A fixed-wing drone flight control method and system

By transforming the UAV flight process into linear and angular motion descriptions and constructing a dual closed-loop control loop, the problem of load limitation in on-orbit maintenance and inspection missions of fixed-wing UAVs was solved, and the stable flight and path tracking capabilities of UAVs were achieved.

CN122195083APending Publication Date: 2026-06-12CHINA RAILWAY SIYUAN SURVEY & DESIGN GRP CO LTD
0 Cites 0 Cited by

Patent Information

Authority / Receiving Office
CN · China
Patent Type
Applications(China)
Current Assignee / Owner
CHINA RAILWAY SIYUAN SURVEY & DESIGN GRP CO LTD
Filing Date
2026-03-18
Publication Date
2026-06-12

AI Technical Summary

⚠Technical Problem

Existing fixed-wing UAVs have limited payload capacity in on-orbit maintenance and inspection missions, which limits the computing power of onboard computers. Therefore, it is necessary to develop a flight control scheme that is robust and has low computational requirements.

⚗Method used

The flight process of the UAV is transformed into a linear motion description under the action of the net external force and an angular motion description under the action of aerodynamic torque. The angular velocity components are represented in the body coordinate system and mapped to the ground coordinate system to construct an inner and outer double closed-loop control loop for roll angle and pitch angle, which is then combined with PI and PD controllers for control.

🎯Benefits of technology

It enables stable flight of UAVs during autonomous take-off missions, reduces the computational load on the onboard computer, improves flight stability and resistance to random wind disturbances, and effectively tracks the planned path.

✦ Generated by Eureka AI based on patent content.

Smart Images

  • Figure 1
    Figure 1
  • Figure 2
    Figure 2
  • Figure 3
    Figure 3
Patent Text Reader

Abstract

The application discloses a fixed-wing unmanned aerial vehicle flight control method and system, which comprises the following steps: converting the flight process of the unmanned aerial vehicle into linear motion description under the action of external force and angular motion description under the action of aerodynamic moment; decomposing the aerodynamic moment received by the unmanned aerial vehicle into each coordinate axis under the body coordinate system and representing the angular velocity component under the body coordinate; mapping the angular velocity component under the body coordinate system to the ground coordinate system and representing the angular change rate under the ground coordinate system; constructing the inner and outer loop double closed loop control circuit of the roll angle of the unmanned aerial vehicle and the inner and outer loop double closed loop control circuit of the pitch angle of the unmanned aerial vehicle under the ground coordinate system, and controlling the roll angle and the pitch angle in the flight process of the unmanned aerial vehicle. The technical scheme of the embodiment of the application can control the unmanned aerial vehicle to stably complete the autonomous take-off task.
Need to check novelty before this filing date? Find Prior Art