论文部分内容阅读
针对导弹速度非定常情况下的协同制导问题,提出了两种分别满足攻击时间约束、攻击时间与攻击角度约束的导引律。首先通过求解导弹在比例导引(PN)及带攻击角度约束的偏置比例导引(BPNIAC)下的系统微分方程,得到导弹飞行的实际剩余航程,并根据指定的攻击时间与导弹的实际速度曲线构造标称剩余航程,将攻击时间控制问题转化为导弹实际剩余航程对标称剩余航程的跟踪问题。然后,在PN及BPNIAC的基础上附加反馈控制项使导弹实际的剩余航程跟踪标称值,从而实现导弹速度时变情况下攻击时间的控制要求。仿真结果验证了该方法的有效性,实际应用中可根据预测速度曲线及在线更新策略对标称剩余航程进行估算。
Aimed at the problem of coordinated guidance at unscheduled missile velocities, two guidance laws that satisfy the constraints of attack time, attack time and attack angle are proposed respectively. First of all, the actual remaining range of the missile flight is obtained by solving the system differential equation of the guided missile in proportional guidance (PN) and offset proportional navigation (BPNIAC) with attack angle constraints. Based on the specified attack time and the actual missile speed The curve constructs the nominal remaining range and transforms the attack time control problem into the tracking of the nominal remaining range by the actual remaining range of the missile. Then, on the basis of PN and BPNIAC, feedback control items are added to make the actual remaining range of the missile follow the nominal value, so as to realize the control requirement of the attack time under the condition that the missile velocity varies. The simulation results verify the effectiveness of the proposed method. In practical applications, the nominal residual range can be estimated according to the predicted speed curve and online updating strategy.