| タイトル | Dynamic Stability Testing of the Mars Science Laboratory Entry Capsule |
| 本文（外部サイト） | http://hdl.handle.net/2060/20090026361 |
| 著者（英） | Hathaway, Wayne; Schroenenberger, Mark; Yates, Leslie |
| 著者所属（英） | NASA Langley Research Center |
| 発行日 | 2009-06-22 |
| 言語 | eng |
| 内容記述 | Results from a 26 shot ballistic range test of the Mars Science Laboratory (MSL) entry capsule are presented. The supersonic pitch damping properties of the MSL capsule were characterized between Mach 1.35 and Mach 3.5 and total angles-of-attack from 0 to 30 degrees. In flight, the MSL entry capsule will utilize a radial center-of-gravity offset to produce a non-zero trim angle-of-attack. This offset trim angle will produce lift, enabling the capsule to fly a guided entry and reducing the landing footprint dimensions to within 10 km of the desired landing site. A lifting configuration could not be tested at the ballistic range used for this test as the models would swerve into the range walls, possibly damaging cameras, the coordinate reference system or other facility assets. Ballistic (non-lifting) data was extracted and will be implemented in a conservative fashion to ensure that the dynamic stability characteristics of the flight vehicle are bounded. A comparison between the MSL pitch damping results and the dynamic model of the Mars Exploration Rover capsule shows generally close agreement with no significant differences in damping characteristics due to the change in backshell geometry. Dynamic moments are also compared to the MSL reaction control system (RCS) control authority to show the controller has sufficient margin to easily damp any dynamic stability effects. |
| NASA分類 | Lunar and Planetary Science and Exploration |
| レポートNO | AIAA Paper 2009-3917
LF99-8967 |
| 権利 | Copyright, Distribution as joint owner in the copyright |
