Separable independent propulsion module system

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...

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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

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