Guidance law modeling based on the ideal line-of-sight with constraint of the terminal flight angle and acceleration

In the process of pursuing the target, we not only expect the least miss distance, but also a better attitude when the missiles impact the target. The better attitude can effect the power of missiles, and what's more, it can avoid the unnecessary disturbance. For instance, a missile always fails to lock the target owing to the too complicated background while attacking a low-attitude target. The strong surficial background and ground clutter will disturb the seeker's ability to intercept and capture the target. It's a serious problem faced by modern missile guidance system, so we must keep some constraints on the terminal direction line of sight to avert the disturbance, enhance the accuracy of control system. This dissertation focus on the optimal guidance law using a new modeling method to achieve the purpose of control the terminal direction of the line of sight. The complementary constrain for the guidance law as the bound on the acceleration show that the new method of modeling is a better way of modeling to solve the problem about final constrain of the final direction of the line of sight when it's compared with the conventional ones. It's more succinct and more suitable of engineering. In the end, we design a strategy for a situation about air-to-air missile attacking low-attitude target. The result of simulation shows the guidance law achieve the requirement commendably.