Launch vehicle sublevel vertical return control method and system based on multiple actuators

A multi-actuator and launch vehicle technology, applied in the field of aircraft control, achieves the effect of simple calculation process, solving singular problems, and small loss of precision

Active Publication Date: 2018-05-01
CHINA ACAD OF LAUNCH VEHICLE TECH
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0005] The technical problem solved by the present invention is: to overcome the deficiencies of the prior art, to provide a method and system for the vertical return control of the carrier rocket sub-stage based on multiple actuators, and to solve the attitude control problem of the flight process after the separation of the first sub-stage of the carrier rocket

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  • Launch vehicle sublevel vertical return control method and system based on multiple actuators
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  • Launch vehicle sublevel vertical return control method and system based on multiple actuators

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Embodiment Construction

[0026] Exemplary embodiments of the present disclosure will be described in more detail below with reference to the accompanying drawings. Although exemplary embodiments of the present disclosure are shown in the drawings, it should be understood that the present disclosure may be embodied in various forms and should not be limited by the embodiments set forth herein. Rather, these embodiments are provided for more thorough understanding of the present disclosure and to fully convey the scope of the present disclosure to those skilled in the art. It should be noted that, in the case of no conflict, the embodiments of the present invention and the features in the embodiments can be combined with each other. The present invention will be described in detail below with reference to the accompanying drawings and examples.

[0027] Method example:

[0028] According to the external environment characteristics of different flight segments during the return process of the first sub-s...

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Abstract

The invention discloses a launch vehicle sublevel vertical return control method and system based on multiple actuators. The method includes the following steps: 1, determining an actuator used by attitude control during the vertical return process of the sublevel rocket body of the launch vehicle; 2, using the actuator according to the use principle of the attitude actuator so as to further control the attitude of the sublevel rocket body; and 3, calculating the attitude parameter of the sublevel rocket body by using a quaternion method based on region division. The method and system solve the attitude control in different flight stages after a sublevel rocket body of the launch vehicle is separated, and satisfies the vertical return requirements of the launch vehicle sublevel.

Description

technical field [0001] The invention belongs to the field of aircraft control, in particular to a method for controlling the vertical return of a carrier rocket sub-stage based on multiple actuators. Background technique [0002] The vertical return of the sub-stage of the launch vehicle refers to that after the sub-stage of the rocket completes the flight mission and separates the stages, it flies back to the landing site autonomously according to the set trajectory through the control system and the power device, and lands stably on the landing site with a vertical rocket body attitude. Designated location of the landing field. [0003] In the process of returning to the ground after the separation of the rocket sub-stages, it has to go through different flight stages such as attitude adjustment, reentry, landing point adjustment, and vertical landing. The airspace span is large and the flight environment is complex. Different flight segments have different attitude contr...

Claims

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Application Information

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IPC IPC(8): G05D1/08G05D1/10
CPCB64G1/244G05D1/101
Inventor 张柳吴胜宝刘丙利汪小卫胡冬生何朔张烽李扬焉宁童科伟张雪梅唐琼
Owner CHINA ACAD OF LAUNCH VEHICLE TECH
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