Aerodynamic optimization design method for discrete adjoint aircraft configuration considering buffeting performance

By constructing a discrete adjoint gradient optimization framework for flow field separation characteristic parameters, and combining CFD numerical simulation and discrete adjoint technology, the problem of combining buffeting performance with aerodynamic optimization design in aircraft design was solved, achieving efficient buffeting performance prediction and control, and improving the aerodynamic efficiency and structural safety of the aircraft.

CN122174348BActive Publication Date: 2026-07-17XI AN JIAOTONG UNIV
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Patent Information

Authority / Receiving Office
CN · China
Patent Type
Patents(China)
Current Assignee / Owner
XI AN JIAOTONG UNIV
Filing Date
2024-07-01
Publication Date
2026-07-17

AI Technical Summary

Technical Problem

Existing technologies struggle to efficiently combine flutter performance requirements with aerodynamic optimization in aircraft design, resulting in low computational efficiency and reliance on empirical judgment. This makes it difficult to improve aerodynamic efficiency while ensuring structural stability and safety.

Method used

A discrete adjoint aircraft configuration aerodynamic optimization design method is adopted. By constructing a discrete adjoint gradient optimization framework for flow field separation characteristic parameters, and combining CFD numerical simulation and discrete adjoint technology, the optimization gradient is accurately calculated, so as to achieve accurate prediction and control of the buffeting boundary.

Benefits of technology

It improves the computational efficiency and accuracy of aerodynamic optimization design, reduces the reliance on professional experience, and achieves efficient integration of flutter performance constraints and aerodynamic optimization design. This ensures that the aircraft meets flutter performance requirements while pursuing aerodynamic performance, thereby improving the aerodynamic efficiency and structural safety of the aircraft.

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Abstract

A discrete adjoint aircraft configuration aerodynamic optimization design method considering buffeting performance incorporates buffeting characteristics into the aerodynamic optimization process by introducing flow field separation feature parameters. Sep As an objective or constraint for aerodynamic optimization, this invention constructs an aerodynamic optimization design method for discrete adjoint aircraft configurations that considers buffeting performance. By building a discrete adjoint gradient optimization framework that integrates flow field separation characteristic parameters, the method utilizes discrete adjoint techniques to accurately calculate the optimization gradient. Combined with real-time analysis of flow field separation characteristic parameters, it achieves accurate prediction and control of buffeting boundaries. This invention not only improves the computational efficiency and accuracy of optimization design but also reduces reliance on professional experience, achieving a highly efficient integration of buffeting performance constraints and aerodynamic optimization design.
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