The embodiment of the invention provides a helicopter balancing method, which comprises the following steps of: projecting the acting force of a helicopter onto a wind axis coordinate system to establish a balance equation on the basis of the wind axis coordinate system; and during flight, solving the inclination angle beta1c of the propeller disc by the balance equation formed by the acting force acting on the helicopter and the wind axis coordinate system. According to the method, main contradictions are grasped, secondary factors are ignored, and an expression of the beta 1c sum is given. The longitudinal force and the longitudinal moment acting on the center of the propeller hub during stable flight and spiral flight can be solved by using the beta1c. The influence on the performance and the aerodynamic layout of the whole aircraft can be evaluated.

    本发明实施例提供一种直升机配平方法,方法包括:以风轴坐标系为基础,并将直升机的作用力投影到风轴坐标系上建立平衡方程;在飞行时,作用在直升机上的作用力与所述风轴坐标系构成的所述平衡方程求解桨盘倾角β1c。该方法抓住主要矛盾,忽略次要因素,给出β1c和的表达式。利用β1c可求出稳定飞行和螺旋飞行时的作用在桨毂中心的纵向力和纵向力矩。通过可评估它对性能和全机气动布局的影响。


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    Title :

    Helicopter balancing method


    Additional title:

    一种直升机配平方法


    Contributors:

    Publication date :

    2021-05-07


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    Chinese


    Classification :

    IPC:    G06F ELECTRIC DIGITAL DATA PROCESSING , Elektrische digitale Datenverarbeitung / B64F GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT , Boden- oder Flugzeugträgerdeckeinrichtungen besonders ausgebildet für die Verwendung in Verbindung mit Luftfahrzeugen



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