According to the assembly method for binding the rocket booster and the core level, main and auxiliary binding point layout is adopted for assembly, the auxiliary binding point is composed of two straight connecting rods and an inclined connecting rod, the auxiliary binding point is assembled after the main binding point is in butt joint, and assembly of the auxiliary binding point comprises the steps that a pair of connecting rod mounting connectors are additionally arranged except for three pairs of connecting rod mounting connectors of the auxiliary binding point, and the connecting rod mounting connectors are connected with the connecting rod mounting connectors; the two motors are respectively mounted on the booster and the core; three process connecting rods are arranged, and the length of each process connecting rod is adjustable; three process connecting rods are installed, two of the process connecting rods are connected with the two pairs of connecting rod installation connectors corresponding to the two straight connecting rods of the auxiliary binding point respectively, the third process connecting rod is connected with the additionally arranged pair of connecting rod installation connectors, and the third process connecting rod and the two process connecting rods form a certain angle; adjusting the length of each process connecting rod to the theoretical length; inclined connecting rods of the auxiliary binding points are installed; gradually dismounting the process connecting rod, and replacing the two straight connecting rods of the auxiliary binding point; and removing the pair of additionally arranged connecting rod mounting interfaces.

    本发明的一种捆绑火箭助推器与芯级的组装方法,组装采用主、辅捆绑点布局,辅捆绑点采用两根直连杆和一根斜连杆构型,主捆绑点对接后组装辅捆绑点,辅捆绑点组装包括:除辅捆绑点的三对连杆安装接口外,增设一对连杆安装接口,分别安装于助推器和芯级;设置三根工艺连杆,各工艺连杆长度可调;安装三根工艺连杆,其中,两根工艺连杆分别与辅捆绑点两根直连杆对应的两对连杆安装接口连接,第三根工艺连杆与增设的一对连杆安装接口连接,第三根工艺连杆与两根工艺连杆均成一定角度;调节各工艺连杆的长度至理论长度;安装辅捆绑点的斜连杆;逐次拆除工艺连杆,并换装辅捆绑点的两根直连杆;拆除增设的一对连杆安装接口。


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    Titel :

    Assembling method for binding rocket booster and core


    Weitere Titelangaben:

    一种捆绑火箭助推器与芯级的组装方法


    Beteiligte:
    LI XINKUAN (Autor:in) / ZHANG XING (Autor:in) / NI FEI (Autor:in) / XU LIN (Autor:in) / LOU YUNFENG (Autor:in) / LI CHENGGANG (Autor:in) / LI HAO (Autor:in)

    Erscheinungsdatum :

    2023-08-11


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Chinesisch


    Klassifikation :

    IPC:    B64G Raumfahrt , COSMONAUTICS / F42B EXPLOSIVE CHARGES, e.g. FOR BLASTING , Explosive Ladungen, z.B. für Sprengungen



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