Integration between unmanned aerial system and unmanned ground robotic vehicle are disclosed herein. One variation of a robotic system may generally comprise an unmanned aerial vehicle (UAV), an unmanned ground vehicle (UGV), and a base station configured to receive the UAV and replace a spent power supply cartridge from the UAV and further having a charging mechanism configured to wirelessly transfer power to the UGV when the UGV is positioned in proximity to the charging pad.

The present disclosure provides distributed drive systems and methods of use thereof A distributed drive system may comprise one or more coils, one or more magnets, and at least one tread. A method for a distributed drive system may comprise the utilization of a plurality of voltage phases. The coils may comprise conductive wiring wrapped in a predefined form. In some embodiments, the coils may alternate in polarity. In some implementations, the coils may be attached directly to the frame of a larger machine or vehicle for uniform heat distribution. The magnets may comprise composite materials with ferrous portions. When the system comprises at least one tread, magnets may be embedded within the tread. In some aspects, the distributed drive system may be contained within a motive system of a machine or vehicle, thereby limiting the need for a transmission between a power source and the motive components of the machine or vehicle.

Unmanned aerial vehicle (UAV) including an inner frame, an inner flight propulsion system mounted on the inner frame, an outer frame, a gimbal system comprising at least two rotational couplings coupling the inner propulsion system to the outer frame, a control system, a power source, and an outer frame actuation system configured to actively orient the outer frame with respect to the inner frame.

An aerial vehicle comprising: at least three support arms for interconnecting at least three motors; at least one battery module; at least one of the support arms is configured to support the at least one battery module such that the battery module forms a structural element of the support arm.

A remote health care apparatus is disclosed that incorporates a drone device and a health kit. The drone device includes one or more communication devices, and the drone device is capable of two-way auditory and visual communication. The health kit is capable of being transported by the drone device and can be detached from the drone device. In one embodiment, the health kit contains one or more medical devices selected from the group consisting of biometric measuring devices, specimen collection devices and lab testing tools.

A motor assembly that includes a motor having a motor casing, a rotatable shaft extending from said motor casing to a shaft length and a hub coupled to said rotatable shaft, the hub having a circumferential skid surface disposed immediately proximal to the motor casing and having a channel configured to seat a propeller, when a propeller is present, wherein a bending moment applied to the shaft through the hub results in the circumferential skid surface contacting said motor casing.

An aircraft (100) includes a body (10) and an outer frame (1) rotatably coupled to the body (10). The body (10) includes a plurality of rotary blades (15a-15d) and a driver (14a-14d) configured to rotate the plurality of rotary blades (15a-15d). The outer frame (1) includes a rotary frame (1a-1c) rotatable about a rotation axis intersecting the direction of gravity, and a center of gravity of the plurality of rotary blades (15a-15d) and the driver (14a-14d) is located lower than the rotation axis in the direction of gravity.

To prove a motor capable of suppressing labor and costs even when the motor may be subjected to a large impact be used for a floating mobile body such as a drone. The motor (1) includes a shaft (41), a cartridge (4) including a plurality of bearings (42) that support the shaft (41), and a sleeve (43) that surrounds the bearings (42), and a housing (5) including a bottom portion (51) for receiving an impact from outside and an attaching portion (54) provided in the bottom portion (51). The bottom portion (51) of the housing (5) extends in a direction intersecting with respect to a longitudinal direction of the shaft (41), and the cartridge (4) is removably attached to the attaching portion (54).

An aero wind power generation apparatus includes: a drone unit including drone wings configured to make the aero wind power generation apparatus move and hover and a sensor unit configured to detect information for controlling the aero wind power generation apparatus; a buoyancy generation unit connected to the drone unit and including a side cover configured to open or close and a balloon provided inside the side cover, wherein the buoyancy generation unit is configured to enable injection of gas into or release of the gas from the balloon; and a power generation unit connected to the buoyancy generation unit and including a rotating unit with a plurality of blades, a blade control unit of adjusting the state of the blades, and a motor unit of converting kinetic energy transferred from the rotating unit into electrical energy.

A method is provided. An airship is maneuvered to a desired location and oriented with the thruster such that ambient wind is traveling in a direction that is substantially parallel to the longitudinal axis of the fuselage. The airflow from the ambient wind is straightened with the flow straightener to generate a substantially laminar flow. The turbine is engaged with the airflow generated by the ambient wind to generate electricity, and the electricity generated by the turbine is rectified with the rectifier and stored in the storage array.