Multipoint coordinated follow-up loading device and method for large-deformation wing

A technology of follow-up loading and multi-point coordination, which is applied in the direction of aircraft component testing, etc.

Active Publication Date: 2020-06-19
CHINA AIRPLANT STRENGTH RES INST
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0005] The purpose of this application is to provide a large deformation wing multi-point coordinated follow-up loading device and method to solve at least one problem existing in the prior art

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  • Multipoint coordinated follow-up loading device and method for large-deformation wing
  • Multipoint coordinated follow-up loading device and method for large-deformation wing
  • Multipoint coordinated follow-up loading device and method for large-deformation wing

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Embodiment Construction

[0105] In order to make the purpose, technical solution and advantages of the application more clear, the technical solution in the embodiment of the application will be described in more detail below in conjunction with the drawings in the embodiment of the application. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are some, but not all, embodiments of the application. The embodiments described below by referring to the figures are exemplary, and are intended to explain the present application, and should not be construed as limiting the present application. Based on the embodiments in this application, all other embodiments obtained by persons of ordinary skill in the art without creative efforts fall within the protection scope of this application. Embodiments of the present application will be described in detail below in conjunction with th...

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Abstract

The invention belongs to the technical field of aircraft structure static tests and particularly relates to a large-deformation wing multi-point coordination follow-up loading device and method. The device comprises a position control actuator cylinder and force control actuator cylinders, wherein a plurality of loading points are arranged on a large-deformation wing, one end of the position control actuator cylinder is fixed, a pulley block fixing support is arranged at the other end of the position control actuator cylinder, a plurality of fixing supporting rods with different heights are arranged on the pulley block fixing support, guide pulleys are arranged on the fixing supporting rods, the force control actuator cylinders are multiple, one end of each force control actuator cylinderis fixed, the other end of each force control actuator cylinder is provided with a steel cable, and the steel cable is connected with a loading point of the large-deformation wing through a guide pulley. The device is advantaged in that the loading force line is ensured to be always perpendicular to a surface of a wing in the whole loading process on the premise that the installation position of the loading point is not changed, moreover, multi-point follow-up loading is realized while follow-up loading is simplified, test load applying accuracy and loading stability are ensured, a test loading error is reduced, test design difficulty is reduced, and test cost is saved.

Description

technical field [0001] The application belongs to the technical field of aircraft structure static testing, and in particular relates to a multi-point coordinated follow-up loading device and method for a large deformation wing. Background technique [0002] In the actual flight of the aircraft, the aerodynamic force is always perpendicular to the wing surface, and the load perpendicular to the wing chord plane can more realistically simulate the actual loading of the aircraft while meeting the requirements of the mission statement. For an aircraft with a large aspect ratio, the wing deformation is very large in the static test, and the test data results often have a certain deviation from the theoretical calculation. The greater the deformation, the more obvious the deviation. In the completed static test of the wing, the researchers found that the main reason for the loading error is that the large deformation of the wing causes the change of the loading direction, such as...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64F5/60
CPCB64F5/60Y02T90/00
Inventor 杨鹏飞杜峰何月洲任鹏王毅
Owner CHINA AIRPLANT STRENGTH RES INST
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