Integrated Guidance-Control Systems for Fixed-Aim Warhead Missiles

摘要

Integrated guidance-control systems have the potential to improve missile system performance by taking advantage of the synergism existing between subsystems. These systems allow the designer to impose unusual performance requirements on the missile. Such requirements may arise out of the new sensor and warhead technologies that may require complex maneuvers at target interception. Integrated guidance-control techniques of missiles incorporating fixed-aim warheads are discussed in this paper. The fixed-aim warhead technology seeks to reduce the weapon system weight by using a highly directional warhead, together with enhancements to the guidance-control systems. The fixed-aim warhead projects the blast fragments in a direction normal to the missile longitudinal axis. In order to be effective, this warhead requires the missile to achieve a specific roll orientation with respect to the target at interception. Moreover, it is desirable to achieve a near-zero relative lateral velocity vector orientation with respect to the target at interception to minimize the sensitivity of the system to fuze delay. These specifications require the missile to perform a combination of conventional lateral acceleration maneuvers and terminal attitude maneuvers during its operation. Recently developed nonlinear control system design software is used to synthesize three different integrated guidance-control strategies. These design approaches use a nonlinear, six-degrees-of-freedom air-to-air missile model. Simulation results for sample engagement scenarios are given.