This study investigated the atmospheric reentry of the Space Maneuver Vehicle from low-earth orbit using an entry guidance concept similar to the Space Shuttle. The Space Maneuver Vehicle was modeled as a point mass with aerodynamic properties as determined using Newtonian impact theory. For the rarefied-flow transition regime bridging formulae are used to capture the effects of both hypersonic continuum flow and free molecular flow. Constraints to the reentry are developed and a reentry corridor is defined in the drag- velocity plane. Bank angle modulation is established as the primary means for controlling drag and range. The guidance concept is applied to both a high inclination orbit and a low inclination orbit with cross-range requirement. Monte Carlo error analysis validates the ability of the control algorithm to guide reentry in the presence of initial state errors, as well as atmospheric variations. (7 tables, 54 figures, 18 refs.).
Investigation of Atmospheric Reentry for the Space Maneuver Vehicle
2004
95 pages
Report
Keine Angabe
Englisch
Algebra, Analysis, Geometry, & Mathematical Logic , Fluid Mechanics , Unmanned Spacecraft , Spacecraft Trajectories & Flight Mechanics , Algorithms , Atmosphere entry , Aerodynamic forces , Lifting reentry vehicles , Terminal guidance , Unmanned spacecraft , Velocity , Computerized simulation , Inclined orbit trajectories , Control systems , Equations of motion , Earth orbits , Low orbit trajectories , Theses , Angle of attack , Monte carlo method , Error analysis , Temperature control , Altitude , Reusable equipment , Spacecraft trajectories , Space missions , Hypersonic flow , Landing , Atmospheric reentry , Space maneuver vehicles , Reentry guidance systems , Drag acceleration profiles , Drag profile guidance , Reentry corridor , Bank angle modulation , X-40a spacecraft , X-37 spacecraft , Entry guidance algorithms , Spacecraft landings , Reentry trajectory , Range modulation , Roll reversal
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