The purpose of this study was to determine the feasibility of launching a Delta Clipper-like vehicle on an optimal, non-coplanar trajectory to rendezvous with an earth orbiting object in one orbit or less. The focus of the research was to determine what such a trajectory would look like, and to determine the cost, in payload mass, of flying such a trajectory. A model for the ascent trajectory was developed using the dynamics equations of motion, an atmosphere model, and an aerodynamic model for the DC-Y concept vehicle. A boundary value problem was posed and solved for a coplanar rendezvous. The non-coplanar solutions were obtained through extrapolation from the coplanar solution.
Optimal Non-Coplanar Launch to Quick Rendezvous
1997
79 pages
Report
Keine Angabe
Englisch
Spacecraft Trajectories & Flight Mechanics , Rendezvous trajectories , Orbits , Payload , Equations of motion , Earth orbits , Dynamics , Costs , Solutions(General) , Feasibility studies , Boundary value problems , Planar structures , Launching , Atmosphere models , Aerodynamics , Ascent trajectories , Delta clipper
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