FOV constrained guidance law for nonstationary nonmaneuvering target interception with any impact angle

This paper presents the nonstationary nonmaneuvering target interception with all possible desired impact angles in a two-dimensional (2D) aerial engagement scenario, where the target can move in any direction. The paper also considers the field-of-view (FOV) constraint for designing the guidance law so that the target is always visible while following the missile trajectory in the entire engagement time, which makes it feasible for real world applications. The guidance law is based on the pure proportional navigation (PPN) to achieve any impact angle of the entire angular spectrum. The proposed guidance law is then simulated for intercepting a nonstationary nonmaneuvering target using a kinematic model of a missile to demonstrate the efficacy of the presented scheme. A comparison with the related work existing in the literature has also been added to establish the superiority of the present work.

Sliding mode–based simultaneous control of impact angle and impact time

In this article, a sliding mode control–based nonlinear guidance scheme for controlling both impact angle and impact time simultaneously is proposed. The problem of impact angle control is first transformed to that of controlling line-of-sight angle and its rate, while the requirement of impact time is achieved by tracking the desired time-to-go. The chosen time-to-go estimate accounts for the curvature required to meet the impact angle requirements toward the target interception. In order to satisfy both of these terminal constraints, the sliding surface is defined as a combination of impact time error and the variable pertaining to the errors in line-of-sight angle and its rate, with appropriate gains assigned to them. The interceptor first performs necessary maneuvers to meet the impact time requirements and then steers its course to achieve the target interception at a desired impact angle. The guidance law is initially derived using nonlinear engagement kinematics against stationary targets and then extended to cater to constant velocity targets using the concept of predicted interception point. Numerical simulations are performed to validate the efficacy of the proposed guidance scheme for various initial engagement geometries. The performance of the proposed guidance scheme is also compared with those of the existing guidance laws and shown to be superior.

Optimal interception strategy of air defence missile system considering multiple targets and phases

Due to the rapid development and wide application of air attack weapons, air defence missiles against them are increasingly important and have become the main air defence weapons in modern war. However, interception strategy of air defence missile system is ignored in previous studies. Thus, using the combinatorial optimization, this paper proposes a methodology to optimize the strategy of ADMS in a missile-target interception process in order to minimize the expected costs for defender. According to the practice, the considered process has multiple targets and multiple phases, and the expected costs are composed of the loss caused by targets and the cost for intercept missiles. Two numerical examples are presented to illustrate the proposed methodology. The results of the examples show that interception strategies have a great impact on the expected costs of ADMS during a missile-target interception process.