain Antenna Form Factor Phased Array Antenna
`(19.55 x 23.00) Fairing Form Factor (30.25 x 35.00)
`Connector Interface Antenna Seal Detail
`
`Beam Steering Unit (BSU) "Antenna Configuration A"
`Beam Steering Unit (BSU) "Antenna Configuration B"
`Beam Steering Unit (BSU) Side Mount Antenna
`"Configuration C"
`Low Gain Antenna
`ARINC 429 Labels and Word Formats Used in the
`Aviation Satellite Communications System
`Equipment Environmental Categories
`(EUROCAE ED-14/RTCA DO-160C)
`Attachment Reference Guide
`
`Bit-Oriented Fault Reporting Protocol
`Acronyms
`
`83
`
`84
`
`85
`86
`87
`
`88
`89
`
`90
`9]
`92
`93
`94
`
`95
`96
`97
`93
`
`99
`100
`
`101
`102
`
`103
`104
`
`106-119
`
`120
`121
`
`122-126
`I27-129
`
`vi
`
`BOEING
`BOEING
`Ex. 1039, p. 8
`Ex. 1039, p. 8
`
`

`
`REVISED: March 31, 1994
`ARHVC CHARACTERISTIC 741 PART 1 - Page 1
`
`1.0 INTRODUCTION AND DES
`
`ION
`
`___,____._..._
`
`(3-4
`
`1.1 Pumose of this Characteristic
`
`desired
`the
`forth
`sets
`1,
`document, Part
`This
`characteristics of the Aviation Satellite Communications
`(SATCOM) System avionics intended for installation in
`all types of commercial transport and business aircraft.
`The intent of this document is to provide general and
`specific guidance on the form factor and pin assignments
`for the installation of the avionics primarily for airline
`use. Part 2 describes the desired operational capability of
`the equipment as configured with the Satellite Data Unit
`(SDU) to provide data and voice communications, as well
`as
`additional
`standards
`necessary
`to
`ensure
`interchangeability. Part 3, Circuit Mode Voice and Data
`Services, describes the standard voice coding algorithm,
`the Data Interface Unit (DIU) and the Terminal Interface
`Function Unit
`(TIFU).
`Part 4, Specification and
`Description Language (SDL) contains the SDL Diagrams
`which show a possible detailed implementation of the
`system protocols.
`
`in project paper form.
`
`STAFF ‘NOTE: Part 5, TDMA System, describes
`the requirements of an alternative Time Division
`Multiple Access (TDMA) system that may be used
`in future satellite systems. Part 5 has been archived
`
`this Document
`of
`1.2 Relationship
`Characteristics 597 and 724
`
`to ARINC
`
`9-4
`
`¢-1
`
`(SATCOM)
`The Aviation Satellite Communications
`System will present standard interfaces to a number of
`other aircraft systems. These include ACARS (where
`installed), multi—purpose
`control
`and display units
`(MCDU), Communication Management Units (CMU)
`(ultimately to be shared with Mode S and VHF Data
`Links) and passenger telephone coder/encoder and CCS
`units. Details of the interfaces may be found in Part 3 or
`subsequent parts of this Characteristic, and in ARINC
`Characteristic 746,
`"Cabin Communications System
`(CCS)“.
`
`"Aircraft
`597A,
`and
`597
`ARINC Characteristics
`Communications Addressing and Reporting System
`(ACARS)", describe ARINC 404A-packaged airborne
`ACARS equipment against the background of a fairly
`detailed system description. ARINC Characteristics 724,
`724A and 724B describe ARINC 600-packaged equipment
`intended to perform essentially the same functions as the
`ARINC 597/597A equipment in the same framework.
`ARINC 7'24/724A equipment will more readily interface
`with other ARINC "700-Series“ equipment on those
`aircraft on which such equipment is employed. However,
`all versions of ACARS avionics should interface with the
`
`Aviation Satellite Communications system avionics by
`means of ARINC 429 data buses.
`
`.1 c_.J
`
`C-1
`
`COMMENTARY
`
`The ARINC 741 Aviation Satellite Communications
`System avionics design envisages the availability of
`ACARS avionics on the aircraft to effect certain data
`
`collection and distribution ftmctions.
`
`Those
`
`operators who do not utilize ACARS may employ an
`appropriately equipped MCDU to perform these
`functions or a specially designed substitute unit.
`In
`practical terms, their most economical solution to the
`problem may be the use of a "Stripped down"
`ACARS unit.
`
`1.3 Function of fluipment
`
`|¢—5
`is the transmission,
`The fimction of this equipment
`reception and processing of signals via a
`satellite I ¢-2
`providing aeronautical services in the L-band (1525- I C-5
`1660.5 MHZ). The system should provide a capability
`for all aeronautical satellite communications requirements
`external to the aircraft, including passenger telephone and
`data services depending on aircraft equipage.
