Foldable propeller blade with locking mechanism
An unmanned aerial vehicle with deployable components (UAVDC) may comprise a foldable propeller blade with a locking mechanism. Foldable propeller blades may have a stowed configuration and a deployed configuration relative to the UAVDC, and the foldable propeller blades may pivot about a hinge to move between configurations. In the deployed configuration, the foldable propellor may experience forward folding forces acting upon it. The locking mechanism may lock the foldable propeller blade in the deployed configuration. The locking mechanism may keep the foldable propeller locked into place to prevent forward folding tendency.
1 . An aerial vehicle comprising:
a fuselage;
at least one propeller blade configured to transition between a folded position adjacent to the fuselage and a deployed position extending from the fuselage; and
a locking mechanism operative to secure the at least one propeller blade in the deployed position to mitigate retraction forces during flight operations.
2 . The aerial vehicle of claim 1 , wherein the at least one propeller blade is subject to operational forces resulting from at least one of:
environmental airflow interactions;
rotational centrifugal activation;
mechanical transitions facilitated by ramp structures;
elastic potential energy from spring elements;
deformation resistance offered by elastomeric materials; and
mechanical actuation for deployment.
3 . The aerial vehicle of claim 1 , wherein the locking mechanism is structured to permit unidirectional movement of the at least one propeller blade from the folded position to the deployed position.
4 . The aerial vehicle of claim 1 , wherein the locking mechanism is inactive in the folded position to allow unfettered deployment of the at least one propeller blade.
5 . The aerial vehicle of claim 1 , wherein upon deployment, the locking mechanism activates to preclude any backward movement towards the folded position of the at least one propeller blade.
6 . The aerial vehicle of claim 1 , wherein the locking mechanism is characterized by comprising elements from the group consisting of:
a ratchet interfacing with a pawl for directional locking;
a spring-assisted ratchet for controlled deployment;
an engagement ramp met by a spring-actuated tab for positional locking;
a mechanical hook for secure locking;
a spring-propelled pin for positional engagement;
a ball and detent arrangement for secure locking;
interfacing ramped surfaces for mechanical engagement;
radially designed surfaces for locking interaction;
an actuator-driven pin for secure positioning;
a component designed to jam against movement for locking; and
magnetic components for secure locking engagement.
7 . An unmanned aerial vehicle comprising:
a fuselage;
at least one foldable propeller blade pivotally connected to the fuselage and movable between a stowed position proximate to the fuselage and a deployed position extending away from the fuselage to generate propulsion in a pusher configuration; and
a locking mechanism operatively coupled to the at least one foldable propeller blade to restrict movement towards the stowed position when in the deployed position due to aerodynamic forces encountered during flight.
8 . The unmanned aerial vehicle of claim 7 , wherein the at least one foldable propeller blade is configured to unfold in response to at least one of aerodynamic forces, mechanical actuation, or centrifugal forces when transitioning from the stowed position to the deployed position.
9 . The unmanned aerial vehicle of claim 7 , wherein the locking mechanism comprises a mechanical interlock feature that engages automatically when the at least one foldable propeller blade reaches the deployed position.
10 . The unmanned aerial vehicle of claim 7 , wherein the locking mechanism includes a manually actuated release mechanism for folding the at least one foldable propeller blade from the deployed position back to the stowed position.
11 . The unmanned aerial vehicle of claim 7 , wherein the locking mechanism is integral to a hinge assembly that pivotally connects the at least one foldable propeller blade to the fuselage.
12 . The unmanned aerial vehicle of claim 7 , further comprising a controller configured to control the movement of the at least one foldable propeller blade between the stowed position and the deployed position.
13 . The unmanned aerial vehicle of claim 7 , wherein the at least one foldable propeller blade comprises a plurality of blades, each blade being independently movable between the stowed position and the deployed position.
14 . The unmanned aerial vehicle of claim 7 , wherein the locking mechanism further comprises a biasing member that urges the at least one foldable propeller blade towards the deployed position.
15 . The unmanned aerial vehicle of claim 7 , wherein the locking mechanism is configured to engage and disengage based on the rotational speed of the at least one foldable propeller blade.
16 . The unmanned aerial vehicle of claim 7 , further comprising a sensor configured to detect the position of the at least one foldable propeller blade and provide feedback to a control system for maintaining the deployed position during flight.
17 . The unmanned aerial vehicle of claim 7 , wherein the at least one foldable propeller blade is configured to deploy from the stowed position to the deployed position using at least one selected from a group consisting of: a linear actuator, a rotary actuator, and a shape memory alloy actuator.
18 . An unmanned aerial vehicle comprising:
a fuselage;
at least one foldable propellor blade pivotally connected to the fuselage and configured to transition between a stowed configuration and a deployed configuration for propulsion;
a hinge mechanism facilitating the pivotal connection of the at least one foldable propellor blade to the fuselage; and
a locking mechanism operatively associated with the at least one foldable propellor blade to maintain the at least one foldable propellor blade in the deployed configuration against forces tending to fold the blade forward towards the fuselage.
19 . The unmanned aerial vehicle of claim 18 , wherein the at least one foldable propellor blade is subjected to aerodynamic forces during flight operations, the locking mechanism configured to resist said forces to prevent involuntary folding of the at least one foldable propellor blade.
20 . The unmanned aerial vehicle of claim 18 , wherein the locking mechanism comprises a mechanical interlock engaging when the at least one foldable propellor blade is in the deployed configuration.