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 AnalysisCycle 1 design challenges came up that made defining the flyable entry corridor for the EM-1 mission critical to mission success. This documentdetails 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.
Definition ofthe Design Trajectory and Entry Flight Corridor for the NASA Orion Exploration Mission 1 Entry Trajectory Using an Integrated Approach and Optimization
2014
13 pages
Report
Keine Angabe
Englisch
Algebra, Analysis, Geometry, & Mathematical Logic , Systems integration , Flight tests , Trajectory optimization , Mathematical models , Entry guidance(Sts) , Design analysis , Crew exploration vehicle , Unmanned spacecraft , Data bases , Monte carlo method , Spacecraft reentry , Degrees of freedom , Navigation , Spacecraft control , Thermal protection
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