CN210258874U - Outer wing butt joint face loading simulation piece - Google Patents
Outer wing butt joint face loading simulation piece Download PDFInfo
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- CN210258874U CN210258874U CN201920795004.1U CN201920795004U CN210258874U CN 210258874 U CN210258874 U CN 210258874U CN 201920795004 U CN201920795004 U CN 201920795004U CN 210258874 U CN210258874 U CN 210258874U
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- butt joint
- loading
- lug
- butt
- outer wing
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Abstract
The utility model belongs to the technical field of aviation, in particular to an outer wing butt joint surface loading simulation piece; the simulation piece is composed of two components with similar structural forms, wherein each component comprises a butt joint flat plate, a lug, a butt joint bolt and a nut; the butt joint flat plate is provided with butt joint holes matched with the bolt holes on the butt joint surface of the outer wing; the lug is vertical to the butt joint flat plate surface, and the axis of the lug is positioned on the central line of the two butt joint holes; the butt bolts are in clearance fit with the butt holes of the middle and outer wings, and can only bear tensile force but not shear force; the butt joint flat plate is in butt joint with the outer wing and is connected with the outer wing through a butt joint bolt, a loading lug hole is formed in the lug plate, and the loading lug hole is matched with the loading actuating cylinder. The utility model discloses propose for the first time to replace the outer wing box section with the dummy and carry out the strength test, solved when original strength test, need cause the problem that the test cost is high, test cycle is long through newly making the outer wing; the simulation piece ensures that the test result is real and reliable, greatly reduces the test cost and shortens the test period.
Description
Technical Field
The utility model belongs to the technical field of the aviation, concretely relates to outer wing butt joint face loading simulation piece for replace outer wing box section to carry out the intensity test.
Background
The strength test is an important basis for identifying the structural strength of the airplane in airplane design and development, and provides test data and conclusions for verifying whether the structure meets the strength requirement. The loading simulation piece of the outer wing butt joint surface is used for replacing a wing box section test in a strength test to carry out test loading, and is mainly used for replacing the wing box section test to carry out test loading in the strength test.
SUMMERY OF THE UTILITY MODEL
Utility model purpose: the utility model provides a replace wing box section to carry out the loaded dummy of intensity test, need cause the problem that test cost is high, test cycle length through new-made outer wing when having solved the intensity test.
The technical scheme is as follows: a simulation piece for loading an outer wing butt joint surface is composed of two components with similar structural forms, wherein each component comprises a butt joint flat plate, a lug, a butt joint bolt and a nut; wherein, the butt joint flat plate is provided with a butt joint hole matched with the bolt hole of the butt joint surface of the outer wing; the lug is vertical to the butt joint flat plate surface, and the axis of the lug is positioned on the central line of the two butt joint holes; the butt bolt is in clearance fit with the butt holes of the middle and outer wings, and can only bear tensile force but not shear force; the butt joint flat plate is in butt joint with the outer wing and is connected with the outer wing through a butt joint bolt, a loading lug hole is formed in the lug piece, and the aperture of the loading lug hole is designed to be matched with the loading actuator cylinder according to the test load condition. The loading simulation piece has the characteristics of small space, convenience in loading and the like.
Preferably, the butt-joint flat plate and the lug can be expanded according to the load condition in a mode that one lug is arranged in every two butt-joint holes. Through this expansion form, can be applicable to the experiment of different outer wing sizes.
Preferably, the axis of the butt bolt is vertical to the axis of the lug loading bolt, no interference occurs in space during assembly, and the axis of the lug loading hole and the axis of the butt bolt are in the same plane; during testing, the test load transfer efficiency is higher, and the test result is more reliable.
Advantageous technical effects
The utility model discloses it replaces the loading simulation spare blank of outer wing box section to have filled aircraft strength test, provides a replacement wing box section and carries out the loaded simulation spare of strength test. The loading simulation piece solves the problems that the test cost of a new outer wing box section is high and the model development period cannot be considered, reduces the test risk, ensures the credibility of the test result, shortens the model development period and reduces the test cost by about 10 percent.