`
`¢-2
`
`1.4 Airborne Avionics Configgrations
`
`The general configuration of the satellite avionics and
`related systems is shown in Attachment 1-1. A more
`detailed block diagram (including alternate configurations)
`is shown in Attachment 1-2.
`.
`
`The Satellite Data Unit (SDU) is capable of sending and
`receiving various data rates. The rate will be dynamically
`selected by pragmatic assessment of current operating
`conditions. The signal is transmitted via geostationary
`satellite transponders
`to designated supporting earth
`stations. A detailed functional description of this system
`configuration is "provided in Part 2 of this document.
`
`c_2
`
`The airborne system may be capable of transmitting
`higher data rates and voice communications, but this may
`necessitate the provisioning of a high gain (i.e. , 12 dBic)
`antenna.
`
`1.5 Unit Description
`
`1.5.1 Satellite Data Unit t-SDU)
`
`The signal-in-space parameters are determined by the
`SDU in relation to modulation/demodulation, error
`correction, coding, interleaving and data rates associated
`with the communication channel(s). This unit contains
`circuits
`for conversion of" digital/audio inputs to a
`baseband or intermediate frequency (IF), if required, and
`interfaces with the radio frequency unit (RFU). The SDU
`also interfaces with the ACARS Management Unit (MU)
`based on ARINC Characteristics 724, 724A and 72413.
`
`1.5.2 Radio Frguency Unit ggggg
`
`The RF unit consists of low power amplifiers, filters,
`frequency conversion and related components.
`‘The RFU
`operates in a full duplex mode (i.e.,
`simultaneous,
`transmission and reception of satellite signals).
`The
`transmit side uses a power amplifier which accepts a
`signal
`from the SDU at either baseband or IF and
`translates it to the appropriate RF.
`'I‘l1e receive side uses
`the output
`from a low noise amplifier
`(LNA) and
`translates signals to baseband or IF for use by the SDU.
`The RFU should be able to accept the wide range of
`
`BOEING
`BOEING
`Ex. 1039, p. 9
`EX. 1039, p. 9
`
`l
`
`H
`
`u
`
`I,
`
`I.
`
`l
`
`

`
`ARINC CHARACTERISTIC 741 PART 1 - Page 2
`
`1.0 INTRODUCTION AND DESCRIPTION [cont’d[
`
`1.5.2 Radio Frguency Unit (ELI) (cont’d]
`
`1.5.7.1 Dual Side Mounted no».
`
`REVISED: December 30, 1994
`
`signal levels from the LNA depending on configuration
`¢"2 and losses.
`
`1.5.3 RF Distribution Units
`
`1.5.3.1 _S_plitter
`
`A dual side—mounted I-IGA antenna should be mounted on
`each side of the aircraft at about 45 degrees from the
`horizon. The coverage of the main antennas is shown in
`Attachment 1-8.
`
`(3-1
`
`The splitter receives medium level RF signals from the
`RFU and divides the power for distribution to the high
`power amplifiers (I-IPA).
`
`1.5 .3.2 Combiner
`
`1.5.7.2 Single Tog Mounted I-IGA
`
`A single top mounted HGA antenna may be used instead
`of the dual side mounted configuration. Drag may be
`increased in this application. Either mechanically or
`electronically steerable antennas may be used.
`
`¢_2
`
`The combiner receives medium level RF signals from the
`low noise amplifiers (LNAS). Note that only one LNA is
`turned on at a time. The combiner
`then provides a
`matching network for distribution of the RF signal from
`each LNA to the RFU.
`
`1.5.3.3 I-Iigl_1 Power Relay [flPR1
`
`'I'he HPR is a coax switch for switching output RF power
`from the HPA to a particular antenna subsystem. The use
`of the I-IPR is optional depending on the aircrafi
`configuration.
`
`1.5.4 Diplexer/Low Noise Amplifier [I_.NA)
`
`The diplexer and LNA are combined into one unit for
`installation. The Diplexer Unit (DU) couples transmit
`signals from the HPA to the respective antenna (and
`couples receive signals from the respective antenna to the
`LNA unit), while preventing transmit-frequency power
`from degrading the receiver system.
`
`¢-2
`
`The LNA amplifies the very low level L—band signal from
`its respective antenna. The LNA also compensates for
`transmission line losses to the RFU.
`
`1.5.5 High Power Amplifier §l;IPA[
`
`The high power amplifier provides an adequate RF power
`level, by automatic control, to the antenna in order to
`maintain the aircraft EIRP within limits. The HPA unit
`may be located near the respective antenna to assure
`minimum loss of energy at the RF operating frequency
`and to avoid excessive thermal dissipation in the HPA
`unit, or it may be located in the radio equipment rack in
`certain aircraft.
