Integrated Aero-Servo-Thermo-Propulso-Elasticity (ASTPE) Methodology for Hypersonic Scramjet Vehicle Design/Analysis

MDO for Hypersonic Scramjet Vehicle Development (Invited)

“…Starkey/Zona generated hypersonic scramjet vehicle performance sensitivities [7][8][9] as shown in Fig. 4 to highlight the differences between finite difference derivatives and complex variable derivatives (CD) for small perturbations in Mach number.…”

“…High-Speed Aircraft MDO Environment: High-speed vehicle design environment developed to simultaneously analyze and optimize for aerodynamics, propulsion, chemically reacting flow, trajectory, thermal protection, structure, trim, control system design, and aeroelasticity effects [6][7][8][9].…”

“…An overview of the Aero-Servo-Thermo-Propulso-Elastic (ASTPE) design environment developed under a phase I/II AF STTR was shown in Fig. 1 [6][7][8][9]. Numerous high-profile examples of hypersonic systems that fell far short of expectations include the National Aerospace Plane (NASP) of the 80's and 90's, DARPA's FALCON program and the NASA/AF X-43 of the 2000's up to the current Air Force X-51 program.…”

“…Control System Sensitivity Derivatives: Hypersonic vehicle sensitivity analysis for control system derivatives to change in Mach using Finite Difference and Complex Variable Differentiation (CVD) approaches[7][8][9].…”

Modeling and Simulation Methodology of Multifield Coupling for Hypersonic Vehicle

“…McNamara [2] studied the aeroelastic behavior of a low aspect ratio three-dimensional wing using third order piston theory. University of Colorado, Zona Technology Inc. and University of Maryland are doing some studies using an integrated Aero-Servo-Thermo-Propulsion-Elasticity method [6]. Falkiewicz [3] modeled the aerothermoelastic characteristics of aerodynamic fins of hypersonic vehicle in order to evaluate the effect of structure deformation to flight control system.…”