CN215851969U - Aircraft structural strength test loading device - Google Patents
Aircraft structural strength test loading device Download PDFInfo
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- CN215851969U CN215851969U CN202121126015.4U CN202121126015U CN215851969U CN 215851969 U CN215851969 U CN 215851969U CN 202121126015 U CN202121126015 U CN 202121126015U CN 215851969 U CN215851969 U CN 215851969U
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Abstract
The application belongs to the field of aircraft structural strength verification tests, and particularly relates to an aircraft structural strength test loading device. The method comprises the following steps: the device comprises a lever (4), a fixed pull plate (2), a pulley (7), a steel wire rope (5) and a controller. The lever (4) is connected with the test piece; the fixed pull plate (2) is connected with the lever (4) through the force measuring sensor (3); the pulley (7) is connected with the other end of the fixed pulling plate (2); one end of the steel wire rope (5) is fixed, and the other end of the steel wire rope penetrates through the pulley (7) to be connected with the actuating cylinder (1); the controller controls the magnitude of the loading force of the actuating cylinder (1) through the received signal of the load cell (3). The loading device and the loading method can realize reliable and accurate loading, eliminate loading errors, avoid risks caused by complex loading forms, improve the installation efficiency of loading equipment, shorten the test period and increase the reliability and safety of tests.
Description
Technical Field
The application belongs to the field of aircraft structural strength verification tests, and particularly relates to an aircraft structural strength test loading device.
Background
In an aircraft structure static force/fatigue test, an actuating cylinder loading mode is generally adopted, the installation position is selected in the loading force line direction, a sensor and a control system which are installed in the loading direction form closed-loop control loading, the loading system is feasible under the normal condition, the loading requirement of the aircraft static strength test can be met, and the loading direction has enough space to facilitate the installation of loading equipment such as the actuating cylinder and the like. However, in some cases, there are obstacles in the loading direction such as structures or auxiliary, supporting and loading devices, which make it difficult to directly mount the ram in the direction of the force line, or the mounting is too complicated, so that the loading risk becomes high. In the current test, a static pulley guide device or a square lever is mainly adopted to bypass the obstacle in the direction of the loading force line. The first mode needs great space fixing guide device, and the second mode needs to adopt large-scale lever when too big to the obstacle face in the line of force direction, and weight is heavier, influences experimental loading precision.
Accordingly, a technical solution is desired to overcome or at least alleviate at least one of the above-mentioned drawbacks of the prior art.
SUMMERY OF THE UTILITY MODEL
The application aims at providing an aircraft structural strength test loading device to solve at least one problem that prior art exists.
The technical scheme of the application is as follows:
an aircraft structural strength test loading device, comprising:
the lever is connected with the test piece;
the fixed pull plate is connected with the lever through the force transducer;
the pulley is connected with the other end of the fixed pulling plate;
one end of the steel wire rope is fixed, and the other end of the steel wire rope penetrates through the pulley and is connected with the actuating cylinder;
and the controller controls the magnitude of the loading force of the actuating cylinder through the received load cell signal.
Optionally, mounting holes are formed in two ends of the lever, and the test piece is mounted in the mounting holes of the lever through fasteners.
Optionally, a first single lug joint and a second single lug joint are respectively arranged at two ends of the force measuring sensor, the first single lug joint is connected with the middle of the lever, and the second single lug joint is connected with the fixed pulling plate.
Optionally, the steel wire ropes on the two sides of the pulley have the same included angle with the vertical direction.
Optionally, the ram is a hydraulic ram.
Utility model has the following beneficial technical effects:
the loading device for the aircraft structural strength test can realize reliable and accurate loading, eliminate loading errors, avoid risks caused by complex loading forms, improve the installation efficiency of loading equipment, shorten the test period and increase the reliability and safety of the test.
Drawings
Fig. 1 is a schematic view of an aircraft structural strength test loading device according to an embodiment of the present application.
Wherein:
1-an actuator cylinder; 2, fixing a pulling plate; 3-a force sensor; 4-a lever; 5-a steel wire rope; 6-load direction; 7-pulley.
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the drawings in the embodiments of the present application. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are a subset of the embodiments in the present application and not all embodiments in the present application. The embodiments described below with reference to the drawings are exemplary and intended to be used for explaining the present application and should not be construed as limiting the present application. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present application. Embodiments of the present application will be described in detail below with reference to the accompanying drawings.
In the description of the present application, it is to be understood that the terms "center", "longitudinal", "lateral", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like indicate orientations or positional relationships based on those shown in the drawings, and are used merely for convenience in describing the present application and for simplifying the description, and do not indicate or imply that the referenced device or element must have a particular orientation, be constructed in a particular orientation, and be operated, and therefore should not be construed as limiting the scope of the present application.
The present application is described in further detail below with reference to fig. 1.
The application provides an experimental loading device of aircraft structural strength, includes: the device comprises a lever 4, a fixed pull plate 2, a pulley 7, a steel wire rope 5 and a controller.
