CN210293906U - Novel loading of tail wing device - Google Patents
Novel loading of tail wing device Download PDFInfo
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- CN210293906U CN210293906U CN201921241667.5U CN201921241667U CN210293906U CN 210293906 U CN210293906 U CN 210293906U CN 201921241667 U CN201921241667 U CN 201921241667U CN 210293906 U CN210293906 U CN 210293906U
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Abstract
A novel loading device for a tail wing of a airplane comprises a tail wing body, a carbon fiber lever piece I, a carbon fiber lever piece II, a carbon fiber lever piece III and a chest expander, wherein 6 loading points are arranged on the tail wing body; the carbon fiber lever piece I, the carbon fiber lever piece II and the carbon fiber lever piece III are respectively provided with 3 loading points; the number of the carbon fiber lever pieces I is 3, the loading points at two ends of each carbon fiber lever piece I are respectively connected to the loading points on the tail wing body, and the loading point on one carbon fiber lever piece I corresponds to the loading point on one tail wing body; the loading points at the two ends of the carbon fiber lever piece II are respectively connected to the loading point in the middle of two carbon fiber lever pieces I; the carbon fiber lever piece III is characterized in that the loading points at the two ends of the carbon fiber lever piece III are respectively connected to the middle loading point of the carbon fiber lever piece II and the middle loading point of the other carbon fiber lever piece I, and the middle loading point of the carbon fiber lever piece III is connected to the chest expander. The utility model discloses simple structure, reasonable in design, it is with low costs, efficient.
Description
Technical Field
The utility model relates to an aircraft performance test technical field specifically is a novel wing loading of tail device.
Background
Unmanned aerial vehicles are an important means for battlefield reconnaissance in modern war. The small unmanned aerial vehicle has the characteristics of small appearance size, good visual stealth effect, low manufacturing cost, flexible and convenient transportation and use, high battlefield maneuverability and the like, and is an important weapon for realizing tactical tasks such as front line peeking and investigation of enemies, information relay, auxiliary communication and the like in modern war. The unmanned aerial vehicle is generally of a long straight wing structure with a high aspect ratio, carries necessary communication and investigation equipment loads, and has certain air stagnation capacity. Foreign famous drones, such as the "scanning eagle" drone, belong to this type.
The airplane structure strength test is usually a structure static test, which is to load a certain level of static load on the surface of an airplane, measure the deformation and strain states of a structure and test the bearing capacity of the airplane under the action of a design load, thereby providing guarantee for the flight safety and the structure safety of the airplane.
At present, when the structural strength of the airplane empennage is tested, 6-8 static load loading points are usually taken on the airplane empennage, and then static loads are simultaneously applied to the loading points through a chest expander or other force application devices. This approach has the following disadvantages: 1) a plurality of force application devices (chest expanders) are needed to apply load to the static load point at the same time, and the cost investment of the chest expander is large; 2) a plurality of chest expanders work simultaneously, and complex operation is not convenient for control.
SUMMERY OF THE UTILITY MODEL
The utility model aims at overcoming the not enough of existence among the prior art, provide a novel tail wing load loading device, solved present when experimental to aircraft fin structural strength, need a plurality of force applying device (chest expander) to exert load to the dead load point simultaneously, the chest expander cost drops into great to a plurality of chest expanders simultaneous workings, complex operation, the problem of being not convenient for control.
In order to realize the purpose, the utility model discloses a technical scheme be:
a novel loading device for a tail wing of a airplane comprises a tail wing body, a carbon fiber lever piece I, a carbon fiber lever piece II, a carbon fiber lever piece III and a chest expander, wherein 6 loading points are fixedly arranged on the tail wing body; the carbon fiber lever piece I, the carbon fiber lever piece II and the carbon fiber lever piece III are respectively provided with 3 loading points, wherein one loading point is positioned in the middle of the carbon fiber lever piece I, the carbon fiber lever piece II and the carbon fiber lever piece III, and the other two loading points are respectively positioned at two ends of the carbon fiber lever piece I, the carbon fiber lever piece II and the carbon fiber lever piece III; 3 carbon fiber lever pieces I are arranged; the loading points at two ends of the 3 carbon fiber lever piece I are connected with the loading points on the tail wing body through steel wire ropes; the loading point on one carbon fiber lever piece I is correspondingly connected with the loading point on one empennage body; one carbon fiber lever piece II is arranged, and the loading points at the two ends of the carbon fiber lever piece II are respectively connected with the loading point in the middle of two carbon fiber lever pieces I through a steel wire rope; the carbon fiber lever piece III is provided with one, and the loading points at the two ends of the carbon fiber lever piece III are respectively connected with the loading point in the middle of the carbon fiber lever piece II and the loading point in the middle of the other carbon fiber lever piece I through steel wire ropes; and a loading point in the middle of the carbon fiber lever piece III is connected with a chest expander through a steel wire rope.
