A modular unmanned aerial system includes a chassis for attaching components of the modular unmanned aerial system and one or more rotary wings. Each of the one or more rotary wings is drivable by a respective motor. A central controller is provided for controlling operation of the modular unmanned aerial system. A modular interface portion attached to the chassis and adapted for removably mounting one or more modular devices.

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 propeller 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.

A water-air amphibious cross-medium bio-robotic flying fish includes a body, pitching pectoral fins, variable-structure pectoral fins, a caudal propulsion module, a sensor module and a controller. The caudal propulsion module is controlled to achieve underwater fish-like body-caudal fin (BCF) propulsion, and the variable-structure pectoral fins is adjusted to achieve air gliding and fast splash-down diving motions of the bio-robotic flying fish. The coordination between the caudal propulsion module and the pitching pectoral fins is controlled to achieve the motion of leaping out of water during water-air cross-medium transition. The ambient environment is detected by the sensor module, and the motion mode of the bio-robotic flying fish is controlled by the controller.

The present invention relates to an unmanned helicopter. The unmanned helicopter comprises a fuselage. Two arms are respectively disposed on each of two sides of the fuselage. One end of each arm is connected to the fuselage, and the other end of each arm is provided with a rotor having a motor. The unmanned helicopter is characterized in that: the four arms are grouped into a front group and a rear group, two arms in each group are disposed symmetrically along the axis of the fuselage, the fuselage is movably connected to each arm, an angle between a length direction of any one of the two arms in each group and a corresponding rotation axis is an angle r, an angle between the rotation axis and a horizontal surface of the fuselage is an angle a, and an angle between a projection line of the rotation axis on the horizontal surface of the fuselage and the axis direction that extends outward the fuselage is an angle b. By ingeniously selecting values of the angle a, the angle r and the angle b, the structure of the unmanned helicopter in a folded state is very compact, thereby effectively saving space.

Various embodiments are described of an unmanned aerial vehicle having a wing. The unmanned aerial vehicle includes a first body of the wing with a first end proximate a body of the vehicle. A second end is opposite the first end. A first joint is on the first end of the first main body of the wing. The joint rotatably couples the wing to the vehicle. A second joint is on the second end of the vehicle. A second body of the wing is rotatably coupled to the first body via the second joint.

An aerial device is provided. The aerial device includes a processor and a memory that includes instructions configured to cause the processor to perform certain operations when the processor executes the instructions. The operations may include receiving a first signal indicative of a first position of the aerial device. The operations may also include generating, based on the first signal and based on a randomly or pseudo-randomly generated sequence, a second signal configured to actuate flight hardware of the aerial device to a second position.

One embodiment is an aircraft including a main body, a plurality of propulsion assemblies, and a plurality of hinges, wherein each of the plurality of propulsion assemblies is rotatably coupled to the main body using a hinge from the plurality of hinges. In an example, the aircraft includes four motor support arms and each motor support arm rotatably couples a specific propulsion assembly to a specific corresponding hinge on the main body of the aircraft and increases a span of the aircraft when the aircraft is in the flight configuration and reduces the footprint of the aircraft when the aircraft is in a storage configuration.

Unmanned vehicles may be terrestrial, aerial, nautical, or multi-mode. Unmanned vehicles may accomplish tasks by breaking out into sub-drones, re-grouping itself, changing form, or re-orienting its sensors.

An unmanned aerial vehicle is provided, including an airframe including a fuselage and at least one stowable wing. The unmanned aerial vehicle can further include a radar panel positioned on the fuselage such that the radar panel is angled downward and extends longitudinally along a ventral region of the fuselage. The unmanned aerial vehicle can further include a drop-away rocket engine that is configured to detachably mount to the airframe adjacent the radar panel.

An unmanned aerial vehicle (UAV) adapted for transit in and deployment from a projectile casing is provided. The UAV includes a wing assembly coupled to the projectile casing and the wing assembly moveable between a closed position and a deployed position. The UAV further includes a propulsion system including at least one rotor disposed on the wing assembly to generate lift, wherein in the closed position, the wing assembly is substantially integral with the projectile casing and in the deployed position, the wing assembly is extended outwards from the projectile casing.