摘要：AbstractGuidance system, which is an integral part of missile flight control system, plays a key role in achieving a desired performance subjected to various criteria. This paper focuses on the design of terminal impact angle constrained guidance laws, against maneuvering targets, for three-dimensional engagements. Impact angles are defined by the elevation and azimuth angles of line-of-sight with respect to the inertial frame of reference. The derivation of guidance strategies are performed with the nonlinear coupled engagement kinematics using dynamic inversion and sliding mode control techniques. The proposed guidance laws are applicable even for large heading angle errors. The comparative study of performance of both guidance laws is done using numerical simulations for various engagement scenarios.
