Aerodynamic, propulsion, and mass models for a generic, horizontal-takeoff, single-stage-to-orbit (SSTO) configuration are presented which are suitable for use in point mass as well as batch and real-time six degree-of-freedom simulations. The simulations can be used to investigate ascent performance issues and to allow research, refinement, and evaluation of integrated guidance/flight/propulsion/thermal control systems, design concepts, and methodologies for SSTO missions. Aerodynamic force and moment coefficients are given as functions of angle of attack, Mach number, and control surface deflections. The model data were estimated by using a subsonic/supersonic panel code and a hypersonic local surface inclination code. Thrust coefficient and engine specific impulse were estimated using a two-dimensional forebody, inlet, nozzle code and a one-dimensional combustor code and are given as functions of Mach number, dynamic pressure, and fuel equivalence ratio. Rigid-body mass moments of inertia and center of gravity location are functions of vehicle weight which is in turn a function of fuel flow.
Hypersonic Vehicle Simulation Model: Winged-Cone Configuration
1990
142 pages
Report
No indication
English
Aircraft , Aerodynamics , Manned Spacecraft , Spacecraft Trajectories & Flight Mechanics , Aerodynamic characteristics , Aerodynamic forces , Ascent trajectories , Control systems design , Hypersonic vehicles , Panel method (Fluid dynamics) , Computerized simulation , Force distribution , Mathematical models , Moment distribution , Aerodynamic coefficients , Angle of attack , Center of gravity , Degrees of freedom , Dynamic pressure , Hypersonics , Mach number , Moments of inertia , Propulsion , Specific impulse
Aerothermodynamics of a Winged Reentry Vehicle in Hypersonic Flow
British Library Conference Proceedings | 2002
|FULL-LENGTH PAPERS - Eigenstructure vs Constrained H(infinity) Design for Hypersonic Winged Cone
Online Contents | 2001
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