CN104807627B - Central wing test supporting device - Google Patents
Central wing test supporting device Download PDFInfo
- Publication number
- CN104807627B CN104807627B CN201510224052.1A CN201510224052A CN104807627B CN 104807627 B CN104807627 B CN 104807627B CN 201510224052 A CN201510224052 A CN 201510224052A CN 104807627 B CN104807627 B CN 104807627B
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- China
- Prior art keywords
- joint
- clamping apparatus
- gripping clamping
- gripping
- outer wing
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- 238000012360 testing method Methods 0.000 title claims abstract description 36
- 210000005069 ears Anatomy 0.000 claims description 23
- 238000003466 welding Methods 0.000 claims description 3
- 230000015572 biosynthetic process Effects 0.000 claims 1
- 230000000694 effects Effects 0.000 description 8
- 238000003556 assay Methods 0.000 description 7
- 238000002474 experimental method Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000004088 simulation Methods 0.000 description 1
Landscapes
- Investigating Strength Of Materials By Application Of Mechanical Stress (AREA)
- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
Abstract
The invention belongs to the technical field of airplane strength tests, in particular to a central wing test supporting device comprising bottom beams (1), press beams (2) and posts (8), which are welded to form an integral structure. One ends of acting tubes (3) are connected to the bottom beams (1), and the other ends are connected to loading cases (4); the loading cases (4) comprise ribs (13), wall boards (14) and beams (15) which are fixedly connected through bolts; the loading case segments (4) and external wing dummy parts (6) are connected through corner cases (5) of the loading case segments (4); the external wing dummy parts (6) and test parts (7) are connected through supporting clamps including first supporting clamps (9), second supporting clamps (10), third supporting clamps (11) and fourth supporting clamps (12). The device is capable of testing a central wing independently and simulating an airplane body supporting the central wing and is simple in structure and low in cost.
Description
Technical field
The invention belongs to strength of aircraft experimental technique field, in particular to a kind of central airfoil test device is supported.
Background technology
During aircraft manufacturing, central wing is crossed middle fuselage and left and right sides outer wing is linked to be into an entirety, the master of central wing
Function is wanted to be to balance and transmit the load that outer wing is transmitted.When testing central wing, to make the simulation of support not only true but also simple
It is single, one section of fuselage is generally taken as support.The jointing and the true part of join domain of central wing and outer wing, outer wing bogusware.
For the testpieces of only central wing, the support for how simulating the fuselage centering centre wing is the emphasis and difficult point for testing success or failure, domestic
The disclosure of related art scheme is there is presently no outward.
The content of the invention
It is an object of the invention to solve above-mentioned deficiency of the prior art, there is provided it is a kind of it is simple and reasonable, test into
Originally central airfoil test that is low, can simulating the wing support of fuselage centering centre supports device.
The purpose of the present invention is achieved through the following technical solutions：Including bottom girder, press beam, pressurized strut, loading box section, loading box
Section-angle box, outer wing bogusware, middle outer wing, column, the first gripping clamping apparatus, the second gripping clamping apparatus, the 3rd gripping clamping apparatus, the 4th support
Fixture, wherein, the bottom girder, the press beam, the column are the integral structure that welding is formed；Pressurized strut one end connection
Bottom girder, the other end is connected with the loading box section；The loading box section includes rib, wallboard, the beam being bolted to connection；Institute
State loading box section to be connected by the loading box section-angle box with the outer wing bogusware；The outer wing bogusware is logical with the middle outer wing
Gripping clamping apparatus connection is crossed, gripping clamping apparatus lower section is connected with column, and column bottom is connected with base.
Preferably, the gripping clamping apparatus include the first gripping clamping apparatus, the second gripping clamping apparatus, the 3rd gripping clamping apparatus, the 4th
Gripping clamping apparatus, the first gripping clamping apparatus, the second gripping clamping apparatus, the 3rd gripping clamping apparatus, the 4th gripping clamping apparatus respectively by the first joint,
Outer wing in second joint, the 3rd joint, the connection of the 4th joint.
