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| 1 | Multidisciplinary integrated design of long-range ballistic missile using PSO algorithm显示文摘In the case of the given design variables and constraint functions, this paper is concerned with the rapid overall parameters design of trajectory, propulsion and aerodynamics for long-range ballistic missiles based on the index of the minimum take-off mass.In contrast to the traditional subsystem independent design, this paper adopts the research idea of the combination of the subsystem independent design and the multisystem integration design.Firstly, the trajectory, propulsion and aerodynamics of the subsystem are separately designed by the engineering design, including the design of the minimum energy trajectory, the computation of propulsion system parameters, and the calculation of aerodynamic coefficient and dynamic derivative of the missile by employing the software of missile DATCOM. Then, the uniform design method is used to simplify the constraint conditions and the design variables through the integration design, and the accurate design of the optimized variables would be accomplished by adopting the uniform particle swarm optimization(PSO) algorithm. Finally, the automation design software is written for the three-stage solid ballistic missile. The take-off mass of 29 850 kg is derived by the subsystem independent design, and 20 constraints are reduced by employing the uniform design on the basis of 29 design variables and 32 constraints, and the take-off mass is dropped by 1 850 kg by applying the combination of the uniform design and PSO. The simulation results demonstrate the effectiveness and feasibility of the proposed hybrid optimization technique. | ZHENG Xu GAO Yejun JINGWuxing WANG Yongsheng | 2020 | Journal of Systems Engineering and Electronics2020，31，2： | 5 |
| 2 | 多学科复杂产品仿真的改进序列Kriging优化方法(英文)显示文摘针对计算机仿真优化耗时较多的问题,Kriging模型被广泛用作原模型的近似以减少仿真时间。但是基于Kriging模型的序列优化还是比较耗时的,本文对期望改进法进行扩展并提出了改进的序列Kriging优化方法。本算法通过每次更新模型时同时增加两个以上的样本点将原方法中两次优化问题变为一次优化。在每次重新构建Kriging模型时,本算法均对新采样点进行验证以使得新加入的点既不与以往样本点重合也避免任两个样本点离得太近。本文还提出了双重收敛法则使得最终Kriging模型的均方根差在容许范围之内,保证结果精度。文中的算例表明了改进的序列Kriging优化方法可以准确并且快速地实现全局优化,并且不受初始优化值影响。本方法在汽车主动悬架系统上的应用表明本文提出的改进法是有效的。 | 王皓 王少萍 Mileta M.Tomovic | 2010 | Chinese Journal of Aeronautics2010，23，5： | 4 |
| 3 | Hyper Heuristic Approach for Design and Optimization of Satellite Launch Vehicle显示文摘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) process.The complexity of problem demands highly effi-cient and effective algorithm that can optimize the design.Hyper 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 systems.Comprehensive empirical study is performed to evaluate the performance advan-tages of proposed approach over popular non-gradient based optimization methods.Design of ASLV encompasses aerodynamics,propulsion,structure,stages layout,mass distribution,and trajectory modules connected by multidisciplinary feasible design approach.This approach formulates explicit system-level goals and then forwards the design optimization process entirely over to optimizer.This distinctive approach for launch vehicle system design relieves engineers from tedious,iterative task and en-ables them to improve their component level models.Mass is an impetus on vehicle performance and cost,and so it is considered as the core of vehicle design process.Therefore,gross launch mass is to be minimized in HHA. | Amer Farhan RAFIQUE HE Linshu Ali KAMRAN Qasim ZEESHAN | 2011 | Chinese Journal of Aeronautics2011，24，2： | 3 |
| 4 | 空基反助推段导弹制导技术综述显示文摘为研究空基反助推段导弹的发展现状和拦截制导面临的关键技术与挑战,对空基反助推段导弹相关的文献进行了分析与总结.空基反助推段导弹由载机发射,对处于助推段飞行的导弹实施拦截,是导弹防御体系的重要组成部分.首先概述空基反助推段系统、导弹和制导技术的发展现状,介绍了典型系统方案的作战流程、拦截弹的结构与性能以及国内外助推段拦截制导技术的研究进展.其次分析了空基助推段拦截制导面临的诸多挑战,体现在拦截弹能力有限、可用时间短、目标机动性强、拦截条件复杂和不确定性强等方面.然后提出了空基助推段拦截制导需要解决的关键技术,包括动力系统配置、发射诸元快速解算、制导指令在线修正、中末制导交班方案和拦截机动目标的高精度制导律等技术.最后总结未来空基助推段拦截制导技术的发展方向为:在线制导、高精度多模复合制导、智能化和协同制导.研究表明:空基反助推段导弹制导技术尚在发展阶段,还存在一些关键问题亟需研究解决,同时,自主规划、人工智能等理论可为关键技术的突破提供参考. | 荆武兴 杨彪 高长生 | 2021 | 哈尔滨工业大学学报2021，53，6： | 2 |
