CN111301713A - Double-beam type wing adhesive tape load sharing method - Google Patents
Double-beam type wing adhesive tape load sharing method Download PDFInfo
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- CN111301713A CN111301713A CN202010276005.2A CN202010276005A CN111301713A CN 111301713 A CN111301713 A CN 111301713A CN 202010276005 A CN202010276005 A CN 202010276005A CN 111301713 A CN111301713 A CN 111301713A
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- load
- adhesive tape
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- adhesive
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- 239000002390 adhesive tape Substances 0.000 title claims abstract description 106
- 238000000034 method Methods 0.000 title claims abstract description 26
- 238000012360 testing method Methods 0.000 claims abstract description 30
- 230000003068 static effect Effects 0.000 claims abstract description 12
- 238000012216 screening Methods 0.000 claims abstract description 5
- 239000000853 adhesive Substances 0.000 claims description 6
- 230000001070 adhesive effect Effects 0.000 claims description 6
- 239000004744 fabric Substances 0.000 claims 1
- 238000013461 design Methods 0.000 description 6
- 230000005540 biological transmission Effects 0.000 description 5
- 238000012545 processing Methods 0.000 description 3
- 230000009977 dual effect Effects 0.000 description 2
- 230000006355 external stress Effects 0.000 description 1
- 238000007689 inspection Methods 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/60—Testing or inspecting aircraft components or systems
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- Engineering & Computer Science (AREA)
- Manufacturing & Machinery (AREA)
- Transportation (AREA)
- Aviation & Aerospace Engineering (AREA)
- Investigating Strength Of Materials By Application Of Mechanical Stress (AREA)
Abstract
The application provides a double-beam type wing adhesive tape load sharing method, which comprises the following steps: taking the intersection points of ribs, a front beam and a rear beam in the wing as nodes, screening out the maximum load of each node according to the working condition load of a full-mechanical static test, and calculating the required adhesive tape parameters of each node according to the maximum load, wherein the adhesive tape parameters comprise the number and the specification of the adhesive tape; the long axis direction of the adhesive tape is parallel to the ribs and arranged along the front and rear beam directions of the wing; calculating a resultant force center of the adhesive tape, redistributing the working condition load of each full-mechanical static test to the resultant force center of the adhesive tape, judging whether the parameters of the adhesive tape are reasonable according to the magnitude of the working condition load, and determining the parameters of the adhesive tape through multiple cycles; and calculating the coordinates and the bearing capacity of the tail end of the lever of the front beam and the rear beam of each rib according to the positions and the loads of the adhesive tapes on the front beam and the rear beam of each rib to obtain the front beam resultant force point and the rear beam resultant force point of each rib. The method can reduce the number of the adhesive tapes and enable the applied load to be more accurate.
Description
Technical Field
The application belongs to the technical field of static test of airplanes, and particularly relates to a double-beam type airplane wing adhesive tape load sharing method.
Background
The wing adhesive tape is an aviation metal adhesive tape and can be used for surface sticking of parts such as airplane external stress, windward parts and the like. In aircraft structural static tests, the wing tapes are typically placed at the intersection of stringers and ribs, with the long axis parallel to the wing spar.
Such an arrangement has two problems: firstly, the number of the adhesive tapes is large, the whole wing airfoil surface is almost covered by the adhesive tapes, the pasting workload is large, the use efficiency of the adhesive tapes is low, and the dense adhesive tapes also bring difficulties for the arrangement of the wing airfoil surface measuring points and the routing of measuring lines; secondly, in the loading process of the large deformation test of the wing, the risk of the adhesive tape falling off exists because the loading direction is not perpendicular to the long axis of the adhesive tape.
In order to more accurately check the loading and force transmission conditions of the wings and simultaneously reserve enough space for the main wing surfaces of the wings to adhere strain gauges to monitor the force transmission conditions of the wings, a wing adhesive tape load distribution method for a full-aircraft static test is needed.
Disclosure of Invention
The application aims to provide a double-beam type wing adhesive tape load distribution method to solve or alleviate at least one problem in the background art.
