Temperature control method for satellite propelling module

A technology for propulsion cabins and satellites, which is applied in the directions of artificial satellites, propulsion system devices of astronauts, and devices for controlling the living conditions of astronauts, etc. problems, to achieve the effect of shortening the development cycle, reducing development costs, power consumption and quality reduction

Inactive Publication Date: 2017-03-01
SHANGHAI SATELLITE ENG INST
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Problems solved by technology

Under this condition, the thermal control system consumes a lot of resources in order to meet the design requirements, which is not conducive to resource utilization.
[0007] 2. Under the condition of traditional propellants, the thermal control method of the propulsion system is complex in design and cumbersome in installation
The main disadvantages are heavy weight and complicated installation, and it is used to control the temperature of the propulsion system, which is expensive

Method used

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  • Temperature control method for satellite propelling module

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Embodiment Construction

[0023] The present invention will be described in detail below in conjunction with specific embodiments. The following examples will help those skilled in the art to further understand the present invention, but do not limit the present invention in any form. It should be noted that those skilled in the art can make several changes and improvements without departing from the concept of the present invention. These all belong to the protection scope of the present invention.

[0024] This embodiment provides a temperature control method for a satellite propulsion cabin, comprising the following steps:

[0025] Carry out thermal design for the propulsion module of the satellite: isolate the radiation heat exchange between the cabin and the outside of the cabin, and the surface of the inner panel of the cabin is covered with multi-layer heat insulation components, so that the temperature distribution of the components 1 in the propulsion cabin is uniform, and the other parts of ...

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Abstract

The invention provides a temperature control method for a satellite propelling module. According to the adopted design method for the independent propelling module installed on the basis of a propelling system, the outer surface of the whole module is coated with multiple thermal insulation components; part of a thruster needs to wrap the thermal insulation components outside the module; a compensating heater is designed to ensure the temperature level of an electromagnetic valve; pipelines and a support which are arranged outside the module wrap the thermal insulation components; no thermal control processing is conducted in the propelling module. By adopting the temperature control method on the basis of novel low-temperature propellant, the temperature control requirements of the satellite propelling module can be met.

Description

technical field [0001] The invention relates to the technical field of spacecraft thermal control, in particular to a temperature control method for a satellite propulsion module. Background technique [0002] In recent years, with the advancement of electronic integration technology and payload miniaturization technology, small satellites have achieved rapid development due to their high technology integration, low cost, and short development cycle. The development of high-performance payloads and low-cost small satellites will play a role in technical traction and support for the advancement of space technology. [0003] As the executive mechanism of the satellite attitude and orbit control subsystem, the main task of the propulsion system is to provide the force or moment required for tasks such as rate damping, initial orbit acquisition, orbit maintenance, orbit maneuvering, and attitude maintenance according to the attitude and orbit control requirements, so as to ensur...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64G1/10B64G1/40B64G1/50B64F5/00
CPCB64G1/10B64F5/00B64G1/40B64G1/50
Inventor 周砚耕赵吉喆杜嘉旻吴自帅盛松
Owner SHANGHAI SATELLITE ENG INST
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