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

Abstract

The invention discloses an in-situ calibration device for the steady state flow rate of a high-temperature propellant of an attitude control engine and a calibration method. The calibration device comprises a propellant supplying device, a high-low temperature box, a weighing and recycling device, a control system and a measuring system; the propellant supplying device is used for supplying flow rate, pressure and propellant at stable temperature for a calibration system according to the flow rate requirement on a mass flow meter to be calibrated; the high-low temperature box is used for heating the propellant supplying device according to the calibration requirement of the mass flow meter to be calibrated; the weighing and recycling device is used for weighing and recycling the propellant which flows through the mass flow meter within the calibration setting time; the control system is used for controlling and regulating the propellant supplying device, the high-low temperature box and the weighing and recycling device; and the measuring system is used for collecting and treating data. By adopting the device, the influence of medium temperature, density and the like on the measuring result of the mass flow meter can be effectively reduced, and the flow rate measuring accuracy is improved.

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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