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Wing pneumatic load follow-up loading device

A technology of follow-up loading and aerodynamic loading, which is used in measurement devices, aerodynamic tests, and testing of machine/structural components. cost effect

Pending Publication Date: 2017-04-26
SHENYANG AIRCRAFT DESIGN INST AVIATION IND CORP OF CHINA
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

During the test process, the long straight wing with large aspect ratio, with the application of load, the wing has a large deformation, and the ordinary fixed form of load application can no longer correctly simulate the direction of aerodynamic load

Method used

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  • Wing pneumatic load follow-up loading device
  • Wing pneumatic load follow-up loading device
  • Wing pneumatic load follow-up loading device

Examples

Experimental program
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specific Embodiment

[0023] Construct the wing aerodynamic load follow-up loading device. If the test requires, place the slide rail 5 under the wing and make the projections of the axes of the two coincide on the ground. If the load application point is on the upper surface of the wing, the canvas can be used to The load application point is connected with the force sensor 4, if the load application point is on the lower surface of the wing, then directly use the load actuator 3 to apply thrust to the load application point.

[0024] When no load is applied, the deformation angle at the point where the load is applied is zero degrees. At this time, the axis of the load actuator 3 coincides with the normal line of the wing. When the external device gives the load command to the load actuator 3, the load actuator 3 Increase the applied load from zero, and the force sensor 4 feeds back the force at the load application point in real time. At this time, the load application point is deformed due to th...

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Abstract

The invention provides a wing pneumatic load follow-up loading device. The device comprises a load actuator and a follow-up device. A wing angle displacement sensor which can detect a load applying point deformation angle is arranged at a load applying point of a wing test component. The load actuator is provided with a force sensor which can detect a size of a force applied to the wing test component. A bottom of the load actuator is fixed to the follow-up device. The follow-up device can push and pull a bottom end of the load actuator so that an axis of the load actuator and a normal of the load applying point are superposed. The follow-up device is provided with an actuator angle displacement sensor which can measure an angle change of the axis of the load actuator relative to the follow-up device. The follow-up loading device adopts a passive mode to carry out follow-up loading of a load under the condition that wing deformation is unknown so that real simulation of a pneumatic load size and a direction when a high-aspect-ratio long straight wing generates large deformation during a test process is realized.

Description

technical field [0001] The invention relates to the technical field of aircraft load tests, in particular to a wing aerodynamic load follow-up loading device. Background technique [0002] When the wing is undergoing a strength test, the test loading system needs to truly simulate the size and direction of the aerodynamic load when the wing is deformed under force. The direction of the normal to the wing curve is the same. During the test process of the long straight wing with large aspect ratio, as the load is applied, the wing has a large deformation, and the ordinary fixed form of load application can no longer correctly simulate the direction of the aerodynamic load. Contents of the invention [0003] In order to overcome the defects in the above-mentioned prior art, the invention provides a wing aerodynamic load follow-up loading device, including a load actuator and a follower, and the load application point of the wing test piece is provided with a device that can ...

Claims

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Application Information

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IPC IPC(8): G01M9/00
CPCG01M9/00
Inventor 郭小鹏盛磊于江侠
Owner SHENYANG AIRCRAFT DESIGN INST AVIATION IND CORP OF CHINA
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