飞行器大气数据系统测压校准风洞试验若干环节的实现方法研究

飞行器大气数据系统压力参数数据通常来源于事先进行的测压校准风洞试验,因此试验结果的准确性对实际飞行时的大气参数解算精度有直接影响。而该风洞试验的准确性受多种因素影响,针对试验段类型、测压管路连接方式和常/降速压方式选择3个环节,基于风洞试验数据开展了研究。研究发现:试验段采用槽壁比采用孔壁更有利于提高测压校准的准确性,故建议采用槽壁进行大气数据系统测压校准试验;连接测压管时,对每个测压孔单独测压取均值和对与这几个测压孔相通的压力腔测压,压力测量精度无明显差异,考虑到后者能减少试验准备时间和压力扫描阀数量,故建议采用后一种测压管连接方式;同风洞、同模型采用常压和降速压方式,压力测量精度无明显差异,而考虑到常压测量在效率、成本上有优势,故建议直接采用常压测量方式进行大气数据测压校准风洞试验。上述结论可为型号飞行器大气数据系统测压校准风洞试验设计提供参考。

Research on the several links of wind tunnel test for pressure measurement and calibration of air-data system

The pressure parameter of the air-data system of aircraft usually comes from the wind tunnel test in advance, so the accuracy of test results has a direct impact in actually flight. Based on wind tunnel test,this paper focuses on three factors: the type of test section、type of pipe connection and normal/reduce pressure. The results show that slotted wall test section is better than perforated wall test section. There was no significant difference in pressure measurement accuracy when connecting the pipe:take the mean value of pressure measurement for each manometer hole separately and the pressure chamber connected with these manometer holes.These were no obvious difference between two types of test method: normal and reduce pressure. The above conclusions can provide reference for the design of wind tunnel test for the pressure measurement calibration of the air data system of the aircraft.