Development of a high-altitude low-temperature and low-pressure simulation test device
In response to the research needs of basic aerodynamic issues related to the high-altitude environment of aircraft,a high-altitude atmospheric environment simulation test device has been constructed using a low-temperature simulation library nested with a low-pressure simulation module above an altitude of 40 km.A dual loop control algorithm has been used to simulation of low-pressure parameters accurately and rapidly,and the system's working vacuum can reach below 200 Pa within 10 minutes.Stable and energy-saving output of temperature has been achieved by de-veloping step-less regulation technology for refrigeration systems and PID adaptive technology for cold and hot dual circuits.The temperature control accuracy is±0.5 ℃,and the temperature uni-formity is better than±1 ℃.Designed and equipped with a circular reflux wind tunnel,propeller and airfoil testing subsystem,providing a reliable testing platform and technical support for conduc-ting aerodynamic performance testing of high-altitude environmental aircraft.
high altituderefrigerationvacuum degreedual loop controltest device
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维普
