Reusable Launch Vehicle Wing Shape Optimization Design Method Research

This paper is major in the preliminary wing design for the Reusable Launch Vehicle (RLV). The vehicle has the following mission profile: vertical takeoff, boost-to-orbit, hypersonic re-entry and horizontal landing. For this vehicle, the wing is sized to meet the re-entry aerodynamic requirements for hypersonic trim, stability, and lift-to-drag ratio, landing velocity.Newtonian Impact Theory and One-order Panel Method are used for hypersonic aerodynamic analysis. For subsonic aerodynamic analysis, Linearized Velocity Potential Theory is used to evaluate the aerodynamic coefficient, and we can get subsonic aerodynamic model of vehicle by Regression Analysis.The aerodynamic model is combined with an existing optimization algorithm to size and shape the wing of RLV with the objective to minimize the wing mass. The optimization design parameters of the wing are leading-edge sweep A/c, trailing-edgesweep Ate, exposed taper ratio Aexp and exposed root length Crexp. Genetic Algorithmand Simulated Annealing Algorithm can get the global minimum of the objective function by probabilistic search, so Simple Genetic Algorithm, Simulated Annealing Algorithm and Hybrid Genetic Algorithm are used to evaluate the optimization design parameters. With the procedure of preliminary wing design, the influences of control surface and center-of-gravity position of the vehicle are investigated.