In one aspect, the technical solution provided by the present application is: a method of double beam wing rubberized tape load sharing, the method comprising:
taking intersection points of ribs, a front beam and a rear beam in the wing as nodes, screening out the maximum load of each node according to the working condition load of a full-mechanical static test, and calculating the required adhesive tape parameters of each node according to the maximum load, wherein the adhesive tape parameters comprise the number and the specification of adhesive tapes;
the long axis direction of the adhesive tape is parallel to the ribs and arranged along the front and rear beam directions of the wing;
calculating a resultant force center of the adhesive tape, redistributing the working condition load of each full-mechanical static test to the resultant force center of the adhesive tape, judging whether the parameters of the adhesive tape are reasonable according to the magnitude of the working condition load, and determining the parameters of the adhesive tape through multiple cycles;
and modularizing the adhesive tapes through the auxiliary lever according to the positions and loads of the adhesive tapes on the front beam and the rear beam of each rib, enabling the finite element node load to be directly equivalent to the tail end resultant force point of the auxiliary lever, and calculating the tail end coordinates and the bearing capacity of the lever of the front beam and the rear beam of each rib to obtain the front beam resultant force point and the rear beam resultant force point of the rib.
In an embodiment of the application, the working condition load of the full-mechanical static test comprises the working condition load of a full-mechanical 2.5G maneuvering balance test and the working condition load of the maximum vertical landing.
In one embodiment of the present application, the maximum load requirement of each node can be achieved by at least one size and number of adhesive tapes.
In this application embodiment, whether the size according to operating mode load judges rubberized tape quantity reasonable, include:
if the magnitude of the working condition load is larger than the adhesive force which can be provided by the plurality of adhesive tapes, the working condition load is unreasonable;
if the size of the working condition load is smaller than the adhesive force which can be provided by the plurality of adhesive tapes, the working condition load is reasonable.
On the other hand, the technical scheme provided by the application is as follows: a dual beam airfoil determined by the dual beam airfoil rubberized tape load sharing method as described in any one of the above.
Compared with the conventional wing adhesive tape arrangement of the same type, the double-beam wing adhesive tape load distribution method can reduce the number of the adhesive tapes by nearly 40 percent, further reduce the workload and save the test time; in addition, the adhesive tape is modularized through the auxiliary lever, the workload of later-stage test design can be greatly reduced, the load of a finite element node is directly equivalent to the resultant force point at the tail end of the auxiliary lever, the intermediate process of load processing is reduced, and the load applied in the test is more accurate; and finally, the tail end resultant force point of the auxiliary lever is close to the front and rear beams of the wing, so that the loaded and force-transferring examination of the wing is more real and accurate, meanwhile, enough space is reserved for the main wing surface of the wing to be adhered with a strain gauge, and the wing surface is clean and tidy.
Drawings
In order to more clearly illustrate the technical solutions provided by the present application, the following briefly introduces the accompanying drawings. It is to be expressly understood that the drawings described below are only illustrative of some embodiments of the invention.
Fig. 1 is a schematic view of a wing adhesive tape load distribution method of the present application.
Fig. 2 is a schematic view of an internal structure of a wing according to an embodiment of the present application.
Fig. 3 is a schematic view of a wing tape layout according to an embodiment of the present application.
Fig. 4 is a schematic view of an auxiliary lever of a wing adhesive tape according to an embodiment of the present application.
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 order to solve the problems that in the prior art, the coverage area of an adhesive tape belt on the surface of a flexible wing with a large aspect ratio is large, the adhesive tape belt bonding workload is large, the adhesive tape belt is low in use efficiency, and the wing is subjected to pull-off risk due to large deformation, the application aims to provide the wing adhesive tape belt load sharing method applicable to the full-aircraft static test of a large civil aircraft, so that the loading and force transmission of the wing are more accurate, a sufficient space is reserved for a main wing surface of the wing to bond a strain gauge to monitor the neat force transmission condition of the wing, the wing surface is clean, the field installation and inspection are convenient, and the test load processing period is shortened.
Therefore, the technical scheme provided by the application is as shown in figure 1:
s1, taking intersection points of ribs of the wings and front and rear beams as nodes, screening out the maximum load of each node according to all working condition test loads in the full-static test, and calculating the needed adhesive tape block parameters of each node according to the maximum loads, wherein the adhesive tape block parameters comprise the number of adhesive tape blocks and the specification of the adhesive tape.
Wherein, the commonly used specifications of the adhesive tape comprise several specifications: for example a 210mm 110 gauge strip which may provide an adhesion with a use force of 4KN, for example a 170mm 110mm gauge strip which may provide an adhesion with a use force of 3 KN.
It should be noted that, for the number and specifications of the adhesive tapes on the nodes, the use requirements can be met by using several adhesive tapes or two or more adhesive tapes in combination, but it is not excluded that the use requirements can be met by only one specification and a single number of adhesive tapes on some nodes.
In an embodiment of the application, in all the working condition loads in the full-static test, only the item with the larger working condition load is generally selected, for example, the full-machine 2.5G maneuvering balance working condition and the maximum vertical landing working condition.
And S2, when the two-dimensional design of the adhesive tapes is carried out, the long axis directions of all the adhesive tapes are parallel to the ribs and are arranged in a line along the front and rear beams of the wing.
