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.

中文翻译：

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基于PSO算法的远程弹道导弹多学科集成设计

在给定设计变量和约束函数的情况下，本文涉及基于最小起飞质量指标的远程弹道导弹的轨迹，推进和空气动力学的快速总体参数设计。与传统的子系统独立设计相反，本文采用了子系统独立设计与多系统集成设计相结合的研究思想。首先，通过工程设计分别设计子系统的轨迹，推进和空气动力学，包括最小能量轨迹的设计，推进系统参数的计算，导弹的气动系数和动态导数的计算。 DATCOM导弹软件。然后，采用统一设计方法通过集成设计简化约束条件和设计变量，采用统一粒子群优化算法实现优化变量的精确设计。最后，为三级固体弹道导弹编写了自动化设计软件。子系统独立设计得出起飞质量29 850 kg，在29个设计变量和32个约束的基础上采用统一设计减少了20个约束，起飞质量下降了1850 kg通过将统一设计和PSO相结合。仿真结果证明了所提混合优化技术的有效性和可行性。