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16-thruster layout designing method of omnidirectional orbital transfer spacecraft

A technology of thruster layout and design method, which is applied in the direction of propulsion system devices of space navigation vehicles, etc., can solve the problems such as the inability to meet the three-axis and six-direction orbit control functions.

Active Publication Date: 2012-08-29
SHANGHAI SATELLITE ENG INST
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0010] The traditional thruster layout often only considers the track height or inclination control function, which cannot satisfy the three-axis and six-direction track control function

Method used

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  • 16-thruster layout designing method of omnidirectional orbital transfer spacecraft
  • 16-thruster layout designing method of omnidirectional orbital transfer spacecraft
  • 16-thruster layout designing method of omnidirectional orbital transfer spacecraft

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Experimental program
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Embodiment Construction

[0026] The implementation mode of this invention is carried out according to the satellite system engineering implementation specification, and the implementation points are as follows:

[0027] 1) Task analysis

[0028] Applying this scheme, the task analysis is carried out first, and the use functions of the satellite's three-axis attitude control and six-direction orbit control are clarified, and they have backup.

[0029] 2) Proposal demonstration

[0030] Carry out program design. According to the corners of the satellite body (the satellite is usually a hexahedron), first determine the area where the thruster can be placed (considering constraints such as antennas, solar arrays, and shading), carry out the layout of the thruster, refine the technical requirements and indicators, and conduct feasibility studies. Analysis and demonstration, including computer simulation verification, etc.

[0031] 3) Detailed design

[0032] According to the determined thruster layout ...

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PUM

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Abstract

The invention provides a 16-thruster layout designing method of an omnidirectional orbital transfer spacecraft. The method comprises the following steps: (step A) forming a group of thruster combined modules by using four thrusters according to a method of uprightly mounting three thrusters and obliquely mounting one thruster; (step B) laying four groups of thruster combined modules at four opposite angles of a satellite, wherein any two groups of thruster combined modules are not adjacent to each other; and (step C) configuring two sets of independent branch pipelines, so that eight thrusters in the 16 thrusters share one set of pipeline and the rest eight thrusters share the other pipeline. According to the invention, a thruster layout scheme of a 16-thruster full-orbit motor spacecraft with optimized angle layout is designed; therefore, three-axis and six-direction thrust force can be provided, posture control and orbit control backup functions are obtained, no area center is occupied by angle layout design, and a larger layout space is provided for a star catalogue single machine.

Description

technical field [0001] The present invention relates to the field of spacecraft attitude and orbit control, especially a 16 thruster layout design that can provide three-axis and six-direction thrust and satisfy omnidirectional orbital maneuvering, specifically a 16 thruster that can change orbit in all directions. Thruster layout design method. Background technique [0002] As an important part of the satellite attitude and orbit control system, the thruster generally cooperates with multiple ones to complete the attitude damping, attitude control, flywheel unloading, and orbit maintenance after the satellite enters orbit and the satellite is separated by ejecting the reaction force and moment of the working medium. , track maneuvering and other functions. [0003] Most of the existing spacecraft are designed for one-time use. In order to ensure the service life, the subsystems usually adopt redundant design. On the other hand, due to cost and weight constraints, there ca...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64G1/40
Inventor 崔本杰沈庆丰黄小虎陈占胜
Owner SHANGHAI SATELLITE ENG INST
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