And S3, calculating a resultant force center of the adhesive tape, redistributing each full-airplane working condition load to the resultant force center of the adhesive tape, judging whether the number of the adhesive tape blocks is reasonable according to the load size, and finally finishing the design of the wing adhesive tape through multiple cycles.
In this application, judge whether reasonable process of adhesive tape quantity is according to the size of operating mode load:
1) if the magnitude of the working condition load is larger than the adhesive force which can be provided by the plurality of adhesive tapes, the working condition load is unreasonable;
2) if the size of the working condition load is smaller than the adhesive force provided by the plurality of adhesive tapes, the size is reasonable.
And S4, finally, combining the universal levers to calculate the coordinates of the tail ends of the front and rear beam levers of the ribs and the bearing capacity according to the positions and the loads of the adhesive tapes on the front and rear beams of the ribs, and obtaining the front beam resultant force point and the rear beam resultant force point of the ribs.
Compared with the conventional arrangement of the adhesive tapes of the same type, the adhesive tape arrangement method for the wings can reduce the number of the adhesive tapes by nearly 40 percent, thereby reducing the workload and saving the test time; in addition, the adhesive tape is modularized through the auxiliary lever, the workload of later-stage test design is greatly reduced, the load of a finite element node is directly equivalent to the resultant force point at the tail end of the auxiliary lever, the intermediate process of load processing is reduced, and the load applied in the test is more accurate; and finally, the tail end resultant force point of the auxiliary lever is close to the front and rear beams of the wing, so that the loaded and force-transferring examination of the wing is more real and accurate, meanwhile, enough space is reserved for the main wing surface of the wing to be adhered with a strain gauge, and the wing surface is clean and tidy.
Taking a certain large civil aircraft as an example, the double-beam type wing adhesive tape load sharing method is introduced.
1. As shown in fig. 2, the wing of a large civil aircraft comprises a plurality of ribs 1, front and rear beams 2-3 extend along the wingspan direction, the source load resultant force point in the test task book is the intersection point 4 of the front and rear beams 2-3 of the wing box and the ribs 1, and each resultant force point has forces in three directions; wherein the vertical force and the lateral force are mainly born by the wing adhesive tape.
Due to the force transmission characteristic of the wing load, the intersection point of each rib 1 and the front and rear beams 2-3 on the wing is taken as a resultant force point, the adhesive tapes are arranged in a straight line as close to the front and rear beams 2-3 as possible, and the load is directly transmitted to the wing main beam through the adhesive tapes in the test. Meanwhile, the long axis direction of the adhesive tape is parallel to the rib line, and the configuration of the loading direction and the loading process is optimized, so that the loading direction is always vertical to the long axis of the adhesive tape in the test process. The arrangement of the adhesive tape is shown in fig. 3.
2. After the arrangement scheme is determined, the number of required adhesive tape blocks of each resultant force point needs to be determined. And (3) combining all test working conditions of the whole machine, firstly screening out the maximum load of each resultant force point, and assuming that each adhesive tape is uniformly stressed and reaches the maximum bearing capacity, so as to obtain the required number of the adhesive tape blocks.
And finishing the two-dimensional design of the adhesive tape according to the result, and calculating the resultant force center of the adhesive tape of each resultant force point. And then, each full-machine working condition load is redistributed to the resultant force center of the adhesive tape, and whether the number of the adhesive tape blocks is reasonable or not is judged according to the size of the load. And finally finishing the design of the wing adhesive tape through multiple cycles.
3. And according to the positions and loads of the front beam adhesive tape and the rear beam adhesive tape of each rib, ensuring that each adhesive tape is uniformly stressed and combined with a universal lever, and calculating the tail end coordinates and the bearing capacity of the front beam lever and the rear beam lever of each rib to obtain the front beam resultant force point and the rear beam resultant force point of each rib. The auxiliary lever of the wing rubberized tape is shown in figure 4.
And (3) integrating the adhesive tapes at the intersection points of each rib and the front and rear beams into a large adhesive tape through a lever system, and equating the load to the large adhesive tape. In subsequent tests, the wing load is equivalently processed to the resultant force point of each rib, the front beam and the rear beam of the wing.
