Four-vertical-fin load loading method

A technology with four vertical tails and loads, applied in the testing of measuring devices, instruments, and mechanical components, etc., can solve the problems of increasing difficulty in the design of the test plan and on-site implementation, and achieve the convenience of applying loads in both directions of tension and compression, accurate loading accuracy, and optimization. The effect of the force transfer path

Active Publication Date: 2019-04-19
CHINA AIRPLANT STRENGTH RES INST
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AI Technical Summary

Problems solved by technology

For structures such as vertical double vertical tails and V-shaped outwardly inclined double vertical tails, the traditional loading method is: through the "adhesive tape-lever" system, the loading device is applied across the single vertical tail. This method needs to solve the problem of loading equipment ( Lever, wire rope) an

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  • Four-vertical-fin load loading method
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Example Embodiment

[0022] The present invention will be further introduced below in conjunction with the accompanying drawings. The four vertical tail load loading method of the present invention includes the following steps:

[0023] Step 1: Install the vertical tail frame 1 between the vertical tails, and connect the upper single lug 2 of the vertical tail frame 1 to the loading beam 3 by bolts. The distance between the lower end of the vertical tail frame 1 and the rear fuselage of the aircraft is not less than 300mm ;

[0024] Step 2: The upper end of the vertical tail frame 1 is connected to the loading beam 3 through the upper end pull plate 4, and the lower end of the vertical tail frame 1 is connected to the lateral loading column through the lower end pull plate 5;

[0025] Step 3: Install the actuator cylinder fixing seat 6 on the corresponding position of the vertical tail frame 1 according to different test conditions, and install the actuator cylinder 7 on the actuator cylinder fixing seat...

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Abstract

The invention discloses a four-vertical-fin load loading method which comprises the following steps: 1) installing a vertical fin frame between inner vertical fins, connecting a single lug at the upper end of the vertical fin frame to a loading cross beam, and enabling the distance between the lower end of the vertical fin frame and a rear fuselage of an aircraft to be not less than 300mm; (2) theupper end of the vertical fin frame being connected with a loading cross beam through an upper end pull plate, and the lower end of the vertical fin frame being connected with a lateral loading standcolumn through a lower end pull plate; 3) installing an actuating cylinder fixing seat at a position corresponding to the vertical fin frame; 4) installing an actuating cylinder base at a position corresponding to the lateral loading cross beam of the vertical fins; 5) connecting the actuating cylinder with a loading cross beam by using a manual hoist, adjusting the actuating loading to meet therequirement by adjusting the manual hoist, and connecting the actuating cylinder with a vertical fin end lever; and (6) repeating the steps (2) to (5) to install the vertical fin loading equipment onthe other side. The four-vertical-fin load loading method can realize bidirectional tension and compression loading of vertical fin loads, and can avoid the spatial interference problem between the loading equipment and between the loading equipment and a test piece.

Description

technical field [0001] The invention relates to the technical field of aircraft structure testing, in particular to a method for loading four vertical tail loads. Background technique [0002] In the aircraft structure test, the vertical tail test is an important test item of the aircraft structure test. For structures such as vertical double vertical tails and V-shaped outwardly inclined double vertical tails, the traditional loading method is: through the "adhesive tape-lever" system, the loading device is applied across the single vertical tail. This method needs to solve the problem of loading equipment ( Lever, wire rope) and the loading equipment, the spatial interference between the loading equipment and the vertical tail, but for the four vertical tail structure, due to the complexity of the structure, the above limitations of this loading method are highlighted, and the design of the test scheme and the difficulty of field implementation Increase. Contents of the...

Claims

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Application Information

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IPC IPC(8): G01M13/00
CPCG01M13/00
Inventor 韩凯夏龙刘兴科
Owner CHINA AIRPLANT STRENGTH RES INST
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