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Separable independent propulsion module system

A propulsion module and propellant technology, applied in space vehicle propulsion system devices, space navigation equipment, space navigation equipment, etc., can solve problems such as heavy system, reduced size of satellite body, waste of propellant consumption, etc., to achieve Improve the bearing ratio and reduce the effect of system sluggishness

Pending Publication Date: 2022-03-25
CHINA GREAT WALL IND CORP +1
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] The dual-component propulsion cabin integrated with other sub-systems of the platform has the following three problems: 1. After the propulsion system is switched to the drop-pressure working mode, the 490N engine and high-pressure gas path used to transfer orbits and change orbits become a system. It is heavy and heavy, which greatly wastes the propellant consumption for orbit maintenance and seriously affects the life of satellite synchronous orbit; 2. The integrated propulsion module and other subsystems of the platform are in a unified layout, and the layout of propulsion modules or pipelines is limited by the layout of various equipment. The layout design of the shortest path cannot be carried out; 3. The design of the integrated propulsion module cannot further reduce the size of the satellite body due to the constraints of the equipment layout space

Method used

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  • Separable independent propulsion module system
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  • Separable independent propulsion module system

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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] This embodiment provides a detachable independent propulsion module system, which is used for the early stage orbit raising task during the orbit trans...

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Abstract

The invention discloses a separable independent propulsion module system which comprises an independent propulsion module structure, a combustion agent storage box, an oxidant storage box, an independent propulsion module storage battery, an N thruster, a Beidou short message terminal, an N engine, an integrated sun sensor, an independent propulsion module control unit and a helium tank. Wherein the combustion agent storage box, the oxidizing agent storage box and the helium tank are arranged on the side wall of the independent propulsion cabin structure; the independent propulsion module storage battery is connected with the independent propulsion module structure; the N thrusters are connected with the independent propelling cabin structure through the bracket; the Beidou short message terminal is connected with the independent propulsion module structure; the N engine is arranged at the bottom of the independent propulsion cabin structure; the integrated sun sensor is connected with the independent propulsion module structure; the independent propulsion module control unit is connected with the independent propulsion module structure through screws. Separation design of the high-orbit satellite platform propelling system is achieved, and the method has the remarkable advantages of improving the satellite bearing capacity and prolonging the in-orbit service life of the satellite.

Description

technical field [0001] The invention belongs to the technical field of orbit raising tasks in the early stage of a satellite transfer orbit section, and in particular relates to a detachable and independent propulsion module system. Background technique [0002] At present, domestic high-orbit satellite platforms are usually equipped with dual-component propulsion modules integrated with other subsystems of the platform. The dry weight of the chemical propulsion subsystem itself under this configuration and the increase in the dry weight of the structure and other platforms due to the configuration change of the satellite caused by the configuration of the chemical propulsion subsystem account for about 30% of the dry weight of the satellite platform. Since the 490N engine and the high-pressure gas path used for the transfer orbit change are only used to lift the transfer orbit after the separation of the satellite and rocket in the early stage, this part of the chemical pro...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64G1/40B64G1/64
CPCB64G1/402B64G1/645
Inventor 刘杰高若飞王敏林滢裴林李炤坤苏宏博李强赵晨
Owner CHINA GREAT WALL IND CORP
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