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针对传统预测校正算法在再入过程中弹道性能与约束无法保障等问题,提出了一种基于倾侧角参数化的离线弹道优化与在线预测校正相结合的再入制导方法。基于平衡滑翔条件对过程约束进行分析,并证明了倾侧角剖面对射程的单调性。离线部分通过控制量参数化(CVP)方法构建控制模型,并使用序列二次规划(SQP)方法对弹道进行优化,从而大幅度提高弹道性能。在线部分利用Gauss-Newton法实时对弹道进行迭代求解,得出满足终端约束的倾侧角剖面,引导飞行器平稳、精确地飞向末端能量段并满足射程约束,Gauss-Newton法求解弹道具有收敛速度快、精度高的特点。针对高升阻比飞行器导致平衡滑翔条件难以成立以及飞行过程中的强干扰使约束超出的问题,提出了一种约束限制方法,对再入时的过程约束进行了有效的保障。仿真结果表明,本文方法对投放偏差、飞行器参数与大气模型等不确定因素具有良好的鲁棒性,对弹道性能的保障具有工程应用价值。
Aiming at the problems such as ballistic performance and constraint can not be guaranteed during reentry, a traditional recursion method based on the combination of off-line trajectory optimization and on-line prediction correction is proposed. The process constraints are analyzed based on the equilibrium gliding conditions and the monotonicity of the roll angle profile to the range is demonstrated. The offline part constructs the control model through CVP and optimizes the trajectory by using the Sequential Quadratic Programming (SQP) method, which greatly improves the trajectory performance. In the online part, Gauss-Newton method is used to solve the trajectory iteratively in real time, and the tilted angle profile which satisfies the terminal constraints is obtained. The guidance aircraft is guided to the end energy segment smoothly and accurately and satisfies the range constraint. Gauss-Newton method solves the problem that the trajectory converges fast , High precision features. Aiming at the problem that the balance gliding condition is hard to be established and the strong interference in flight process causes the constraint to be exceeded, a restriction method is proposed to effectively protect the process constraints during reentry. The simulation results show that the proposed method has good robustness to uncertainties such as deviations of flight parameters, aircraft parameters and atmospheric model, and has value in engineering application for the guarantee of ballistic performance.