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. A method for distributing load of a double-beam type wing adhesive tape is characterized by comprising the following steps:
taking intersection points of ribs, a front beam and a rear beam in the wing as nodes, screening out the maximum load of each node according to the working condition load of a full-mechanical static test, and calculating the required adhesive tape parameters of each node according to the maximum load, wherein the adhesive tape parameters comprise the number and the specification of adhesive tapes;
the long axis direction of the adhesive tape is parallel to the ribs and arranged along the front and rear beam directions of the wing;
calculating a resultant force center of the adhesive tape, redistributing the working condition load of each full-mechanical static test to the resultant force center of the adhesive tape, judging whether the parameters of the adhesive tape are reasonable according to the magnitude of the working condition load, and determining the parameters of the adhesive tape through multiple cycles;
and modularizing the adhesive tapes through the auxiliary lever according to the positions and loads of the adhesive tapes on the front beam and the rear beam of each rib, enabling the finite element node load to be directly equivalent to the tail end resultant force point of the auxiliary lever, and calculating the tail end coordinates and the bearing capacity of the lever of the front beam and the rear beam of each rib to obtain the front beam resultant force point and the rear beam resultant force point of the rib.
2. The method for distributing the load of the double-beam wing rubberized fabric tape of claim 1, wherein the working load of the full-mechanical static test comprises the working load of a full-mechanical 2.5G dynamic balance test and the working load of the maximum vertical landing.
3. A method of loading a twin beam airfoil tape as defined in claim 1 wherein the maximum load requirement at each node is achieved by at least one gauge and number of tapes.
4. The method for distributing the adhesive tapes of the double-beam wing according to claim 1, wherein the step of judging whether the number of the adhesive tapes is reasonable according to the magnitude of the working condition load comprises the following steps:
if the magnitude of the working condition load is larger than the adhesive force which can be provided by the plurality of adhesive tapes, the working condition load is unreasonable;
if the size of the working condition load is smaller than the adhesive force which can be provided by the plurality of adhesive tapes, the working condition load is reasonable.
5. A twin beam airfoil characterized in that it is determined by the twin beam airfoil tape load sharing method of any one of claims 1 to 4.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010276005.2A CN111301713A (en) | 2020-04-09 | 2020-04-09 | Double-beam type wing adhesive tape load sharing method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010276005.2A CN111301713A (en) | 2020-04-09 | 2020-04-09 | Double-beam type wing adhesive tape load sharing method |
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| Publication Number | Publication Date |
|---|---|
| CN111301713A true CN111301713A (en) | 2020-06-19 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202010276005.2A Pending CN111301713A (en) | 2020-04-09 | 2020-04-09 | Double-beam type wing adhesive tape load sharing method |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116698471A (en) * | 2023-08-07 | 2023-09-05 | 四川腾盾科技有限公司 | Static strength test method for aircraft control surface |
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|---|---|---|---|---|
| GB127311A (en) * | 1917-04-13 | 1919-06-05 | Hugh Brett Dudd | Improvements in and relating to Means for Applying Tape and the like to the Wings of Aeroplanes and for like Purposes. |
| CN203889083U (en) * | 2014-04-29 | 2014-10-22 | 中国飞机强度研究所 | Adhesive tape loading rod fixing device for adhesive tape and lever loading system |
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| CN210205880U (en) * | 2019-05-24 | 2020-03-31 | 西安理工大学 | Model airplane wing assembling frame |
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2020
- 2020-04-09 CN CN202010276005.2A patent/CN111301713A/en active Pending
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| GB127311A (en) * | 1917-04-13 | 1919-06-05 | Hugh Brett Dudd | Improvements in and relating to Means for Applying Tape and the like to the Wings of Aeroplanes and for like Purposes. |
| CN203889083U (en) * | 2014-04-29 | 2014-10-22 | 中国飞机强度研究所 | Adhesive tape loading rod fixing device for adhesive tape and lever loading system |
| CN105716842A (en) * | 2014-12-05 | 2016-06-29 | 中国飞机强度研究所 | Double-beam type long straight wing load processing method |
| CN107521721A (en) * | 2017-07-20 | 2017-12-29 | 中国航空工业集团公司西安飞机设计研究所 | A kind of full scale fatigue test fuselage course load designing load method |
| CN109573098A (en) * | 2018-12-04 | 2019-04-05 | 中国航空工业集团公司西安飞机设计研究所 | A kind of high vertical fin vertical load designing load method of full scale fatigue test |
| CN210205880U (en) * | 2019-05-24 | 2020-03-31 | 西安理工大学 | Model airplane wing assembling frame |
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| Title |
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| 刘冰等: "基于误差控制的大展弦比机翼静强度试验载荷处理技术", 《科学技术与工程》 * |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116698471A (en) * | 2023-08-07 | 2023-09-05 | 四川腾盾科技有限公司 | Static strength test method for aircraft control surface |
| CN116698471B (en) * | 2023-08-07 | 2023-11-07 | 四川腾盾科技有限公司 | Static strength test method for aircraft control surface |
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Application publication date: 20200619 |