In an embodiment an unmanned aerial vehicle comprises a central body and a plurality of support structures extending outwards from the central body. Each support structure supports a rotor blade assembly and is provided with one or more deformable portions. The rotor blade assembly defines a rotational axis of one or more rotor blades associated with the rotor blade assembly.

A landing gear device for reducing crash landings includes a mounting assembly that is configured to couple to a bottom of a vertical take-off and landing aircraft, such as a remotely controlled helicopter. Each of a plurality of rods, which are resiliently flexible, is coupled to and extends transversely from the mounting assembly to define a pyramid, with the mounting assembly being positioned at an apex of the pyramid. The plurality of rods is configured to reduce a frequency of crash landings of the vertical take-off and landing aircraft.

A mechanical joiner for an airframe includes a joiner core and first and second caps. The joiner core has a first side with a first cradle shaped to hold a first structural member and a second side with a second cradle shaped to hold a second structural member. The first cap is shaped to mate to the first side and clamp the first structural member into the first cradle. The joiner core includes a first hole for a first mechanical fastener to extend through and across the first cradle and secure the first cap to the joiner core. The second cap is shaped to mate to the second side and clamp the first structural member into the second cradle. The second cap includes second holes for second mechanical fasteners, distinct from the first mechanical fastener, to secure the second cap to the joiner core.

The present disclosure is directed to systems and methods too of implementing a hybrid robotic system capable of reversibly transitioning producing propulsion units may be coupled to the payload platform. In a first position, the payload platform may be positioned such that the thrust-producing propulsion units generate a substantially horizontal thrust to provide horizontal movement of the robotic system. In a second position, the payload platform may be positioned such that the thrust-producing propulsion units generate a substantially vertical thrust to provide vertical movement of the robotic system.

The present disclosure is directed to systems and methods too of implementing a hybrid robotic system capable of reversibly transitioning producing propulsion units may be coupled to the payload platform. In a first position, the payload platform may be positioned such that the thrust-producing propulsion units generate a substantially horizontal thrust to provide horizontal movement of the robotic system. In a second position, the payload platform may be positioned such that the thrust-producing propulsion units generate a substantially vertical thrust to provide vertical movement of the robotic system.

A drone includes a frame and a plurality of motors attached to the frame. Each motor of the plurality of motors is connected to a respective propeller located below the frame. A tail motor is attached to the frame. The tail motor is connected to a tail propeller located above the frame. Cameras are attached to the frame and located above the frame. The cameras have fields of view extending over the plurality of propellers.

Methods and systems are provided for responding to an attacker including a shooter who opens fire at a site where people are gathered, including identifying, neutralizing, and restraining the attacker. A system may include a central control unit configured to receive signals indicative of gun fire, to responsively determine an origin of the gun fire, to identify features of a shooter associated with the gun fire and to release a UAV from a shielded UAV housing to engage the shooter. The UAV may be configured to fly towards the shooter, according to the origin of the gun fire and the identifying features of the shooter, and to neutralize the shooter by operating a UAV incapacitating mechanism.

A heavy-lift UAV frame includes a central frame portion having a symmetrical shape and forming a pocket area for receiving an avionics package. Top and bottom plates are secured to the central frame portion and include four corner members that extend diagonally outward therefrom. A plurality of boom hinges are interposed between each of the corner members and an elongated boom arm. Each of the boom hinges pivot the boom arms between an extended position for flight and a retracted position for storage and transport. Each boom arm and hinge combination includes a complementary dimension to one side of the central frame portion to position a boom arm parallel thereto when in the retracted position.

An integrated multimode thermal energy transfer system, method and apparatus for full-scale clean fuel electric-powered multirotor aircraft with automatic on-board-capability to provide sensor-based temperature awareness and adjustment to critical components and zones of the aircraft. Automatic computer monitoring, including by a programmed triple-redundant digital autopilot computer, controls each motor-controller and motor to produce pitch, bank, yaw and elevation, while simultaneously measuring, calculating, and adjusting temperature and heat transfer of aircraft components and zones, to protect critical components from exceeding operating parameters and to provide a safe, comfortable environment for occupants during flight. By using the results of the measurements to inform computer monitoring, the methods and systems can use byproducts including thermal energy disparities and differentials related to both fuel supply systems and power generating systems to both add and remove heat from different aircraft zones to improve aircraft function, comfort, and efficiency.

A falling-resistant and anti-drifting unmanned aerial vehicle has a main body and at least one rotor wing thereon. Both sides of the main body have a wing with an airbag filled with gas lighter than air. Bulges protruding downwards are arranged at the bottoms of the airbag. The two airbags are at the same height symmetrically arranged based on the main body. The airbag can function as an undercarriage when the aircraft lands down, and as a buffer when crash landing and then reduce damage to the main body. If the aircraft falls in water, the aircraft can float on the water to avoid damage caused by sinking. As bulges protruding downwards are arranged at the bottoms of the airbags, in spraying operation, side wing can be relatively well baffled by the bulges in case of side wing blowing in the flying process, resulting in less droplets draft.