The Control System Design Of BTT Guided Ammunition

Along with the High-Tech application in air defense and the growing complexity of operational requirement, the development of SOPGM(Standoff Precision-Guided Munition) is greatly promoted. Long-range strike and directional attack become the outstanding characteristic in the modern battlefield. Because of high aerodynamic efficiency, wide maneuvering range, long range,etc. the BTT guided munition have attached much attention, Consequently, in this paper the design of BTT control system has been relatedly researched based on the background of a BTT gliding missile.Firstly, the BTT control system is divided into two parts: the guidance law and the autopilot. According to the force and moment analysis of the BTT gliding missile, The kinematics model and dynamical model were established. Then, the dynamical model was simplified based on some assumption,and the coupling between different channels was analyzed emphatically. Simultaneously, the generated method of control command was presented.Secondly, in view of the design of guidance law with terminal constraint, the relative motion model of missile and target was established in 2D plane, and the mathematical description of angle constraint was presented. Then, two kinds of guidance law with terminal constraint were deduced. The robust guidance law: its form is simple, and the guidance information can be obtained easily. The guidance law can guarantee both the attack precision and terminal impact angle, as well as has a good robustness to maneuvering target. The finite time convergent guidance law: the convergence in finite time and Lyapunov stability have been proved with application of finite time stability theory. The proposed guidance law ensures to shape the missile trajectory in advance,and make the overload command converge as soon as possible.Thirdly, in terms of the BTT autoploit, three methods of obtaining coordination turn were discussed in detail including their advantage and disadvantage. Three channels of BTT atuoploit were designed independently based on SISO design method,and a coordinate branch was introduced into the yaw channel.Then during simulation the coupling were introduced artificially, the control performance of with and without coordinate branch were compared by numerical simulation.Finally, for the two-channel coupling in the gliding missile guidance, a BTT 3D guidance law with compensation of channels coupling was derived based on chapter iii. In order to confirm the performance of guidance law and BTT autoploit, overall six degrees-of-freedom(6DOF) mathematical simulation was carried on. Simulation results indicated that the guidance law can not only guarantee the integrity of guidance information, but also can satisfy the requirement of precision and terminal constraints.