Drawings
FIG. 1 is a schematic view of the butt-joint surface of the middle wing and the outer wing,
figure 2 is a front view of an outer wing interface loading simulator,
figure 3 is a top view of the loading simulator of the outer wing interface,
figure 4 is a cross-sectional view a-a,
figure 5 is a view of a docking bolt,
figure 6 is a schematic view of a cylindrical socket gasket,
description of numbering: 1-outer wing butt joint surface, 2-loading simulation piece, 3-outer wing butt joint hole, 4-butt joint bottom plate, 5-bottom plate butt joint hole, 6-lug plate, 7-loading lug hole, 8-butt joint bolt and 9-cylindrical socket washer.
Detailed Description
The invention is described in further detail below with reference to the accompanying drawings:
referring to fig. 1-6, the present invention provides an outer wing butt-joint surface loading simulation member, as shown in fig. 1, the simulation member is composed of two components with similar structural forms, wherein any one of the components at least includes a butt-joint flat plate, an ear piece, a butt-joint bolt and a nut; the butt joint flat plate is provided with butt joint holes matched with the bolt holes on the butt joint surface of the outer wing; the lug is vertical to the surface of the butt joint flat plate; the butt bolt is in clearance fit with the butt holes of the middle and outer wings, and can only bear tensile force but not shear force; the butt joint flat plate is in butt joint with the outer wing and is connected with the outer wing through a butt joint bolt, a loading lug hole is formed in the lug plate, and the loading lug hole is matched with the loading actuating cylinder.
On the basis of the design of the simulation piece, the overall dimension of the butt joint flat plate, the overall dimension of the lug piece and the aperture of the ear hole in the assembly are given by theoretical calculation. To further verify the authenticity of the test results.
Wherein, any component adopts high strength steel to make, and the butt bolt adopts the material unanimous with outer wing butt bolt assembly material. And a more real test result is obtained while enough test strength is ensured.
Meanwhile, the butt joint flat plate and the lug piece can be expanded according to the load condition in a mode that one lug piece is arranged in each two butt joint holes. Through this expansion form, can be applicable to the experiment of different outer wing sizes.
The butt bolt further includes a washer that is form-fit to the butt hole cylindrical socket structure.
When the simulation piece is designed, the axial lines of the butt bolt and the lug loading bolt are vertical and are assembled, no interference occurs in space, and the axial line of the lug loading hole and the axial line of the butt bolt are in the same plane. The design can lead the force transmission path to be more direct, additional component force cannot be generated, the test load transmission efficiency is higher, and the test result is more reliable.
1. Selecting the middle and outer wing butt joint holes as loading simulation piece connecting holes through calculation and analysis according to the figure 1;
2. the loading simulation piece consists of two parts, namely a loading simulation piece near the front beam and a loading simulation piece near the rear beam;
3. according to the illustration in fig. 1, three butt bolt holes near the front beam and the rear beam are taken as examples, and a double-lug joint and a flat plate base are designed, wherein the base is attached to a butt joint surface and connected through butt bolts.
4. If the outer wing loading condition is greater, butt bolt holes would need to be added in FIG. 1, as would joint tabs.
The test process comprises the following steps: the loading simulation piece is assembled with the butt joint face of the middle and outer wings according to design requirements, the lug hole is connected with the lug hole of the loading actuator through a bolt, during testing, the actuator applies load, the lug hole and the connecting bolt of the actuator transmit the load to the butt joint flat plate, the pulling load transmits the load to the middle and outer wings through the butt joint bolt, and the pressing load is transmitted to the middle and outer wings through the extrusion of the butt joint face.
The strength test should be performed mainly considering the following problems:
1. when a strength test project is planned, an examination part and a non-examination part need to be distinguished, the examination part needs to be manufactured in a brand-new mode, and when the non-examination part is only used as a loading part, simplified processing can be considered, and a simulation part is designed to replace the loading part.
