Modeling and Design Optimization of a Common Aero Vehicle with Parameterized Configuration

摘要

A modeling approach for a Common Aero Vehicle (CAV) with parameterized configuration is presented in this paper. A 6 degrees of freedom (DOF) rigid-body model based on winged-cone configuration is proposed. The aerodynamic coefficients are calculated using both the engineering experimental method and computational fluid dynamics (CFD) method. Two kinds of aerodynamic modals for simulation, engineering aerodynamic model (EAM) and merged aerodynamic model (MAM), are developed, and the advantages of MAM are revealed. The nominal CAV model based on MAM is obtained, which is in a general form of CAV aerodynamic model for hypersonic vehicle control design. The impact of configuration parameters on design objectives (including lift-drag ratio, volume-area ratio and longitudinal static stability) are examined. Vehicle optimization is also examined to get the optimized parameters. The Self-Adaptive Evolution (SAE) algorithm and the Sequential Quadratic Programming (SQP) algorithm are used to produce diverse sets of optimal solutions, which enable the designer to quantify tradeoffs among conflicting objectives.