General propelling module for small satellites

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...

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

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