Method for determining maximum hinge moment of all-moving V-tail of aircraft
By determining the speed, angle of attack, and yaw rate corresponding to the maximum hinge moment of the all-moving V-tail, calculating the maximum hinge moment under each all-moving V-tail yaw rate and taking the larger value, the problems of computational complexity and low efficiency in the prior art are solved, and rapid and accurate calculations are realized in aircraft design.
CN117669054BActive Publication Date: 2026-06-26XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Patents(China)
- Current Assignee / Owner
- XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
- Filing Date
- 2023-12-12
- Publication Date
- 2026-06-26
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Figure CN117669054B_ABST
Abstract
The application belongs to the technical field of data processing for determining maximum hinge moment of a full-movement V-tail of an airplane, and particularly relates to a method for determining maximum hinge moment of a full-movement V-tail of an airplane, comprising the following steps: step one, determining a speed state corresponding to the maximum hinge moment of the full-movement V-tail; step two, determining an airplane attack angle, an airplane sideslip angle and a full-movement V-tail deflection corresponding to the maximum hinge moment of the full-movement V-tail; step three, calculating the maximum hinge moment under each full-movement V-tail deflection; and step four, comprehensively determining the maximum hinge moment of the full-movement V-tail.
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