Optimal control theory is employed to determine the performance of abort to orbit (ATO) and return to launch site (RTLS) maneuvers for a single-stage to orbit vehicle. The vehicle configuration examined is a seven engine, winged-body vehicle, that lifts-off vertically and lands horizontally. The abort maneuvers occur as the vehicle ascends to orbit and are initiated when the vehicle suffers an engine failure. The optimal control problems are numerically solved in discretized form via a nonlinear programming (NLP) algorithm. A description highlighting the attributes of this NLP method is provided. ATO maneuver results show that the vehicle is capable of ascending to orbit with a single engine failure at lift-off. Two engine out ATO maneuvers are not possible from the launch pad, but are possible after launch when the thrust to weight ratio becomes sufficiently large. Results show that single engine out RTLS maneuvers can be made for up to 180 seconds after lift-off and that there are scenarios for which RTLS maneuvers should be performed instead of ATO maneuvers.
Abort Performance for a Winged-Body Single-Stage to Orbit Vehicle
1995
83 pages
Report
Keine Angabe
Englisch
Space Launch Vehicles & Support Equipment , Abort trajectories , Aerodynamic characteristics , Engine failure , Multiengine vehicles , Single stage to orbit vehicles , Winged vehicles , Algorithms , Ascent propulsion systems , Control theory , Horizontal spacecraft landing , Launching sites , Optimal control , Vertical takeoff
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