In any of the above-described scheme preferably, first gripping clamping apparatus include the first joint (16), pin, straight hole ears
First joint is connected by pin with straight hole ears；Second gripping clamping apparatus include the second joint, pin, strip hole ears,
Second joint is connected by pin with strip hole ears；3rd gripping clamping apparatus include the 3rd joint, spill backing plate；Described
Four gripping clamping apparatus include the 4th joint, flat bolster, wherein, the first joint, the second joint, the 3rd joint, the 4th joint are installed on
On the same face of middle outer wing, the first joint is coaxial with the earhole of the 4th joint, and the second joint is coaxial with the earhole of the 3rd joint.
In any of the above-described scheme preferably, first joint and the 4th joint symmetrically, the second joint and the 3rd joint
Symmetrically.
In any of the above-described scheme preferably, the diameter phase of first joint, the radius of straight hole ears and the pin
Together.
In any of the above-described scheme preferably, the aperture of second joint, the earhole radius of the strip hole ears with
The diameter of pin is identical.
In any of the above-described scheme preferably, the arc surface of the 3rd joint is fitted with the arc surface of spill backing plate.
In any of the above-described scheme preferably, the cambered surface of the 4th joint is fitted with flat bolster plane.
Central airfoil test provided by the present invention supports that the beneficial effect of device is to devise four joints of central wing
The version of gripping clamping apparatus, individually central wing can be tested, simulate fuselage centering centre the wing support, simple structure, into
This is low.
Description of the drawings
Fig. 1 is the structure front view of the preferred embodiment that device is supported according to the central airfoil test of invention；
Fig. 2 is adding for the central wing assay device of the embodiment illustrated in fig. 1 that device is supported according to the central airfoil test of invention
Carry the structure top view of box section；
Fig. 3 is adding for the central wing assay device of the embodiment illustrated in fig. 1 that device is supported according to the central airfoil test of invention
Carry the structural representation of box section；
Fig. 4 is the of the central wing assay device of the embodiment illustrated in fig. 1 that device is supported according to the central airfoil test of invention
The structural representation of one gripping clamping apparatus；
Fig. 5 is the of the central wing assay device of the embodiment illustrated in fig. 1 that device is supported according to the central airfoil test of invention
The structural representation of two gripping clamping apparatus；
Fig. 6 is the of the central wing assay device of the embodiment illustrated in fig. 1 that device is supported according to the central airfoil test of invention
The structural representation of three gripping clamping apparatus；
Fig. 7 is the of the central wing assay device of the embodiment illustrated in fig. 1 that device is supported according to the central airfoil test of invention
The structural representation of four gripping clamping apparatus；
Fig. 8 is the length of the central wing assay device of the embodiment illustrated in fig. 1 that device is supported according to the central airfoil test of invention
The structural representation of bar hole ears；
Reference：
1- bottom girders, 2- press beams, 3- pressurized struts, 4- loading box sections, 5- loading box section-angle boxes, 6- outer wing boguswares, 7- China and foreign countries
The wing, 8- columns, the gripping clamping apparatus of 9- first, the gripping clamping apparatus of 10- second, the gripping clamping apparatus of 11- the 3rd, the gripping clamping apparatus of 12- the 4th, 13-
Rib, 14- wallboards, 15- beams, the joints of 16- first, 17- pins, 18- straight hole ears, the joints of 19- second, 20- strip hole ears,
The joints of 21- the 3rd, 22- spill backing plates, the joints of 23- the 4th, 24- flat bolsters.
Specific embodiment
In order to more fully understand that the central airfoil test according to the present invention program supports device, below in conjunction with the accompanying drawings to the present invention
Central airfoil test support device a preferred embodiment be further elaborated explanation.
