The invention belongs to the technical field of helicopter pneumatic design, and particularly relates to a method for correcting the indicated airspeed of a helicopter through a pneumatic attack angle. Comprising the following steps: S1, additionally arranging a front rod for measuring a pneumatic attack angle and indicating an air speed on a helicopter; s2, the indicated airspeed of the front rod is calibrated in the selected level flight state, and a relation curve of the indicated airspeed and the calibrated airspeed of the front rod is obtained; s3, selecting a climbing state and a gliding state, and obtaining a pneumatic attack angle AOA of a front rod test; s2, according to the relation curve, obtained in S2, of the indicated airspeed and the calibrated airspeed of the front rod, the calibrated airspeed of the climbing state and the calibrated airspeed of the descending state are obtained, then the indicated airspeed error of the climbing state and the indicated airspeed error of the gliding state are obtained, and the indicated airspeed error is the difference value of the calibrated airspeed and the onboard indicated airspeed; s4, the true speed TAS and the lifting speed Vz in the climbing and gliding process are obtained, and the theoretical pneumatic attack angle AOA1 of the helicopter is preliminarily calculated; and S5, according to the theoretical pneumatic attack angle AOA1 calculated in the step 4 and the indicated airspeed error relation curve corresponding to different actually-measured pneumatic attack angles obtained in the step 3, correcting the onboard indicated airspeed according to the indicated airspeed error corresponding to the theoretical pneumatic attack angle AOA1.

    本发明属于直升机气动设计技术领域,尤其涉及一种通过气动攻角修正直升机指示空速的方法。包括:S1,在直升机上加装测量气动攻角和指示空速的前置杆;S2,选定平飞状态下对前置杆的指示空速进行校准,得到前置杆的指示空速和校准空速的关系曲线;S3,选定爬升和下滑状态,获取前置杆测试的气动攻角AOA;根据S2获得的前置杆的指示空速与校准空速的关系曲线,获得爬升和下降状态的校准空速,继而得到爬升和下滑状态的指示空速误差,指示空速误差为校准空速与机上指示空速的差值;S4,获取爬升下滑过程的真速度TAS、升降速度Vz,初步计算直升机的理论气动攻角AOA1;S5,根据步骤4计算的理论气动攻角AOA1和步骤3得到的实测不同气动攻角对应的指示空速误差关系曲线,根据理论气动攻角AOA1对应的指示空速误差修正机上指示空速。


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    Title :

    Method for correcting indicated airspeed of helicopter through pneumatic attack angle


    Additional title:

    一种通过气动攻角修正直升机指示空速的方法


    Contributors:
    ZHANG ZHIMING (author) / QIU LIANGJUN (author) / ZHOU LINGLING (author) / CHEN RUI (author) / XU YUMAO (author) / MENG SHENGXUE (author)

    Publication date :

    2025-01-03


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    Chinese


    Classification :

    IPC:    B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT



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