A delivery drone apparatus for automatically delivering packages includes a drone body having a body cavity. A pair of landing skids is coupled to the drone body. A battery, a CPU, and a GPS are coupled within the body cavity. A transceiver is coupled within the body cavity and is in operational communication with the battery, the CPU, and the GPS. The transceiver is configured to communicate with a smartphone. At least one camera is coupled to the drone body. The camera is in operational communication with the battery, the CPU, the GPS, and the transceiver. A plurality of motors are coupled to the drone body. Each motor has a propeller and is in operational communication with the battery and the CPU. An electromagnet is coupled to the drone body. A package magnet is selectively engageable with the electromagnet and is configured to be coupled to a package.

A flying robot executing predetermined work, the flying robot comprising: a body unit; and a propulsion portion comprising a plurality of propulsion units configured to cause propulsion to occur by driving rotor blades, the plurality of propulsion units being provided on the body unit; the flying robot further comprising: a contact support unit configured to contact a predetermined contact surface to be capable of supporting at least a part of the body unit; a sensor configured to detect an inclination of the body unit; and a control unit configured to, when the contact support unit contacts the predetermined contact surface, and the predetermined work is being performed, execute posture control to drive at least one of the plurality of propulsion units based on the inclination of the body unit detected by the sensor so that the inclination of the body unit is kept within a predetermined angle range.

One embodiment is a navigation system for an aircraft including a positioning system to generate information related to a position of the aircraft, a group of cameras mounted to a body of the aircraft, each camera of the group of cameras to simultaneously capture images of a portion of an environment that surrounds the aircraft, and a processing component coupled to the positioning system and the group of cameras, the processing component to determine a current position of the aircraft based on the information related to the position of the aircraft and the images.

The present invention discloses an unmanned aerial vehicle, including: a fuselage; a battery accommodation cavity, disposed on the fuselage; a battery pack, including at least two battery blocks and mounted inside the battery accommodation cavity; a battery circuit board, electrically connected to the battery blocks in the battery pack; and a functional module, electrically connected to the battery circuit board, the battery blocks in the battery pack supplying power to the functional module via the battery circuit board at the same time. By using the solution of the present invention, endurance of the unmanned aerial vehicle is increased.

A multi-rotor UAV (unmanned aerial vehicle) includes a fuselage, four aircraft wings and a landing stand, wherein the landing stand comprises four landing support legs, every landing support leg is installed below an outermost end of a corresponding aircraft wing to form a landing support structure of the UAV, every landing support leg comprises a main pole and a base soft rubber, wherein the base soft rubber enwraps a base of the main pole for buffering. The multi-rotor UAV of the present invention is stable while taking off or landing, and is light in weight.

Systems and methods include providing vertical takeoff and landing (VTOL) aircraft with a cargo pod having a selectively inflatable bladder system that firmly secures a payload disposed within the cargo pod when the bladder system is pressurized. The bladder system also controls the location, position, and/or orientation of the payload in order to adjust, control, and/or maintain the center of gravity of the aircraft during flight. The aircraft includes an impact protection system that further pressurizes the bladder system to protect the payload and/or that disperses a flame-retardant fluid into the cargo pod to protect electrical components of the aircraft. The aircraft is fully autonomous and self-directed via a preprogrammed location-based guidance system to allow for accurate delivery of the payload to its intended destination. The bladder system is depressurized in response to a landing event to allow for e f the payload from the cargo pod.

Thermal management system for unmanned aerial vehicles are disclosed. An example housing for an unmanned aerial vehicle includes a central portion defining a cavity. The housing also includes a first arm to support a first propeller. The first arm has a first proximal end coupled to the central portion and a first distal end spaced from the central portion. The first distal end defines an inlet. The first arm defines a first fluid path in communication with the inlet and the central cavity. The housing also includes a second arm to support a second propeller. The second arm has a second proximal end coupled to the central portion and a second distal end spaced from the central portion. The second distal end defines an outlet. The second arm defines a second fluid path in communication with the outlet and the central cavity. The inlet and outlet are in fluid communication via the first path, the central cavity and the second path.

The present disclosure provides an agricultural plant protection machine. The machine includes a frame, a liquid storage tank for storing liquid, a pipeline connected to the liquid storage tank, a nozzle, and a pump for pumping the liquid in the liquid storage tank to the nozzle. The pump includes a pump body including a liquid inlet, a liquid outlet, and a pressure relief port; a pressure relief device disposed at the pressure relief port, the pressure relief device including a valve and an elastic reset member, the valve being disposed corresponding to the pressure relief port for sealing the valve. In response to a hydraulic pressure in the pump body exceeding a preset pressure threshold, the valve is separated from the pressure relief port under the force of the liquid and the liquid flows out of the pressure relief port.

Provided is an aerial vehicle, including: a package carrier including a plurality of vertical members being changeable in relative positions in a horizontal direction and surrounding a package in the horizontal direction to prevent falling of the package. A plurality of rotary wings are changeable in relative positions in the horizontal direction. The relative positions of the plurality of vertical members and the relative positions of the plurality of rotary wings are changeable. The package carrier is changed in shape in the horizontal direction in accordance with the relative positions of the plurality of vertical members. The change in the relative positions of the plurality of rotary wings is in conjunction with the shape of the package carrier.

The technology described herein relates to autonomous aerial vehicle technology and, more specifically, to autonomous unmanned aerial vehicle with folding collapsible arms. In some embodiments, a UAV including a central body, a plurality of rotor arms, and a plurality of hinge mechanisms is disclosed. The plurality of rotor arms each include a rotor unit at a distal end of the rotor arm. The rotor units are configured to provide propulsion for the UAV. The plurality of hinge mechanisms mechanically attach (or couple) proximal ends of the plurality of rotor arms to the central body. Each hinge mechanism is configured to rotate a respective rotor arm of the plurality of rotor arms about an axis of rotation that is at an oblique angle relative to a vertical median plane of the central body to transition between an extended state and a folded state.