Reference picture 1- Fig. 7, the present invention provide central airfoil test support device include bottom girder 1, press beam 2, pressurized strut 3, plus
Carry box section 4, loading box section-angle box 5, outer wing bogusware 6, middle outer wing 7, column 8, the first gripping clamping apparatus 9, the second gripping clamping apparatus 10,
3rd gripping clamping apparatus 11, the 4th gripping clamping apparatus 12, wherein, the bottom girder 1, the press beam 2, the column 8 are formed for welding
Integral structure；The one end of the pressurized strut 3 connects bottom girder 1, and the other end is connected with the loading box section 4；The loading box section 4 is wrapped
Include rib 13, wallboard 14, the beam 15 being bolted to connection；The loading box section 4 is with the outer wing bogusware 6 by the loading
Box section-angle box 5 connects；The outer wing bogusware 6 is connected with the middle outer wing 7 by gripping clamping apparatus.The middle outer wing 7 is false with outer wing
Part 6 is designed according to corresponding experiment demand.The gripping clamping apparatus include the first gripping clamping apparatus 9, the second gripping clamping apparatus the 10, the 3rd
Gripping clamping apparatus 11, the 4th gripping clamping apparatus 12, the first gripping clamping apparatus 9, the second gripping clamping apparatus 10, the 3rd gripping clamping apparatus 11, the 4th
Fixture 12 is held respectively by outer wing 7 in the first joint 16, the second joint 19, the connection of the 3rd joint 21, the 4th joint 23.
The central airfoil test that the present invention is provided supports that the first gripping clamping apparatus 9 of device include the first joint 16, pin 17, straight
Hole ears 18, effect is that constraint is vertical, opens up to degree of freedom；Second gripping clamping apparatus 10 include the second joint 19, pin 17, length
Bar hole ears 20, effect is to constrain vertical freedom degree and do not constrain course and open up to degree of freedom；3rd gripping clamping apparatus 11 are wrapped
The 3rd joint 21, spill backing plate 22 are included, effect is constraint course and vertical freedom degree；4th gripping clamping apparatus 12 include the 4th
Joint 23, flat bolster 24, effect is to constrain vertical and open up to degree of freedom.Wherein, the first joint 16, the second joint the 19, the 3rd connect
The 21, the 4th joint 23 is installed on the same face of middle outer wing 7, wherein, the first joint 16 is coaxial with the earhole of the 4th joint 23,
Second joint 19 is coaxial with the earhole of the 3rd joint 21.First joint 16, the radius of straight hole ears 18 and the pin 17
Diameter it is identical；The aperture of second joint 19, the strip hole ears 20 earhole radius it is identical with the diameter of pin 17；
The arc surface of the 3rd joint 21 is fitted with the arc surface of spill backing plate 22；The cambered surface of the 4th joint 23 and flat bolster 24
Plane is fitted.
During specifically used, middle outer wing 7 and outer wing bogusware 6 are provided by consigner, are left at the front and rear beam of middle outer wing 7
The interface being connected with the first gripping clamping apparatus 9, the second gripping clamping apparatus 10, the 3rd gripping clamping apparatus 11, the 4th gripping clamping apparatus 12.Test into
The first joint 16, the second joint 19, the 3rd joint 21, the 4th joint 23 are bolted on into seam before row.Test into
The first gripping clamping apparatus 9, the second gripping clamping apparatus 10, the 3rd gripping clamping apparatus 11, the 4th gripping clamping apparatus 12 are fixed on column 8 during row
And be fixedly connected with the interface on corresponding middle outer wing 7 by bolt.Wherein, the first gripping clamping apparatus 9 include the first joint 16, pin
The earhole radius of son 17, straight hole ears 18, the first joint 16 and straight hole ears 18 is identical with the diameter of pin 17, and effect is constraint
It is vertical, open up to degree of freedom.Second gripping clamping apparatus include the second joint 19, pin 17 and strip hole ears 20, the second joint 19
Radius, strip hole ears 20 earhole arc radius it is identical with the diameter of pin 17, the second joint 19 is pacified with strip hole ears 20
There are both sides respectively to leave 5mm spacing after dress, effect is to constrain vertical freedom degree and do not constrain course and open up to degree of freedom.3rd supports
Fixture 11 includes the 3rd joint 21, spill backing plate 22, and the circular arc cambered surface of the 3rd joint 21 is pasted with the circular arc cambered surface of spill backing plate 22
Close, effect is constraint course and vertical freedom degree.4th gripping clamping apparatus 12 include the 4th joint 23, flat bolster 24, the 4th joint
23 cambered surface is fitted with the plane of flat bolster 24, and effect is to constrain vertical and open up to degree of freedom.