| 5 | Performance comparison between waverider and wide-speed-range gliding vehicle based on CFD approaches显示文摘Wide-speed-range gliding vehicle(WSRGV) is designed to adapt to the variable cruising environment that hypersonic vehicles will encounter during the mission implementation. Based on the cone-derived theory, a novel design technique of WSRGV has been developed. Theoretically, the functional relationship between cone-derived waverider’s volumetric efficiency and its design Mach number can be built through sampling approach as long as the geometries of design conical shock wave and the upper base curve are fixed. Based on the functional relationship, a cone-derived waverider that owns the same volumetric efficiency with a giving WSRGV can be acquired. This paper compared the aerodynamic performance between WSRGV and the cone-derived waverider sharing the same volumetric efficiency in a wide Mach number range. Their aerodynamic properties versus angle of attack have also been compared under the waverider’s design Mach number. The obtained result shows that WSRGV shares similar aerodynamic performance with the cone-derived waverider with the same volumetric efficiency. The aero-surfaces in the margin area of this kind of configuration have a larger contribution to the lift-to-drag ratio in comparison with the aero-surfaces in the central area. The configuration with a thick central body and thin margin place owns not only better aerodynamic performance but also better loading property. | ZHANG TianTian WANG ZhenGuo HUANG Wei YAN XiaoTing | 2019 | Science China(Technological Sciences)2019，62，10： | 1 |
| 6 | Design methodology of a mini-missile considering flight performance and guidance precision显示文摘The design of mini-missiles(MMs)presents several novel challenges.The stringent mission requirement to reach a target with a certain precision imposes a high guidance precision.The miniaturization of the size of MMs makes the design of the guidance,navigation,and control(GNC)have a larger-thanbefore impact on the main-body design(shape,motor,and layout design)and its design objective,i.e.,flight performance.Pursuing a trade-off between flight performance and guidance precision,all the relevant interactions have to be accounted for in the design of the main body and the GNC system.Herein,a multi-objective and multidisciplinary design optimization(MDO)is proposed.Disciplines pertinent to motor,aerodynamics,layout,trajectory,flight dynamics,control,and guidance are included in the proposed MDO framework.The optimization problem seeks to maximize the range and minimize the guidance error.The problem is solved by using the nondominated sorting genetic algorithm II.An optimum design that balances a longer range with a smaller guidance error is obtained.Finally,lessons learned about the design of the MM and insights into the trade-off between flight performance and guidance precision are given by comparing the optimum design to a design provided by the traditional approach. | ZHANG Licong GONG Chunlin SU Hua ANDREA Da Ronch | 2024 | Journal of Systems Engineering and Electronics2024，35，1： | 0 |
| 7 | MDO关键问题及其在液氧/煤油发动机设计中的应用探讨显示文摘多学科设计优化是一种通过充分探索和利用系统的相互作用机制来设计复杂系统及其子系统的方法论,是当前复杂系统工程设计中最活跃的研究领域。大推力液氧/煤油补燃循环发动机设计的多学科本质属性给传统的设计方法带来了新的挑战,在分析液氧/煤油发动机设计的多学科特征基础上,重点讨论了在液氧,煤油发动机设计中应用MDO技术的关键问题,综述了国内外相关领域的研究进展,阐明了在大推力液氧/煤油补燃循环发动机设计中应用MDO的前景。 | 赵剑 谭永华 陈建华 付平 | 2016 | 火箭推进2016，42，6： | 0 |
| 8 | Principal component analysis and cluster analysis based orbit optimization for earth observation satellites显示文摘This paper proposes a design optimization method for the multi-objective orbit design of earth observation satellites, for which the optimality of orbit performance indices with different units, such as: total coverage time, the frequency of coverage, average time per coverage and maximum coverage gap, etc. is required simultaneously. By introducing index normalization method to convert performance indices into dimensionless variables within the range of [0, 1], a design optimization method based on the principal component analysis and cluster analysis is proposed, which consists of index normalization method, principal component analysis, multiple-level cluster analysis and weighted evaluation method. The results of orbit optimization for earth observation satellites show that the optimal orbit can be obtained by using the proposed method. The principal component analysis can reduce the total number of indices with a non-independent relationship to save computing time. Similarly, the multiple-level cluster analysis with parallel computing could save computing time. | 卫晓娜 DONG Yun-feng LIU Feng-rui TIAN Lu HAO Zhao SHI Heng | 2016 | Journal of Chongqing University2016，15，3： | 0 |
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