The invention relates to an aircraft and a counterweight balancing method.The aircraft comprises a main oil tank, a first cavity, a second cavity and a pump driving mechanism, the first cavity is located at the position, close to the main oil tank, of the main oil tank, and the second cavity is located at the position, away from the main oil tank, in the first direction; the first direction is the direction from the head of the aircraft to the tail of the aircraft, balance liquid is stored in the first cavity and the second cavity, the first cavity communicates with the second cavity, and the pump driving mechanism is used for achieving conveying of the balance liquid between the first cavity and the second cavity. The balance liquid is adjusted according to the balance amount required by the aircraft to ensure the balance weight of the aircraft, so that the flight balance and stability of the aircraft are improved.

    本申请涉及一种飞行器和配重平衡方法,其中,飞行器包括主油箱、第一腔体、第二腔体和泵驱机构,所述第一腔体位于所述主油箱或靠近所述主油箱的位置,所述第二腔体位于第一方向上远离所述主油箱的位置,所述第一方向为所述飞行器的头部指向尾部的方向,所述第一腔体和第二腔体内存储有平衡液体,且所述第一腔体与所述第二腔体相连通,所述泵驱机构用于实现所述第一腔体与第二腔体之间平衡液体的输送,其中,所述平衡液体根据飞行器所需的平衡量进行调节,以保证飞行器的配重平衡,从而提高飞行器的飞行平衡性和稳定性。


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    Title :

    Aircraft and counterweight balancing method


    Additional title:

    飞行器和配重平衡方法


    Publication date :

    2023-10-27


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    Chinese


    Classification :

    IPC:    B64C AEROPLANES , Flugzeuge / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT



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