An unmanned aerial vehicle is provided and includes: an unmanned aerial vehicle body, including an airframe and an articles storing device; an arm, including at least two front arms symmetrically arranged with respect to a central axis of the airframe along a front-rear direction and at least two rear arms symmetrically arranged with respect to the central axis of the airframe; and a rotor-wing electric motor, including a front electric motor and a rear electric motor. A first end of the front arm is connected with a front end of the airframe, and a second end of the front arm is provided with the front electric motor to drive the unmanned aerial vehicle. A first end of the rear arm is connected with a rear end of the airframe, and a second end of the rear arm is provided with the rear electric motor to drive the unmanned aerial vehicle.

An unmanned aerial vehicle is provided and includes: an unmanned aerial vehicle body, including an airframe and an articles storing device; an arm, including at least two front arms symmetrically arranged with respect to a central axis of the airframe along a front-rear direction and at least two rear arms symmetrically arranged with respect to the central axis of the airframe; and a rotor-wing electric motor, including a front electric motor and a rear electric motor. A first end of the front arm is connected with a front end of the airframe, and a second end of the front arm is provided with the front electric motor to drive the unmanned aerial vehicle. A first end of the rear arm is connected with a rear end of the airframe, and a second end of the rear arm is provided with the rear electric motor to drive the unmanned aerial vehicle.

Methods and systems to electrically assist an internal combustion engine of an aircraft may be provided. A first bladed rotor may be rotated by a first internal combustion engine. Electricity may be generated from a first motor generator by rotating a first shaft of the first motor generator with the first internal combustion engine. In response to a predetermined event, such as an engine failure, mechanical power may be generated from the first motor generator instead of electricity. The mechanical power may be transferred to the first bladed rotor. The mechanical power may be generated by applying electricity to the first motor generator. The electricity applied is received from a second motor generator, where the electricity received from the second motor generator is generated by rotating a second shaft of the second motor generator with a second internal combustion engine that powers a second bladed rotor.

A waterproof unmanned aerial vehicle includes an airframe, a first gasket, and a breathability member. The airframe includes an upper cover, a below cover assembled to the upper cover, and a receiving room. The upper cover includes a first protruding portion projecting from a bottom surface of the upper cover and a plurality of breathable holes in communication with the receiving room. The below cover defines a first receiving groove located in a top surface of the below cover. The first gasket is received in the first receiving groove, and the first protruding portion presses the first gasket to seal the upper cover and the below cover. The at least one breathability member includes a waterproof film covering the plurality of breathable holes to prevent water seep into the airframe and a fixing cover to fix the waterproof film on the upper cover.

A waterproof unmanned aerial vehicle includes an airframe, a first gasket, and a breathability member. The airframe includes an upper cover, a below cover assembled to the upper cover, and a receiving room. The upper cover includes a first protruding portion projecting from a bottom surface of the upper cover and a plurality of breathable holes in communication with the receiving room. The below cover defines a first receiving groove located in a top surface of the below cover. The first gasket is received in the first receiving groove, and the first protruding portion presses the first gasket to seal the upper cover and the below cover. The at least one breathability member includes a waterproof film covering the plurality of breathable holes to prevent water seep into the airframe and a fixing cover to fix the waterproof film on the upper cover.

A takeoff and landing control method of a multimodal air-ground amphibious vehicle includes: receiving dynamic parameters of the multimodal air-ground amphibious vehicle; processing the dynamic parameters by a coupled dynamic model of the multimodal air-ground amphibious vehicle to obtain dynamic control parameters of the multimodal air-ground amphibious vehicle, wherein the coupled dynamic model of the multimodal air-ground amphibious vehicle comprises a motion equation of the multimodal air-ground amphibious vehicle in a touchdown state; and the motion equation of the multimodal air-ground amphibious vehicle in a touchdown state is determined by a two-degree-of-freedom suspension dynamic equation and a six-degree-of-freedom motion equation of the multimodal air-ground amphibious vehicle in the touchdown state; and controlling takeoff and landing of the multimodal air-ground amphibious vehicle according to the dynamic control parameters of the multimodal air-ground amphibious vehicle. The method is used for takeoff and landing control of a multimodal air-ground amphibious vehicle.

An unmanned vehicle is provided. The unmanned vehicle includes: a base; a driving unit including an actuator and a propeller rotating by using power of the actuator, the driving unit being provided outside the base capable of pivoting with respect to the base; and a supporter protruding from the base and supporting the base.

An unmanned vehicle is provided. The unmanned vehicle includes: a base; a driving unit including an actuator and a propeller rotating by using power of the actuator, the driving unit being provided outside the base capable of pivoting with respect to the base; and a supporter protruding from the base and supporting the base.

A multicopter (100) having a plurality of propellers (1) is configured to be electrically operated. The multicopter (100) is provided with electric motors (2), at least one main battery (3), a generator (4), an engine (5), and a battery condition detecting section (71). The electric motors (2) drive the propellers (1). The main battery (3) is a first electric power source that supplies the electric power to the electric motors (2). The generator (4) is a second electric power source that supplies the electric power to the electric motors (2). The engine (5) drives the generator (4). The battery condition detecting section (71) detects abnormality of the main battery (3). When the battery condition detecting section (71) detects the abnormality of the main battery (3), the generator (4) supplies the electric power that has been converted from motive power from the engine (5) directly to the electric motors (2).

A multicopter (100) having a plurality of propellers (1) is configured to be electrically operated. The multicopter (100) is provided with electric motors (2), at least one main battery (3), a generator (4), an engine (5), and a battery condition detecting section (71). The electric motors (2) drive the propellers (1). The main battery (3) is a first electric power source that supplies the electric power to the electric motors (2). The generator (4) is a second electric power source that supplies the electric power to the electric motors (2). The engine (5) drives the generator (4). The battery condition detecting section (71) detects abnormality of the main battery (3). When the battery condition detecting section (71) detects the abnormality of the main battery (3), the generator (4) supplies the electric power that has been converted from motive power from the engine (5) directly to the electric motors (2).