Investigation On Warheads’ Separation Dynamics And Control Methods

Sub-guided missile with multiple warheads as a strategic weapon has strong deterrent effects and actually operational significances. The main cabin may collide with the multiple warheads that separate from the sub-guided missile due to the initial pose of the warhead or external environment. The collision would make the separation fail. So that the validity and robust of the separate control method are very important. At the same time, the main cabin should be guidance and control before beat the next target. To solve these problems, the research work in this thesis mainly about the algorithm of spacecraft separation distance calculation, the control method of the separation and guidance method after separation. This thesis mainly completed following aspects of work:1) Many different algorithms for calculating the distance between two special bodies had been researched and contrasted. A faster algorithm for calculating the shortest distance between two spatial bodies based on existing algorithms was presented. A simulation analysis of missile model’s separation process was built.2) The model of the separation was built by using MATLAB/Simulink. And then the model was validated by using ADAMS.3) This thesis researched the timing control for the separation of sub-guided missile or multi-satellite. And then a new closed-loop control method based on the yaw angle’s error threshold was advanced. The model of separation was established and simulated, and compared the two methods. Advantages and disadvantages of the two separate control methods are compared form safety and robust.4) A new guidance and control method of the separated missile was researched for counteracting the effects of the separation and beating a new goal. In theory, this new method could accomplish the assignment of beating the immobile goal or slowly-moving goal. The dynamics and mathematical model of the main cabin was built. The process of guidance was simulated. The method in this thesis and the exciting method were compared and researched. The stability application conditions was been analyzed.It can be proved that the control method of separation and the guidance method in this thesis can fulfill the assignment of separation by simulation. These methods have certain referenced and applied value for precision strike missions in the future.