Further, the carbon fiber lever piece I, the carbon fiber lever piece II and the carbon fiber lever piece III are identical in structure size; the carbon fiber lever piece I, the carbon fiber lever piece II and the carbon fiber lever piece III are all provided with a moving chute; the loading points are all arranged in the movable sliding groove and can slide along the movable sliding groove.
Further, the loading point is a group of bolt and nut structures, nuts are installed in the moving sliding grooves, and bolts are installed on the nuts.
Furthermore, a display screen is arranged on the chest expander; the display screen can display the real-time tension of the chest expander.
When the novel loading device for the tail wing loads a tail wing structure, the positions of 3 loading points on 3 carbon fiber lever pieces I are respectively adjusted only according to the load size required to be applied by each load point on a tail wing body, so that the load of the novel loading device meets the load size required in the test, the positions of 3 loading points on the carbon fiber lever piece II are adjusted according to the resultant force of the middle loading points of two carbon fiber lever pieces I, the positions of 3 loading points on the carbon fiber lever piece III are adjusted according to the resultant force of the middle loading points of the other carbon fiber lever piece I and the resultant force of the middle loading points of the carbon fiber lever piece II, and finally, the resultant force load with the same size is provided by a tension device according to the size of the resultant force of the middle loading points of the carbon fiber lever piece III.
This novel tail wing load loading device, because each loading point is the bolt and nut structure, when adjusting the position of loading point, can unscrew the bolt earlier, make it along carbon fiber lever piece I, carbon fiber lever piece II, the removal spout that sets up on the carbon fiber lever piece III freely slides, make carbon fiber lever piece I, carbon fiber lever piece II, each loading point on the carbon fiber lever piece III all be in appropriate position, make the load size that requires when the load on each loading point on the fin body accords with the experiment.
The utility model discloses simple structure, and reasonable design can adjust carbon fiber lever piece I according to the lever theorem, carbon fiber lever piece II, the position of each loading point on the carbon fiber lever piece III, when the size that makes the load that each loading point on the fin body received accords with the test requirement, only need a chest expander can accomplish the load loading to a plurality of points on the fin body, the input cost of experimental equipment has been reduced, become a chest expander by a plurality of chest expanders originally, and convenient for operation and control are convenient for.
Drawings
FIG. 1 is a schematic view of the structure of the device of the present invention;
fig. 2 is a schematic structural view of the carbon fiber lever sheet of the present invention;
FIG. 3 is a schematic view of a mechanical model of the present invention;
FIG. 4 is a schematic view of a prior art tail load sensing device;
in the figure: 1. the empennage body, 2, carbon fiber lever pieces I and 3, carbon fiber lever pieces II and 4, carbon fiber lever pieces III and 5, a chest expander, 6 and a movable sliding groove.
Detailed Description
The present invention will be described in further detail with reference to the accompanying drawings.
The novel loading device for the tail wing load shown in fig. 1-2 comprises a tail wing body 1, a carbon fiber lever piece I2, a carbon fiber lever piece II3, a carbon fiber lever piece III4 and a chest expander 5, wherein 6 loading points are fixedly arranged on the tail wing body 1; the carbon fiber lever piece I2, the carbon fiber lever piece II3 and the carbon fiber lever piece III4 are respectively provided with 3 loading points, wherein one loading point is positioned in the middle of the carbon fiber lever piece I2, the carbon fiber lever piece II3 and the carbon fiber lever piece III4, and the other two loading points are respectively positioned at two ends of the carbon fiber lever piece I2, the carbon fiber lever piece II3 and the carbon fiber lever piece III 4; 3 carbon fiber lever pieces I2 are provided; the loading points at the two ends of the 3 carbon fiber lever piece I2 are connected with the loading points on the tail wing body 1 through steel wire ropes; a loading point on a carbon fiber lever piece I2 is correspondingly connected with a loading point on the tail wing body 1; one carbon fiber lever piece II3 is provided, and the loading points at the two ends of the carbon fiber lever piece II3 are respectively connected with the loading point in the middle of the two carbon fiber lever pieces I2 through a steel wire rope; the carbon fiber lever piece III4 is provided with one, and the loading points at the two ends of the carbon fiber lever piece III4 are respectively connected with the loading point in the middle of the carbon fiber lever piece II3 and the loading point in the middle of the other carbon fiber lever piece I2 through steel wire ropes; the middle loading point of the carbon fiber lever piece III4 is connected with the chest expander 5 through a steel wire rope; the carbon fiber lever piece I2, the carbon fiber lever piece II3 and the carbon fiber lever piece III4 are the same in structure size; the carbon fiber lever piece I2, the carbon fiber lever piece II3 and the carbon fiber lever piece III4 are all provided with a movable chute 6; the loading points are all arranged in the moving chute 6 and can slide along the moving chute 6; the loading points are of a group of bolt and nut structures, nuts are arranged in the moving chute 6, and bolts are arranged on the nuts; a display screen is arranged on the chest expander 5; the display screen can display the real-time tension of the chest expander 5.
