基于FADS的飞行器迎角求解方法研究

构建X-33的1/10比例前端模型.利用计算流体力学方法求解模型前端压力分布,采用三点法求解迎角和侧滑角.应用Matlab工具,对求解数据进行修正,最后分析了压力测量误差对迎角精度的影响.结果表明,低马赫数(不大于1.2Ma)下基于仿真数据的嵌入式大气数据传感系统求解迎角误差在0.5°,压力测量误差对迎角精度影响明显.

The Study of Solving Angle of Attack Based on Flush Airdate Sensing System

1/10 scale of X—33 front-end model is build,used the computational fluid dynamics(CFD) method to solve the model front-end pressure distribution,applied the triples method to solve the angle of attack and sideslip angle,adopt Matlab tools for the data correction and finally analyses the effect to the angle of attack accuracy caused by pressure measurement error.The results prove that the error caused by using FADS system based on simulation data to solve the angle of attack is no more than 0.5°at low Mach number(less than 1.2Ma).The pressure measurement error effect is obvious to accuracy of the angle of attack.