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Hyper Heuristic Approach for Design and Optimization of satellite launch vehicle

Chinese Journal of Aeronautics 2011年第2期24卷 150-163页

作者： Amer Farhan RAFIQUE HE Linshu Ali KAMRAN Qasim ZEESHAN Department of Spacecraft Technology School of Astronautics Beihang University Beijing 100191 China Department of Space Propulsion School of Astronautics Beihang University Beijing 100191 China

satellite launch vehicle lies at the cross-road of multiple challenging technologies and its design and optimization present a typical example of multidisciplinary design and optimization（MDO） *** complexity of problem demands highly effi-cient and effective algorithm that can optimize the *** heuristic approach（HHA） based on meta-heuristics is applied to the optimization of air launched satellite launch vehicle（ASLV）.A non-learning random function（NLRF） is proposed to con-trol low-level meta-heuristics（LLMHs） that increases certainty of global solution,an essential ingredient required in product conceptual design phase of aerospace *** empirical study is performed to evaluate the performance advan-tages of proposed approach over popular non-gradient based optimization *** of ASLV encompasses aerodynamics,propulsion,structure,stages layout,mass distribution,and trajectory modules connected by multidisciplinary feasible design *** approach formulates explicit system-level goals and then forwards the design optimization process entirely over to *** distinctive approach for launch vehicle system design relieves engineers from tedious,iterative task and en-ables them to improve their component level *** is an impetus on vehicle performance and cost,and so it is considered as the core of vehicle design ***,gross launch mass is to be minimized in HHA.

关键词： multidisciplinary design optimization satellite launch vehicle heuristic optimization methods hyper heuristic air launched vehicles

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Multidisciplinary Design and Optimization of satellite launch vehicle Using Latin Hypercube Design of Experiments

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Computer Aided Drafting,Design and Manufacturing 2009年第1期19卷 1-7页

作者： AMER Farhan Rafique QASIM Zeeshan School of Astronautics Beijing University of Aeronautics and Astronautics

The design of new satellite launch vehicle （SLV） is of interest, especially when a combination of Solid and Liquid Propulsion is included. Proposed is a conceptual design and optimization technique for multistage Low Earth Orbit （LEO） bound SLV comprising of solid and liquid stages with the use of Genetic Algorithm （GA） as global optimizer. Convergence of GA is improved by introducing initial population based on the Design of Experiments （DOE） Technique. Latin Hypercube Sampling （LHS）-DOE is used for its good space filling properties. LHS is a stratified random procedure that provides an efficient way of sampling variables from their multivariate distributions. In SLV design minimum Gross Lift offWeight （GLOW） concept is traditionally being sought. Since the development costs tend to vary as a function of GLOW, this minimum GLOW is considered as a minimum development cost concept. The design approach is meaningful to initial design sizing purpose for its computational efficiency gives a quick insight into the vehicle performance prior to detailed design.

关键词： multidisciplinary design and optimization satellite launch vehicle solid propulsion liquid propulsion latin hypercube sampling design of experiments

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