An unmanned aerial signal relay includes an unmanned aerial vehicle, including a communication relay unit and at least one antenna, communicatively connected to the communication relay unit; a tether comprising at least two wires and at least one fiber optic cable, the wires and cable communicatively connected to the unmanned aerial vehicle; and a surface support system comprising a spool physically connected to the tether and a ground-based receiver communicatively connected to the at least one fiber optic cable, wherein the unmanned aerial vehicle is powered by electrical energy provided by the at least two wires, and wherein the communication relay unit is configured to relay signals received from the at least one antenna via the fiber optic cable to the ground-based receiver. Various systems and methods related to an unmanned aerial signal relay are also described.

An unmanned aerial signal relay includes an unmanned aerial vehicle, including a communication relay unit and at least one antenna, communicatively connected to the communication relay unit; a tether comprising at least two wires and at least one fiber optic cable, the wires and cable communicatively connected to the unmanned aerial vehicle; and a surface support system comprising a spool physically connected to the tether and a ground-based receiver communicatively connected to the at least one fiber optic cable, wherein the unmanned aerial vehicle is powered by electrical energy provided by the at least two wires, and wherein the communication relay unit is configured to relay signals received from the at least one antenna via the fiber optic cable to the ground-based receiver. Various systems and methods related to an unmanned aerial signal relay are also described.

The present invention is aimed to provide a multi-functional flying platform with a simple structure, which is easy to operate and can achieve the mounting of different functional equipment. It includes rotor arm system and mounting plate (1). A plurality of evenly distributed fixing devices (2) are provided on the mounting plate (1). Mounting plate (1) is fixedly connected to rotor arm (3) of the rotor arm system by fixing device (2). A plurality of mounting positions (4) are provided on the lower side of the mounting plate (1). The present invention can be used in the field of agricultural aviation.

In one embodiment, a controller instructs an unmanned aerial vehicle (UAV) docked to a landing perch to perform a pre-flight test operation of a pre-flight test routine. The controller receives sensor data associated with the pre-flight test operation from one or more force sensors of the landing perch, in response to the UAV performing the pre-flight test operation. The controller determines whether the sensor data associated with the pre-flight test operation is within an acceptable range. The controller causes the UAV to launch from the landing perch based in part on a determination that UAV has passed the pre-flight test routine.

A propulsion system for an aircraft includes an air intake, an engine assembly, a turbocompressor, an electrical assembly, and at least one propulsor. The engine assembly includes an engine. The engine includes an air inlet, an exhaust outlet, and an engine output shaft. The turbocompressor assembly includes a turbocompressor. The turbocompressor includes a turbine and a compressor. The turbine and the compressor form a rotational assembly. The rotational assembly includes a shaft, a bladed turbine rotor of the turbine, and a bladed compressor rotor of the compressor. The shaft interconnects the bladed turbine rotor and the bladed compressor rotor. The turbine includes a turbine inlet and a turbine outlet. The turbine inlet is connected in fluid communication with the exhaust outlet. The compressor includes a compressor inlet and a compressor outlet. The compressor inlet is connected in fluid communication with the air intake. The rotational assembly is mechanically independent of the engine output shaft.

A propulsion system for an aircraft includes an air intake, an engine assembly, a turbocompressor, an electrical assembly, and at least one propulsor. The engine assembly includes an engine. The engine includes an air inlet, an exhaust outlet, and an engine output shaft. The turbocompressor assembly includes a turbocompressor. The turbocompressor includes a turbine and a compressor. The turbine and the compressor form a rotational assembly. The rotational assembly includes a shaft, a bladed turbine rotor of the turbine, and a bladed compressor rotor of the compressor. The shaft interconnects the bladed turbine rotor and the bladed compressor rotor. The turbine includes a turbine inlet and a turbine outlet. The turbine inlet is connected in fluid communication with the exhaust outlet. The compressor includes a compressor inlet and a compressor outlet. The compressor inlet is connected in fluid communication with the air intake. The rotational assembly is mechanically independent of the engine output shaft.

An unmanned aerial vehicle includes a body, a first wing, a second wing, a first rotor assembly, a third rotor assembly, and a fourth rotor assembly. The body has a first accommodating cavity and a second accommodating cavity. The first wing and the second wing are disposed on two sides of the body. The first rotor assembly is mounted to the first wing, and the second rotor assembly is mounted to the second wing. The third rotor assembly includes a third motor and a third propeller connected to the third motor. The third motor is mounted in the first accommodating cavity and partially exposed to the body. The fourth rotor assembly includes a fourth motor and a fourth propeller connected to the fourth motor. The fourth motor is mounted in the second accommodating cavity and partially exposed to the body.

An unmanned aerial vehicle includes a body, a first wing, a second wing, a first rotor assembly, a third rotor assembly, and a fourth rotor assembly. The body has a first accommodating cavity and a second accommodating cavity. The first wing and the second wing are disposed on two sides of the body. The first rotor assembly is mounted to the first wing, and the second rotor assembly is mounted to the second wing. The third rotor assembly includes a third motor and a third propeller connected to the third motor. The third motor is mounted in the first accommodating cavity and partially exposed to the body. The fourth rotor assembly includes a fourth motor and a fourth propeller connected to the fourth motor. The fourth motor is mounted in the second accommodating cavity and partially exposed to the body.

An unmanned aerial device includes a body, a heat-generating assembly, and a propulsion assembly. The body has a head end, an airflow guide space, and a tail end. The head end is opposite to the tail end, and the airflow guide space is located between the head end and the tail end. The head end has an air intake, and the tail end has an exhaust vent. The airflow guide space is communicated with the air intake and the exhaust vent. The heat-generating assembly is disposed in the airflow guide space. The propulsion assembly is connected to the tail end, and the propulsion assembly is adapted to generate a propulsion airflow through the air intake, the heat-generating assembly, and the exhaust vent.

An unmanned aerial vehicle (UAV) that includes a chassis and a gimbal module. The gimbal module includes at least one optical component that facilitates image capture, and is configured for removable connection to the chassis to facilitate repeated connection and disconnection of the gimbal module and interchangeability amongst a plurality of gimbal modules.