DESIGN AND DEVELOPMENT OF AN ADAPTABLE FLIGHT DEMONSTRATION VEHICLE WITH MODULAR GUIDANCE AND CONTROL
Brophy, Christopher M.
Dobrokhodov, Vladimir N.
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The ability to evaluate new missile technologies and explore various flight profiles through experimental flight tests is an essential step in most technology development paths. This capability is often an expensive option and designs are frequently limited to a particular vehicle layout. An adaptable and recoverable two-stage missile flight system was designed with configurability in mind such that either ballistic flight paths or a boost-sustain configuration with a final horizontal flight profile can be evaluated. The vehicle developed included tunable guidance and control, servo actuation, structure, recovery, and avionics. The system was designed to utilize a canard control strategy for the boost phase and tail control for the sustainer phase regardless of which flight option was used. Flight testing was conducted to demonstrate structural concepts, inertial navigation sensor resolution, data collection, two stage events, and recovery
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