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A Method for Accurately Evaluating the Vacuum Specific Impulse Performance of Space Orbit Control Engine

A technology of rail-controlled engines and engines, which is applied in the direction of complex mathematical operations to achieve precise and definite results

Inactive Publication Date: 2014-04-23
SHANGHAI INST OF SPACE PROPULSION
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  • Application Information

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Problems solved by technology

[0005] The technical problem to be solved by the present invention is to accurately evaluate the vacuum specific impulse performance of small and medium-thrust space orbit control engines in the application process. The present invention provides a method for accurately evaluating the vacuum specific impulse of space orbit control engines

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  • A Method for Accurately Evaluating the Vacuum Specific Impulse Performance of Space Orbit Control Engine
  • A Method for Accurately Evaluating the Vacuum Specific Impulse Performance of Space Orbit Control Engine

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Embodiment Construction

[0010] The present invention will be described in further detail below in conjunction with the accompanying drawings.

[0011] figure 1 The relationship curve of the influence of the oxidant temperature of an engine on the vacuum specific impulse performance is given. From the figure, it can be seen that the relationship between the vacuum specific impulse performance of the engine and the propellant temperature is a parabola. Therefore, the engine's specific impulse can be determined according to the propellant temperature under different conditions. Vacuum specific impulse.

[0012] Its implementation process is as follows:

[0013] 1) The vacuum specific impulse of the engine is mainly obtained by actually measuring the vacuum thrust and propellant flow of the engine, and is calculated according to the relationship between vacuum specific impulse, vacuum thrust and propellant flow. The vacuum thrust and propellant flow of the engine are mainly measured on the high-altitud...

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Abstract

The present invention proposes a method for accurately evaluating the vacuum specific impulse performance of a space orbit control engine. The method actually measures the vacuum thrust of the engine, the propellant flow rate, and the propellant temperature to fit the relationship between the vacuum specific impulse and the propellant temperature, and at the same time Obtain relationship curve and relationship formula: I sv =aT 2 +bT+c. The precise control and evaluation of the vacuum specific impulse of the engine is realized through the application of the relational formula. The present invention can effectively and accurately determine the performance state of the space orbit control engine, and then accurately calculate the consumption of propellant when the spacecraft changes orbit, and provide a reliable tool for the accurate assessment of the remaining propellant of the spacecraft and the prediction of the life of the spacecraft. in accordance with.

Description

technical field [0001] The invention relates to a small and medium-thrust dual-component attitude-orbit control engine used in a spacecraft propulsion system, in particular to a vacuum specific impulse performance evaluation method. Background technique [0002] The vacuum specific impulse of the space orbit control engine is the thrust generated by the propellant per unit flow. As a liquid orbit control rocket engine used by a spacecraft, the vacuum specific impulse is a very important performance parameter. Usually, the propellant carried by the spacecraft The quantity is certain, most of which are consumed by the orbit control engine, and the rest are consumed by the attitude control engine. The vacuum specific impulse performance of the orbit control engine is mainly affected by the following aspects: First, improving the vacuum specific impulse performance of the orbit control engine can effectively reduce the consumption of propellant during orbit change, thereby prolo...

Claims

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Application Information

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IPC IPC(8): G06F17/11
Inventor 周红玲刘昌国姚锋林庆国姜文龙杨成虎赵婷刘犇
Owner SHANGHAI INST OF SPACE PROPULSION
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