2. In the existing test project, the structural form of the outer wing is not changed and is often used as a test loading piece to apply outer wing load, but the test project is not examined, for example, the test cost and the test piece manufacturing cost are increased through the integral loading of the outer wing;
3. according to the model test load condition, the loading simulation piece can be designed to replace the outer wing for loading, so that the test requirement is met;
4. the load condition is required to be considered in the design of the loading simulation piece, and the structural form and the size of the loading simulation piece are determined after calculation and analysis.
Claims (9)
1. An outer wing abutting surface loading simulation member, which is composed of two components with similar structural forms, and is characterized in that: any component at least comprises a butt joint flat plate, a lug, a butt joint bolt and a nut; the butt joint flat plate is provided with butt joint holes matched with the bolt holes on the butt joint surface of the outer wing; the lug is vertical to the surface of the butt joint flat plate; the butt bolt is in clearance fit with the butt holes of the middle and outer wings, and can only bear tensile force but not shear force; the butt joint flat plate is in butt joint with the outer wing and is connected with the outer wing through a butt joint bolt, a loading lug hole is formed in the lug plate, and the loading lug hole is matched with the loading actuating cylinder.
2. The loading simulator of claim 1, wherein: the axis of the lug loading hole is perpendicular to the axis of the lug loading bolt, and the lug loading hole and the axis of the butt bolt are in the same plane without interference in space during assembly.
3. A loading simulation according to claim 1 or 2, wherein: the axis of the lug is positioned on the central line of the two connected butt joint holes.
4. The loading simulator of claim 1, wherein: the butt joint flat plate and the lug can be expanded according to the load condition in a mode that one lug is arranged in each two butt joint holes.
5. The loading simulator of claim 1, wherein: the aperture of the loading ear hole is matched with the loading actuating cylinder according to the test load condition.
6. The loading simulation of claim 1 or 4, wherein: the overall dimension of the butt joint flat plate, the overall dimension of the lug and the aperture of the ear hole are all given by theoretical calculation.
7. The loading simulator of claim 1, wherein: any one of the components is made of high strength steel.
8. The loading simulator of claim 1, wherein: the butt bolts are made of materials completely consistent with the assembling materials of the outer wing butt bolts.
9. The loading simulator of claim 1, wherein: the butt bolt further includes a washer that is form-fit to the butt hole cylindrical socket structure.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920795004.1U CN210258874U (en) | 2019-05-29 | 2019-05-29 | Outer wing butt joint face loading simulation piece |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920795004.1U CN210258874U (en) | 2019-05-29 | 2019-05-29 | Outer wing butt joint face loading simulation piece |
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| Publication Number | Publication Date |
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| CN210258874U true CN210258874U (en) | 2020-04-07 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201920795004.1U Active CN210258874U (en) | 2019-05-29 | 2019-05-29 | Outer wing butt joint face loading simulation piece |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112591137A (en) * | 2020-11-13 | 2021-04-02 | 中国航空工业集团公司沈阳飞机设计研究所 | Horizontal tail large shaft test device for airplane |
-
2019
- 2019-05-29 CN CN201920795004.1U patent/CN210258874U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112591137A (en) * | 2020-11-13 | 2021-04-02 | 中国航空工业集团公司沈阳飞机设计研究所 | Horizontal tail large shaft test device for airplane |
| CN112591137B (en) * | 2020-11-13 | 2023-11-28 | 中国航空工业集团公司沈阳飞机设计研究所 | Airplane horizontal tail large shaft test device |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CP03 | Change of name, title or address |
Address after: 723213 Liulin Town, Chenggu County, Hanzhong City, Shaanxi Province Patentee after: Shaanxi Aircraft Industry Co.,Ltd. Address before: 723213 box 34, Hanzhong City, Shaanxi Province Patentee before: Shaanxi Aircraft INDUSTRY(GROUP) Co.,Ltd. |
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| CP03 | Change of name, title or address |