Major-diameter airframe test loading clamp

An aircraft fuselage, large-diameter technology, applied in the field of large-diameter aircraft fuselage test loading fixtures, can solve problems such as constraints, and achieve the effect of ensuring rationality, good constraints, and convenient weighting

Active Publication Date: 2013-11-27
CHINA AIRPLANT STRENGTH RES INST
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] The purpose of the present invention is to provide a large-diameter aircraft fuselage test loading fixture that can solve the problem of constraints and load

Method used

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  • Major-diameter airframe test loading clamp
  • Major-diameter airframe test loading clamp

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Example Embodiment

[0017] The present invention will be further explained below in conjunction with the drawings:

[0018] See figure 1 The test loading fixture for the large-diameter aircraft fuselage of the present invention includes a butting end plate, a force equalizing ring, a skin, a triangular beam, and a loading beam. The butting end plate is a circular ring structure that matches the transition section of the fuselage. The equalizing ring surrounds the inner and outer rings of the butting end plate. One side of the equalizing ring is connected to the butting end plate, and the other side is connected by the skin to apply concentrated load. Load the device.

[0019] Among them, the structural design features and functions of each component are as follows:

[0020] Butt end plate—designed according to the size of the test piece butt end frame. The center ring of the butt end plate is a butt ring that butts with the test piece butt bolts. The distance of the butt ring is equal to the inner and ...

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Abstract

The invention belongs to the test loading technology, and relates to a major-diameter airframe test loading clamp. The major-diameter airframe test loading clamp comprises a butt joint end plate, a force averaging ring and skin. The butt joint end plate is of a circular ring structure matched with an airframe transition section, an inner ring and an outer ring of the butt joint end plate are surrounded by the force averaging ring, one side of the force averaging ring is connected with the butt joint end plate, the other side of the force averaging ring is connected with a loading device through the skin, and the loading device is used for exerting concentrated loads. The major-diameter airframe test loading clamp is applied to a certain type airplane wing body combined body force transmission characteristic test, accurate exertion of various loads on a butt joint end frame section is achieved, rationality of stress distribution of a butt joint end frame is guaranteed, good limitation to a tested piece is provided, and convenience is brought to tare of the loading device. In theory, the loading device and the testing technology of the loading device can achieve exertion of any load on any airframe frame section.

Description

technical field [0001] The invention belongs to the test loading technology, and relates to a large-diameter aircraft fuselage test loading fixture. Background technique [0002] For the test of aircraft fuselage frame sections, the usual method is to add a docking transition frame section on the end face of the aircraft fuselage assessment frame section, and fix the transition frame section on the load-bearing wall with a special test fixture to realize the fixed support constraint of the test piece , various loads on the frame end of the fuselage are passively applied by the bearing wall. This method is only applicable to the case where the test piece has only one section. Since the load-bearing wall is the constraint of the test piece, it has to bear the unbalanced load of the test piece and other active point loading errors. In theory, the passively applied load is often difficult to meet the requirements of the test loading accuracy, which increases the difficulty of t...

Claims

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Application Information

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IPC IPC(8): B64F5/00B64F5/60
Inventor 郑建军张建峰夏峰王刚王征崔明贺金利
Owner CHINA AIRPLANT STRENGTH RES INST
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