Design And Analysis For A Certain Air-to-Ground Missile

Aiming at actual demands for a certain air-to-ground missile fitted to helicopter, the conceptual design is investigated in this paper. Corresponding results are obtained through the development of optimization design for thrust, design for project trajectory, ballistic simulation of Six-DOF (six-degree-of-freedom) , analysis of dynamic characteristics and maneuvering performance, which will provide theoretical fundamentals and practical results for its further design.Firstly, the research begins with the development of optimization design for thrust. Optimization thrust parameter model for single-chamber single-stage motor and single-chamber double-stage motor are built respectively to lighten missiles. MATLAB function library of genetic algorithm is employed to program the software of optimization design for thrust. Experimental results show that the genetic algorithm is efficient in global convergence and has a faster evolution. The approach to single-chamber double-stage motor is determined as the final scheme.Secondly, mass trajectory mathematical model and acquisition field of view model are established. Mass trajectory simulation and acquisition field of view calculation program, which can accomplish trajectory simulation and draw the acquisition field of view is built. The influence of trajectory parameter on acquisition field of view is analyzed deeply, besides the results are applied to project trajectory design to complete the detail design. The simulation results verify that the project trajectory can make seeker acquire the target and attack tank top armor reliably.In the third part, missiles'dynamics characteristic is calculated. Six-DOF missile flight mathematical model is presented. Trajectory simulation calculating is implemented by software, which is programmed. Longitudinal and lateral dynamics characteristic mathematical model is built, and the relative calculating module is added to compute the coefficient and transfer function ,the step response, as well as frequency characteristic, so the analysis results of dynamics characteristic is obtained.Finally, missiles'mobility is analyzed. Nonlinear of lift, actuator control force and the location of pressure center which is verified with angle of attack .The method of moment equilibrium is adopted. The modeling of useable normal overload calculation and necessary overload are established, which is added based on Six-DOF trajectory simulation software that fulfill relative calculation. The results testify missiles'mobility meet needs.