This research investigates an approach to provide precise, coordinated maneuver control during excursions from a hypersonic cruise flight path while observing the necessary flight condition constraints. The approach achieves specified guidance commands by resolving altitude and cross-range errors into a load factor and bank angle command through a coordinate transformation which acts as an interface between outer loop guidance controls and inner loop flight controls. This interface, referred to as a 'resolver', applies constraints on angle-of-attack and dynamic pressure perturbations while prioritizing altitude regulation over crossrange. An unpiloted test simulation, in which the resolver was used to drive inner-loop flight controls, produced time histories of responses to guidance commands at Mach numbers of 6, 10, 15, and 20. It is shown that angle-of-attack and throttle perturbation constraints, combined with high-speed flight effects and the desire to maintain constant dynamic pressure, significantly impact the maneuver envelope for a hypersonic vehicle. Turn rate, climb rate, and descent rate limits are expressed in terms of these constraints.
Control concept for maneuvering in hypersonic flight
1991-12-01
Aufsatz (Konferenz)
Keine Angabe
Englisch
Control concept for maneuvering in hypersonic flight
AIAA | 1991
|Aerodynamic maneuvering hypersonic flight mechanics
NTRS | 1988
|Aerodynamic Maneuvering Hypersonic Flight Mechanics
NTIS | 1988
|AIAA | 1998
|Online Contents | 1998
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