CN108088672B - A kind of aircraft nose landing gear outer cylinder suspension joint slow test fixture - Google Patents
A kind of aircraft nose landing gear outer cylinder suspension joint slow test fixture Download PDFInfo
- Publication number
- CN108088672B CN108088672B CN201711229922.XA CN201711229922A CN108088672B CN 108088672 B CN108088672 B CN 108088672B CN 201711229922 A CN201711229922 A CN 201711229922A CN 108088672 B CN108088672 B CN 108088672B
- Authority
- CN
- China
- Prior art keywords
- outer cylinder
- suspension joint
- cylinder suspension
- load
- fixed plate
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Classifications
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M13/00—Testing of machine parts
Landscapes
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Investigating Strength Of Materials By Application Of Mechanical Stress (AREA)
Abstract
The present invention provides a kind of aircraft nose landing gear outer cylinder suspension joint slow test fixture, including rack, outer cylinder suspension joint component, connection component, diagonal brace bar assembly and two pressurized struts, rack is cuboid framework, it is placed on horizontal plane by backing plate, a pair of of girder is set on the rack, and this to trabecular interior rabbet the second floor stringer, in first floor stringer placed to girder top overlap joint for multilayer fixed plate component, outer cylinder suspension joint is set in fixed plate, the outer cylinder suspension joint respectively with the pressurized strut that is set on backing plate, the load(ing) point being plugged in load lever draws auricle, and it is installed on the hound member hinges on the second floor stringer, wherein load lever one end by XY to small connector with mount it is hinged in the pressurized strut on rack, the other end is connected with the pulling-on piece being arranged on girder.Fixture provided by the present invention, being capable of connection and loaded state and the static(al) that is able to bear big load under and fatigue test of the actual response testpieces on undercarriage.
Description
Technical field
The invention belongs to aircraft testing device fields, and in particular to before a kind of aircraft for launch under marine environment
Undercarriage outer cylinder suspension joint slow test fixture.
Background technique
Nose-gear static(al) and fatigue behaviour certification test are the necessary links of aircraft landing gear structures design.It is previous to use
Full-scale nose-gear carries out guaranteed performance test, and there are testpieces manufacturing cycles long, the Test-bed Design manufacturing cycle
Long, the disadvantages of test period is long, development cost is high, the aircraft nose landing gear outer cylinder strut connector of launch carries under marine environment
Lotus is big, and existing test fixture is unable to satisfy requirement.
Summary of the invention
The purpose of the present invention is to provide a kind of aircraft nose landing gear outer cylinder suspension joint slow test fixtures, overcome or subtract
At least one drawbacks described above of the light prior art enables connection of the actual response testpieces on undercarriage and loaded
State and the static(al) being able to bear under big load and fatigue test, it is safe and reliable under the load of guarantee test part.
The purpose of the present invention is achieved through the following technical solutions: a kind of aircraft nose landing gear outer cylinder suspension joint slow test
Fixture, for testing outer cylinder suspension joint, including,
Rack, which is cuboid framework made of being docked as more beam items, and is placed on horizontal plane by backing plate,
A pair of parallel arranged first floor stringer wherein is overlapped by the way that a pair of of girder is arranged with respect on beam item in rack bottom end two, and
And rabbet second floor stringer between two girders；
Outer cylinder suspension joint component, including the multilayer fixed plate component being overlapped between two first floor stringers and installation
Outer cylinder suspension joint on multilayer fixed plate component, wherein the locking dress of its restricted movement is arranged on outer cylinder suspension joint
It sets；
Connection component, including load lever, pulling-on piece and load(ing) point draw auricle, and load lever two sides have double ear knot
Structure, wherein side ears structure and the grafting of pulling-on piece one end, the drawing on the pulling-on piece other end and girder between two first floor stringers
Piece support is hinged；It is ears structure that load(ing) point extraction auricle one end, which is the monaural structure other end, and monaural one end is plugged in load thick stick
Bar middle position, ears one end are coupled by bolt assembly and outer cylinder suspension joint；
Diagonal brace bar assembly, it is hingedly another including the diagonal brace support and one end that are set on the second floor stringer and diagonal brace support
The diagonal brace exemplar that one end is connected with outer cylinder suspension joint；
Pressurized strut is arranged two, and respectively Z-direction pressurized strut and XY is to pressurized strut, and wherein Z-direction pressurized strut both ends are respectively and outside
Cylinder suspension joint and backing plate are hinged and connected；XY is cut with scissors by docking XY to small connector and the load lever other side to pressurized strut one end
It connects, the other end is mounted on bench top beam item.
