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在对飞机侧滑角准确测量中,由于飞机侧滑角存在一些缺陷是静压差与侧滑角之间不是直接的关系,还需要额外的全静压系统的数据,而全静压系统性能会出现误差,另外,静压差法的测量易产生非线性的结果。针对上述问题,建立了压差系数与实际侧滑角的换算关系模型,同时,利用CFD软件划分了机身前段网格,并预测了静压孔周围的压差系数,也在马赫数和攻角平面下对压差系数曲面进行了拟合,得到了计算侧滑角所需的比例系数,最终仿真得出了压差系数与实际侧滑角的关系。仿真结果表明,静压孔周边的平均压差系数是负数,因而,通过总压和静压计算得出的真实空速和动压数值偏大,依然存在误差,但误差较小。研究结果可为采用静压差技术测量飞机侧滑角提供理论支持。
In the accurate measurement of the side slip angle of the aircraft, due to the flaw in the aircraft side slip angle, the static pressure difference is not directly related to the side slip angle, and additional data on the total static pressure system is needed. The performance of the full static pressure system There will be errors, In addition, the static pressure difference measurement is easy to produce non-linear results. In order to solve the above problems, a model of conversion between differential pressure coefficient and actual side slip angle is established. At the same time, the CFD software is used to divide the grid in front of the fuselage and predict the differential pressure coefficient around the static pressure hole. The pressure coefficient surface is fitted under the angle plane, and the proportion coefficient needed to calculate the side slip angle is obtained. Finally, the relationship between the pressure differential coefficient and the actual side slip angle is obtained. The simulation results show that the average differential pressure coefficient around the static pressure hole is negative. Therefore, the error of the real airspeed and dynamic pressure calculated by the total pressure and static pressure is large, but the error is still small. The results can provide theoretical support for measuring the side slip angle of aircraft using static pressure difference technology.