Guidance Law for Maneuvering Targets with Impact Time Constraint and Field-of-View Range Analysis

The issue of intercepting maneuvering targets at a specific time with multiple constraints is of great practical significance. To solve this problem, an impact time control guidance (ITCG) laws is proposed to intercept maneuvering targets with desired constraints. First, by introducing nonlinear virtual relative model, the newly defined virtual field-of-view (FOV) angle is represented as a polynomial function in range domain. Then, the relative trajectory length is analytically derived. By leveraging optimal error dynamics technique, the proposed guidance law in nonlinear virtual relative model can be deduced, which results in the combination of proportional navigation guidance (PNG) and an augmented biased feedback term. And the overall guidance command in inertial frame has the characteristic of terminal convergence. Furthermore, to fulfill virtual FOV limits, an auxiliary function is added into the biased term. Through the quantitative relation of realistic and virtual FOVs, missile’s FOV range analysis and constraint are realized. The characteristics of proposed guidance law is theoretically analyzed and extensive simulations are conducted to validate the guidance performance. Comparison studies indicate the advantages of proposed guidance law compared to preceding relevant work.