System Introduction Of Fixed-wing UAVs

A typical fixed-wing unmanned aerial vehicle (UAV) system consists of five main parts: airframe, avionics system, power system, takeoff and landing system, and ground control station.

The airframe is composed of a detachable modular structure, facilitating portability and allowing for rapid assembly and takeoff. Furthermore, the frame structure employs a truss-type fuselage and modular wing surface design, achieving a balance between strength and weight through a lightweight frame.

The avionics system comprises a flight control computer, sensors, payload, wireless communication, and an empty battery, fulfilling the requirements of the aircraft control system. The flight control system, as the core, possesses large-capacity storage and high-frequency data recording capabilities, and integrates a multi-mode satellite navigation module supporting BDS/GPS/GLONASS.

The power system consists of a power battery, propellers, and brushless motors, providing the power required for flight. Various power types are available, including pure lithium polymer battery drive and hybrid power (hybrid power).

Fixed-wing UAVs offer flexible takeoff and landing methods to adapt to different operating environments. Takeoff methods include vertical takeoff, catapult takeoff, and hand-launched takeoff; recovery methods include vertical landing and parachute landing. The takeoff and landing system consists of a catapult rope, catapult frame, and parachute, assisting the aircraft in completing catapult takeoff and parachute landing. In particular, vertical takeoff and landing fixed-wing UAVs combine the advantages of multi-rotor vertical takeoff and landing with the high-efficiency cruise of fixed wings, allowing them to take off and land in complex terrain without a runway, and their applications are becoming increasingly widespread.