An unmanned aerial device having cleaning function includes a fuselage, a washing assembly and two propulsion assemblies. The washing assembly is disposed at a head of the fuselage. The propulsion assemblies are connected to two opposite sides of the fuselage. The two opposite sides are connected to the head. The propulsion assemblies each have an axial direction, and the axial direction is parallel to a direction from a bottom of the fuselage to a top of the fuselage.

A computer-implemented method, system, and/or computer program product optimizes an operation of an aerial drone. A drone on-board computer on an aerial drone receives sensor readings from sensors on the aerial drone, where the sensor readings detect a change in flight conditions while the aerial drone is flying between a first location and a second location. In response to the sensors on the aerial drone detecting a change in the flight conditions while the aerial drone is flying between the first location and the second location, the drone on-board computer disengages an electric motor from propellers on the aerial drone and engages an internal combustion engine to the propellers.

A rotor system for an aircraft includes a rotor assembly comprising a plurality of rotor blades connected to a rotor mast, wherein the rotor assembly is tiltable relative to a wing of the aircraft between a first position corresponding to an airplane mode of the aircraft and a second position corresponding to a helicopter mode of the aircraft; and a drive system for providing rotational energy to the rotor assembly via the rotor mast. The drive system includes at least one electric motor for generating rotational energy to a motor shaft; and a gearbox connected to receive rotational energy from the at least one electric motor via the motor shaft and to provide rotational energy to the rotor mast via a rotor shaft, wherein the at least one electric motor is fixed relative to the wing of the aircraft.

A propulsion system includes a motor, the motor disposed at a center portion of the propulsion system, the motor further including a rotor shaft. The system includes a splitter gearbox coupled to the rotor shaft, the splitter gearbox further comprising at least one splitter output shaft. The system includes at least one continuously variable transmission (CVT), the CVT coupled to the splitter output shaft, the CVTs further including a driveshaft. The system includes at least one bevel gearbox, the bevel gearbox comprising a bevel gearbox input shaft and a bevel gearbox output shaft, the bevel gearbox input shaft disposed parallel to the horizontal plane and the bevel gearbox output shaft disposed at an angle to the bevel gearbox input shaft, wherein the bevel gearbox input shaft is coupled to the driveshaft. The system includes at least one propeller coupled to the bevel gearbox output shaft.

A computer-implemented method, system, and/or computer program product optimizes an operation of an aerial drone. A drone on-board computer on an aerial drone receives sensor readings from sensors on the aerial drone, where the sensor readings detect a change in flight conditions while the aerial drone is flying between a first location and a second location. In response to the sensors on the aerial drone detecting a change in the flight conditions while the aerial drone is flying between the first location and the second location, the drone on-board computer disengages an electric motor from propellers on the aerial drone and engages an internal combustion engine to the propellers.

A flying object 20 is provided with a rotor blade 200 that generates lift and thrust by rotating and a rotating electrical machine unit that rotates the rotor blade 200. The rotor blade 200 receive wind power and rotate when not flying. The rotating electrical machine unit generates electric power based on a power that rotates the rotor blades 200 when not flying. In addition, the flying object 20 may be provided with a power storage device 230 that stores electric power generated by the rotating electrical machine unit. In addition, the flying object 20 may be provided with a detachably connected cartridge 260 that has a desired function.

A vehicle and method of control comprising generating a geometric control envelope in a geometric space of operation points defined by a number of control aspects, the envelope having vertices representing maximum values of the control aspects, and determining a desired operation point in the geometric space representing a control input. Further, the method includes if the desired operation point is outside the envelope, scaling up a first one of the control aspects by a first factor, determining an effective operation point in the envelope geometrically closest to the desired operation point, scaling down all of the control aspects by a second factor inverse of the first factor, and instructing the propulsion mechanisms to propel the vehicle according to the effective operation point.

A computer-implemented method, system, and/or computer program product optimizes an operation of an aerial drone to transport a product to a customer. Processor(s) receive an order for a product from a customer. In response to determining that the customer is authorized to have the product delivered by the aerial drone, the processor(s) identify a weight, size, item type, and value of the product, and determine whether the aerial drone is physically able to lift and transport the product, based on a distance to the customer and a cost effectiveness of using the aerial drone over another mode of transportation. The aerial drone is coupled to the product and launched. In response to sensors on the aerial drone detecting a change in flight conditions while the aerial drone is flying to the customer, a drone on-board computer disengages an electric motor and engages an internal combustion on the aerial drone.

A spherical drone and a control method thereof relate to a field of drones. The spherical drone includes a main shell defines an accommodating space, an inner support arranged in the accommodating space, a main control board, a power supply, a motor, a fixing shaft, an upper blade and an lower blade rotatably arranged on the fixing shaft, and a first crown gear and a second crown gear arranged on the inner support. Slotted holes are defined on the main shell. The first crown gear and the second crown gear are sleeved on the fixing shaft. The upper blade is fixed on the first crown gear. The lower blade is fixed on the second crown gear. The motor drives the first crown gear and the second crown gear to rotate, so as to simultaneously drive the upper blade and the lower blade to rotate.

Rotary-wing aircraft, comprising: a drive motor (12) with a motor output shaft (12-3), a transfer gearbox (14) having the motor output shaft (12-3) as an input and having a first output (14-1) and a second output (14-2), a cockpit with associated cockpit electronics, a rotary wing with rotor and blades, a tail and tail rotor (20) with a drive shaft (20-1) for driving the tail rotor, and a skids unit with equipment suited to the intended application, characterized in that the motor shaft (12-3) of the motor (12), the transfer gearbox (14) with its second output (14-2) and the drive shaft (20-1) that drives the tail rotor (20) are aligned.