A projectile-launched aircraft system includes a projectile launcher including a triggering mechanism, a rotary-wing, hover-capable aircraft including a rotor assembly that includes at least one rotor blade, wherein the rotor blade includes a stowed configuration and a deployed configuration that is circumferentially spaced from the stowed configuration about a pivot axis, wherein, upon actuation of the triggering mechanism, the projectile launcher is configured to launch the aircraft along a flightpath.

A projectile-launched aircraft system includes a projectile launcher including a triggering mechanism, a rotary-wing, hover-capable aircraft including a rotor assembly that includes at least one rotor blade, wherein the rotor blade includes a stowed configuration and a deployed configuration that is circumferentially spaced from the stowed configuration about a pivot axis, wherein, upon actuation of the triggering mechanism, the projectile launcher is configured to launch the aircraft along a flightpath.

Systems and methods for a vehicle-compatible drone. In one embodiment, a computer-implemented method includes providing a drone having a plurality of blades and an expansion device. The expansion device is adapted to reconfigure the position of at least one blade of the plurality of blades from a first configuration of the drone to a second configuration of the drone. The computer-implemented method also includes identifying the drone being in a first mode that is associated with the first configuration. The computer-implemented method further includes detecting a trigger signal based on an event. The computer-implemented method includes transmitting a transition signal configured to cause the drone to transition to the second mode that is associated with the second configuration.

Systems and methods for a vehicle-compatible drone. In one embodiment, a computer-implemented method includes providing a drone having a plurality of blades and an expansion device. The expansion device is adapted to reconfigure the position of at least one blade of the plurality of blades from a first configuration of the drone to a second configuration of the drone. The computer-implemented method also includes identifying the drone being in a first mode that is associated with the first configuration. The computer-implemented method further includes detecting a trigger signal based on an event. The computer-implemented method includes transmitting a transition signal configured to cause the drone to transition to the second mode that is associated with the second configuration.

The invention discloses a vertical take-off and landing triphibian flight vehicle that can travel on land, water and air. These three traveling modes are realized by changing the position of the propeller module. The vehicle has retractable and foldable wings and has the accommodate space in the vehicle body to store the wings. When the vehicle is in land mode, the wings are stowed in the accommodate space to reduce the size of the vehicle and the air resistance. When the vehicle is in flight mode, the wings can be extended out of the accommodate space through the control system, so that the vehicle can use the wings to obtain aerodynamic force to counter gravity, thereby reducing the energy consumption required for countering gravity during flight and increasing the flight mileage.

An unmanned flying device including a body; a first blade and at least a second blade; a coupling assembly for coupling the first blade and the at least second blade to the body, wherein the coupling assembly urges the collapsing of the first blade and the at least second blade towards the body; and wherein both the first blade and the at least second blade are rotatable about the body, and wherein the first blade and the at least second blade are deployable away from the body via rotation of the first and the at least second blades about the body.

An unmanned flying device including a body; a first blade and at least a second blade; a coupling assembly for coupling the first blade and the at least second blade to the body, wherein the coupling assembly urges the collapsing of the first blade and the at least second blade towards the body; and wherein both the first blade and the at least second blade are rotatable about the body, and wherein the first blade and the at least second blade are deployable away from the body via rotation of the first and the at least second blades about the body.

A rotor blade attachment assembly for use with a rotor hub to which a rotor blade assembly is connected includes a hub extender having an inboard end and an outboard end. The inboard end of the hub extender is configured to form a connection with the rotor hub. A blade fold axis about which the rotor blade rotates relative to the rotor hub is defined at the connection. An inboard bearing is mounted within an interior of the hub extender adjacent the inboard end and an outboard hearing is mounted within the interior of the hub extender adjacent the outboard end. A tension torsion strap is operably coupled to the inboard bearing and the outboard bearing.

A rotor blade attachment assembly for use with a rotor hub to which a rotor blade assembly is connected includes a hub extender having an inboard end and an outboard end. The inboard end of the hub extender is configured to form a connection with the rotor hub. A blade fold axis about which the rotor blade rotates relative to the rotor hub is defined at the connection. An inboard bearing is mounted within an interior of the hub extender adjacent the inboard end and an outboard hearing is mounted within the interior of the hub extender adjacent the outboard end. A tension torsion strap is operably coupled to the inboard bearing and the outboard bearing.

A rotor includes a rotor axis, two elongate blades, a hub on the rotor axis, and a rotational drive system on the rotor axis. The hub supports the blades for pivotation relative thereto, including folding one blade over the hub between radial opposition with the other blade about the rotor axis and alongside the other blade. The rotational drive system supports the blades on the hub for rotation about the rotor axis, and supports the blades on the hub for teetering.