| タイトル | Definition ofthe Design Trajectory and Entry Flight Corridor for the NASA Orion Exploration Mission 1 Entry Trajectory Using an Integrated Approach and Optimization |
| 本文（外部サイト） | http://hdl.handle.net/2060/20140004224 |
| 著者（英） | McNamara, Luke W.; Braun, Robert D. |
| 発行日 | 2014-01-31 |
| 言語 | eng |
| 内容記述 | One of the key design objectives of NASA's Orion Exploration Mission 1 (EM- 1) is to execute a guided entry trajectory demonstrating GN&C capability. The focus of this paper is defining the flyable entry corridor for EM-1 taking into account multiple subsystem constraints such as complex aerothermal heating constraints, aerothermal heating objectives, landing accuracy constraints, structural load limits, Human-System-Integration-Requirements, Service Module debris disposal limits and other flight test objectives. During the EM-1 Design Analysis Cycle 1 design challenges came up that made defining the flyable entry corridor for the EM-1 mission critical to mission success. This document details the optimization techniques that were explored to use with the 6-DOF ANTARES simulation to assist in defining the design entry interface state and entry corridor with respect to key flight test constraints and objectives. |
| NASA分類 | Spacecraft Design, Testing and Performance; Fluid Mechanics and Thermodynamics; Numerical Analysis |
| レポートNO | AAS 14-094
JSC-CN-30088 |
| 権利 | Copyright, Distribution as joint owner in the copyright |
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