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Rocket soft landing guidance method

A soft landing and rocket technology, which is applied in the direction of the landing device of the spacecraft, the guidance device of the spacecraft, and the system of the spacecraft returning to the earth's atmosphere, etc., can solve the problems of inaccurate soft landing position, easy to fly out of the feasible area, etc.

Active Publication Date: 2021-04-16
BEIJING AEROSPACE AUTOMATIC CONTROL RES INST
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Problems solved by technology

[0003] The purpose of the present invention is to provide a rocket soft landing guidance method, which aims to solve the problem that the existing rocket is easy to fly out of the feasible area under the interference state when the rocket lands vertically, resulting in inaccurate soft landing position

Method used

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Embodiment Construction

[0075] In order to make the technical problems, technical solutions and beneficial effects to be solved by the present invention clearer, the present invention will be further described in detail below in conjunction with the accompanying drawings and embodiments. It should be understood that the specific embodiments described here are only used to explain the present invention, not to limit the present invention.

[0076] Please also refer to figure 1 , 2 , a kind of rocket soft-landing guidance method provided by the present invention is described now. A rocket soft landing guidance method, comprising:

[0077] Step 101: Obtain an engine start command by using an adaptive engine start method;

[0078] In order to obtain the engine start-up conditions for the rocket to enter the power soft landing section, the present invention proposes a reusable launch vehicle power soft landing section adaptive engine start-up method, so that the rocket can enter the power soft landing ...

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Abstract

The invention provides a rocket soft landing guidance method, and belongs to the technical field of carrier rocket control. According to the method, an engine starting instruction is obtained through a self-adaptive engine starting method, a good initial access condition is created for the landing process after the engine is started, a rocket power soft landing section online track planning equation is established according to a rocket landing flight state, and a nominal track with the strongest deviation adaptability in a subsequent flight process can be planned in a real-time online rolling manner; through a guidance tracking method, a rocket can be guided to the nominal track generated in real time, and influence of interference in rocket landing process is greatly reduced; in addition, an engine shutdown condition is determined through a small-step-length prediction shutdown method, and the landing precision of the rocket is further improved.

Description

technical field [0001] The invention belongs to the technical field of launch vehicle control, and more specifically relates to a rocket soft landing guidance method. Background technique [0002] At present, the Falcon series of rockets that can achieve vertical landing of the rocket have nine Merlin 1D engines in the first stage or booster stage. By turning on only a few of them instead of all the engines during the landing process, the thrust-to-weight ratio can be greatly reduced, and the Maintain thrust symmetry and attitude control stability. By adjusting the engine thrust, the rocket makes the thrust-to-weight ratio equal to 1 before landing, and achieves a constant speed landing at a safe falling speed. However, at present, only a small number of engines are connected in parallel in the first stage or booster stage of many active rockets, such as the Chinese CZ-5 and CZ-7 rockets, the European Ariane 6, and the Japanese H3 rocket, etc., each of which is equipped wit...

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64G1/62B64G1/24F42B15/01
Inventor 宋征宇王聪胡海峰巩庆海
Owner BEIJING AEROSPACE AUTOMATIC CONTROL RES INST
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