Study On Compound Guidanceand Control Problems For Long-range Air To Air Missile

The performance of air threatening target is improved with the development of science and technology. The performance of air-to-air missile has become an important factor to decide the outcome of war as a weapon to take the air domination. Especially the long-range air-to-air missile requires the precision strike ability of multitasking, all-weather, all round attack and beyond visual range. Which the guidance and control system as the core component decide the guidance precision and maneuver ability. This paper will study on midcourse guidance law and terminal guidance law of long-range air-to-air missile. Furthermore, a research is carried out that about multiple-input multiple-output(MIMO) system decoupling control law.Firstly, establish the six degrees of freedom model of long-range air-to-air missile. According to the structure size of missile and general parameters, calculate the aerodynamic forces and torque in the process of missile in flight. Finally, the dynamic characteristics of missile are analyzed in the simulation. The results verify the reasonability of aerodynamic parameters.Secondly, the midcourse guidance law of long-range air-to-air missile is designed. The stand or fall of the guidance law design directly affects the missile in terminal guidance phase of mobility. The hand-over point is predicted by estimating time-to-go of missile and the formula of constraint angle is given. According the condition of missile at hand-over point to design the midcourse guidance law by optimization theory: a optimal modified proportional guidance law and a guidance law based on pseudo-spectral method. The simulation result shows that the designed guidance law satisfies the requirement of the hand-over point in speed and angle, the acceleration and trajectory changed smoothly.Then, this paper design a terminal guidance law. Introduced the motion camouflage based on bionic. The infinitesimal characterization of motion camouflage and cost function that satisfies the characterization are proposed. The dynamics equations in the Frenet frame are developed so as to describe the motion of missile and target. A feedback guidance command based on curvature and torsion according to cost function is proposed. In order to apply to the guidance system, developing a motion camouflage guidance law that combining with the pure proportional navigation. Simulation result shows that the proposed guidance law works well and effectively in the proposed engagement, and it performs better than PN guidance law.According to the attitude control system is a nonlinear system with multivariate, strong coupling and uncertainty. First, using a disturbance-accommodating observer to estimate the uncertainty and disturbance of dynamic inversion control law, thus the new control law has adaptability. Then, designing a output feedback controller based on linear parameter varying. Using the weight coefficient for vertex controller to convex interpolation and getting the full controller. The result demonstrates the control law works well and has better tracking accuracy and good dynamic characteristic.