descent trajectory hover trajectory ld code integration
DESCRIPTION
Descent Trajectory Hover Trajectory LD Code Integration. John Aitchison March 5 th , 2009. Finalized Descent Trajectory {all payloads} De-Circularize → Retro →Throttle Down Coast→ Vertical Steering program a possibility - PowerPoint PPT PresentationTRANSCRIPT
AAE450 Spring 2009
Descent TrajectoryHover Trajectory
LD Code Integration
John AitchisonMarch 5th, 2009
[John Aitchison] [Mission Ops]
AAE450 Spring 2009 [John Aitchison] [Mission Ops]
Finalized Descent Trajectory {all payloads}– De-Circularize → Retro→Throttle Down Coast→Vertical– Steering program a possibility
• Does provide savings if we need to start descent at altitudes approximately >25km
• Dependent on TLI/LD iterations
LD Code Integration {all payloads}– Complete, will be finalized with updated code from each group
Hover Trajectory {arbitrary payload}– Near complete, small attitude control adjustments needed
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AAE450 Spring 2009 [John Aitchison] [Mission Ops]
Arbitrary Payload Analysis– Falcon 9 LLO Deliverable: ~5700kg– Falcon 9 H LLO Deliverable: ~18000kg
Mass Deliverable to Lunar Surface– LD Budget available for Structure, Power, Thermal,
Comm, Attitude Inert, Usable Payload– Assuming descent engine thrust & attitude thrust
scale accordingly
Mass in LLO DE Thrust Propellant Inert Prop LD Budget
5,700 kg 44,000 N 2,825 kg 342 kg 2,532 kg
18,000 kg 143,950 N 8,722 kg 998 kg 8,280 kg
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AAE450 Spring 2009
Backup Slide Content
[John Aitchison] [Mission Ops]
LD Code Integration– Sample Output (pg. 5)– Flow (pg. 6)– Code (pg. 10-26)
Hover Trajectory (pg. 7-8) Descent Trajectory (pg. 9) Steering Program Code (pg. 27-28) Circ-Elliptical Using Attitude Thrusters (pg. 29-31)
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AAE450 Spring 2009
Sample LD Integration Output
[John Aitchison] [Mission Ops]5
AAE450 Spring 2009
LD Code Integration Flow
[John Aitchison] [Mission Ops]6
Mass Inputs– Power, Communications, Attitude Inert,
Payload/Locomotion
Iterates– Hop/Hover Trajectory, Prop System Inert Mass,
Structural “Frame” Inert Mass, Attitude Prop Mass
Outputs– All final masses in LLO
AAE450 Spring 2009
Hover Trajectory
[John Aitchison] [Mission Ops]7
AAE450 Spring 2009
Hover Trajectory Code
[John Aitchison] [Mission Ops]8
AAE450 Spring 2009
Descent Trajectory
[John Aitchison] [Mission Ops]9
AAE450 Spring 2009 [John Aitchison] [Mission Ops]
LD Integrated Code (pg. 1)
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AAE450 Spring 2009 [John Aitchison] [Mission Ops]
LD Integrated Code (pg. 2)
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AAE450 Spring 2009 [John Aitchison] [Mission Ops]
LD Integrated Code (pg. 3)
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AAE450 Spring 2009 [John Aitchison] [Mission Ops]
LD Integrated Code (pg. 4)
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AAE450 Spring 2009 [John Aitchison] [Mission Ops]
LD Integrated Code (pg. 5)
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AAE450 Spring 2009 [John Aitchison] [Mission Ops]
LD Integrated Code (pg. 6)
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AAE450 Spring 2009 [John Aitchison] [Mission Ops]
LD Integrated Code (pg. 7)
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AAE450 Spring 2009 [John Aitchison] [Mission Ops]
LD Integrated Code (pg. 8)
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AAE450 Spring 2009 [John Aitchison] [Mission Ops]
LD Integrated Code (pg. 9)
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AAE450 Spring 2009 [John Aitchison] [Mission Ops]
LD Integrated Code (pg. 10)
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AAE450 Spring 2009 [John Aitchison] [Mission Ops]
LD Integrated Code (pg. 11)
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AAE450 Spring 2009 [John Aitchison] [Mission Ops]
LD Integrated Code (pg. 12)
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AAE450 Spring 2009 [John Aitchison] [Mission Ops]
LD Integrated Code (pg. 13)
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AAE450 Spring 2009 [John Aitchison] [Mission Ops]
LD Integrated Code (pg. 14)
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AAE450 Spring 2009 [John Aitchison] [Mission Ops]
LD Integrated Code (pg. 15)
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AAE450 Spring 2009 [John Aitchison] [Mission Ops]
LD Integrated Code (pg. 16)
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AAE450 Spring 2009 [John Aitchison] [Mission Ops]
LD Integrated Code (pg. 17)
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AAE450 Spring 2009 [John Aitchison] [Mission Ops]
Steering Program Code
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AAE450 Spring 2009
Steering Program Code (cont.)
[John Aitchison] [Mission Ops]28
AAE450 Spring 2009 [John Aitchison] [Mission Ops]
Circ-Elliptical Using Attitude Thrusters
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AAE450 Spring 2009 [John Aitchison] [Mission Ops]
Circ-Elliptical Using Attitude Thrusters (pg.2)
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AAE450 Spring 2009 [John Aitchison] [Mission Ops]
Circ-Elliptical Using Attitude Thrusters (pg.3)
DeltaV = 9.2 m/sAttitude Propellant Mass = .82 kg
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