The Research Of Missile Guidance Optimum Control Method

Along with the science and technology development, in the air fight the goalmobility strengthens day by day, if the missile use some classical guidance laws tointercept greatly mobile goal, obviously cannot satisfy the request. The futurerencountre urgent need a guidance law which is able to adapt the more complexoperational environment, therefore, it has already been an important work which willbecome currently must carry on urgently to develop and apply the new guidance law.In this paper, tracing method, parallel approach method, three-point method,proportional navigation law and so on of classic missile guidance laws are analyzed askinematics. With increasing of the goal’s mobility speed, the classic guidance laws cannot meet the demand of guide parameters. The paper makes some research of an extendoptimal terminal guidance law from modern guidance laws on the basis of existingtheoretical results. I analyzed its related theories and simulated parameter. Comparedwith the simulation result, we may see when considering dynamics lag of extensionoptimal terminal guidance law, its terminal acceleration command is zero, and no matterhow short the guidance time is, the miss distance of guidance system is almost zero.As a modern guidance law, extend optimal terminal guidance law is closely relatedwith target maneuvering speed, direction and other command informations. The actualsystem is impossible without guidance dynamics lag, so this guidance law have goodperformance for acceleration command, miss distance and so on when compares theother guidance laws. It is a practical, high-precision guidance law.