Multiple Missiles Cooperative Guidance Based on Proportional Navigation Guidance

Abstract

In this paper, two open-loop cooperative guidance laws are proposed. First, a new time cooperative proportional navigation guidance (TCPNG) law is proposed based on the conventional proportional navigation guidance (PNG) law. In order to meet the impact time cooperative requirement, the navigation gain in the TCPNG law is designed as the function of the time error, which is the difference between the designated impact time and the time-to-go estimation of the missile. Second, an improved impact time control guidance (IITCG) law is proposed based on the existing impact time control guidance (ITCG) law. When the initial leading angle is large, the ITCG law may fail and there will be a singularity in the denominator in the later period of the guidance, which will cause the control instruction to oscillate. Therefore, the IITCG law is proposed to cope with this problem. Simulation results show that the TCPNG law can be applied to different initial leading angles and the salvo attack scenario. And the IITCG law can avoid the singularity in the later period of the guidance law, which solves the problem of the control instruction oscillation.