casd presentazione avio

1 All information contained in this document is property of AVIO @ Copyright All rights reserved

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

All information contained in this document is property of AVIO @ Copyright All rights reserved


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”


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


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


C130 J

B767

C27J


SALTO system definition

Support Aircraft

Communication Satellite

Ground Control Station

Electrical Ground Support Equipment

DEPL SYS

Canister

Launch Vehicle

Aircraft

Crew


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


Launch Vehicle deployment approach

Xxxxxxxxxxxxxxxx

xxxxxxxxxxxxxxxxx

Courtesy of AEROSEKUR


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


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

12 All information contained in this document is property of AVIO @ Copyright All rights reserved File: 301110 SALTO

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


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.



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


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


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


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.


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

casd presentazione avio

Documents