Preferably, the XY to pressurized strut be 30 tons of hydraulic actuators.
Preferably, the load lever amplifies load to pressurized strut to the XY, according to the magnification ratio system of 1:2
It makes.
Preferably, the multilayer fixed plate component includes the first fixed plate and the second fixed plate, and two fixed plates pass through
Bolt stacking is connected, wherein offering the through-hole for being embedded in the outer cylinder suspension joint in the first fixed plate, and sets on hole wall
It is equipped with multiple protrusions of limitation outer cylinder suspension joint rotation.
Preferably, the locking device includes cylinder fixture and the fixture nut that is coupled with the cylinder fixture,
The through-hole that wherein cylinder fixture passes through in first fixed plate is installed in second fixed plate, and the outer cylinder is hung
Fitting sleeve is wherein threadedly engaged phase inside fixture nut insertion outer cylinder suspension joint and with cylinder fixture on the cylinder fixture
It connects.
Preferably, the load(ing) point draw auricle, the load lever, the pulling-on piece, the XY to small connector and
The XY, with Y-direction in 10.36 ° of placements, is loaded to pressurized strut with guaranteeing that X synthesizes a power to power and Y-direction power.
Preferably, to guarantee load angle, load(ing) point extraction auricle ears one end front and rear sides pass through stay bolt
Two panels clamp clip is clamped, which is bonded the auricle setting in ears structure, and it is outstanding that the other end is then bonded the outer cylinder
Hanging joint setting；Wherein stay bolt is arranged three groups altogether.
Preferably, the bolt assembly includes the pin through the load lever and outer cylinder suspension joint setting
The fixed spiral shell of axis and the Z-direction fixed plate and Z-direction fixture nut being coupled respectively with the pin shaft both ends, Z-direction fixed plate and Z-direction
It is both female to clamp load lever, prevent its Z-direction mobile.
A kind of beneficial effect of aircraft nose landing gear outer cylinder suspension joint slow test fixture provided by the present invention is,
Situation is carried according to undercarriage and selects wherein structural weak link or the biggish key position of carrying, by rising before a kind of ultrafort steel
Frame laser forming typical structure part is fallen, to substitute full-scale undercarriage, content of the test is concentrated on typical structure part carrying out quiet
Power and experiment on fatigue properties examination, can not only verify the landing gear structure based on laser direct deposition forming technology technical characteristic
The reliability of form design provides technical support for full-scale undercarriage design of part optimization design, and can reduce superpower
The full-scale undercarriage developing risk of steel laser forming and development cost shorten the lead time, provide effectively for other Project R&Ds
Test method and means.
Detailed description of the invention
Fig. 1 is overall structure diagram of the invention；
Fig. 2 is the structural schematic diagram of outer cylinder suspension joint component in the present invention；
Fig. 3 is the structural schematic diagram of connection component in the present invention；
Fig. 4 is the structural schematic diagram of diagonal brace bar assembly in the present invention；
Fig. 5 is the scheme of installation of two pressurized struts in the present invention；
Fig. 6 is the structural schematic diagram that lever is loaded in the present invention；
Fig. 7 is the structural schematic diagram that load(ing) point draws auricle in the present invention；
Fig. 8 is the structural schematic diagram of the first fixed plate in the present invention；
Fig. 9 is the structural schematic diagram of cylinder fixture in the present invention；
Figure 10 is the structural schematic diagram of fixture nut in the present invention；
Figure 11 be the present invention in structural schematic diagram from XY to small connector.
