Guidance law based on fast convergence of impact time

For the problem of of missile salvo, the impact-time-control-guidance (ITCG) method controls the remaining flight time by designing the guidance law, so as to achieve the target at the specified collision time. In this paper, on the basis of the ITCG method, the feedback control method is used to offset the control command of the original guidance law to realize the control of the collision time. Firstly, the heading angle of the missile is adjusted by Bang-bang control to achieve the purpose of quickly adjusting the residual flying time. Secondly, when the residual flying time error is small, the remaining flight time error is further eliminated by PID control. In this paper, the results indicates that the ITCG method can effectively contain the actual flight time of the missile and converge to the expected missile flight time more quickly than the PNG method, so as to achieve the purpose of accurately striking the target.