An optimization method for a roll wing paddle linkage mechanism

By establishing a unified parametric model and surrogate model optimization method for the rotor linkage mechanism of rolling wing aircraft, the problem of cross-disciplinary index collaborative optimization in the existing technology is solved. It realizes efficient global optimization under multiple objectives and multiple working conditions, improves design efficiency and reliability, and the output solution is applicable to the detailed design and manufacturing of rolling wing aircraft.

CN121765848BActive Publication Date: 2026-06-26HUAZHONG UNIV OF SCI & TECH
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Patent Information

Authority / Receiving Office
CN · China
Patent Type
Patents(China)
Current Assignee / Owner
HUAZHONG UNIV OF SCI & TECH
Filing Date
2026-03-04
Publication Date
2026-06-26

AI Technical Summary

Technical Problem

Existing design methods for rolling wing aircraft are difficult to achieve cross-disciplinary collaborative optimization of indicators, have low iteration efficiency, insufficient handling of engineering constraints, and a disconnect between design and verification processes, resulting in unstable performance of the blade linkage mechanism under different operating conditions.

Method used

A unified parametric model of the blade linkage mechanism is established. The blade swing angle is characterized by structural parameters. A multi-objective function is constructed. Combining kinematics, dynamic stability, aerodynamic efficiency and aeroacoustic indicators, a surrogate model and an adaptive sampling mechanism are used for optimization to reduce the number of high-fidelity simulations and achieve global optimization under multiple objectives and multiple operating conditions.

Benefits of technology

It significantly improves design efficiency and overall performance, achieves synergistic trade-offs in performance across multiple disciplines, enhances design reliability and engineering practicality, and ensures that the output solution is structurally and dynamically feasible and reliable, supporting subsequent detailed design and prototype manufacturing.

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Abstract

The application discloses an optimization method of a rolling wing blade connecting rod mechanism, and belongs to the field of rolling wing aircrafts.The blade swing angle is represented by structural parameters of the blade connecting rod mechanism, and the structural parameters of the blade connecting rod mechanism, including the lengths of the connecting rods, the coordinates of key hinge points and configuration bias, are defined as a variable vector; multiple target functions are constructed for multiple key working conditions such as hovering, forward flight and transition, the multiple target functions not only quantify the performance of the connecting rod mechanism itself, such as kinematic fitting error with a target motion law, dynamic stability index and force transmission efficiency index, but also cover aerodynamic efficiency index and aerodynamic acoustic index which are directly related to the performance of the whole machine; and the optimal structural parameters of the blade connecting rod mechanism are obtained by solving the multiple target functions under constraints, so that the global optimization of the structural parameters of the blade connecting rod mechanism under multiple working conditions, multiple targets and multiple constraints can be realized.
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