Integrated Guidance and Control for Collision Course Stabilization of Dual-Controlled Interceptors

Resumen

We propose an integrated guidance and control law for dual-controlled interceptor dynamics controlled via tail-fin deflection and reaction jets. Because dual-controlled interceptors have two input channels in each axis, we define two error variables as the first step to derive an integrated controller. One variable is configured as a line-of-sight rate for nullifying heading errors to a target, and the other is established to allocate the control strategy for the fast response of an integrated loop. Consequently, interceptor dynamics are controlled to produce a required maneuver by the net force of the two control inputs when a large heading error occurs, thereby accelerating the control response compared with conventional control methods. After the heading error is sufficiently reduced, it is switched to a general control strategy that performs a maneuver through the lift generated by the fuselage angle of attack to prevent excessive use of the control inputs. Based on such a control strategy, the proposed integrated law is expected to exhibit enhanced homing performance compared with existing control methods that perform guidance and control in separate loops. Moreover, numerical simulations considering engagement scenarios with highly maneuverable targets are conducted to evaluate the performance of the proposed integrated guidance and control law.