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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
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Descent TrajectoryHover TrajectoryLD Code Integration John Aitchison March 5th, 2009 [John Aitchison] [Mission Ops]
[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
[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
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)
Sample LD Integration Output [John Aitchison] [Mission Ops]
LD Code Integration Flow [John Aitchison] [Mission Ops] • 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 6
Hover Trajectory [John Aitchison] [Mission Ops] 7
Hover Trajectory Code [John Aitchison] [Mission Ops] 8
Descent Trajectory [John Aitchison] [Mission Ops] 9
LD Integrated Code (pg. 1) [John Aitchison] [Mission Ops]
LD Integrated Code (pg. 2) [John Aitchison] [Mission Ops]
LD Integrated Code (pg. 3) [John Aitchison] [Mission Ops]
LD Integrated Code (pg. 4) [John Aitchison] [Mission Ops]
LD Integrated Code (pg. 5) [John Aitchison] [Mission Ops]
LD Integrated Code (pg. 6) [John Aitchison] [Mission Ops]
LD Integrated Code (pg. 7) [John Aitchison] [Mission Ops]
LD Integrated Code (pg. 8) [John Aitchison] [Mission Ops]
LD Integrated Code (pg. 9) [John Aitchison] [Mission Ops]
LD Integrated Code (pg. 10) [John Aitchison] [Mission Ops]
LD Integrated Code (pg. 11) [John Aitchison] [Mission Ops]
LD Integrated Code (pg. 12) [John Aitchison] [Mission Ops]
LD Integrated Code (pg. 13) [John Aitchison] [Mission Ops]
LD Integrated Code (pg. 14) [John Aitchison] [Mission Ops]
LD Integrated Code (pg. 15) [John Aitchison] [Mission Ops]
LD Integrated Code (pg. 16) [John Aitchison] [Mission Ops]
LD Integrated Code (pg. 17) [John Aitchison] [Mission Ops]
Steering Program Code [John Aitchison] [Mission Ops]
Steering Program Code (cont.) [John Aitchison] [Mission Ops]
Circ-Elliptical Using Attitude Thrusters [John Aitchison] [Mission Ops] 29
Circ-Elliptical Using Attitude Thrusters (pg.2) [John Aitchison] [Mission Ops] 30
Circ-Elliptical Using Attitude Thrusters (pg.3) DeltaV = 9.2 m/s Attitude Propellant Mass = .82 kg [John Aitchison] [Mission Ops] 31