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.
Deployment mechanism
2017-04-19
Patent
Elektronische Ressource
Englisch
IPC: | B64C AEROPLANES , Flugzeuge |