针对某飞机需要在机头配置空速管的设计要求,提出了采用机头气动补偿空速管的设计方法并给出了设计思路。通过数值计算得到了该飞机的机头位置误差,由此给出了一种气动补偿空速管外形;对给出的空速管的气动补偿特性进行了计算,并通过风洞试验对比验证了模型和数值计算方法的正确性,得到了该空速管的补偿曲线和补偿区的最佳静压开孔位置;在此基础上,对补偿空速管与飞机机头的匹配性进行分析,确定了空速管的结构长度。最后对补偿空速管与飞机机头进行一体化计算,结果显示补偿效果良好。研究结果表明,该设计思路和方法具有可行性,设计结果可以满足设计指标要求。该方法可为机头气动补偿空速管的设计提供参考。
A design method of a nose aerodynamic compensation pitot-static tube is proposed according to the aircraft design requirement for the pitot-static tube to be placed at the head of the aircraft. The aircraft nose position error is obtained by numerical calculation and then an aerodynamic compensation pitot-static tube configuration is given. Numerical calculations are conducted on the pitot-static tube in order to study its aerodynamic compensation characteristics. Calculation results are verified by comparing them with experimental data. Compensation curves of the pitot-static tube and the best static pressure port location in the compensation region are obtained. On this basis, the compatibility of the compensation pitot-static tube with the aircraft nose is analyzed so as to determine the length of the pitot-static tube. Finally, an integrated calculation of the compensation pitot-static tube and the aircraft nose is presented. The results show that the pitot-static tube is able to provide the desired compensation for aircraft nose position error. Research results of this paper can validate the feasibility of the design approach and method, and the aerodynamic compensation pitot-static tube of this design can satisfy the design requirement. These findings can provide references for aircraft nose aerodynamic compensation pitot-static tube design.
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