A radio controlled model rotorcraft implemented with features improving flight performance using increasing structural stability and increasing rotorcraft visibility and orientation awareness through the use of multifunctioning, configurable, and aesthetically pleasing components.

A modular unmanned aerial vehicle (UAV) system comprises a body module, a rotor module, and a wing module. The body module includes a flight controller and a power distribution device. The body module is releasably attachable to the rotor module or the wing module, and the body module is releasably attachable to the rotor module. The rotor module includes one or more motors and electronic speed controllers (ESCs), while the wing module includes a wing having a flap, elevator, aileron, or rudder. Various UAV configurations can be formed from the body module, the rotor module, and the wing module. Each configuration includes different advantages for flight time, distance, battery life, and payload capacity. A UAV can be configured to a particular configuration to optimize parcel delivery.

Disclosed is a system and method for reducing the total latency for transferring a frame from the low latency camera system mounted on an aerial vehicle to the display of the remote controller. The method includes reducing the latency through each of the modules of the system, i.e. through a camera module, an encoder module, a wireless interface transmission, wireless interface receiver module, a decoder module and a display module. To reduce the latency across the modules, methods such as overclocking the image processor, pipelining the frame, squashing the processed frame, using a fast hardware encoder that can perform slice based encoding, tuning the wireless medium using queue sizing, queue flushing, bitrate feedback, physical medium rate feedback, dynamic encoder parameter tuning and wireless radio parameter adjustment, using a fast hardware decoder that can perform slice based decoding and overclocking the display module are used.

An unmanned aerial vehicle (UAV) includes a central body, a plurality of arms extending out from the central body and in fluid communication with the central body, and a plurality of propulsion units. The plurality of arms are configured to route fluid away from the central body of the UAV. Each propulsion unit attached to a corresponding arm of the plurality of arms.

A multi-rotor aircraft (100) is provided, comprising: a main aircraft assembly (10) comprising a first magnetic medium (13), a main housing (11), and a control motherboard accommodated in the main housing (11), wherein the first magnetic medium (13) is provided on the main housing (11), a slot (1120) is further provided on the main housing (11), and a connection point of the control motherboard is provided in the slot (1120); and a plurality of rotor systems (20), wherein each of the plurality of rotor systems comprises a second magnetic medium (23), a rotor mechanism (21), and a rotor protection cover (22) that is of a hollow annular structure and is fixed outside the rotor mechanism (21), wherein the second magnetic medium (23) is fixed to the rotor protection cover (22) and attracting the first magnetic medium (13), and a pin (2200) matching the slot (1120) is further provided on the rotor protection cover (22). The rotor systems (20) can be quickly mounted on or dismounted from the main aircraft assembly (10), thereby achieving the technical effects of shortening the mounting and dismounting time and improving the operation efficiency.

A power package includes a motor and at least one of a propeller or a propeller mounting structure. The propeller mounting structure is configured to detachably mount the propeller at the motor and includes a mounting seat configured to be fixed at an end surface of the motor and rotationally engage with the propeller, a lock member, and an elastic member configured to apply an elastic force to the lock member along an axial direction of a motor shaft of the motor to cause at least part of the lock member to block the propeller from being disengaged from the mounting seat. The motor shaft passes through the mounting seat. The propeller includes a connection assembly and a blade disposed at the connection assembly. The connection assembly is configured to mount at the motor shaft and includes an annular connector configured to rotationally engage with the propeller mounting structure.

An aircraft for generating torque. The aircraft includes a motor coupling a lifting rotor and a torque rotor, and is configured to spin the lifting rotor in a first direction to generate lift and spin the torque rotor in a second direction to generate drag-torque. The torque rotor and the lifting rotor are coupled or decoupled from one another during flight or on ground.

A modular unmanned aerial vehicle (UAV) system comprises a body module, a rotor module, and a wing module. The body module includes a flight controller and a power distribution device. The body module is releasably attachable to the rotor module or the wing module, and the body module is releasably attachable to the rotor module. The rotor module includes one or more motors and electronic speed controllers (ESCs), while the wing module includes a wing having a flap, elevator, aileron, or rudder. Various UAV configurations can be formed from the body module, the rotor module, and the wing module. Each configuration includes different advantages for flight time, distance, battery life, and payload capacity. A UAV can be configured to a particular configuration to optimize parcel delivery.

A modular unmanned aerial vehicle (UAV) system comprises a body module, a rotor module, and a wing module. The body module includes a flight controller and a power distribution device. The body module is releasably attachable to the rotor module or the wing module, and the body module is releasably attachable to the rotor module. The rotor module includes one or more motors and electronic speed controllers (ESCs), while the wing module includes a wing having a flap, elevator, aileron, or rudder. Various UAV configurations can be formed from the body module, the rotor module, and the wing module. Each configuration includes different advantages for flight time, distance, battery life, and payload capacity. A UAV can be configured to a particular configuration to optimize parcel delivery.

A quadrotor UAV including ruggedized, integral-battery, load-bearing body, two arms on the load-bearing body, each arm having two rotors, a control module mounted on the load-bearing body, a payload module mounted on the control module, and skids configured as landing gear. The two arms are replaceable with arms having wheels for ground vehicle use, with arms having floats and props for water-surface use, and with arms having pitch-controlled props for underwater use. The control module is configured to operate as an unmanned aerial vehicle, an unmanned ground vehicle, an unmanned (water) surface vehicle, and an unmanned underwater vehicle, depending on the type of arms that are attached.