A Precise Guidance Method for Launch Vehicle Sub-stage Return Stage Based on Trajectory Shaping

Abstract

The invention provides a method for accurately guiding a sublevel return stage of a carrier rocket based on ballistic forming, and belongs to the technical field of guidance and control. The method ischaracterized in that a virtual inertial sight angular velocity model which uses a grid rudder as an actuator and is composed of the rocket-loaded navigation output sublevel state and before-shootingbinding target information is designed, the optimal guidance expression of ballistic forming under a ballistic system is derived, and then real-time flight overload commands of the sublevel return stage are obtained. The method can effectively improve the sublevel dropping area and sublevel reusing return guidance precision, and effectively ensures high-precision landing of a sublevel at a target landing point with the desired dropping angle by fully utilizing the high control efficiency of the grid rudder in the large dynamic pressure area.

Description

technical field [0001] The invention relates to a trajectory forming-based precise guidance method for the sub-stage return section of a launch vehicle, which belongs to the technical field of guidance and control. Background technique [0002] At present, after the completion of the sub-stage work of our country's rockets, they fall freely without control. The flight paths often pass through densely populated areas, the landing speed is relatively high, and the landing points are scattered in a wide range. , a potential safety hazard. The huge impact force during the fall of the separated body wreckage made the rocket body likely to explode, causing serious damage to surrounding objects, causing great physical and psychological impact on personnel near the landing point, and threatening the safety of ground personnel; For the remaining residual propellant, since conventional toxic propellants are usually used at present, the leakage of propellant after falling to the groun...

AI Technical Summary

Problems solved by technology

[0004] In order to solve the problem that the existing traditional guidance method is difficult to achieve a large terminal ballistic inclination angle, and at the same time face the precise control of the rocket sub-stage landing area and the need for repeated use and recovery, the present invention proposes a sub-stage return segment guidance method based on ballistic shaping

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