When the novel loading device for the tail wing loads a tail wing structure, the positions of 3 loading points on 3 carbon fiber lever pieces I2 are respectively adjusted only according to the load size required to be applied by each load point on a tail wing body 1, so that the load meets the load size required in the test, the positions of 3 loading points on a carbon fiber lever piece II3 are adjusted according to the resultant force of the middle loading points of two carbon fiber lever pieces I2, the positions of 3 loading points on a carbon fiber lever piece III4 are adjusted according to the resultant force of the middle loading points of the other carbon fiber lever piece I2 and the resultant force of the middle loading points of the carbon fiber lever piece II3, and finally, the resultant force of the load with the same size as that of the resultant force is provided by a tension device 5 according to the size of the resultant force of the middle loading points of the carbon fiber lever piece III 4.
This novel tail wing load loading device, because each load point is the bolt and nut structure, when adjusting the position of load point, can loosen the bolt earlier, make it along carbon fiber lever piece I2, carbon fiber lever piece II3, the removal spout 6 that sets up on the carbon fiber lever piece III4 freely slide, make each load point on carbon fiber lever piece I2, carbon fiber lever piece II3, carbon fiber lever piece III4 all be in suitable position, make the load size that requires when the load on each load point on the fin body 1 accords with the experiment.
Specific example 1:
as shown in the mechanical model of fig. 3, the sizes of the 6 load points of the tail body 1 are respectively F1, F2, F3, F4, F5 and F6, and according to the lever theorem, the positions of the three load points on the two carbon fiber lever pieces I2 connected with the carbon fiber lever piece II3 are adjusted to: one is as follows: f3 × L3-F4 × L4=0, wherein the resultant force F8 of the intermediate load points is: f8= F3+ F4; the other one is as follows: f5 × L5-F6 × L6=0, wherein the resultant force F9 of the intermediate load points is: f9= F5+ F6. The positions of the three load points of the carbon fiber lever piece I2 connected with the carbon fiber lever piece III4 should be adjusted as follows: f1 × L1-F2 × L2=0, wherein the resultant force F7 of the intermediate load points is: f7= F1+ F2. Three load points on the carbon fiber lever piece II3 are adjusted to be the following positions: f8 × L8-F9 × L7=0, i.e.: (F3 + F4) × L8- (F5 + F6) × L7=0, wherein the resultant force F10 at the intermediate load point has the magnitude: f10= F8+ F9, i.e. F10= F3+ F4+ F5+ F6. The positions of three load points on the carbon fiber lever piece III4 are adjusted as follows: f7 × L9-F10 × L10=0, i.e.: (F1 + F2) × L9- (F3 + F4+ F5+ F6) × L10=0, in which the resultant force F11 at the intermediate load point has the magnitude: f11= F7+ F10, i.e. F11= F1+ F2+ F3+ F4+ F5+ F6. Therefore, only three load points on the carbon fiber lever piece I2, the carbon fiber lever piece II3 and the carbon fiber lever piece III4 are required to be adjusted to the calculated positions respectively and then screwed and fixed, and the tension device 5 provides a load force with the load size being the total load required on the tail wing body 1.
The utility model has the advantages of simple structure, and reasonable design, can adjust carbon fiber lever piece I2 according to the lever theorem, carbon fiber lever piece II3, the position of each loading point on carbon fiber lever piece III4, when the size that makes the load that each loading point on the fin body 1 received accords with experimental requirement, only need a chest expander 5 can accomplish the load loading to a plurality of points on the fin body, the input cost of experimental equipment has been reduced, become a chest expander 5 by original a plurality of chest expanders 5, and the operation is convenient, and the control is also convenient.
