Project Trajectory Optimization And Terminal Guidance Law Design Of Cruise Missile

Cruise missiles, because of their widely using, high attacking precision, powerful damage, high defense penetration, high cost performance, have rapidly become one of the most important guided weapons in the modern arsenal. It has become the hot spot of the world to improve the missiles' range, ballistic characteristics, better attack effect. On the background of small cruise missile, this paper conducted a study on the design and optimization of the programmed trajectory, and analysis of ballistic characteristics of terminal guidance section. The main work is as follows:First, the dynamic model of the missile on 2-3-1 transformation frame was constructed.The corresponding coordinates systems were designed, and transformation relations were given. Based on above, the dynamic model of missile was deduced, which includes the translational dynamics equations, the rotational dynamics, equations, the translational kinematical equations and the rotational kinematical equations. Quaternion was introduced to solve the problem of vertical attack targets. The relationship between the quaternion and Euler angle was studied.Secondly, the optimization of programmed trajectory was studied. The type of theoretical trajectory was introduced and the choice of the trajectory was made. A two-dimensional dynamic model was used in trajectory optimization to increase the computing speed. The practical flight attack angle was considered to the initial non control section. The direct shooting method trajectory optimization based on complex optimization algorithm was established. Instead of the maximum range of the missile, the maximum range of missile with thrust is regarded as the objective function. The control angle of attack was optimized with the constraints of overload, angle of attack, and velocity. The optimization results show that the control angle of attack of missile satisfy the overall requirements, and achieves the maximum range.Thirdly, the optimal guidance law with multi-constraints was studied. The relative motion model between missile and target was established in the three-dimensional space. The constraints were changed into the terminal constrains in the optimal control problems. The optimal guidance law with one-order dynamic was obtained by solving the two quadratic optimal. The guidance law for lag free system was obtained by simplifying the guidance obtained above. The initial condition without no jumping was analyzed.Finally, the simulation with six degree of freedom of the complete trajectory was conducted. Combined with the above theory, the simulation program to six degree of freedom simulation of missile trajectory was compiled. The results were analyzed combined with the related curve.This paper studied the trajectory optimization and the terminal guidance law for the small cruise missile. It provides a solution and a basis for further study of related issues.