Integrated guidance and control of dual missiles considering trade-off between input usage and response speed

摘要

An integrated guidance and control law for agile dual missiles is proposed using sliding mode control. For tight integration, engagement kinematics and missile dynamics are combined without linearization. Then, two sliding surfaces are defined because dual missiles have two degrees of freedom for control. One surface is defined for making line of sight (LOS) angle rate converge, and the other for fast response of the missile. Response speed of the missile is adjusted flexibly with the control. If heading error exists, a fast controller that consumes large input is applied. On the contrary, a relatively slow controller consuming smaller input is applied when heading error is zero. For this strategy, transition control technique is applied. As a result, an integrated guidance and control law with fast response speed is derived. Performance of the proposed integrated law is evaluated with highly maneuverable target using nonlinear simulations.