It is described in detail above in association with the specific embodiment of the present invention, but is not limitation of the present invention, for example, sends out
The central airfoil test of bright offer supports quantity, quantity of joint of device gripping clamping apparatus etc., every technology reality according to the present invention
Any simple modification made for any of the above embodiments of verifying belongs to the technical scope of the present invention, in addition it is also necessary to explanation, according to this
The central airfoil test of invention supports that the category of device technique scheme includes the combination in any between each part mentioned above.
Claims (8)
1. a kind of central airfoil test supports device, it is characterised in that：Device body is symmetrical structure, including bottom girder (1), press beam
(2), pressurized strut (3), loading box section (4), loading box section-angle box (5), outer wing bogusware (6), middle outer wing (7), column (8), first
Gripping clamping apparatus (9), the second gripping clamping apparatus (10), the 3rd gripping clamping apparatus (11), the 4th gripping clamping apparatus (12),
Wherein, the bottom girder (1), the integral structure that the press beam (2) is welding formation；Pressurized strut (3) one end connection
Bottom girder (1), the other end is connected with loading box section (4)；Loading box section (4) is including the rib being bolted to connection
(13), wallboard (14), beam (15)；Loading box section (4) is with the outer wing bogusware (6) by the loading box section-angle box (5)
Connection；The outer wing bogusware (6) is connected with the middle outer wing (7) by gripping clamping apparatus, and gripping clamping apparatus lower section is connected with column
(8), column (8) bottom is connected with base.
2. central authorities' airfoil test as claimed in claim 1 supports device, it is characterised in that：The gripping clamping apparatus are supported including first
Fixture (9), the second gripping clamping apparatus (10), the 3rd gripping clamping apparatus (11), the 4th gripping clamping apparatus (12), the first gripping clamping apparatus (9),
Two gripping clamping apparatus (10), the 3rd gripping clamping apparatus (11), the 4th gripping clamping apparatus (12) pass through respectively the first joint (16), the second joint
(19), outer wing (7) in the 3rd joint (21), the connection of the 4th joint (23).
3. central authorities' airfoil test as claimed in claim 2 supports device, it is characterised in that：First gripping clamping apparatus (9) include
First joint (16), pin (17), straight hole ears (18), the first joint (16) is connected by pin (17) and straight hole ears (18)
Connect；Second gripping clamping apparatus (10) include the second joint (19), pin (17), strip hole ears (20), the second joint (19)
It is connected with strip hole ears by pin (17)；3rd gripping clamping apparatus (11) are including the 3rd joint (21), spill backing plate
(22)；4th gripping clamping apparatus (12) including the 4th joint (23), flat bolster (24), wherein, the first joint (16), second connect
Head (19), the 3rd joint (21), the 4th joint (23) are installed on the same face of middle outer wing (7), the first joint (16) and the 4th
The earhole of joint (23) is coaxial, and the second joint (19) is coaxial with the earhole of the 3rd joint (21).
4. central authorities' airfoil test as claimed in claim 3 supports device, it is characterised in that：First joint (16) connects with the 4th
Head (23) is symmetrical, the second joint (19) is symmetrical with the 3rd joint (21).
5. central authorities' airfoil test as claimed in claim 3 supports device, it is characterised in that：First joint (16), straight hole are double
The radius of ear (18) is identical with the diameter of the pin (17).
6. central authorities' airfoil test as claimed in claim 3 supports device, it is characterised in that：The aperture of second joint (19),
The earhole radius of the strip hole ears (20) is identical with the diameter of pin (17).
7. central authorities' airfoil test as claimed in claim 3 supports device, it is characterised in that：The arc surface of the 3rd joint (21)
Fit with the arc surface of spill backing plate (22).
