1 / 6

Lunar Descent Trajectory Optimization

Lunar Descent Trajectory Optimization. February 12, 2009. Page 1. Goal: To minimize propellant used during Lunar descent. Trajectory conditions: Apolune at 110km Vary perilune from 15km to 5km Allow sufficient time for attitude changes

berke
Download Presentation

Lunar Descent Trajectory Optimization

An Image/Link below is provided (as is) to download presentation Download Policy: Content on the Website is provided to you AS IS for your information and personal use and may not be sold / licensed / shared on other websites without getting consent from its author. Content is provided to you AS IS for your information and personal use only. Download presentation by click this link. While downloading, if for some reason you are not able to download a presentation, the publisher may have deleted the file from their server. During download, if you can't get a presentation, the file might be deleted by the publisher.

E N D

Presentation Transcript

  1. Lunar Descent Trajectory Optimization February 12, 2009 [Alex Whiteman] [Mission Ops] Page 1

  2. Goal: To minimize propellant used during Lunar descent • Trajectory conditions: • Apolune at 110km • Vary perilune from 15km to 5km • Allow sufficient time for attitude changes • Leave propellant and altitude margin to allow for hover and obstacle avoidance Page 2

  3. Propellant use for each trajectory • Conclusions: • Lowering perilune decreases propellant mass • Diminishing returns as perilune keeps decreasing Page 3

  4. Backup Slide 1 EOM’s Mass flow rate equation Thrust perpendicular to surface of Moon Thrust parallel to surface of Moon Isp = 295s (H2O2/Polyethylene) Page 4

  5. Backup Slide 2 MATLAB EOM Script Page 5

  6. Backup Slide 3 MATLAB EOM Script (cont.) Page 6

More Related