Closed Loop Guidance with Ballistic Inclination Constraint and the Curve Planning Based Energy Management

In this paper, an improved closed loop guidance method for solid ballistic missile is presented. Firstly, the dynamics model of the rocket is established in the launch inertial coordinate system. Then the conversion relation between the launch coordinate system and the launch inertial coordinate system is illustrated. Secondly, based on the traditional closed loop guidance scheme, an improved closed loop guidance method with the ballistic inclination constraint of the reentry point is presented, which by introducing the reentry point velocity information. Then, to achieve the management of the remaining energy of the solid rocket, a curve planning based energy management scheme is adopted. Combined with the proposed closed loop guidance scheme, the guidance commands which satisfying the complex constraint can be generated in real time. Finally, multiple scenarios under nominal and disturbance conditions are simulated to verify the proposed closed loop guidance with energy management scheme. Results indicate that the proposed method has good attack accuracy and task adaptability.