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Engine performance parameter correction method based on in-orbit data

A technology of parameter correction and track-controlled engine, applied in the direction of electrical digital data processing, special data processing application, computer-aided design, etc., can solve the problems of ground heat scale accuracy to be improved, loss, system error, etc., to improve prediction accuracy and Orbit change efficiency, wide application value and promotion prospects, and the effect of improving estimation accuracy

Active Publication Date: 2021-08-06
BEIJING INST OF CONTROL ENG
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  • Abstract
  • Description
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  • Application Information

AI Technical Summary

Problems solved by technology

If the actual performance of the engine deviates too much, it will not only affect the number of orbit changes, consume unnecessary manpower and material resources, but also cause waste of propellant, which will reduce the life of the satellite and bring inevitable losses
[0004] Since the engine performance parameters are generally given by the small deviation equation near the rated point, there is a certain systematic error in the parameter processing method itself, and the use is limited.
In addition, the working conditions of the engine on orbit are not the same as those of the thermal calibration on the ground, and the accuracy of the thermal calibration on the ground needs to be improved, and there are certain method errors in the parameter conversion between the cold test and the hot test.
Therefore, there are often non-negligible differences between the actual on-orbit performance of the engine and the ground

Method used

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  • Engine performance parameter correction method based on in-orbit data
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  • Engine performance parameter correction method based on in-orbit data

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Embodiment Construction

[0042] The present invention will be described below in conjunction with the accompanying drawings.

[0043] Such as figure 1 As shown, a method for revising engine performance parameters based on on-orbit data includes the following steps:

[0044](1) Before each orbit change of the satellite, turn on the ultrasonic flowmeter configured on the satellite to measure the propellant flow during the working process of the engine. After the orbit control engine is ignited, turn off the ultrasonic flowmeter and stop the flow measurement; during each orbit change, Integrate the output of the ultrasonic flowmeter to obtain the propellant consumption Δm during the orbit change process ui ;

[0045]

[0046] Among them, Q o , Q f Respectively, the output flow rate of the ultrasonic flowmeter corresponding to the downstream of the oxidant and combustion agent storage tanks, t i is the time of the i-th orbital maneuver; i is a positive integer;

[0047] (2) Record the ignition ti...

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Abstract

The invention proposes an engine performance parameter correction method based on on-orbit data, and the method comprises the steps: correcting the performance parameters of the engine through the on-orbit actual performance data, thereby facilitating the improving of the analysis level of the on-orbit data, and deepening the understanding of the working performance of an engine. According to the method, the engine performance parameters can be corrected without redundant hardware, the estimation precision of the on-orbit residual propellant can be improved, the prediction precision and orbital transfer efficiency of the on-orbit thrust can be further improved, waste of the propellant can be avoided, and the method has great significance on long-term on-orbit management of subsequent satellites.

Description

technical field [0001] The invention relates to a method for revising engine performance parameters. Background technique [0002] my country's geostationary orbit satellites generally adopt a dual-component unified propulsion system, and are equipped with remote engines and attitude control thrusters. The apogee engine is mainly used to provide thrust for the orbit maneuver of the spacecraft. [0003] During satellite orbital maneuvering, parameters such as the mass of the entire star, the specific impulse of the engine, and thrust are required to formulate an orbit change strategy. Among them, the specific impulse of the engine can be obtained through the engine ground heat scale test, and the engine thrust and the whole star mass need to be introduced into the small deviation equation of the engine. Therefore, the orbit change control effect of the whole satellite and the long-term on-orbit management are closely related to the accuracy of the engine parameters. If the...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F30/17G06F30/20G06F111/10G06F119/02G06F119/08G06F119/12G06F119/14
CPCG06F30/17G06F30/20G06F2111/10G06F2119/02G06F2119/08G06F2119/12G06F2119/14Y02T90/00
Inventor 尹文娟宋涛刘磊何刚李文王祥李泽李湘宁马云华焦焱
Owner BEIJING INST OF CONTROL ENG
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