C130 Cargo Carrier Potential

1All 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, cont
Aircraft, 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
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Courtesy of AEROSEKUR

Launch Vehicle escape approach
LI: Max structural
deflection (from WI)
V: Local vertical
NI: Nominal
ignition 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 @ equatorial
orbit
PL mass @ polar orbit
Min orbital life (days)
absolute WC
credible WC

12All information contained in this document is property of AVIO @ Copyright All rights reservedFile: 301110 SALTO
SALTO Performance Map
0
50
100
150
200
250
300
200 300 400 500 600
Orbit circular altitude (Km)
PL mass @ equatorial
orbit
PL mass @ polar orbit
absolute WC
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 Model
To test the functionality of the extraction
system in flight conditions
Flight Extr & Orientation Model
To 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=465km
6 camere affiancate = 840 – 870 km4 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

C130 Cargo Carrier Potential

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