The first test flight of the Orion Multi-Purpose Crew Vehicle presented additional challenges for guidance, navigation and control as compared to a typical re-entry from the International Space Station or other Low Earth Orbit. An elevated re-entry velocity and steeper flight path angle were chosen to achieve aero-thermal flight test objectives. New IMU's, a GPS receiver, and baro altimeters were flight qualified to provide the redundant navigation needed for human space flight. The guidance and control systems must manage the vehicle lift vector in order to deliver the vehicle to a precision, coastal, water landing, while operating within aerodynamic load, reaction control system, and propellant constraints. Extensive pre-flight six degree-of-freedom analysis was performed that showed mission success for the nominal mission as well as in the presence of sensor and effector failures. Post-flight reconstruction analysis of the test flight is presented in this paper to show whether that all performance metrics were met and establish how well the pre-flight analysis predicted the in-flight performance.
Post-Flight Analysis of the Guidance, Navigation, and Control Performance During Orion Exploration Flight Test 1
2015
14 pages
Report
No indication
English
Industrial & Mechanical Engineering , Unmanned Spacecraft , Manned Spacecraft , Navigation , Global positioning system , Reentry , Attitude (inclination) , Spacecraft modules , Altimeters , Atmospheric pressure , Crew exploration vehicle , Flight tests , Guidance (motion) , Attitude control , Spacecrews , Jettisoning , Deployment , Parachute descent , Postflight analysis , Launching , Aerodynamic loads , Degrees of freedom
British Library Conference Proceedings | 2015
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