This document analyzes the feasibility of an Airship Assisted Launch System (AALS) for small satellite launch. It first reviews the growing small satellite market and existing launch options. It then outlines the proposed AALS design process, including determining the required thrust, airship envelope size, and helium amount. Environmental factors like wind and losses are also analyzed. Finally, it evaluates the technical feasibility of AALS compared to ground launches and identifies areas for further study, such as propulsion options and expanding possible applications.
Our Smart Voyage Optimisation solutions can unleash further potential in your fleet, today.
At Wärtsilä, we have always been committed to making vessel operations more efficient, safe and ecological. We deliver solutions that help our customers boost profitability while meeting global environmental and safety compliance.
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Our Smart Voyage Optimisation solutions can unleash further potential in your fleet, today.
At Wärtsilä, we have always been committed to making vessel operations more efficient, safe and ecological. We deliver solutions that help our customers boost profitability while meeting global environmental and safety compliance.
Smart Voyage Optimisation entails the creation of a Smart Marine ecosystem, whereby every vessel can connect to services that make voyaging safer and greener. We are developing a unique integrated infrastructure that combines the bridge systems, cloud data management, data services, decision support tools, and access to real-time information.
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1. Andrea
Testore
-‐
Cranfield
UniversityAALS
-‐
feasibility
study 1
Innovation in Small Satellite
Launch: Airship Assisted Launch
System Feasibility Study
MSc - Individual Research
Project
Andrea Testore
1st September 2015
2. Andrea
Testore
-‐
Cranfield
UniversityAALS
-‐
feasibility
study 2
AALS - feasibility study
How solve small launcher lack?
LTA system
• Sizes
• Quality
• Market
• Cost
4. Andrea
Testore
-‐
Cranfield
UniversityAALS
-‐
feasibility
study 4
Nano & Micro-Satellites
Market
Trend:
• Dove 3U
• OneWeb
Mission purpose:
• Commercial principal nano-sats
purpose
• Micro-sats promising market share
+300 %
+160 %
5. Andrea
Testore
-‐
Cranfield
UniversityAALS
-‐
feasibility
study 5
Competitors
AALS RQM:
• 200 kg LEO
• 20 000 kg
AdvantagesAir launch:
• 332 kg LEO
• 30 k$/kg
• 23 000 kg
• 225 kg LEO
• 45 k$/kg
• 17 000 kg
• 100% orbit inclination
• Weather tolerance
6. Andrea
Testore
-‐
Cranfield
UniversityAALS
-‐
feasibility
study 6
Ground Launch
Orbit availability:
Alcantara
• VLM
• VLS
Wallops
• Ares
• Minotaur
Dedicated launch
• Piggyback first choice
Except for:
Demanding RQM:
• Commercial
• Military
• Civil
7. Andrea
Testore
-‐
Cranfield
UniversityAALS
-‐
feasibility
study 7
Environment analysis
Losses
• Air drag
• Atmospheric
• Gravity
Wind Affects
• Attitude
• Safe Range
• Ground Operations
Launch delays & abortion
8. Andrea
Testore
-‐
Cranfield
UniversityAALS
-‐
feasibility
study 8
Wind Trend
Wallops
AALS RQM:
• 20 m/s
• 20 000 m
9. Andrea
Testore
-‐
Cranfield
UniversityAALS
-‐
feasibility
study 9
Design Process
• Thrust required
• Envelope size
• Amount of Helium
PL capab.
• 20 000 kg
Height
Cruise V.
• 20 m/s
• 20 000 m
Top level Requirements
10. Andrea
Testore
-‐
Cranfield
UniversityAALS
-‐
feasibility
study 10
0.25 kg/m^2
Envelope and Mass
Breakdown
725 000 m^3• Helium (10.126 N/m^3)
11. Andrea
Testore
-‐
Cranfield
UniversityAALS
-‐
feasibility
study 11
Propulsion
Power density Mass available
Air Density
• Fuel Cell: 3 400 m
• Photovoltaic: 12 000 m
• Thermoelectric: 23 000 m
Fully operational
altitude
Fuel cell
Photov. Thermoe.
Ava. mass
12. Andrea
Testore
-‐
Cranfield
UniversityAALS
-‐
feasibility
study 12
Development & Production
Ground launch:AALS:
$340 M
HAA
Low heritage
$49 - 207 M
HLA
Production
High heritage
13. Andrea
Testore
-‐
Cranfield
UniversityAALS
-‐
feasibility
study 13
Production Costs
AALS: Ground launch:
$168 M
HAA
Valuable
experience
HLA
$49 - 207 M
Production
High heritage
Helium
14. Andrea
Testore
-‐
Cranfield
UniversityAALS
-‐
feasibility
study 14
Operational Costs
AALS: Ground launch:
Integration
Rocket launch interaction
Safe Range Safe Range
Salt
Acidic exhaust gasses
Depreciation Depreciation
15. Andrea
Testore
-‐
Cranfield
UniversityAALS
-‐
feasibility
study 15
Feasibility
TechnicalEconomic
• Market
• Development
• Operation
• Production
• Hydrogen
• Applications
• Rigid/Modular
• Hydrogen
Solutions
• Propulsion
• Launch Windows
• Size
• Payload
?
?
16. Andrea
Testore
-‐
Cranfield
UniversityAALS
-‐
feasibility
study 16
Further works
Technical:
• Propulsion / Power
• Structure
Economic:
• Applications
• Hydrogen
Heavy lift
Long Endurance