A deployment or hinge mechanism for a compact unmanned aerial vehicle (UAV) comprises first and second wing mounts 135,145 that are formed on tube and sleeve structures and which are rotatable relative to each other in a helical fashion. The helical motion is defined by virtue of a helical slot 135b cooperating with an annular slot 145a in respective mounts with a pin 155 extending through these slots. In a retracted configuration wings 200, which are connected to the wing mounts, are arranged one above the other within a tubular aircraft fuselage. The wings are moved to a deployed configuration by relative motion between sleeve and tube causing the wings to move to a configuration where they extend in the same plane but on opposite sides of the fuselage. An actuating mechanism may include a biasing spring to help in the rapid deployment of the wings.


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    Title :

    Deployment mechanism


    Contributors:

    Publication date :

    2017-04-19


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    B64C AEROPLANES , Flugzeuge



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