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General propelling module for small satellites

A propulsion module and satellite technology, applied in the field of satellite propulsion module, can solve the problems of prolonging the development cycle of small satellites, the influence of on-board sensors, and the large influence of electric thrusters, so as to shorten the development cycle, reduce the influence of plumes, reduce the The effect of small complexity

Active Publication Date: 2013-05-01
AEROSPACE DONGFANGHONG SATELLITE
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] If a conventional satellite configuration is adopted and the small satellite propulsion system and other electronic equipment are installed in the same cabin, due to the influence of the star space, the fuel that the small satellite can carry will be limited, and at the same time, the engine plume will directly impact on the satellite. The sensor will have a certain impact, and the impact will be greater when using electric thrusters
In addition, since the propulsion system and other electronic equipment are installed in the same cabin, the installation, precise measurement, and leak detection of the propulsion system equipment will occupy the main line of satellite development, prolonging the development cycle of small satellites

Method used

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  • General propelling module for small satellites
  • General propelling module for small satellites
  • General propelling module for small satellites

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Embodiment Construction

[0014] like figure 1 As shown, the propulsion cabin of the present invention is mainly composed of two parts: the main body of the propulsion cabin and the tank bracket 2, wherein the main body of the thrust cabin is divided into three parts: the upper flange 1, the lower flange 4, and the casing 3. For the convenience of description, first define the body coordinate system (O-XYZ) of the propulsion cabin as follows:

[0015] Coordinate origin O: 4 places on the lower flange of the propulsion cabin, the theoretical center of the star-arrow separation surface; X-axis: point to the direction of the upper flange 1 of the propulsion cabin along the coordinate origin; Z-axis: pass the coordinate origin and be perpendicular to the X-axis, flight state Downward pointing to the ground; Y axis: form a right-handed system with the Z and Y axes.

[0016] like figure 1 , figure 2 As shown, the propulsion cabin is docked with the electronic cabin of the satellite through the upper flan...

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Abstract

The invention discloses a general propelling module for small satellites. The propelling module comprises an upper flange, a lower flange, a storage box bracket, an engine bracket and a shell, wherein the upper flange and the lower flange are positioned on two end faces of the shell respectively, the upper flange is connected with an electronic compartment, and the lower flange is a satellite arrow butted face. The shell has a hollow round table-shaped structure consisting of a purlin structure and is provided with an aluminum envelope, and the storage box bracket is positioned at the lower part of the inside middle part of the shell. The storage box bracket has a cover-like structure, the upper surface of which is smooth and the lower surface of which is provided with reinforcing ribs; the center of the storage box bracket is provided with an ion propeller pipeline outlet; the storage box bracket is provided with bottleneck mounting holes at the quadrants of the Y axis and the Z axisof the YOZ plane of a propelling module body coordinate system and in the direction forming 45-degree angles with the coordinate axes; and the upper surface of the storage box bracket is a mounting surface for spreading equipment and pipelines. An engine bracket is respectively arranged at four intersection points of the shell and the Y axis and the Z axis of the propelling module body coordinatesystem, wherein the brackets at the two intersection points of the shell and the Y axis are positively arranged engine brackets, and the brackets at the two intersection points of the shell and the Zaxis are obliquely arranged engine brackets.

Description

technical field [0001] The invention relates to a satellite propulsion module. Background technique [0002] With the development of small satellite applications, the functions of small satellites are continuously enhanced, and the system is becoming more and more complex. In order to meet the attitude and orbit control needs of small satellites operating in orbit for a long time, small satellites need to carry more fuel or use electric propulsion as the orbit control engine of small satellites. At the same time, with the shortening of the development cycle of small satellites, it is also necessary to carry out part of the satellite development and test work in parallel to optimize the development process and speed up the development progress. [0003] If a conventional satellite configuration is adopted and the small satellite propulsion system and other electronic equipment are installed in the same cabin, due to the influence of the star space, the fuel that the small sa...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64G1/40
Inventor 翟峰韩冬邓宇华
Owner AEROSPACE DONGFANGHONG SATELLITE
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