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Rigidity control method for aircraft high lift device

A lift-increasing device and stiffness control technology, which is applied in the direction of instruments, geometric CAD, and electrical digital data processing, etc., can solve the problem of large chord deformation of the structure, difficulty in controlling the stiffness index, and unsatisfactory ultra-thin hinged lift-increasing device with large chord length Rigidity control requirements and other issues to achieve the effect of reducing structural weight

Pending Publication Date: 2021-06-29
XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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Problems solved by technology

The high-lift device adopts hinged fixed-axis rotation, and the design space is limited. The chord is long and the airfoil is thin. Arranging reasonable support points to achieve the purpose of controlling deformation has become a major difficulty in the design of large chord length (chord length more than 3 meters) ultra-thin (airfoil less than 150mm) hinged high-lift device design, the existing engineering algorithm can no longer meet the large Rigidity control requirements for chord-length ultra-thin hinged lifter

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  • Rigidity control method for aircraft high lift device
  • Rigidity control method for aircraft high lift device
  • Rigidity control method for aircraft high lift device

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Embodiment Construction

[0027] Referring to the accompanying drawings, the application proposes a stiffness control method for an aircraft high-lift device. The high-lift device includes an airfoil structure 1 and a plurality of joints 2, and the joints 2 are connected to the span beams 3 of the airfoil structure. The known high-lift device Structural form, the stiffness of the airfoil structure 1 is controlled by the number and position of the joints 2 on the spanwise beam 3 of the airfoil structure 1, and the calculation method for the number and position of the joints 2 is as follows:

[0028] (1) divide the airfoil structure into several sections along the span direction, calculate the centroid and section moment of inertia of each section, and obtain the spanwise and chordwise bending torsional stiffness parameters of the airfoil structure;

[0029] (2) Simplify the airfoil structure into a straight beam, which coincides with the span beam, and use multiple joints connected to the span beam as mu...

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Abstract

A rigidity control method for an aircraft high lift device comprises the steps that the rigidity of an airfoil structure is controlled according to the number and position of joints on a spanwise beam of the airfoil structure, the airfoil structure is divided into a plurality of sections in the spanwise direction, and spanwise and chordwise bending torsional rigidity parameters of the airfoil structure are obtained; the airfoil structure is simplified into a straight beam, the straight beam coincides with the spanwise beam, and a plurality of connectors connected to the spanwise beam serve as a plurality of supporting points of the straight beam; spanwise and chordwise deformation of an airfoil structure of the high lift device is taken as an optimization target, minimum support point bearing reaction difference is taken as a constraint condition, a fitness function of a straight beam support point position and quantity optimization problem is set, and optimization is performed to obtain support point positions and quantity meeting the constraint condition, wherein the positions and the number of the supporting points on the straight beams are the positions and the number of the joints on the spanwise beams.

Description

technical field [0001] The invention relates to the technical field of structural strength analysis, in particular to a method for controlling the stiffness of an ultra-thin hinge-type high-lift device with a large chord length for an aircraft. Background technique [0002] Aircraft lift devices are widely used in large aircraft to improve the take-off and landing performance of the aircraft. The high-lift device adopts hinged fixed-axis rotation, and the design space is limited. The chord is long and the airfoil is thin. Arranging reasonable support points to achieve the purpose of controlling deformation has become a major difficulty in the design of large chord length (chord length more than 3 meters) ultra-thin (airfoil less than 150mm) hinged high-lift device design, the existing engineering algorithm can no longer meet the large Rigidity control requirements for chord-length ultra-thin hinged lifter. Contents of the invention [0003] The purpose of this applicatio...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F30/15G06F119/14
Inventor 郑茂亮韩思聪赵占文
Owner XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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