基于粒子群算法的类“匕首”导弹最大航程计算

Calculation of Maximum Range for “Dagger”-type Missile Based on Particle Swarm Optimization Algorithm

摘要

针对类“匕首”导弹初步方案轨迹设计阶段的最大航程寻优问题，在确定飞行器状态参数的基础上，将飞行过程简化为多个阶段，并将各阶段控制量设定为常值，构建了基于最小二乘-牛顿迭代的轨迹规划方法，用于计算不同轨迹最高点高度下的航程。创新地提出了二层迭代框架:外层采用粒子群算法优化轨迹最高点高度参数，内层基于最小二乘牛顿迭代方法进行轨迹规划，以最大航程为优化目标，实现最优轨迹的自动寻优。仿真结果表明，基于最小二乘牛顿迭代的轨迹规划方法在各阶段迭代3~7次后均能收敛，目标函数均小于0.01，满足精度要求，单次轨迹规划用时为90.78s，具备较高的计算效率。提出的基于粒子群算法的最大航程优化方法经8~10次外层迭代即可收敛，迭代规划总时间小于300s，较传统方法具有耗时少，对迭代初始值不敏感，鲁棒性强等优势，展现出较好的工程应用前景，为类“匕首”导弹初步方案阶段的轨迹设计提供了有效方法。

Abstract

For the maximum range optimization problem during the preliminary trajectory design phase of hypersonic vehicles, based on predetermined vehicle state parameters, the flight process was simplified into multiple phases with control variables set as constant values in each phase. A trajectory planning method based on the least squares-Newton iteration was developed to calculate the flight range under different trajectory apex altitudes. A novel two-layer iterative framework was proposed: the outer layer employs particle swarm optimization (PSO) to optimize the trajectory apex altitude parameter, while the inner layer performs trajectory planning using the least squares-Newton iteration method, with the maximum range as the optimization objective for automatic optimal trajectory search. Simulation results indicate that the least squares-Newton iteration-based trajectory planning method achieves convergence within 3 to 7 iterations per phase, with the objective function values below 0.01, meeting the precision requirements. A single trajectory planning operation takes 90.78s, demonstrating relatively high planning efficiency. The proposed PSO-based maximum range optimization method converges within 8 to 10 outer iterations, with total iterative planning time under 300s. Compared to traditional methods, this approach shows advantages including reduced computation time, insensitivity to initial values, and strong robustness, indicating good potential for engineering applications. This work provides an effective methodology for trajectory design in the preliminary phase of hypersonic vehicle development.

关键词

“匕首”导弹 / 粒子群优化 / 最大航程 / 牛顿迭代方法

Key words

“Dagger” missile / particle warm optimization / maximum range / Newton iteration

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