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Rocket soft landing trajectory planning method based on convex optimization

A technology of trajectory planning and convex optimization, which is applied in spaceflight equipment, spaceflight vehicles, spaceflight guidance devices, etc. It can solve the problems of poor anti-interference ability and insufficient adaptability of rocket power soft landing section, etc.

Active Publication Date: 2021-03-26
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 trajectory planning method based on convex optimization, aiming to solve the technical problems of poor anti-interference ability of the rocket after entering the powered soft landing section and insufficient deviation adaptability of the rocket powered soft landing section

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  • Rocket soft landing trajectory planning method based on convex optimization
  • Rocket soft landing trajectory planning method based on convex optimization
  • Rocket soft landing trajectory planning method based on convex optimization

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[0052] 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.

[0053] Please also refer to Figure 1 to Figure 3 , a convex optimization-based rocket soft landing trajectory planning method provided by the present invention will now be described. Described a kind of rocket soft landing trajectory planning method based on convex optimization, comprises the following steps:

[0054] S1. According to the rocket soft landing process, establish the rocket power soft landing segment motion equation satisfying convex optimization, the rocket power soft landing segment state constraint equation, and obtain the rocket power soft landi...

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Abstract

The invention provides a rocket soft landing trajectory planning method based on convex optimization, and belongs to the technical field of carrier rocket control. The method comprises the following steps: building a rocket power soft landing section motion equation and a rocket power soft landing section state constraint equation meeting the convex optimization according to a rocket soft landingprocess, and obtaining an objective function of a rocket power soft landing section; establishing a rocket power soft landing section online trajectory sequence convex optimization equation accordingto the rocket power soft landing section motion equation, the rocket power soft landing section state constraint equation and the rocket power soft landing section target function; and planning an ideal track with the maximum feasible region of the soft landing section in an online rolling manner. According to the rocket soft landing trajectory planning method based on convex optimization providedby the invention, the anti-interference capability of the reusable rocket after entering the power soft landing section is improved, and the method is suitable for solving the trajectory planning problem of complex constraints on line.

Description

technical field [0001] The invention belongs to the field of launch vehicle control, and more specifically relates to a trajectory planning method for rocket soft landing based on convex optimization. Background technique [0002] The vertical recovery technology of reusable launch vehicles is one of the important development directions of new generation launch vehicles. According to the actual flight status in the powered soft landing stage, online planning of the landing trajectory is one of the effective ways to enhance the deviation adaptability and improve the landing accuracy. In the current online trajectory planning method, the optimal thrust amplitude command planned online usually has the characteristics of Bang-Bang control, that is, the engine works with the minimum thrust first, and then switches to the maximum thrust. However, when the thrust adjustment process is considered for this type of ideal landing trajectory, due to the large thrust span, the delay of ...

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64G1/24
CPCB64G1/242
Inventor 王聪宋征宇胡海峰巩庆海
Owner BEIJING AEROSPACE AUTOMATIC CONTROL RES INST
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