The invention relates to the technical field of aircraft design, and discloses an aircraft design test heat preservation sealing system and a parameter optimization method thereof. The system comprises a warehouse plate, a large-section air duct penetrating through the warehouse plate, and a heat preservation sealing structure connecting the warehouse plate and the large-section air duct, wherein a crossing opening is formed in the warehouse plate; and the heat preservation sealing structure comprises a glass fiber reinforced plastic frame arranged on the crossing opening and heat preservation filler filled between the glass fiber reinforced plastic frame and the large-section air duct. The parameter optimization method comprises the following steps of S1, determining the shape and the size of the crossing opening; S2, designing the shape and the size of the glass fiber reinforced plastic frame, and enabling the glass fiber reinforced plastic frame to be matched with the crossing opening; and S3, controlling the thicknesses of the heat preservation filler, a polyurethane pouring foaming layer, a rubber heat preservation layer and a flexible silicone rubber layer. According to the aircraft design test heat preservation sealing system and the parameter optimization method thereof provided by the invention, the problem of poor sealing safety of a connector for the air duct and the warehouse plate in an aircraft climate laboratory in an extreme environment can be solved, and the connector for the air duct and the warehouse plate is ensured to be well sealed in a contact area in an extreme temperature and severe vibration environment.

    本发明涉及飞机设计技术领域,公开了一种飞机设计试验保温密封系统及其参数优化方法,所述系统包括库板,贯穿所述库板的大截面风道,连接所述库板与大截面风道的保温密封结构;所述库板上设置有穿越口;所述保温密封结构包括设置在所述穿越口上的玻璃钢框体,填充在所述玻璃钢框体、大截面风道之间的保温填充物;参数优化方法包括:S1、确定穿越口形状与大小;S2、设计玻璃钢框体的形状与大小,使其与穿越口相适配;S3、控制保温填充物、聚氨酯灌注发泡层、橡胶保温层、以及柔性硅橡胶层的厚度;本发明能够解决飞机气候实验室在极端环境下风道与库板接口密封安全性差的问题,保证风道、库板连接口在极端温度、振动剧烈环境下,接触区域密封良好。


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    Titel :

    Aircraft design test heat preservation sealing system and parameter optimization method thereof


    Weitere Titelangaben:

    一种飞机设计试验保温密封系统及其参数优化方法


    Beteiligte:
    WANG BINWEN (Autor:in) / CAO QI (Autor:in) / LU GUOJIE (Autor:in) / WU JINGTAO (Autor:in) / LI XUAN (Autor:in)

    Erscheinungsdatum :

    2022-01-18


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Chinesisch


    Klassifikation :

    IPC:    F16L PIPES , Rohre / 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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