Integrated Guidance And Control For BTT Missile With Terminal Impact Angle Constraint

In recent years, BTT missile receives extensive attentions, considering its outstanding aerodynamic stability and high lift-to-drag ratio. The techniques pertinent to BTT missile are investigated by many researchers. Among these techniques, guidance and control is one of the most important. Integrated guidance and control design is proposed by researchers to enhance maneuver capability and improve guidance precision. In this paper, design method for guidance law with impact angle constraint and control loop dynamics is researched. Then, an integrated guidance and control method with impact angle constraint for BTT missile are presented. The contents are listed as follows:First, models of target and missile, as well as missile-target engagement geometry model are established in a planet-fixed coordinate frame for guidance law design. Then, the motion of missile is formulated mathematically considering the curvature and self-rotation of Earth to support the guidance and control demonstration.Second, design method for BTT missile guidance law with impact angle constraint and control loop dynamics is proposed. Based on the missile-target engagement geometry model defined in line-of-sight coordinate frame and BTT concept, a guidance law design model is formulated. Using sliding mode control theory, guidance law with impact angle constraint and control loop dynamic is designed. The above guidance law is demonstrated via 3DOF simulation.Third, an integrated guidance and control method for BTT missile with impact angle constraint using multiple sliding surface control theory is presented. Based on the aforementioned missile-target engagement geometry model and the motion model of BTT missile, an integrated guidance and control model is presented. According to multiple sliding surfaces control theory, integrated guidance and control laws are designed. 6DOF simulation is conducted under nominal conditions to validated the integrated guidance and control method.Finally, numerical simulation are conducted to demonstrate the guidance law with impact angle constraint and control loop dynamic, as well as integrated guidance and control law under various conditions. Pertinent analysis is given at the end of this paper. Simulation result suggests that both the guidance law and integrated guidance and control law can satisfy the requirement of miss distance and angle constraint, the integrated guidance and control law shows better guidance and control performances.