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应用于X-43A飞行器中的嵌入式大气数据传感(Flush Air Data Sensing,FADS)系统,由于部分测压孔测得的表面压力值明显低于数值计算或风洞试验的数值,所以,FADS系统并没有完全利用所有的测压孔,只是利用正常工作的测压孔来配合惯性导航系统(INS)解算攻角。对于部分失效的测压孔,并不是由硬件故障及测压管路故障引起的,而是由于部分测压孔配置区域的流动结构引起的。就FADS系统中部分测压孔失效的原因进行了分析,对于改进应用于其它同类飞行器的FADS系统的测压孔配置具有指导意义。
The FADS (Embedded Air Data Sensing) system used in the X-43A aircraft, because the surface pressure measured by some of the pressure-measuring holes is significantly lower than that of the numerical calculation or wind tunnel test, the FADS The system does not make full use of all the pressure-measuring holes, just use the normal working pressure-measuring hole to solve the angle of attack with the inertial navigation system (INS). For some failure of the pressure hole, not by the hardware failure and pressure piping problems caused by, but because of part of the configuration of the pressure hole configuration caused by the flow structure. The reason of failure of some pressure-measuring holes in FADS system is analyzed, which is instructive for improving the pressure-measuring hole configuration of FADS system applied to other similar aircraft.