高超声速飞行器攻角和侧滑角测量算法

摘要

高超声速飞行器超燃冲压发动机对飞行器的攻角变化十分敏感，在高超声速飞行条件下，需要实时测量高超声速飞行器的攻角和侧滑角。研究了一种尖劈状乘波体构型高超声速飞行器嵌入式大气数据传感系统（ FADS）的测量算法，利用已有实验数据，采用多元线性回归分析方法对攻角和侧滑角进行测量，提出了一种乘波体高超声速飞行器攻角和侧滑角的求解方案，建立了模型并进行了误差分析。在飞行马赫数等于5时，攻角测量精度达到0．03°，侧滑角测量精度达到0．02°。在飞行马赫数等于8时，攻角测量精度达到0．02°，侧滑角测量精度达到0．01°。为乘波体高超声速飞行器FADS系统的后续研究提供技术参考。%The scramjet of hypersonic vehicles is highly sensitive to attack angle. Under the hypersonic flight conditions, at⁃tack angle and side⁃slip angle are in the need of real time precise measurement. This paper studies the measurement algo⁃rithm of a flush airdata sensing system of hypersonic vehicle of ride wave body. Based on achieved experimental data, meas⁃urement approach of attack angle and sideslip angle is presented including mathematics model and error analysis in the use of multiple linear regression analysis. The measurement error of attack angle can reach 0. 03 degrees and measurement error of side⁃slip angle can reach 0. 02 degrees when Mach number equals 5. The measurement error of attack angle can reach 0. 02 degrees and measurement error of side⁃slip angle can reach 0. 01 degrees when Mach number is 8. All these researches can provide technology reference for the future development of the flush airdata sensing system of hypersonic vehicle of ride wave body.