Cooperative guidance law with multiple constraints for intercepting maneuvering target

In order to make multiple air-to-air missiles hit different key parts of maneuvering targets simultaneously at different impact angles, a three-dimensional cooperative guidance law with constraints of impact angle and field of view is proposed. First, in the yaw and pitch planes of the missile, the acceleration commands with impact angle constraint is derived by using the Riccati equation with the optimal control of the quadratic type to ensure that missiles hit the target at desired impact direction and angle. Next, the field of view is corrected using a controlled switch to reverse the original acceleration command to ensure that the target is always in the missiles' field of view. Then, by applying the finite time consistency theory, a cooperative guidance law with time-varying navigation coefficient is designed on the basis of the impact angle constraint and the field of view constraint, so that each missile hits the maneuvering target at the same time. Finally, the simulation results show the effectiveness and correctness of the designed multi-constraint cooperative guidance law. Compared with proportional guidance, the proposed method can achieve coordinated strikes on different directions of the target, the miss distance, impact angle error and time error are controlled within 0.41 m, 0.23 ° and 0.1 s respectively, and the jitter of maneuvering commands is effectively avoided. © 2023 Editorial Department of Journal of Chinese Inertial Technology. All rights reserved.