1 / 9

Lunar Lander Handling Qualities Terminal Descent to Touchdown

Lunar Lander Handling Qualities Terminal Descent to Touchdown. Dr. Karl Bilimoria NASA Ames Research Center “Go for Lunar Landing” Conference Tempe, AZ 4 – 5 March 2008. Background. Handling Qualities Ease & precision with which the pilot can execute a flying task

lynna
Download Presentation

Lunar Lander Handling Qualities Terminal Descent to Touchdown

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 Lander Handling QualitiesTerminal Descent to Touchdown Dr. Karl Bilimoria NASA Ames Research Center “Go for Lunar Landing” Conference Tempe, AZ 4 – 5 March 2008

  2. Background • Handling Qualities • Ease & precision with which the pilot can execute a flying task • HQs depend on vehicle response, guidance cues, inceptors, etc. • Comprehensive standards exist for aircraft • NASA has initiated an effort to study handling qualities of piloted spacecraft designed for Constellation program • Lunar Lander experiment • May 2007 at Ames, on the Vertical Motion Simulator (VMS) • A first step in the handling qualities effort

  3. Precision Landing Task: Horizontal Profiles Two horizontal profiles • Centerline approach • 250 ft offset approach 1,350 ft Landing Site Land within 15 ftof target center Offset distance= 250 ft Centerline Approach Left Offset Approach

  4. Precision Landing Task: Vertical Profile Trajectory based on Apollo missions: “Low Gate” to Touchdown INITIAL CONDITIONS: Distance = 1,350 ft Altitude = 500 ft Horizontal speed = 60 fps Vertical speed = –16 fps Pitch angle = 16 deg Reference Trajectory 95 sec to touchdown Uncontrolled Trajectory 31 sec to impact Dist = 0 Alt = 150 ft Horiz spd = 0 Vert spd = –3 fps

  5. Out the window field of view Simulator Cab Layout

  6. Cockpit Displays Guidance cues: • Roll, pitch, and yaw angles • Forward and lateral speeds • Altitude rate

  7. Lunar Lander Experiment Objectives • Evaluate a basic model of Apollo Lunar Module • Study handling qualities for various combinations of: • Control power (various levels of acceleration) • Guidance (ON or OFF) Pilots fly 3 approaches in each cell – Cooper-Harper Rating – Workload Rating (NASA-TLX) – Comments

  8. Control Power Study – Guidance On Task Load Index Rating Handling Qualities Rating Not satisfactory for tasks that couldresult in crew or vehicle loss Level 3: Improvement mandatory Level 2: Deficiencies warrant improvement Satisfactory for tasks that couldresult in crew or vehicle loss Level 1: Satisfactory without improvement Evaluating a basic model of Apollo Lunar Module

  9. Concluding Remarks • Control power study • Nominal configuration model is close to Level 1 boundary • Handling qualities degrade rapidly after control power drops below 50% of nominal value • Guidance is essential for precision landing task • Lateral offset approach not flyable without guidance • Centerline approach very difficult to fly without guidance • Suggested discussion topic:Does a ground-based simulator with high motion fidelity negate the need to build a LLRV-like vehicle for Cx?

More Related