Several topics of the separation maneuver of two-stage hypersonic vehicles are considered. Results which have been obtained from wind tunnel tests of the separation maneuver and related investigations on flight dynamics will be presented. In test facilities of DLR (Cologne), the aerodynamics characteristics of a two-stage space transportation system were investigated. The test campaign was focused on aerodynamic interference effects which exist when the two stages are in close proximity. The results of the wind tunnel tests provide a detailed data base for flight mechanics investigations. Numerical simulation of flight dynamics based on a well founded aerodynamics model is an appropriate technique to investigate such a highly dynamic maneuver. Control of both vehicles for achieving an optimal motion of the system is investigated. In addition, adequate stability and control characteristics from a piloting point of view are considered. Particular emphasis is put on a robust control technique. This is because robust control is an adequate means for dealing with a system which shows great changes. During close proximity of the first and orbital stages, system changes are due to the separation maneuver itself because of aerodynamic interference effects.
Separation of Lifting Vehicles at Hypersonic Speed Wind Tunnel Tests and Flight Dynamics Simulation
1995
8 pages
Report
Keine Angabe
Englisch
Separation of Lifting Vehicles at Hypersonic Speed Wind Tunnel Tests and Flight Dyanmics Simulation
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