`
`1.5.8 Keyhole Antennas
`
`installation makes no provision for keyhole
`A typical
`antennas to provide coverage in the "Blind Areas"
`(keyholes) shown in Attachment 1-8.
`Pins are not
`presently reserved on the SDU for any such antennas.
`
`C-4
`
`1.5.9 Antenna Control Unit (ACU)
`
`is used with a
`(ACU)
`The antenna control unit
`mechanically steered antenna to translate antenna beam
`positioning data and beam position change commands
`received from the SDU in a standard digital format into
`the form needed to position the antenna beam correctly.
`
`c-2
`
`1.5.10 Beam Steering Unit (BSU1
`
`The beam steering unit (BSU) is used with electronically
`steered antennas to translate antenna position data and
`beam change commands received from the SDU in a
`standard digital fonnat into the signals needed to select
`antenna elements in combinations that result in the beam
`pointing at the desired satellite.
`
`1. 6 System Performance
`
`1.6.1 Transmitter fluipment Performance
`
`The following table provides an indication of the level of
`service that should be expected from a typical aircraft
`satellite system, assuming that equipment of nominal
`performance is utilized.
`
`1.5.6 Low Gain Antenna jlfim
`
`Aircraft EIRP Performance ([3
`
`A low gain (i.e., 0 dBic) antenna may be used to provide
`communications in case of failure of a main antenna or to
`provide a means for additional service. Service will be
`restricted to low data rates when this antenna is
`
`employed.
`
`1.5.7 Hi h Gain Antenna
`
`- High gain antennas provide at least 12 dBic gain and are
`¢'2 essential for both high data rates and voice services.
`
`Voice/Data
`Service
`Parameters
`
`RF channel
`rate
`
`snap per
`carrier
`
`Circuit-vlvlode
`Voice
`
`Circuit—Mode
`Data
`
`Packet-Mode
`Data
`
`21 lcbit/s
`
`10.5 kbitls
`
`600 bit/s
`
`19.5 dBW‘2’
`
`21.0 dBw
`
`7.5 dBW
`
`C-3
`
`BOEING
`BOEING
`Ex. 1039, p. 10
`EX. 1039."_p. 10
`
`

`
`. REVISED: June 1, 1992
`ARJNC CHARACTERISTIC 741 PART 1 - Page 3
`
`1.0 INTRODUCTION AND DESCQETON jcont’dL
`
`Notes:
`
`(1) These values assume an INMARSAT-II Satellite
`(satellite G/T = -12.5 dBfK, satellite gain = 158.4
`dB) and operation at a satellite elevation angle of 20°
`or above. Values will differ for other satellites and
`
`For example, with spot-beam
`elevation angles.
`satellites these figures are expected to be reduced by
`at least 7 dB.
`
`the
`SDU and
`the
`the RFU,
`LNA/Diplexer,
`This includes all of the
`interconnecting RF cables.
`SATCOM equipment’s RF systems and circuits from the
`antenna to the demodulated baseband output. The design
`parameters of each of these system elements have been
`described to achieve the following receiver Figure-of-
`Merit (G/T) values. These are minimum values with a
`sky temperature of l00°K.
`For the switched beam
`(I-IGA) this example corresponds to the main beam for
`any pointing angle.
`
`(2) A 12 dBic aircraft antenna driven from a 40 watt
`linear HPA per ARINC Characteristic 741, through
`2.5 dB of loss, will radiate an EIRP of up to 25.5
`dBW, which can support four of these channels.
`
`LGA
`
`I-IGA
`
`G/T
`
`-26 dB/K-13 dB/K
`
`the EIRP
`The transmit system is equipped to adjust
`according to commands from the GES. For a single
`channel system using a Class "C_“ HPA, the back-off is
`accomplished entirely in the HPA, while the RFU
`maintains a constant power level to assure adequate drive
`to the non-linear HPA. For a multi-channel system using
`a linear HPA, the back-off is a combination of I-IPA back-
`off (collective control of all channel carriers) and RFU
`output carrier level control on an individual channel basis
`(to accommodate channels operating at different data
`rates).
`
`The transmit gain of a High Gain Antenna (l-IGA) may
`vary as its beam position is changed while tracking a
`satellite from an aircraft in motion. To maintain a more
`constant EIRP as the antenna’s beam position is changed,
`the ACU/BSU outputs the antenna’s transmit again for the
`current beam position on its ARINC 429 bus (in the
`ACU/BSU status word) to the SDU. The SDU in turn
`incorporates this gain information into the commanded
`back—off values it sends via its ARINC 429 bus to the
`HPA, thereby increasing or decreasing the HPA output
`(within the maximum and minimum limits of I-IPA output)
`to compensate for changes in antenna gain.
