Final design of the High Altitude Supersonic Target (HAST) and supporting equipment was completed and flight test vehicles and supporting equipment were fabricated in this phase. Ground test programs were conducted on subsystems and components. Acceptance tests were conducted on components and the complete vehicle. Analyses confirmed that the canard-clipped delta wing configuration could meet required maneuvers. Materials for the airframe were selected which provide a fair compromise of both manufacturing costs and efficient and reliable thermo-structural performance capability. A hybrid rocket propulsion system was specified and test firings have confirmed the ignition and boost thrust capability and that a variable thrust can be obtained by the use of an oxidizer throttle valve. To meet maneuvering requirements a free siphon device has been developed to provide positive expulsion of the oxidizer under all vehicle flight conditions. Maneuvers can be preprogrammed or initiated by radio command and hardware computer tie-in simulations have confirmed the effectiveness of the automatic flight control system to control the vehicle throughout the required flight regime.
High Altitude Supersonic Target (HAST), Phase II
1974
218 pages
Report
Keine Angabe
Englisch
Aircraft , Rocket Engines & Motors , Target drones , Supersonic aircraft , Remotely piloted vehicles , Aerial targets , High altitude , Maneuverability , Flight maneuvers , Flight envelope , Canard configuration , Delta wings , Test vehicles , Captive tests , Hybrid rocket engines , Hybrid rocket propellants , Controllable thrust rocket engines , Command and control systems , Computer applications , Flight control systems , Automatic pilots , Aerodynamic heating , Ground support equipment , Recovery , Military requirements , Joint military activities , Computerized simulation , Flight simulation , HAST(High Altitude Supersonic Targets) , High altitude supersonic targets , Design
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