On-orbit performance adjustment compensation method and system for spacecraft propulsion system

A technology for propulsion system and spacecraft, applied in the field of spacecraft dual-component propulsion system, can solve the problems of increased system complexity and structural weight, no configuration of air supply system, etc., to achieve the effect of improving utilization rate and increasing on-orbit life.

CN112693632AActive Publication Date: 2021-04-23SHANGHAI INST OF SPACE PROPULSION
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Patent Information

Authority / Receiving Office
CN · China
Patent Type
Applications(China)
Current Assignee / Owner
Publication Date
2021-04-23

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Abstract

The invention provides an on-orbit performance adjusting and compensating method and system for a spacecraft propulsion system. The method comprises the steps of 1, arranging a plurality of pressure sensors and a plurality of parallel on-orbit control self-locking valves on an on-orbit control pipeline; 2, obtaining the flow resistance value of each single rail control self-locking valve through single-machine liquid flow debugging of the rail control self-locking valve; 3, enabling the ground adjusting values of the inlet pressures of the oxidant path and the fuel path to be equal when the orbit control engine works; 4, ensuring that the mixing ratio precision of the engine meets the requirement during single-machine liquid flow debugging of the orbit control engine; 5, in the on-orbit flight process of the propulsion system, obtaining the measured value of the engine inlet pressure in the ignition working process of the orbit control engine; and 6, comparing the measured values of the oxidant path inlet pressure and the fuel path inlet pressure, and executing an on-orbit performance adjustment compensation strategy as required. Active adjustment compensation control within a certain range can be conducted on the mixing ratio of the orbit control engine, and the propellant utilization rate is increased.
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Description

technical field

[0001] The invention relates to the technical field of spacecraft dual-component propulsion systems, in particular to a method and system for adjusting and compensating the on-orbit performance of a spacecraft propulsion system. Background technique

[0002] At present, spacecraft generally have higher and higher requirements on the propulsion system's mixing ratio accuracy and propellant utilization rate. Propulsion systems that require high mixing ratio accuracy generally use the ground orbit control pipeline flow resistance adjustment to ensure the orbit control engine mixing ratio. During the flight in orbit, if the actual flow resistance of the orbit control pipeline deviates from the ground debugging value, it will affect the mixing ratio of the orbit control engine, thereby affecting the propellant utilization rate.

[0003] However, most propulsion systems do not have an on-orbit adjustment and compensation method for the engine mixture ratio performa...

Examples

Embodiment Construction

[0047] 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.

[0048] An embodiment of the present invention provides a method for adjusting and compensating the on-orbit performance of a spacecraft propulsion system, referring to figure 1 As shown, firstly, a plurality of pressure sensors and a plurality of parallel rail control self-locking valves are arranged on the rail control pipeline. Under normal working mode, the rail control pipeline and the rail control self-locking valve are simultaneously opened and closed. Wherein the rail control pipeline includes an...