Post on 07-Aug-2015
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Mauro Balduccini AVIO Head of R&D for Space Division
-LANCIATO per TRASFERIMENTO in ORBITASISTEMA
S A L T O:
THE POTENTIALITIES OF A CARGO CARRIER
Aerosekur, MBDA Italia and Space Sys supported the preparation of this presentation
2
CONTENTS
• Recall of strategic objective, operative requirements and constraints(*)
• Architectural and Aircraft trade-offs
• SALTO system definition
• SALTO baseline performances
• Development plan characteristics and planning
Appendix: Afganistan mission example
(*) The operative requirement and constraints presented are an hypothesis developed by AVIO/ELV still not subjected to review/ iteration with AD
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Recall of strategic objective, operative requirements and constraints
The Strategic Objective: to implement, FOR ITALY and in the short time, an independent access to Space capability focused to allow a rapid reaction in worldwide crisis area
Key operative requirement: 60 days of minimum operative orbit life; 100 Kg minimum Payload, Equatorial to Sunsyncronous inclinations, max 3 days “Alert to Orbit”
Key constraints: Aircraft under the stable availability of AM; no modification to Aircraft, short time availability (6 y max), Equipment under mid term national “control”
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Architectural and Aircraft trade-offs
Architectural, alternatives (*):
Land launch from fix Base : impossible from homeland Italy (overfly safety)
Sea Launch from movable platform: not compatible with 3days “alert to orbit”; plus high rec cost for maintenance and logistic
Launch from Aircraft : potentially compliant with al req’s & constraints
Aircraft launch retained
(*) only major trade-off alternative are shown
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Architectural and Aircraft trade-offs, contAircraft, alternatives:
Fighter (Tornado): too low orbit performance mass (<<100Kg) (*)
Cargo
C27J : too low orbit performance mass (<<100Kg) (*)
B767 : major aircraft modification required due to “side loading”
C130J : potentially compliant with al req’s & constraints
C130/J30 : still not fully available; good ref for improved SALTO(**)
C130J retained for the baseline (short term) SALTO
(*) not introducing new technologies that need specific development, and consequently not compatible with the short term availability requirement of 6y max
(**) C130J/J30 improvement of cargo lenght and max deployable mass consent a very significant growth capability of the baseline SALTO System
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C130 J
B767
C27J
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SALTO system definition
Support Aircraft
Communication Satellite
Ground Control Station
Electrical Ground Support Equipment
DEPL SYS
Canister
Launch Vehicle
Aircraft
Crew
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SALTO system definition, cont (numeri da introdurre)
Launch Vehicle:
Overall: monocaliber 1.xm, 10m lenght, xton mass; constituteed by: 3 solid stages and 1 upper stage with storable biprop housing equipment for platform service provisuion to the operative payload
Stage pr.Ty pro(Kg) Iner(Kg)SR L(m) Dia(m) Isp(s)
1° stage solid 8000 700 0.08 5 1.35 278
1° stage solid 8000 700 0.08 5 1.35 278
1° stage solid 8000 700 0.08 5 1.35 278
1° stage solid 8000 700 0.08 5 1.35 278
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Launch Vehicle deployment approach
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Courtesy of AEROSEKUR
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Launch Vehicle escape approach LI: Max structuraldeflection (from WI)
V: Local vertical
NI: Nominalignition attitude
WI: Worst Case ignition attitude
Delta x
Delta Z
AV: Aircraft view angle
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The performances (in fase di revisione))
SALTO Performance Map
0
50
100
150
200
250
300
200 300 400 500 600
Orbit circular altitude (Km)
PL mass @ equatorialorbit
PL mass @ polar orbit
Min orbital life (days)absolute WC
Min orbital life (days)credible WC
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SALTO Performance Map
0
50
100
150
200
250
300
200 300 400 500 600
Orbit circular altitude (Km)
PL mass @ equatorialorbit
PL mass @ polar orbit
Min orbital life (days)absolute WC
Min orbital life (days)credible WC
2
3
1
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The implementation program planning
Total of 6 years, see planning (including margins)
Strategy is to implement in the first C/D phase (3y,named phase 1) the 3 Demonstration Models testing aimed to verify the capability to carry out all operations relevant to the Deployment of the Launch Vehicle from the Cargo; including Aircraft manoeuvering aspects.
The second C/D phase (3y, Phase 2 on planning) will complete the development program up to the first flight, at negligible risk.
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The implementation program planning
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The implementation program planning
The only critical element of the proposed program (and only due to the
limited national heritage on subject, see note) is the deployment of 12t LV from the C130J cargo. The following specific Development Models are foreseen to eliminate tech risk: Ground Extraction Model
To test, on ground, the LV-cannister relative positions during extraction (check of potential interferences and local stress concentrations on LV structures)
Flight Extraction ModelTo test the functionality of the extraction system in flight conditions
Flight Extr & Orientation ModelTo test the functionality of both extraction and orientation systems in flight conditionsNote: Russians deployed 85t from xxx
Aircraft
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Appendix: Afganistan mission example
Mission requirement: to carry out 2 main observation tasks:
a) Sinoptic (general view: NIIRS level 2) of all Afganistan territory and enabling the identification of targets to be subject of “close-eye” observation
b) “close-eye” observation of any selected target areas in order to achieve NIIRS level 4
Territory: 647000Km2; 1240X565Km at 30-40 deg North and 65-75 deg East
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Appendix: Afganistan mission example, cont
Mission results:
Operative mission life > > 200 days (460 Km orbit altitude)
Full synoptic coverage of Afganistan in 3 days
Delay of data transmission to a (single) Ground Control Station located in Italy = 3 hours
Payload Sensor key data on the following pages
Max Off-nadir of 45 deg
Complete Payload mass below 70Kg
Complete compatibility with the SALTO System
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Appendix: Afganistan mission example,cont
H =
465
km
6 camere affiancate = 840 – 870 km 4 camere affiancate= circa 480 km
2 camere affiancate = circa 240 km
Synoptic (off-the-shelf) sensor•La singola telecamera pancromatica fornisce una risoluzione a terra di circa 10 m da altezza 465 km e una swath di circa 120 km . L’unità pesa meno di 1 kg e consuma 15 W ed ha una datarate in uscita di 75 Mbps precompressione nella configurazione specifica di questa missione.
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Appendix: Afganistan mission example, cont
Close-eye sensor
Pushbroom , medium-short focal lenght , panchromatic telescope equipped with CMOS linear array; Candidate CMOS array: Awaiba DK-8k-3.5: 8162 pixels; pixel size 3.5 micron, 12 bit resolution; scanrate 80 kpixel/sec Telescope: 25 cm dia. aperture; F# 3.6 , Focal lenght 90 cm , folded optics Howthon-Cassegrain design, 1.78 m ground resolution at nadir ; 2.5 m resolution at 45° off-nadir