A Design Method for Airfoil Frame Structure of High Aspect Ratio Aircraft

Abstract

The present invention discloses a high-aspect-ratio wing frame architecture design method and relates to the technical field of aircrafts. The design method comprises a rigid wing optimization step and an elastic wing optimization step. The rigid wing optimization step comprises generating an initial population of the wing architecture, performing lift-drag ratio calculation to obtain a local optimal solution, then carrying out optimizing calculation, performing lift-drag ratio calculation on the local optimal solution and comparing with the local optimal solution obtained after the initial population is subjected to the lift-drag ratio calculation, and finally judging the globally optimal solution; and the elastic wing optimization step comprises calculating the aerodynamic load borne by an elastic wing during an flight, then calculating the elastic deformation of the wing, solving the true form of the wing structure under elastic balance at the flight state through multiple iterative computations to obtain the flight load after the elastic deformation and acquire the twist angle of a wing profile architecture, and thus completing the design of the wing frame architecture. The wings designed through the high-aspect-ratio wing frame architecture design method have good geometrical aerodynamic twist angle distribution, the lift distribution is better, the smaller induced resistance can be produced, the best lift-drag ratio is obtained, and thus the cruising efficiency is improved.

Description

technical field [0001] The invention relates to the technical field of aircraft, in particular to a method for designing an airfoil frame structure with a large aspect ratio. Background technique [0002] In the design of civil aircraft and long-endurance UAVs, improving the cruise lift-to-drag ratio and improving cruise efficiency is the focus of the design, and the design of the wing frame is one of the effective means to obtain the optimal cruise configuration and improve cruise efficiency . [0003] Generally, a wing with an elliptical lift distribution has a uniform downwash distribution and has a smaller induced drag. For any wing with a large aspect ratio, there is always an optimized geometric aerodynamic twist angle distribution, which makes the lift distribution the most optimal. Good, resulting in less induced resistance and obtaining the best lift-to-drag ratio. At the same time, due to the light structure and low stiffness of the wing with large aspect ratio, ...

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Problems solved by technology

[0005] This patent document discloses a method for manufacturing a wing with a super-large aspect ratio, light weight, and high lift-to-drag ratio. By calculating the force of each tension line, the load distribution of the wing, and the maximum deformation of the wing, it is judged whether the wing meets the limit. Due to the design requirements of elastic deformation and the influence of tensioning wires on the elastic deformation of the wing, this method cannot accurately measure the geometric aerodynamic torsion angle distribution of the wing, and it is difficult to obtain the best lift-to-drag ratio, resulting in low cruise efficiency

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