The invention discloses a wind tunnel test method for aerodynamic characteristics of helicopter landing, which adopts a six-degree-of-freedom parallel mechanism to realize ship attitude simulation, adopts a master-slave mode synchronization method to realize synchronous acquisition of helicopter model load and ship attitude, and realizes single-degree-of-freedom or multi-degree-of-freedom combined motion simulation of a ship through computer control. The ship attitude simulation accuracy is improved, synchronous acquisition of the ship attitude and the helicopter load is realized through a master-slave synchronization mode, abundant data can be acquired, and the ship attitude simulation method has important significance for analyzing and researching the influence relationship between the ship attitude and the helicopter load.

    本发明公开了一种直升机着舰气动特性风洞试验方法,采用六自由度并联机构实现舰船姿态模拟,采用主从模式同步方法实现直升机模型载荷和舰船姿态的同步采集,通过计算机控制实现舰船单自由度或多自由度的组合运动模拟,提高了舰船姿态模拟的准确性,通过主从同步模式,实现了舰船姿态和直升机载荷的同步采集,可获取丰富的数据,对分析和研究舰船姿态与直升机载荷之间的影响关系,具有重要意义。


    Zugriff

    Download


    Exportieren, teilen und zitieren



    Titel :

    Helicopter landing aerodynamic characteristic wind tunnel test method


    Weitere Titelangaben:

    一种直升机着舰气动特性风洞试验方法


    Beteiligte:
    CHE BINGHUI (Autor:in) / SHI ZHEYU (Autor:in) / PENG XIANMIN (Autor:in) / ZHANG GUICHUAN (Autor:in) / LUO HUAN (Autor:in) / ZHAO GUANGYIN (Autor:in)

    Erscheinungsdatum :

    2023-04-04


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Chinesisch


    Klassifikation :

    IPC:    G01M TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES , Prüfen der statischen oder dynamischen Massenverteilung rotierender Teile von Maschinen oder Konstruktionen / 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



    Wind tunnel test device and method for rotation aerodynamic characteristics of object hung on helicopter

    CHE BINGHUI / HUANG ZHIYUAN / SHI ZHEYU et al. | Europäisches Patentamt | 2023

    Freier Zugriff

    Helicopter rotor model icing wind tunnel test method

    YUAN HONGGANG / HUANG MINGQI / PENG XIANMIN et al. | Europäisches Patentamt | 2020

    Freier Zugriff

    Wind tunnel test method for measuring unsteady aerodynamic coefficient in take-off and landing process of airplane

    ZHANG JUNYI / CHEN HAO / BU CHEN | Europäisches Patentamt | 2023

    Freier Zugriff

    EXPERIMENTING ROTORCRAFT FLIGHT IN COMPLEX ENVIRONMENTAL CONDITIONS USING THE WIND TUNNEL: HELICOPTER SHIP LANDING CASE

    Taymourtash, N. / Zanotti, A. / Gibertini, G. et al. | British Library Conference Proceedings | 2022


    Helicopter wind tunnel tests

    Ross, R.S. | Engineering Index Backfile | 1947