Study on the Optimal Terminal Guidance Law with Interception and Impact Angle

An optimal terminal guidance law with both interception and impact angle constraint is derived according to simplified missile movement equation and Lagrange method. The effect of guidance systems dynamics on the miss distance and impact angle error is studied. Simulations demonstrate that it is the time constant of the system but not the system order which is the main factor inducing the miss. Increasing engagement time will decrease the miss distance and impact angle error, and the appropriate multiple is concluded.