Lunar Descent Trajectory

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Presentation transcript:

Lunar Descent Trajectory February 5th, 2009 [John Aitchison] [Mission Ops]

[John Aitchison] [Mission Ops] Descent Trajectory Goal Determine trajectory, attitude, burn time, range & altitude EOM Derivation Assumptions Moon/spacecraft system, spherical & does not rotate, point masses 2-D problem T/m varies only with changing propellant mass (no throttling) [John Aitchison] [Mission Ops]

[John Aitchison] [Mission Ops] Useful Numbers Variability with: Vehicle Mass Thrust Capability Lunar Parking Orbit Time (s) Action Downrange (km) Altitude (km) 0.0 Retro 15 170.3 27° 170.1 5.7 207.5 Vertical 175.4 0.9 222.1 Touchdown [John Aitchison] [Mission Ops]

[John Aitchison] [Mission Ops] Code (pg. 1) [John Aitchison] [Mission Ops]

[John Aitchison] [Mission Ops] Code (pg. 2) [John Aitchison] [Mission Ops]

[John Aitchison] [Mission Ops] Code (pg. 3) [John Aitchison] [Mission Ops]

[John Aitchison] [Mission Ops] Code (pg. 4) [John Aitchison] [Mission Ops]

[John Aitchison] [Mission Ops] Coordinate System [John Aitchison] [Mission Ops]

Coordinate System Definitions [John Aitchison] [Mission Ops]

[John Aitchison] [Mission Ops] Assumptions [John Aitchison] [Mission Ops]

[John Aitchison] [Mission Ops] Calculations (pg. 1) [John Aitchison] [Mission Ops]

[John Aitchison] [Mission Ops] Calculations (pg. 2) [John Aitchison] [Mission Ops]

[John Aitchison] [Mission Ops] Calculations (pg. 3) [John Aitchison] [Mission Ops]

[John Aitchison] [Mission Ops] Calculations (pg. 4) [John Aitchison] [Mission Ops]