飞机侧滑角静压差准确测量仿真研究

发布时间：2018-06-06 03:39

本文选题：静压差 + 压差系数　；参考：《计算机仿真》2016年10期

【摘要】：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。
[Abstract]:In the accurate measurement of aircraft sideslip angle, because there are some defects in aircraft sideslip angle, there is not a direct relationship between static pressure difference and sideslip angle, and additional data of total hydrostatic pressure system are required. The measurement of static pressure difference method is easy to produce nonlinear results. To solve the above problems, a conversion model between the pressure difference coefficient and the actual side slip angle is established. At the same time, the front mesh of the fuselage is divided by using CFD software, and the pressure difference coefficient around the static pressure hole is predicted. The surface of pressure difference coefficient is fitted under Mach number and angle of attack, and the proportion coefficient needed to calculate the side slip angle is obtained. Finally, the relation between the pressure difference coefficient and the actual side slip angle is obtained by simulation. The simulation results show that the average pressure difference coefficient around the static pressure hole is negative. Therefore, the real space velocity and dynamic pressure calculated by the total pressure and static pressure are larger than those of the static pressure, and there are still errors, but the errors are small. The results can provide theoretical support for the measurement of aircraft sideslip angle by using static pressure differential technique.
【作者单位】：上海工程技术大学航空运输学院;同济大学航空航天与力学学院;
【分类号】：V211

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