Design method of conventional layout rigid-elastic coupling flutter flight test model

By adjusting the wing sweep angle and the position and mass of the fuselage counterweight, a conventional layout rigid-elastic coupling flutter flight test model was designed, which solved the problem that existing technologies could not adapt to the flutter of conventional layout aircraft bodies, and achieved efficient, low-cost simulation and accurate test data.

CN121723707APending Publication Date: 2026-03-24NORTHWESTERN POLYTECHNICAL UNIV +1
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Patent Information

Authority / Receiving Office
CN · China
Patent Type
Applications(China)
Current Assignee / Owner
Filing Date
2025-12-24
Publication Date
2026-03-24

AI Technical Summary

Technical Problem

Existing technologies cannot effectively excite and accurately simulate the body degree of freedom flutter characteristics of conventional layout aircraft, resulting in the loss of reference value of test data. Furthermore, the existing test model design methods for flying wing layouts cannot be adapted to conventional layout variant aircraft.

Method used

A design method for a conventional layout rigid-elastic coupled flutter flight test model is provided. Through systematic parameter design and optimization, including adjusting the wing sweep angle and the position and mass of the fuselage counterweight, a body-degree-of-freedom flutter mode that conforms to the characteristics of a real aircraft is generated. Modal analysis and flutter calculation are performed using MSC NASTRAN software.

Benefits of technology

It enables the low-cost and high-reliability excitation and simulation of body degree-of-freedom flutter characteristics of conventional layout aircraft, provides an efficient means of experimental model design, reduces economic costs and technical barriers, shortens the development cycle, and enhances the reference value of experimental data.

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Abstract

The invention provides a conventional layout rigid-elastic coupling flutter flight test model design method, and belongs to the technical field of aeroelastic tests of aircrafts. Through collaborative design of the overall aerodynamic layout of a flight test model, the sweepback angle of a wing, the position and mass of a fuselage counterweight and the flutter characteristic of the degree of freedom of an excitation body, the specific method comprises the following steps: determining the aerodynamic boundary dimension and mass distribution of the model according to the overall aerodynamic layout design requirement; in the typical sweepback angle range of the conventional layout, the sweepback angles of the wings are adjusted, and the degree-of-freedom flutter characteristic of the body is excited; and at the specific position of the fuselage, the optimal mass and position combination of the fuselage counterweight is determined through iterative optimization, and the goal of minimizing the flutter critical speed is achieved. On the premise that a flight test model keeps a conventional aerodynamic shape, a coupling flutter mode which is required by a flight test and comprises rigid body motion and elastic vibration of a machine body is accurately simulated and excited, and a core technical support is provided for the flutter problem of the body degree of freedom of a conventional layout in the future.
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