固体运载器大气飞行段内弹道优化设计研究

摘要

为提升固体运载器射程能力并改善复杂大气飞行段的姿态控制、载荷条件，以射程最大为目标，利用离散化方法建立了内弹道优化设计模型。通过等比调节与值域调控的迭代处理方法，将有约束优化模型转化为无约束优化模型。以自适应差分进化法开展优化仿真。仿真结果表明，固体运载器内弹道推力曲线采用“前高后低”的形式将有利于提高射程，并对改善大气飞行段飞行环境具有积极意义。研究成果可为固体运载体总体方案论证提供借鉴。%To improve range capacity,attitude control performance and flight load in the phase of atmosphere flight of solid launch vehicle(SLV),the discrete optimization model was developed to achieve the goal of maximizing range capacity.By proportional adj ustment and value domain control,the optimization model with constraints is tranformed into the optimization model with no constraints.The simulations were carried out based on adaptive differential evolutionary algorithms.The simulation results show that the interior ballistics thrust-curve in the form of high-to-low can improve both range capacity and flight conditions of atmosphere flight phase. This optimization conclusion can be used for future reference in SLV design.