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Aircraft test setups, restraint and loading methods, tare and loading methods

A test device and aircraft technology, applied in the direction of aircraft component testing, etc., can solve problems such as tare, and achieve the effects of simple function switching, small footprint, and simple design

Active Publication Date: 2022-07-15
CHINA AIRPLANT STRENGTH RES INST
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, some parts of the test aircraft (such as the center wing, belly landing gear, etc.) cannot be buckled by the reverse counterweight method due to structural layout restrictions, making the traditional buckle method unable to solve new problems

Method used

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  • Aircraft test setups, restraint and loading methods, tare and loading methods

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Embodiment Construction

[0014] The present application will be further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are only used to explain the related application, but not to limit the application. In addition, it should be noted that, for the convenience of description, only the parts related to the present application are shown in the drawings.

[0015] It should be noted that the embodiments in the present application and the features of the embodiments may be combined with each other in the case of no conflict. The present application will be described in detail below with reference to the accompanying drawings and in conjunction with the embodiments.

[0016] figure 1 The aircraft test device provided by the embodiment of the present application is shown.

[0017] like figure 1 As shown, the aircraft test device includes a support structure 1, the support structure 1 has a cavit...

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Abstract

The application provides an aircraft test device, a restraint and loading method, and a tare and loading method. The device includes a support structure, and has a cavity, and a plurality of balls are arranged in the cavity; a hydraulic actuator is arranged on the support structure. The upper surface of the adjusting structure, one end is connected with the end of the hydraulic actuator that is far away from the support structure; the load sensor is connected with the other end of the adjusting structure; the connecting end of the test piece is connected with the load sensor; the displacement sensor is connected with the connecting end of the test piece Connection, used to detect the displacement of the connection end of the test piece.

Description

technical field [0001] The present application relates to the technical field of aircraft structural strength, and specifically provides an aircraft test device, a restraint and loading method, and a weighting and loading method. Background technique [0002] When conducting a full-scale aircraft structure ground strength test, it is necessary to constrain the aircraft in a fixed coordinate system. The method of constraining is usually to design a six-degree-of-freedom statically determinate constraint at the landing gear with a strong concentrated load capacity of the aircraft. The composition of statically indeterminate constraints is usually three vertical constraints on three landing gears in the vertical direction, two landing gear headings and one lateral displacement constraint in the horizontal direction. By adjusting the displacement of the six constraint points The overall coordinate position of the aircraft can be uniquely defined. [0003] In the vertical restra...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64F5/60
Inventor 郑建军刘玮郭琼裴连杰张赟刘冰王孟孟
Owner CHINA AIRPLANT STRENGTH RES INST
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