The Trajectory Design And Flight Control Analysis Of The Gun-launched Cruise Missiles

Modern war is the war of technology, along with the each passing day of a new era of military technology. To achieve precision strike has become a top priority of new conventional weapons. Rapid detection and destroy enemy targets must be required of modern warfare, then there appeared missile patrol, It not only can undertake an investigation mission but also to achieve targets. This article is to develop a platform for the use of artillery fired missile patrol, aerodynamic characteristics analysis and research patrol missiles, ballistic flight, flight control and other aspects.Firstly, structure the model artillery of missile patrol, To mesh its structural model, and simulate missile patrol through aerodynamic flow field calculation software dedicated aerodynamic characteristics under different conditions, To obtain the loitering Missile lift coefficient, drag coefficient, lift-drag ratio, the pressure coefficient heart, quiet moment coefficient, static stability and other variation with Mach number, angle of attack and angle of the rudder, complete the patrol missile aerodynamic simulation, lay the foundation for the subsequent trajectory design.Secondly, design the flight trajectory of missile patrol, In the guided missile patrol section is designed based on the maximum lift-drag ratio method, use GPS/INS navigation make patrol missile based on the maximum lift-drag ratio according to the gliding flight trajectory program, When gliding to a predetermined height, rear solid missile patrol engine start work to promote missile patrol set high straight flight, into the straight level flight segment; when flying over the area to enemy targets, reconnaissance patrol flying into the segment began reconnaissance combat missions.Thirdly, in order to make the patrol missile can fly in accordance with the desired trajectory program, design the patrol missile control system:respectively Set up loitering Missile rudder loop damping circuit, the pitch angle stabilization loop, height loop and tilt stabilization stability loop, Each stabilization loop designed with PID controller, and the PID controller tuning parameters were so tuning parameters in the frequency domain and time domain has good control performance, the design of the control system has good dynamic performance and stability.Finally, based on the establishment of a control loop to make a ballistic missile patrol digital simulation, Simulation results show that the control trajectory to reach the preset requirements, control system designed to meet the general requirements of flight control.Trajectory design method proposed in this paper, the numerical simulation of the flight control program and the results for the development of missile patrol provides theoretical and technical support.