The above-described embodiments are illustrative of the present invention and not restrictive, it being understood that various changes, modifications, substitutions and alterations may be made herein without departing from the principles and spirit of the invention, the scope of which is defined by the appended claims and their equivalents.
Claims (4)
1. The novel loading device for the tail wing of the airplane is characterized by comprising an empennage body (1), a carbon fiber lever piece I (2), a carbon fiber lever piece II (3), a carbon fiber lever piece III (4) and a chest expander (5), wherein 6 loading points are fixedly arranged on the empennage body (1); the carbon fiber lever piece I (2), the carbon fiber lever piece II (3) and the carbon fiber lever piece III (4) are respectively provided with 3 loading points, wherein one loading point is positioned in the middle of the carbon fiber lever piece I (2), the carbon fiber lever piece II (3) and the carbon fiber lever piece III (4), and the other two loading points are respectively positioned at two ends of the carbon fiber lever piece I (2), the carbon fiber lever piece II (3) and the carbon fiber lever piece III (4); the number of the carbon fiber lever pieces I (2) is 3; the loading points at the two ends of the 3 carbon fiber lever piece I (2) are connected with the loading points on the tail wing body (1) through steel wire ropes; a loading point on one carbon fiber lever piece I (2) is correspondingly connected with a loading point on one empennage body (1); one carbon fiber lever piece II (3) is arranged, and the loading points at the two ends of the carbon fiber lever piece II are respectively connected with the loading point in the middle of two carbon fiber lever pieces I (2) through a steel wire rope; one carbon fiber lever piece III (4) is arranged, and the loading points at the two ends of the carbon fiber lever piece III are respectively connected with the loading point in the middle of the carbon fiber lever piece II (3) and the loading point in the middle of the other carbon fiber lever piece I (2) through steel wire ropes; and a loading point in the middle of the carbon fiber lever piece III (4) is connected with a chest expander (5) through a steel wire rope.
2. The novel loading device for the tail wing of the airplane as claimed in claim 1, wherein the carbon fiber lever piece I (2), the carbon fiber lever piece II (3) and the carbon fiber lever piece III (4) are the same in structural size; the carbon fiber lever piece I (2), the carbon fiber lever piece II (3) and the carbon fiber lever piece III (4) are all provided with a movable sliding chute (6); the loading points are all arranged in the moving chute (6) and can slide along the moving chute (6).
3. The novel tail wing load loading device of claim 2, wherein the loading point is a set of bolt and nut structures, nuts are installed in the moving sliding grooves (6), and bolts are installed on the nuts.
4. The novel tail wing load loading device of claim 1, wherein a display screen is arranged on the chest expander (5); the display screen can display the real-time tension of the chest expander (5).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921241667.5U CN210293906U (en) | 2019-08-02 | 2019-08-02 | Novel loading of tail wing device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921241667.5U CN210293906U (en) | 2019-08-02 | 2019-08-02 | Novel loading of tail wing device |
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| Publication Number | Publication Date |
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| CN210293906U true CN210293906U (en) | 2020-04-10 |
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| CN201921241667.5U Active CN210293906U (en) | 2019-08-02 | 2019-08-02 | Novel loading of tail wing device |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113176143A (en) * | 2021-03-30 | 2021-07-27 | 中国飞机强度研究所 | Full-size aircraft structure test double-wheel restraint system |
| CN113911390A (en) * | 2021-09-30 | 2022-01-11 | 上海交通大学 | Dynamic synchronous loading test device and method for morphing wing |
-
2019
- 2019-08-02 CN CN201921241667.5U patent/CN210293906U/en active Active
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113176143A (en) * | 2021-03-30 | 2021-07-27 | 中国飞机强度研究所 | Full-size aircraft structure test double-wheel restraint system |
| CN113176143B (en) * | 2021-03-30 | 2023-10-24 | 中国飞机强度研究所 | Full-size aircraft structural test double round restraint system |
| CN113911390A (en) * | 2021-09-30 | 2022-01-11 | 上海交通大学 | Dynamic synchronous loading test device and method for morphing wing |
| CN113911390B (en) * | 2021-09-30 | 2024-02-23 | 上海交通大学 | Dynamic synchronous loading test device and method for deformed wing |
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Address after: 333000 No. 01, Zhihang Road, High tech Zone, Jingdezhen, Jiangxi Patentee after: Jiangxi Helicopter Co.,Ltd. Address before: 333000 No. 01, Zhihang Road, High tech Zone, Jingdezhen, Jiangxi Patentee before: BGAC JIANGXI HELICOPTER CO.,LTD. |
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