A Hold Down Release Mechanism, HDRM, interface (8) for attachment of a spacecraft (3) to an adjacent structure of a launch vehicle (1) or of another spacecraft (54), wherein the HDRM interface (8) is configured for forming part of a single-point or multipoint releasable attachment of the spacecraft (3) to said adjacent structure. The HDRM interface (8) comprises a first connector part (11) and a second connector part (12), wherein one of the first and second connector parts (11, 12) is configured to be fastened to said adjacent structure, and the other of the first and second connector parts (11, 12) is configured to be fastened to the spacecraft (3); wherein the first connector part (11) has a tapered projection (19) with a non-circular external surface; wherein the second connector part (12) has a matching formed tapered recess (20) with a non-circular interior surface configured for form-lockingly receiving the tapered projection (19), for enabling transfer of at least torsion load and shear load between the first and second connector parts (11, 12), when the tapered projection (19) is inserted in the tapered recess (20) and the first and second connector parts (11, 12) are pressed together; and wherein both the tapered projection (19) of the first connector part (11) and the tapered recess (20) of the second connector part (12) have a central through-hole (22, 23) for receiving a release bolt (47) configured to clamp the first and second connector parts (11, 12) together.


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    Title :

    A SEPARABLE CLAMPED HDRM INTERFACE FOR MANAGING TORSION LOADS


    Additional title:

    TRENNBAR EINGESPANNTE HDRM-SCHNITTSTELLE ZUR VERWALTUNG VON TORSIONSBELASTUNGEN
    INTERFACE HDRM FIXÉE SÉPARABLE POUR GÉRER DES CHARGES DE TORSION


    Contributors:

    Publication date :

    2023-05-17


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    B64G Raumfahrt , COSMONAUTICS



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