Aircraft traction air-drop stable feedback control gain determination method and system
By constructing the typical state of weight, center of gravity, and moment of inertia during the aircraft traction airdrop, and determining and calculating the feedback control gain in real time, the handling burden and potential danger problems caused by the drastic changes in the aircraft state during the traction airdrop are solved, and stable control of aircraft response is achieved.
Patent Information
- Application Number
- CN202411821429.7
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2024-12-11
- Publication Date
- 2025-03-25
- Estimated Expiration
- 2044-12-11
AI Technical Summary
During the traction airdrop process, the aircraft status will change drastically, and the crew needs to respond quickly to control the aircraft, resulting in heavy handling burden and large potential dangers. The existing feedback control design is mainly aimed at normal flights of all-inclusive lines, and there is a lack of design for traction airdrop tasks.
A method for determining the steady feedback control gain of the aircraft traction airdrop is provided. By constructing a typical state covering the changes in the aircraft weight, center of gravity, and moment of inertia during the traction airdrop, the corresponding feedback control gain of the feedback control state amount under each typical state is determined, and real-time feedback control gain is obtained through interpolation calculation.
It realizes real-time adjustment of feedback control gain during the traction airdrop process, adapting to the cargo movement state, reducing the manipulation burden of crew members, and reducing the risk of unstable aircraft response.