Design Of Three-dimensional Cooperative Guidance Law With Impact Angle Constraint For Anti-ship Missile

In recent years, it has been taking place several disputes in the East China Sea andSouth China Sea that neighboring countries seriously provoke China’s territorialsovereignty. Therefore, it is an inevitable trend to develop the anti-ship missiletechnology to further strengthen our military maritime power. If we want to maximizethe counter large sea fleet in the naval battles in the future, attacking to a particularstandpoint is one of the effective means of defense system. In addition, salvo attack canalso make self-ship defense system (SSDS) unable to intercept all the incoming missiles,with the same that it will achieve maximum damage efficiency. Thus, the thesis choosesanti-ship missile as the research object, and it takes terminal miss distance, attack angleand attack time three aspects as the necessary pointers to make the terminal guidancelaw design. The main contents are as follows:First of all, this paper has established a mathematical model of the relativemovement between missile and target, and has made it clear that the meanings of attackwith angle constraint and miss distance are presented. Besides, it has introduced thebasic principles of designing a guidance law. What’s more, the basic knowledge ofsliding mode variable structure control theory has been introduced to prepare for furtherresearch.Secondly, the three dimensional guidance model of inertial coordinate system hasbeen derived. Since the classical proportional navigation guidance law is relativelymature and widely used, the advantages and disadvantages of traditional proportionalguidance law have been discussed. At the same time, according to the requirement ofthe attack angle, the biased proportional navigation guidance has been designed andsimulated. Then, considering terminal sliding mode control method of the goodrobustness, it has been applied in the two-dimensional guidance model, and itssimulation has proved the validity. Then, the approach further has been extended to the3d model design. The simulation results have proved that the designed guidance law canachieve the precision of missile with angle constraints.Finally, according to both attack time and attack angle constraints, this paper hasproposed a control strategy in stages: in the first stage, the guidance law is designed onthe method of dynamic inversion to implement accurate control of the attack time andrough angle control in the vertical plane; in the second stage, the law designed on thebasis of sliding mode control that has proposed in Chapter Three is to further realize theattack angle of accurate control. Through the experimental simulation, it can be seen that the proposed guidance strategy and the design of guidance law can satisfy therequirements of both the time and angle.