Research On Guidance Law Design With Terminal Impact Angle Constraints In Aerial Penetrating Bomb

To ensure an effective attack to various underground military targets, it is of urgent military demand and realistic significance to develop aerial penetrating bomb, of which guidance scheme design is a crucial part. Based on aerial penetrating bomb trajectory design, combining scheme guidance and navigation guidance, this thesis researches on a compound guidance scheme adaptable to aerial penetrating bomb.The thesis is mainly concerned with the follows:Firstly,the design of aerial penetrating bomb flight trajectory. From a comprehensive consideration of the relationship between aerial penetrating bomb end-games constraint conditions and its trajectory, this thesis designs a trajectory consisting of turn phase, terminal guidance phase, and attitude control phase, and their respective guidance methods,i.e.,fixed overload scheme guidance, optimal guidance law and attitude scheme guidance.Secondly,the design of an optimal guidance law. To solve problems in terminal guidance phase,on the basis of optimal control theory, this thesis introduces missile overload information to optimal guidance law and designs an optimal guidance law with comprehensive consideration of restraints from terminal miss-distance, impact angular(orientation angular) , attack angle(yaw angel) to terminal velocity.Thirdly, the design of terminal active attitude control scheme. For attitude control phase, active attitude aiming guidance scheme is designed to realize small attack angel in end-games.In the end,through simulation program, a simulation test is done to check the feasibility of this compound guidance scheme.