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Reusable launch vehicle wing shape optimization design method

Author: WangYunLiang
Tutor: LiWeiJi
School: Northwestern Polytechnical University
Course: Aircraft design
Keywords: Reusable Launch Vehicles Optimal design Regression analysis Genetic Algorithms Simulated annealing algorithm
CLC: V224
Type: Master's thesis
Year: 2003
Downloads: 195
Quote: 0
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Abstract


In this paper, reusable launch vehicle wing shape of the preliminary design and optimization methods . In general, reusable launch vehicle mission profile is divided into : a vertical takeoff , orbit hypersonic re-entry , a horizontal landing several stage . Wing shape should be designed so that reusable launch vehicle re-entry to the hypersonic flight and horizontal landing , to meet the trim and stability , the aerodynamic design of the lift to drag ratio , landing speed requirements . This article during hypersonic aerodynamic analysis , the application of modified Newtonian collision theory and the order of flat- panel method to calculate the aerodynamic characteristics of the carrier obtained its trim angle of attack and lift-to-drag ratio ; performing subsonic aerodynamic analysis application the aerodynamic coefficients linearized velocity potential theory to calculate the carrier , then regression analysis model carrying subsonic aerodynamic characteristics . The aerodynamic characteristics of the carrier will be able to re-use a combination of models and optimization techniques , the lightest wing weight optimization objectives wing shape optimization and design . Optimize the design variables : the wing leading edge sweep angle A le , the trailing edge sweep angle A te , the exposed wing slightly root ratio λ exp < / sub> and exposed root chord length C r exp . Consider the preliminary design of the wing control surface deflection and delivery position of the center of gravity change different design conditions , genetic algorithms and simulated annealing algorithm to random search technology to find the global minimum of the objective function from the sense of probability , suitable for reusable launch vehicle wing shape of the preliminary design . Therefore , the application of genetic algorithms, simulated annealing algorithm and hybrid genetic algorithm computer wing shape optimization parameters.

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