ESA ANTARES CA UT Study. Will Birkinshaw 27 May 2010
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1 Will Birkinshaw 27 May 2010
2 Introduction Design aims Certification and installation time line Performance targets UT Block Diagram Installation constraints Antenna installation configuration DLNA/HPA/Modem configuration options Prototype development 2
3 Design Aims Able to carry COCR traffic in parallel with L-DACS Must work as well as or better than VHF Must be available during aircraft manoeuvres Holding stacks etc. Must be available when satellite elevation is low Northern Trans-Atlantic routes Northern Europe CA UT to be certified to DAL level C UT to be capable of being an HF replacement Must work as well as or better than HF Must be capable of operation in a dual redundant system 3
4 Certification and Installation time line System development phases and indicative time to key milestones ~20 years Standardisation Generic and Satellite System specific standards Technology Evaluation Includes UT and fixed system evaluation Selection of Future System Fixed and space infrastructure implementation Infrastructure Certification Airworthiness certification of first operational aircraft System full operational capability Avionics deployment Deadline for mandatory fit Time lines from previous Avionics Systems Certifications:- Early Trials 1952, TCAS programme launched 1981, mandatory in USA ADS-B RTCA DO242 specification 2002, mandatory 2020 L Band Satcom System Definition Manual ~1987, TSO-C (non-mandatory system), 4
5 UT Performance targets The ideal target is to achieve full spherical coverage from the airframe whilst maintaining the following parameters:- Achieve the defined EIRP (nominally 0dBic) Achieve the defined G/T Ability for fitment to all commercial airframes Equipment certified to DAL level C Some compromise from this ideal coverage target will be required if the UT is to be acceptable to airframe manufactures and from a cost and reliability viewpoint. Compromise options include:- Reduction in the acceptable coverage of the UT at the defined EIRP and G/T levels. Reduction in the EIRP and G/T requirements. 5
6 UT Block Diagram Antenna 1 Antenna 2 (Optional) Outside the fuselage DLNA Switch or mixer DLNA Very close to antenna switch HPA Cabin area/crown area RF TX RF RX MUX/DEMUX 6 Modem/Avionics Processing Basic functional blocks of the UT showing a possible antenna switching option. Cockpit/EEbay Locations on an airframe
7 Installation constraints Airframe imposed limitations Minimise the number of antennas required. Minimise the antenna height and profile. Maintain minimum distance from other antenna installations Comply with certification requirements Airframe specific location limitations Availability of adequate space adjacent to antenna inside the airframe Antenna location must not infringe non-ionising radiation limits UT should not require the external forced cooling air System imposed limitations System EIRP and modulation scheme dictates the heat required to be dissipated from LRUs. Other constraints Interchangeability and standardisation of LRUs and interfaces 7
8 Antenna installation configuration #1 The preferred individual antenna option is a Low Gain fix beam antenna. (Nominal gain 0dBic). Advantages:- Simplicity, small size and weight, low cost, high reliability, low stress on airframe. Disadvantages:- low gain hence low radiated RF power levels if HPA power not increased to compensate Antenna system options:- Single antenna Advantages:- minimal effect on airframe, low cost, suited to small airframes. Disadvantages:- No antenna redundancy, restricted system availability. Dual antenna Advantages:- Can offer dual redundancy or can be used to improve coverage. Disadvantages:- cannot offer acceptable coverage and dual redundancy simultaneously. Higher cost than single antenna. More difficult to fit on smaller airframes. Multiple antennas (4) Advantages:- offers improved coverage and dual redundancy. Disadvantages:- Higher cost, more difficult installation and more significant impact on airframe design. 8
9 Antenna installation configuration #2 A320 AVRO RJ CRJ200 80m A380 13m Falcon 100 Aircraft simulation models 9
10 Antenna installation configuration #3 AVRO RJ Fuselage top front Single antenna coverage Higher gain towards red 10
11 Antenna installation configuration #4 AVRO RJ Fuselage top rear Single antenna coverage Higher gain towards red 11
12 Antenna installation configuration # 5 CRJ Fuselage top middle Single antenna coverage Higher gain towards red 12
13 Antenna installation configuration # 6 CRJ Fuselage top rear Single antenna coverage Higher gain towards red 13
14 Antenna installation configuration # 7 A320 Fuselage top front Single antenna coverage Higher gain towards red 14
15 Antenna installation configuration # 8 15 A320 Fuselage top middle Single antenna coverage Higher gain towards red
16 Antenna installation configuration #10 A320 Fuselage top front fuselage side Single antenna coverage Higher gain towards red 16
17 DLNA/HPA/Modem configuration options Considerations:- RF loss to antenna(s) Amount of heat to be dissipated Space available limits physical size of modules Adequate air flow in proposed locations Number of antennas to be supported. 17
18 DLNA/HPA/Modem configuration options ANTENNA 1 DLNA HPA RF_RX RF_RX RF_TX ADC ADC DAC MUX/DEMUX High Speed Serial Interface MUX/DEMUX High Speed Serial Interface DDC_RX DUC_TX MODEM AND AVIONICS PROCESSOR AIRCRAFT DATA INTERFACES ANTENNA 2 Modems located in Avionics Bay DLNA HPA RF_RX RF_RX RF_TX ADC ADC DAC MUX/DEMUX High Speed Serial Interface MUX/DEMUX High Speed Serial Interface DDC_RX DUC_TX MODEM AND AVIONICS PROCESSOR 18 Redundant Backup System High Speed Serial Interface Potentially Fibre Optic ring network preventing single point failure. One potential 2 antenna configuration option
19 Prototype development in Phase B Antares UT prototype hardware to be built in modular form to facilitate construction and testing. Prototype HPA, RF modules and modem will be produced. The prototypes will be developed to demonstrate operation of the system physical layer and will communicate with the Verification Test Bench. 19
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