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

2

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

3

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)

4

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)

10

AAE450 Spring 2009 [John Aitchison] [Mission Ops]

LD Integrated Code (pg. 2)

11

AAE450 Spring 2009 [John Aitchison] [Mission Ops]

LD Integrated Code (pg. 3)

12

AAE450 Spring 2009 [John Aitchison] [Mission Ops]

LD Integrated Code (pg. 4)

13

AAE450 Spring 2009 [John Aitchison] [Mission Ops]

LD Integrated Code (pg. 5)

14

AAE450 Spring 2009 [John Aitchison] [Mission Ops]

LD Integrated Code (pg. 6)

15

AAE450 Spring 2009 [John Aitchison] [Mission Ops]

LD Integrated Code (pg. 7)

16

AAE450 Spring 2009 [John Aitchison] [Mission Ops]

LD Integrated Code (pg. 8)

17

AAE450 Spring 2009 [John Aitchison] [Mission Ops]

LD Integrated Code (pg. 9)

18

AAE450 Spring 2009 [John Aitchison] [Mission Ops]

LD Integrated Code (pg. 10)

19

AAE450 Spring 2009 [John Aitchison] [Mission Ops]

LD Integrated Code (pg. 11)

20

AAE450 Spring 2009 [John Aitchison] [Mission Ops]

LD Integrated Code (pg. 12)

21

AAE450 Spring 2009 [John Aitchison] [Mission Ops]

LD Integrated Code (pg. 13)

22

AAE450 Spring 2009 [John Aitchison] [Mission Ops]

LD Integrated Code (pg. 14)

23

AAE450 Spring 2009 [John Aitchison] [Mission Ops]

LD Integrated Code (pg. 15)

24

AAE450 Spring 2009 [John Aitchison] [Mission Ops]

LD Integrated Code (pg. 16)

25

AAE450 Spring 2009 [John Aitchison] [Mission Ops]

LD Integrated Code (pg. 17)

26

AAE450 Spring 2009 [John Aitchison] [Mission Ops]

Steering Program Code

27

AAE450 Spring 2009

Steering Program Code (cont.)

[John Aitchison] [Mission Ops]28

AAE450 Spring 2009 [John Aitchison] [Mission Ops]

Circ-Elliptical Using Attitude Thrusters

29

AAE450 Spring 2009 [John Aitchison] [Mission Ops]

Circ-Elliptical Using Attitude Thrusters (pg.2)

30

AAE450 Spring 2009 [John Aitchison] [Mission Ops]

Circ-Elliptical Using Attitude Thrusters (pg.3)

DeltaV = 9.2 m/sAttitude Propellant Mass = .82 kg

31