`In a system
`with a linear HPA this information may be used in setting
`both the HPA baclc—off values and the individual channel
`
`carrier levels output from the RFU. The antenna shall
`report its gain in the direction of the satellite with a
`resolution of 1 dB. The SDU shall make an appropriate
`_I-IPA adjustment to maintain a given EIRP within :1 dB
`when an antenna gain change is reported. The SDU shall
`also monitor HPA output power when one data channel is
`active or under other determined signal conditions and
`make appropriate HPA adjustments to maintain the EIRP
`within ;t1 dB to compensate for drifts in the HPA output
`power.
`
`Note: In the above examples the LGA G/T is degraded
`by 1 dB to-allow for installation variations.
`
`The above values for GIT should be achieved under the
`following conditions:
`
`(i)
`
`(ii)
`
`clear sky climatic conditions;
`
`satellite elevation angles greater than or equal to 5
`degrees, within the coverage volume of the aircraft
`antenna;
`
`(iii) with residual antenna pointing errors (including the
`effects of errors introduced by the antenna beam
`steering system);
`
`(iv)
`
`(v)
`
`(Vi)
`
`including the noise contribution of the complete RF
`subsystem including antenna and low noise
`amplifier, at a temperature of 290°K;
`
`with the transmitter power amplifier at maximum
`output level;
`
`temperature
`noise
`and
`loss
`the
`including
`contribution of a radome, where a radome is fitted.
`
`(vii) under the operational RF environment; e. g. , when
`the receive antenna is illuminated in its operating
`bandwidth (29 MHz) by a total RF flux density of
`-100 dBW/m2.
`
`For the high data rate system using the high-gain antenna,
`the thermal contribution of finite losses within: the HGA
`may cause the G/T to be degraded below ~13 dB/K even
`when the HGA gain, LNA noise figure and diplexer plus
`cable losses are within tolerance.
`
`The steering control signals should be provided through
`an ARINC 429 bus from the SDU and should be derived
`from a signal representing the received signal strength.
`This is commonly called "closed loop" steering.
`
`Antenna performance is expressed in terms of gain. The
`system noise temperature is achieved in consideration of
`the RF cable
`loss
`factors
`and the noise
`figure
`contributions from the RFU and the LNA/Diplexer.
`
`The antenna beam steering function should be capable of
`maintaining the transmitted beam performance with
`aircraft attitude rates of at least 7.5 degrees per second.
`
`The receiver system performance provides a bit error rate
`(BER) of 11110" for packet mode data, 1x104 for circuit
`mode voice and 1x10‘5 for circuit mode data.
`
`4 \._._a'’
`
`‘
`
`I
`
`«I
`
`1
`
`¢-4
`
`1.6.2 Rec'eiver Fguipment Performance
`
`(3-3
`
`The receiver system performance is determined by the
`characteristics
`of
`the
`antenna
`sub-system,
`the
`
`The steering control signals should be provided through
`an ARINC 429 bus from the SDU and should be derived
`from a signal representing the received signal strength.
`This is commonly called "closed loop" steering.
`
`'
`BOEING
`BOEING
`Ex. 1039, p. 11
`EX. 1039, p. 11
`
`

`
`ARINC CHARACTERISTIC 741 PART I - Page 4
`
`REVISED: March 31, 1994
`
`1.0 INTRODUCTION AND DESCRIPTION §cont’d[
`
`1.6.2 Receiver Euipment Performance §cont’d)
`
`¢-4
`
`The antenna beam steering function should be capable of
`maintaining the received beam performance with aircraft
`attitude rates of at least 7.5 degrees per second.
`
`1.7 Interchangeability
`
`741 Aviation Satellite
`The ARINC Characteristic
`Communications
`System comprises
`two major
`sub-systems and a number of individual units. System
`interchangeability, as defined in Section 2.0 of ARINC
`Report 403,
`"Guidance for Designers of Airborne
`Electronic Equipment", is desired by the users for each of
`the major sub-systems and unit interchangeability, also
`defined in the above-referenced ARINC Report, is desired
`for the individual units. The first major sub-system
`comprises the SDU and the RFU. The second is the
`¢_3 antenna sub-system, comprising the antenna itself, the
`beam steering unit (when used) and the antenna control
`unit (when used).
`Interchangeability is also desired for
`the HPA and the diplexer!LNA Units.
`
`Additional interchangeability standards may be found in
`Part 2 of this Characteristic. Cabin/cockpit voice an