Hypersonic Vehicle Simulation Model: Winged-Cone Configuration

By National Aeronautics and Space Administration

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. Shaughnessy, John D. and Pinckney, S. Zane and Mcminn, John D. and Cruz, Christopher I. and Kelley, Marie-Louise Langley Research Center AERODYNAMIC CHARACTERISTICS; AERODYNAMIC FORCES; ASCENT TRAJECTORIES; COMPUTERIZED SIMULATION; CONTROL SYSTEMS DESIGN; FORCE DISTRIBUTION; HYPERSONIC VEHICLES; MATHEMATICAL MODELS; MOMENT DISTRIBUTION; PANEL METHOD (FLUID DYNAMICS); AERODYNAMIC COEFFICIENTS; ANGLE OF ATTACK; CENTER OF GRAVITY; DEGREES OF FREEDOM; DYNAMIC PRESSURE; HYPERSONICS; MACH NUMBER; MOMENTS OF INERTIA; PROPULSION; SPECIFIC IMPULSE...

• Format: Paperback
• Language: English
• ISBN: 1731319258
• ISBN13: 9781731319258
• Release Date: January 1
• Publisher: Independently Published
• Length: 150 Pages
• Weight: 0.80 lbs.
• Dimensions: 0.3" x 8.5" x 11.0"