8. central authorities' airfoil test as claimed in claim 3 supports device, it is characterised in that：The cambered surface of the 4th joint (23) with
Flat bolster (24) plane is fitted.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510224052.1A CN104807627B (en) | 2015-05-05 | 2015-05-05 | Central wing test supporting device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510224052.1A CN104807627B (en) | 2015-05-05 | 2015-05-05 | Central wing test supporting device |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN104807627A CN104807627A (en) | 2015-07-29 |
| CN104807627B true CN104807627B (en) | 2017-05-17 |
Family
ID=53692650
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510224052.1A Active CN104807627B (en) | 2015-05-05 | 2015-05-05 | Central wing test supporting device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN104807627B (en) |
Families Citing this family (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106248322B (en) * | 2016-07-05 | 2018-11-13 | 中国飞机强度研究所 | A kind of wing-box experimental rig of curved scissors loading |
| CN108238282B (en) * | 2017-12-04 | 2021-03-26 | 中国飞机强度研究所 | Central wing box test equipment |
| CN109094815B (en) * | 2018-07-27 | 2020-05-12 | 哈尔滨工业大学 | Test support system for connecting strength between aircraft vertical stabilizer and fuselage |
| CN109110153B (en) * | 2018-07-27 | 2020-04-24 | 哈尔滨工业大学 | Supporting device for connection strength test of airplane vertical fin and airplane body |
| CN109094814B (en) * | 2018-07-27 | 2020-05-26 | 哈尔滨工业大学 | Adjustable rigidity support system for connection strength test of vertical stabilizer and airplane body of airplane |
| CN109625318B (en) * | 2018-12-07 | 2022-04-19 | 中国飞机强度研究所 | Test local restraint device |
| CN110282153B (en) * | 2019-05-27 | 2022-09-20 | 中国飞机强度研究所 | Ear fork-box section structure static strength test device |
| CN111409856B (en) * | 2020-04-17 | 2023-03-14 | 中国飞机强度研究所 | Engine body cabin section structural strength test restraint system |
| CN113654882B (en) * | 2021-06-18 | 2022-04-26 | 中国商用飞机有限责任公司 | Experimental loading device of horizontal tail |
| CN113702181A (en) * | 2021-08-16 | 2021-11-26 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | Butt joint test device and test method for lower wall plate of wing root of airplane wing with upper dihedral angle |
| CN113911389B (en) * | 2021-09-24 | 2024-05-17 | 中国飞机强度研究所 | External test loading device for airplane |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US8146242B2 (en) * | 2005-11-01 | 2012-04-03 | The Boeing Company | Methods and systems for manufacturing a family of aircraft wings and other composite structures |
| CN202322186U (en) * | 2011-11-15 | 2012-07-11 | 李健 | Wing and tail jack |
| CN202345908U (en) * | 2011-09-22 | 2012-07-25 | 西北工业大学 | Wing with movable wing surface |
| CN202599649U (en) * | 2012-05-11 | 2012-12-12 | 中国航空工业集团公司西安飞机设计研究所 | Self-balanced fixture for box test |
| CN103963993A (en) * | 2013-01-29 | 2014-08-06 | 中国航空工业集团公司西安飞机设计研究所 | Wing section simulation structure of aircraft iron bird test platform |
-
2015
- 2015-05-05 CN CN201510224052.1A patent/CN104807627B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US8146242B2 (en) * | 2005-11-01 | 2012-04-03 | The Boeing Company | Methods and systems for manufacturing a family of aircraft wings and other composite structures |
| CN202345908U (en) * | 2011-09-22 | 2012-07-25 | 西北工业大学 | Wing with movable wing surface |
| CN202322186U (en) * | 2011-11-15 | 2012-07-11 | 李健 | Wing and tail jack |
| CN202599649U (en) * | 2012-05-11 | 2012-12-12 | 中国航空工业集团公司西安飞机设计研究所 | Self-balanced fixture for box test |
| CN103963993A (en) * | 2013-01-29 | 2014-08-06 | 中国航空工业集团公司西安飞机设计研究所 | Wing section simulation structure of aircraft iron bird test platform |
Non-Patent Citations (1)
| Title |
|---|
| 一种襟翼操纵系统的可靠性分析方法;庞宝才 等;《测控技术》;20131231;第32卷;531-533 * |
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| Publication number | Publication date |
|---|---|
| CN104807627A (en) | 2015-07-29 |
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Inventor after: Wei Yulong Inventor after: Xie Yuhang Inventor after: Li Shanshan Inventor after: Dong Dengke Inventor after: Zhang Lihong Inventor after: Zhao Bin Inventor before: Wei Yulong Inventor before: Xie Yuhang Inventor before: Li Shanshan Inventor before: Dong Dengke Inventor before: Zhang Lihong Inventor before: Li Xiaojun |
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