Vacuum plume pneumatic thermal full field measurement system based on pressure sensitive/temperature sensitive paint

Abstract

The invention provides a vacuum plume pneumatic thermal full field measurement system based on pressure sensitive / temperature sensitive paint. The system includes a vacuum chamber, a pneumatic model,an engine, a pressure sensitive / temperature sensitive paint layer, an excitation light assembly, an emission light channel and an image acquisition and analysis module, wherein the pneumatic model andthe engine are placed in the vacuum chamber, the pressure sensitive / temperature sensitive paint layer is attached to a to-be-detected surface of the pneumatic model, the emission light channel includes an observation window, a beam splitter and a band pass filter sequentially arranged in the emission light observation direction, the image acquisition and analysis module is connected with the emission light channel, when measurement is performed, the light emitted by the pressure sensitive / temperature sensitive paint layer is received by the emission light channel, the light after filtering and beam splitting processing is transmitted to the image acquisition and analysis module, and pressure distribution and temperature distribution of the pneumatic model surface are obtained by a computer according to difference of illuminating states of the pneumatic model pressure sensitive / temperature sensitive paint layer before and after working of the engine. The system is capable of measuringthe pneumatic force and pneumatic heat of a vacuum plume in a non-contact manner.

Description

technical field [0001] The invention relates to the technical field of measurement equipment, in particular to a vacuum plume aerodynamic thermal full-field measurement system based on pressure-sensitive / temperature-sensitive paint. Background technique [0002] When the attitude and orbit control engines used on spacecraft such as satellites, spaceships and space stations work in a high vacuum environment, the gas is ejected from the nozzle at high speed and then expands rapidly into the vacuum to form a vacuum plume. The influence range of the plume is very wide, and it will even spread to the front of the engine, causing aerodynamic and aerothermal effects on the spacecraft, affecting the attitude maintenance and control of the spacecraft, resulting in excessive local heat load, thereby reducing the life of the spacecraft, seriously Sometimes it can even lead to the failure of the spacecraft. [0003] Using real engines or simulated engines to generate plumes in ground v...

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Problems solved by technology

Although this method is simple and reliable, due to the discrete measurement points, errors in the measurement data of the hole interval area obtained by interpolation are inevitable, and the measurement spatial resolution is low; if too many measurement points are arranged, the surface of the model will be destroyed, resulting in the flow field Deviation from the actual situation, and the time and economic costs are greatly increased

[0004] The comparative document "2010102351235 Measuring Device for the Aerodynamic Force of the Plume of the Attitude Control Engine on the Large Solar Cell Wing" discloses a measurement device for the aerodynamic force of the plume of the attitude control engine on the large solar cell wing, using a displacement sensor and an electromagnetic force calibration device to measure the aerodynamic force of the solar cell wing The overall aerodynamic force can only obtain the overall aerodynamic force components in two directions, and the details of the pressure distribution on the surface of the model cannot be obtained, which is not conducive to in-depth scientific research on the plume aerodynamic force; moreover, the measurement device replaces different solar cell wings or other aerodynamic models, it is necessary to redesign the brackets and fixtures; in addition, the measurement device is only suitable for larger force-bearing surfaces, otherwise the displacement sensor cannot distinguish the model displacement caused by the small aerodynamic force

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