基于预测校正法的高超声速飞行器再入制导

Reentry guidance for hypersonic vehicle based on predictor-corrector method

针对新一代高超声速飞行器在制导方法的精度及抗干扰能力上的要求,提出了一种基于能量的预测校正制导方法.建立了以能量为自变量的三自由度运动学方程,给出再入过程中的主要约束条件,在此基础上分别设计纵向制导律和侧向制导律.在纵向制导律中,不断预测剩余航程相对理论目标点之间的偏差,并以此偏差作为模糊校正器的输入,输出合适的侧倾角更新值,从而达到校正效果,保证纵向制导精度;在侧向制导律中,设计了一种基于横程偏差的侧倾角反转逻辑,当横程偏差超过所设定的边界条件时,侧倾角便进行一次反转,从而保证侧向制导精度.分别在标准初始条件下和存在偏差条件下进行了数值仿真,仿真结果验证了所设计的制导律的有效性.

An energy-based predictor-corrector guidance algorithm was proposed to handle the need for high precision and robustness of reentry guidance for hypersonic vehicle. A detailed derivation of three degrees of freedom reentry kinematic equations based on energy was conducted, and the path constraints and terminal constraints were also included. Based on the derivation, the longitudinal and lateral guidance law was de signed. For the longitudinal part, longitudinal range errors were repeatedly calculated, and a fuzzy corrector was designed to eliminate the errors which guarantee the accuracy of the longitudinal guidance; for the lateral guidance law, a cross-range error based lateral reversal logic was designed, whenever the cross-range exceeds the sited boundaries, a bank reversal was conducted. Simulation results on both standard and deviation condi- tions verified the effectiveness of the proposed guidance law.