In-situ calibration device and calibration method for high-temperature propellant steady-state flow rate of attitude control engine

Abstract

The invention discloses an in-situ calibration device and calibration method for high-temperature propellant steady-state flow of an attitude control engine. The calibration device includes a propellant supply device, a high and low temperature box, a weighing recovery device, a control system and a measurement system; The device is used to provide propellant supply with stable flow, pressure and temperature for the calibration system according to the flow requirements of the mass flowmeter to be calibrated; the high and low temperature box heats the propellant supply device according to the calibration requirements of the mass flowmeter to be calibrated; the weighing recovery device It is used to weigh and recover the propellant flowing through the mass flowmeter within the calibration setting time; the control system is used to control and adjust the propellant supply device, high and low temperature box, and the weighing recovery device; the measurement system performs data processing Collection and processing. The device can effectively reduce the influence of medium temperature and density on the measurement results of the mass flowmeter, and improve the flow measurement accuracy.

Description

technical field [0001] The invention relates to an aerospace engine test, in particular to an in-situ calibration device and a calibration method for a high-temperature propellant steady-state flow rate of an attitude-controlled engine. Background technique [0002] At present, the mass flowmeters used in the liquid rocket attitude control engine test mostly use the flowmeter parameters and accuracy calibrated by the metrology department as the basis for accuracy. The medium used by the flowmeter is different from the medium used in the test site test run in terms of physical properties, temperature, and viscosity. There are also differences between the calibrated flowmeter and the operating environment. These factors will affect the accuracy of small flow measurement and cause attitude control engine failure. Technical difficulties in steady-state small flow measurement. [0003] The mass flowmeter used in the liquid attitude control engine test site is mainly used to meas...

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Problems solved by technology

[0002] At present, the mass flowmeters used in the liquid rocket attitude control engine test mostly use the flowmeter parameters and accuracy calibrated by the metrology department as the basis for accuracy. The medium used by the flowmeter is different from the medium used in the test site test run in terms of physical properties, temperature, and viscosity. There are also differences between the calibrated flowmeter and the operating environment. These factors will affect the accuracy of small flow measurement and cause attitude control engine failure. Technical Difficulties in Steady-state Small Flow Measurement

[0003] The mass flowmeter used in the liquid attitude control engine test site is mainly used to measure the supply flow rate of hydrazine and nitrogen oxide liquid medium. The density and viscosity of the mass flowmeter differ greatly from the properties of the water medium used in the laboratory of the flowmeter calibration department. The test medium generally has Highly toxic, volatile, and highly corrosive, it is easy to introduce system errors. In addition, when the temperature of the propellant required for the test run is high, the physical parameters such as the density and viscosity of the propellant will change with the temperature. The system error introduced by this Larger, seriously affecting the accuracy of flow measurement

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