Specifically, as shown in fig. 1, the lever 4 is connected with the test piece to form load distribution and transfer load, wherein the test piece is mounted in the mounting hole of the lever 4 through a fastener by forming mounting holes at two ends of the lever 4. The fixed pulling plate 2 is connected with a lever 4 through a force sensor 3. In this embodiment, a first monaural joint and a second monaural joint are respectively disposed at two ends of the load cell 3, the load cell 3 is hinged to the middle of the lever 4 through the first monaural joint, the load cell 3 is hinged to the fixed pulling plate 2 through the second monaural joint, and the load cell 3 is further connected to a controller to feed back the load of a loading point. The pulley 7 is connected with the other end of the fixed pulling plate 2 and used for converting the loading direction; one end of the steel wire rope 5 is fixed, the other end of the steel wire rope penetrates through the pulley 7 to be connected with loading equipment, the loading equipment is the actuating cylinder 1, the steel wire rope 5 can bear the pulley 7 and transmit load, and the fixing position of the steel wire rope 5 is adjustable. In this embodiment, the actuator cylinder 1 is a hydraulic actuator cylinder. The controller can control the magnitude of the loading force of the actuator cylinder 1 through the received signal of the load cell 3.
In a preferred embodiment of the application, the steel cables 5 on both sides of the pulley 7 have the same angle to the vertical. The V-shaped steel wire ropes 5 are arranged, the forces on two sides of the movable pulley are equal, the isosceles triangle equal division principle is adopted, the resultant force direction is always along the angular bisector direction in the test loading and test piece deformation processes, the stress direction of the test piece is kept unchanged, the loading accuracy is guaranteed, meanwhile, a small-tonnage actuator cylinder can apply a larger load to a certain extent, and the influence of the self weight of loading equipment on the loading accuracy is reduced. Different direction loading can also be satisfied by changing the loading direction 6.
In the loading process of the aircraft structural strength test loading device, the controller controls the hydraulic actuator cylinder to contract, the steel wire rope 5 is driven to contract, the pulling force is transmitted to the other end fixing part by bypassing the pulley 7 through the steel wire rope 5, according to the load transmission principle of the movable pulley, the pulling forces at two ends of the steel wire rope 5 are always equal, the resultant force direction is along the symmetrical angular bisector direction, the force is transmitted to the controller through the force measuring sensor 3 in a feedback manner, the control loading is realized, the loading of an interfering object is bypassed, the coordination of space loading is simplified, and the reliability and the accuracy of the test are ensured simultaneously.
According to the loading device for the aircraft structural strength test, the loading equipment occupies a small space in the direction of the force line, and the installation position is convenient to coordinate; the form is simple, the adjustment is flexible, and the installation position of the equipment is selected more; multi-directional loading can be carried out; the control is conventional and is the same as a single hydraulic ram loading system. The loading device and the loading method can realize reliable and accurate loading, eliminate loading errors, avoid risks caused by complex loading forms, improve the installation efficiency of loading equipment, shorten the test period and increase the reliability and safety of tests.
The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (5)
1. The utility model provides an aircraft structural strength tests loading device which characterized in that includes:
the lever (4), the said lever (4) is connected with test piece;
the fixed pull plate (2) is connected with the lever (4) through the force transducer (3);
the pulley (7), the said pulley (7) is connected with another end of the said fixed pulling plate (2);
one end of the steel wire rope (5) is fixed, and the other end of the steel wire rope (5) penetrates through the pulley (7) to be connected with the actuating cylinder (1);
and the controller controls the magnitude of the loading force of the actuating cylinder (1) through the received signal of the load cell (3).
2. The aircraft structural strength test loading device according to claim 1, wherein mounting holes are formed in two ends of the lever (4), and the test piece is mounted in the mounting hole of the lever (4) through a fastener.
3. The aircraft structural strength test loading device according to claim 2, wherein a first single lug joint and a second single lug joint are respectively arranged at two ends of the load cell (3), the first single lug joint is connected with the middle part of the lever (4), and the second single lug joint is connected with the fixed pulling plate (2).
4. The aircraft structural strength test loading device according to claim 3, wherein the steel wire ropes (5) on both sides of the pulley (7) have the same included angle with the vertical direction.
5. The aircraft structural strength test loading device of claim 1, wherein the ram (1) is a hydraulic ram.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202121126015.4U CN215851969U (en) | 2021-05-25 | 2021-05-25 | Aircraft structural strength test loading device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202121126015.4U CN215851969U (en) | 2021-05-25 | 2021-05-25 | Aircraft structural strength test loading device |
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| Publication Number | Publication Date |
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| CN215851969U true CN215851969U (en) | 2022-02-18 |
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| CN202121126015.4U Active CN215851969U (en) | 2021-05-25 | 2021-05-25 | Aircraft structural strength test loading device |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114778050A (en) * | 2022-06-27 | 2022-07-22 | 中国飞机强度研究所 | Fatigue load flexible applying system for testing aircraft vibration superposition fatigue strength |
-
2021
- 2021-05-25 CN CN202121126015.4U patent/CN215851969U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114778050A (en) * | 2022-06-27 | 2022-07-22 | 中国飞机强度研究所 | Fatigue load flexible applying system for testing aircraft vibration superposition fatigue strength |
| CN114778050B (en) * | 2022-06-27 | 2022-09-02 | 中国飞机强度研究所 | Fatigue load flexible applying system for testing aircraft vibration superposition fatigue strength |
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