Deployment mechanism

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...

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Bibliographic Details
Main Authors Nicholas L. Barnes, Ryan M. Alderfer, Timothy J. Marley, Stephen J. Schober
Format Patent
LanguageEnglish
Published 19.04.2017
Subjects
AEROPLANES
AIRCRAFT
AVIATION
COSMONAUTICS
HELICOPTERS
PERFORMING OPERATIONS
TRANSPORTING
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Summary: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.
Bibliography:Application Number: GB20160008571