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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
Andrea	
  Testore	
  -­‐	
  Cranfield	
  UniversityAALS	
  -­‐	
  feasibility	
  study 2
AALS - feasibility study
How solve small launcher lack?
LTA system
• Sizes
• Quality
• Market
• Cost
Andrea	
  Testore	
  -­‐	
  Cranfield	
  UniversityAALS	
  -­‐	
  feasibility	
  study 3
Contents
1.Market analysis
2.Environment
3.Design
4.Cost analysis
RQM
RQM
Sizes
Feasibility
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 %
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
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
Andrea	
  Testore	
  -­‐	
  Cranfield	
  UniversityAALS	
  -­‐	
  feasibility	
  study 7
Environment analysis
Losses
• Air drag
• Atmospheric
• Gravity
Wind Affects
• Attitude
• Safe Range
• Ground Operations
Launch delays & abortion
Andrea	
  Testore	
  -­‐	
  Cranfield	
  UniversityAALS	
  -­‐	
  feasibility	
  study 8
Wind Trend
Wallops	
  
AALS RQM:
• 20 m/s
• 20 000 m
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
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)
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
Andrea	
  Testore	
  -­‐	
  Cranfield	
  UniversityAALS	
  -­‐	
  feasibility	
  study 12
Development & Production
Ground launch:AALS:
$340 M
HAA
Low heritage
$49 - 207 M
HLA
Production
High heritage
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
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
Andrea	
  Testore	
  -­‐	
  Cranfield	
  UniversityAALS	
  -­‐	
  feasibility	
  study 15
Feasibility
TechnicalEconomic
• Market
• Development
• Operation
• Production
• Hydrogen
• Applications
• Rigid/Modular
• Hydrogen
Solutions
• Propulsion
• Launch Windows
• Size
• Payload
?
?
Andrea	
  Testore	
  -­‐	
  Cranfield	
  UniversityAALS	
  -­‐	
  feasibility	
  study 16
Further works
Technical:
• Propulsion / Power
• Structure
Economic:
• Applications
• Hydrogen
Heavy lift
Long Endurance

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AALS presentationpdf

  • 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
  • 3. Andrea  Testore  -­‐  Cranfield  UniversityAALS  -­‐  feasibility  study 3 Contents 1.Market analysis 2.Environment 3.Design 4.Cost analysis RQM RQM Sizes Feasibility
  • 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