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-Extracted 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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Method used

Step 1: the vertical tail frame 1 is installed between the inner vertical tails, the upper end single ear 2 of the vertical tail frame 1 is connected to the loading beam 3 by bolts, the distance between the vertical tail frame 1 lower end and the rear fuselage of the aircraft Not less than 300mm, the connection form between the single ear 2 at the upper end of the vertical tail frame 1 and the loading beam 3 is a hinge joint, which only bears the force load, and the bending moment load is borne by the connection between the lower end of the ve...
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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.

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  • Four-vertical-fin load loading method
  • Four-vertical-fin load loading method

Examples

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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 6 for inner vertical tail loading;
[0026] Step 4: Install the actuator base on the corresponding position of the vertical tail lateral loading beam 8 according to different test conditions, and install the actuator 7 on the actuator base for external vertical tail loading;
[0027] Step 5: Use the manual hoist 9 to connect the actuator 7 and the loading beam 3, by adjusting the length of the rewinding chain of the manual hoist 9, adjust the load angle of the actuator 7 to different test conditions, and connect the actuator 7 to the vertical The tail end special-shaped lever 10 is connected to complete the installation of the vertical tail loading equipment on one side of the aircraft;
[0028] Step 6: Repeat steps 2-5 to install the vertical tail loading equipment on the other side of the aircraft.
[0029] 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 The connection between the upper lug 2 of the vertical tail frame 1 and the loading beam 3 is hinged, which only bears the force load, and the bending moment load is borne by the lower end of the vertical tail frame 1 and the lateral loading column, thereby optimizing the vertical The force transmission path of the tail frame 1 reduces the bearing risk at the connection between the vertical tail frame 1 and the loading beam 3 and ensures the safety of loading.
[0030] The upper end of the vertical tail frame 1 described in step 2 is connected to the loading beam 3 through the upper end pull plate 4, the lower end of the vertical tail frame 1 is connected to the lateral loading column through the lower end pull plate 5, and the upper end pull plate 4 is kept in a relaxed state. To bear the load, it only plays a protective role, and the lower end pull plate 5 maintains a tensioned state to limit the deformation of the vertical tail frame 1 and balance the load caused by the load.
[0031] The vertical tail of the present invention adopts the loading method of "special-shaped lever-tension and compression pad", which facilitates the application of load in both directions of tension and compression, reduces the space occupied by the lever, and solves the problem of narrow loading space of the internal vertical tail.
[0032] In the airplane’s four vertical tail static test, this method was applied, solved the key problems, and achieved obvious results. Practice has proved that this method can not only realize the application of vertical tail load bidirectional tension and compression loading, but also avoid loading equipment. The problem of space interference between the loading equipment and the test piece facilitates the design of the test plan and the implementation of on-site installation work, and can ensure an open and unobstructed measurement space, which is conducive to non-contact optical measurement technology (such as camera displacement measurement system) Applications.
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