Flight test method based on control strategy of horizontal tail capable of rotating around shaft
By adjusting the flat tail installation angle at different total distances and flight speeds, recording the pitch angle change curve, and determining the preferred flat tail angle, the test flight safety hazards and accuracy problems of the flat tail control strategy that can rotate around the axis in the prior art are solved, and safer , more precise flat tail control, improves flight performance and field of view.
Patent Information
- Application Number
- CN202411438518.3
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2024-10-15
- Publication Date
- 2025-01-03
AI Technical Summary
The test flight method of a flat tail control strategy that can rotate about the axis in the prior art has safety risks in the test flight, and the pilot may lose his field of vision or flat tail stall, and it is difficult to accurately determine the required flat tail angle at different speeds.
By introducing total distance and airspeed as control variables, the flat tail installation angle is adjusted at different total distances and flight speeds, the pitch angle change curve is recorded, and the preferred flat tail angle is determined to ensure the optimal configuration of flat tail angle at different speed points to meet the flight Performance, field of view and speed-pose gradient requirements.
It achieves a safer and more accurate acquisition of the flat tail angle required at different total distances and speeds, avoiding the risk of pilots losing field of vision and flat tail stalling, improving flight performance and field of vision, and ensuring the stability of the speed-attitude gradient.
Smart Images
Figure CN119239974A_ABST