The invention discloses an aircraft compound control wind tunnel semi-physical simulation test system. The semi-physical simulation test system comprises a flight control system, a safety protection system, a model support system, a parameter measurement system, a test model system and a high-pressure gas supply system which are arranged by taking a wind tunnel test section as a core, and also comprises signal transmission and power supply cables for connecting the systems, and a wind tunnel high-pressure air source providing high-pressure air for the high-pressure air supply system, and a high-pressure ventilation pipeline communicated with the high-pressure air supply system and the wind tunnel high-pressure air source. According to the aircraft compound control wind tunnel semi-physical simulation test system, the advantages that a large wind tunnel can achieve flight physical environment real simulation, aircraft full-size simulation, high efficiency, accuracy, low cost and repeatable simulation are fully utilized, and optimization design and performance evaluation are conducted on aircraft compound control; the development cost and the development risk of the aircraft are reduced, and the development period is shortened.

    本发明公开了一种飞行器复合控制风洞半实物仿真试验系统。该半实物仿真试验系统包括以风洞试验段为核心布置的飞行控制系统、安全保护系统、模型支撑系统、参数测量系统、试验模型系统和高压供气系统,还包括连接各系统的信号传输和电源线缆,以及为高压供气系统提供高压空气的风洞高压气源、连通高压供气系统和风洞高压气源的高压通气管路。本发明的飞行器复合控制风洞半实物仿真试验系统充分利用大型风洞能够实现飞行物理环境真实模拟、飞行器全尺寸模拟、高效准确和低成本可重复模拟的优点,对飞行器复合控制进行优化设计和性能评估,降低了飞行器研制成本、研制风险,缩短了研制周期。


    Zugriff

    Download


    Exportieren, teilen und zitieren



    Titel :

    Aircraft compound control wind tunnel semi-physical simulation test system


    Weitere Titelangaben:

    一种飞行器复合控制风洞半实物仿真试验系统


    Beteiligte:
    LI HAO (Autor:in) / ZHAO ZHONGLIANG (Autor:in) / LI HAIFENG (Autor:in) / XU YANGFAN (Autor:in) / MIAO LEI (Autor:in) / YAN LIANG (Autor:in) / YANG HAIYONG (Autor:in) / LI YUPING (Autor:in) / CHEN JIANZHONG (Autor:in) / WANG XIAOBING (Autor:in)

    Erscheinungsdatum :

    2021-08-13


    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




    Numerical Simulation of Transonic Aircraft in Comparison to Wind Tunnel Test

    J. Miyakawa / S. Takanashi / K. Fujii et al. | NTIS | 1986


    Simulation motor structure for deformable aircraft wind tunnel test and assembly method

    ZENG DEQIANG / JIE LIANG / LIN JIAN et al. | Europäisches Patentamt | 2024

    Freier Zugriff

    Wind Tunnel Test on Models of V.T.O. Aircraft

    Emslie, K. | Emerald Group Publishing | 1966


    Wind tunnel test on models of V.T.O. Aircraft

    Emslie, K. | Engineering Index Backfile | 1966