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Orbiter Trajectory Analysis for a Two-Stage Reusable Launch VehicleTrajectory analysis performed on NASA's reference two-stage-to-orbit launch vehicle upper stage will be presented. The work was completed in support of the Hypersonics Multidisciplinary Analysis and Optimization effort for the NASA-Air Force Joint System Study. Three degree-of-freedom (3-DOF) untrimmed trajectory analysis was performed for the orbiter ascent, closure and re-entry. An iterative closure process resulted in a 333,000 lb initial mass for the orbiter. The re-entry trajectory satisfied heating constraints for all payload out cases and met the constraints with reduced margins for payload in cases. Abort trajectories for engine out at staging, engine out during ascent, and failure to circularize in orbit, gave insight to the robustness of the orbiter. A trimmed ascent trajectory defined an engine gimbal location and the body flap angle best suited for maximizing injected mass. A trimmed re-entry trajectory revealed a need to update the trim routine to accommodate full flap aerodynamic data.
Document ID
20110010980
Acquisition Source
Langley Research Center
Document Type
Conference Paper
Authors
Cowling, Adam L. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
August 25, 2013
Publication Date
April 11, 2011
Subject Category
Launch Vehicles And Launch Operations
Report/Patent Number
NF1676L-12493
Meeting Information
Meeting: 17th AIAA International Space Planes and Hypersonic Systems and Technologies Conference
Location: San Francisco, CA
Country: United States
Start Date: April 11, 2011
End Date: April 14, 2011
Sponsors: American Inst. of Aeronautics and Astronautics
Funding Number(s)
WBS: WBS 599489.02.07.07.09.11.01
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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