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This paper considers the guidance and control problem of a flight vehicle with side-window detection. In order to guarantee the target remaining in the seeker's sight of view, the line of sight and the attitude of the flight vehicle should be under some constraints caused by the side-window, which leads to coupling between the guidance and the attitude dynamics model. To deal with the side-window constraints and the coupling, a novel Integrated Guidance and Control (IGC) design approach is proposed. Firstly, the relative motion equations are derived in the body-Line of Sight (LOS) coordinate system. And the guidance and control problem of the flight vehicle is formulated into an IGC problem with state constraints. Then, based on the singular perturbation method, the IGC problem is decomposed into the control design of the quasi-steady-state subsystem and the boundary-layer subsystem which can be designed separately. Finally, the receding horizon control is applied to the control design for the two subsystems. Simulation results show the effectiveness of the proposed approach. Keywords: Integrated guidance and control, Receding horizon control, Side-window detection, Singular perturbation, Terminal guidance

In the interception engagement, if the target movement information is not accurate enough for the mid-course guidance of intercepting missiles, the interception mission may fail as a result of large handover errors. This paper proposes a novel cooperative mid-course guidance scheme for multiple missiles to intercept a target under the condition of large detection errors. Under this scheme, the launch and interception moments are staggered for different missiles. The earlier launched missiles can obtain a relatively accurate detection to the target during their terminal guidance, based on which the latter missiles are permitted to eliminate the handover error in the mid-course guidance. A significant merit of this scheme is that the available resources are fully exploited and less missiles are needed to achieve the interception mission. To this end, first, the design of cooperative handover parameters is formulated as an optimization problem. Then, an algorithm based on Monte Carlo sampling and stochastic approximation is proposed to solve this optimization problem, and the convergence of the algorithm is proved as well. Finally, simulation experiments are carried out to validate the effectiveness of the proposed cooperative scheme and algorithm.

This article analyzes the problem about the missile overload requirement in a homing terminal guidance under various engagement scenarios. An augmented proportional navigation guidance (APNG) model is introduced on the basis of linear kinematics. To analyze the peak-to-peak performance of the terminal guidance system, a new finite time L1 performance measure for a linear time-varying (LTV) continuous system is proposed. Then, according to the idea of the adjoint system, a novel method for computing the L1 norm of a linear continuous system is first derived. Within the finite time L1 framework, the quantitative relation between the guidance loop dynamics and the maximum missile-target maneuver ratio is offered. This relation is expressed in the form of graphs and formulas that can be used to synthesize some of the major subsystem specifications for the missile guidance system. The illustrative examples show that a significant performance improvement is achieved with the proposed guidance loop dynamics.