| タイトル | An adaptive guidance algorithm for an aerodynamically assisted orbital plane change maneuver |
| 本文（外部サイト） | http://hdl.handle.net/2060/19860017461 |
| 著者（英） | Blissit, J. A. |
| 著者所属（英） | Draper (Charles Stark) Lab., Inc. |
| 発行日 | 1986-05-01 |
| 言語 | eng |
| 内容記述 | Using analysis results from the post trajectory optimization program, an adaptive guidance algorithm is developed to compensate for density, aerodynamic and thrust perturbations during an atmospheric orbital plane change maneuver. The maneuver offers increased mission flexibility along with potential fuel savings for future reentry vehicles. Although designed to guide a proposed NASA Entry Research Vehicle, the algorithm is sufficiently generic for a range of future entry vehicles. The plane change analysis provides insight suggesting a straight-forward algorithm based on an optimized nominal command profile. Bank angle, angle of attack, and engine thrust level, ignition and cutoff times are modulated to adjust the vehicle's trajectory to achieve the desired end-conditions. A performance evaluation of the scheme demonstrates a capability to guide to within 0.05 degrees of the desired plane change and five nautical miles of the desired apogee altitude while maintaining heating constraints. The algorithm is tested under off-nominal conditions of + or -30% density biases, two density profile models, + or -15% aerodynamic uncertainty, and a 33% thrust loss and for various combinations of these conditions. |
| NASA分類 | COMPUTER PROGRAMMING AND SOFTWARE |
| レポートNO | 86N26933
CSDL-T-902
NASA-CR-177296
NAS 1.26:177296 |
| 権利 | No Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/153954 |
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