Precise vertical recovery control method for large-airspace high-dynamic rocket sublevel landing area

Abstract

The invention discloses a precise vertical recovery control method for a large-airspace high-dynamic rocket sublevel landing area. A guidance control system adopts a quick time-varying and multi-channel coupling attitude control method for design, an algorithm and a program operate on a dual-core embedded computer in a navigation and guidance control integrated system, control law calculation in alarge-airspace high-dynamic high-Mach flight state is carried out by using current Mach number and pose information, calculated by the dual-core embedded computer, of a rocket sub-stage, pitching, yawing and rolling channel control instructions of a rocket sub-stage grid rudder are solved in real time, and the sub-stage is guided to vertically land towards a target point area. The method is mainly used for solving the accurate control problem of the sub-stage of a carrier rocket under the conditions of violent flight state change, high Mach, large airspace and high dynamic flight, the systemis simple in structure, convenient to implement and high in universality, and the main flight task of the carrier rocket is not affected.

Description

technical field [0001] The invention belongs to the field of navigation and guidance control, and in particular relates to a precise vertical recovery control method for a large airspace high dynamic rocket sub-stage landing area. Background technique [0002] With the normalization of high-intensity and high-density launches of launch vehicles around the world, more and more mature launch technologies have prompted people to explore the direction of low launch costs. Recycling and reuse of launch vehicles is one of the effective ways to reduce launch costs; at the same time When a traditional carrier rocket is launched, it is usually necessary to determine the range of the rocket wreckage landing area, and select a sparsely populated area of ​​more than one thousand square kilometers for evacuation of personnel, to facilitate the search for wreckage and reduce secondary accidents caused by wreckage. With the rapid economic development, Due to the free-fall flight of the roc...

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Problems solved by technology

[0004] At the same time, the guidance methods used in my country's active launch vehicles, such as perturbation guidance and iterative guidance, cannot be directly applied to the guidance law design of the rocket's vertical recovery section. Perturbation guidance needs to track the standard trajectory, but the rocket's flight trajectory during its return to the atmosphere The deviation from the standard trajectory is large, resulting in the failure to guarantee the accuracy of the landing point. Therefore, each rocket needs to be designed with a standard trajectory, which does not have generalization and versatility; iterative guidance is based on the analytical solution of the optimal control problem, and has a high accuracy, but it is difficult to obtain high-precision guidance law analysis results in the vertical recovery section

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