Appended drawing reference:
1- rack, 2- outer cylinder suspension joint component, 3- connection component, 4- diagonal brace bar assembly, 5-Z to pressurized strut, 6-XY to
Pressurized strut, 11- girder, the first floor stringer of 12-, 13- backing plate, the second floor stringer of 14-, 21- outer cylinder suspension joint, 22- first are solid
Fixed board, the second fixed plate of 23-, 24- cylinder fixture, 25- fixture nut, 31- load lever, 32- pulling-on piece, 33- load(ing) point are drawn
Auricle, 34- pulling-on piece support, 35- clamp clip, 36-Z load auricle, 41- to fixed plate, 37-Z to fixture nut, 38- pressurized strut
Diagonal brace support, 42- diagonal brace exemplar, 61-XY are to small connector.
Specific embodiment
Aircraft nose landing gear outer cylinder suspension joint slow test fixture of the invention is done further in detail with reference to the accompanying drawing
It describes in detail bright.
As shown in Fig. 1 to 11, a kind of aircraft nose landing gear outer cylinder suspension joint slow test fixture is outstanding for testing outer cylinder
Hanging joint, including rack 1, outer cylinder suspension joint component 2, connection component 3, diagonal brace bar assembly 4 and two pressurized struts.
As shown in Figure 1, rack 1 is cuboid framework made of being docked as more beam items, and water is placed in by backing plate 13
In plane, wherein overlapping a pair of parallel arranged the by the way that a pair of of girder 11 is arranged on the opposite beam article in 1 bottom end two of rack
One floor stringer 12, and rabbet second floor stringer 14 between two girders 11.
As shown in Fig. 2, outer cylinder suspension joint component 2 includes that the outer cylinder suspension to be tested of multilayer fixed plate component and institute connects
First 21.The multilayer fixed plate component includes that phase is laminated by bolt in the first fixed plate 22 and the second fixed plate 23, two fixed plates
Even, wherein offering the through-hole of embedded outer cylinder suspension joint 21 in the first fixed plate 22, and it is arranged outside restricted on hole wall
Multiple protrusions of cylinder suspension joint rotation, the first fixed plate 22 are shown in Fig. 8.Two connected fixed plates of stacking are taken by bolt and are loaded on
On two first floor stringers 12, wherein 23 side of the second fixed plate is in contact with the first floor stringer 12,22 side of the first fixed plate is logical
Outer cylinder suspension joint 21 is installed at hole, it is mobile in order to limit the outer cylinder suspension joint 21, locking device is set inside it, the lock
Tight device includes cylinder fixture 24 (as shown in Figure 9) and the fixture nut 25 being coupled with the cylinder fixture (see Figure 10 institute
Show), the through-hole that wherein cylinder fixture 24 passes through in the first fixed plate 22 is installed in the second fixed plate 23, and outer cylinder suspension is connect
First 21 are sleeved on the cylinder fixture 24, wherein fixture nut 25 be embedded in the inside of outer cylinder suspension joint 21 and with 24 spiral shell of cylinder fixture
Line cooperation connects.The setting of the cylinder fixture 24 for preventing the swaying style of outer cylinder suspension joint 21, the fixture nut 25
Upward play for preventing outer cylinder suspension joint 21 is set, and fixture nut 25 clamps outer cylinder suspension with about 24 cylinder fixture and connects
First 21, to limit its axial freedom.
As shown in figure 5, due to bearing power of the X to, Y-direction both direction at the outer cylinder suspension joint 21, but in view of load
X is synthesized a power load to Y-direction by point position and testpieces spatial position and size factor, and Z-direction individually loads.From
And pressurized strut is arranged two, respectively Z-direction pressurized strut 5 and XY is to pressurized strut 6, and wherein 5 one end of Z-direction pressurized strut is added by pressurized strut
It carries auricle 38 to be hinged and connected with outer cylinder suspension joint 21, the backing plate of 1 lower section of other end rack connects.XY is then mounted to pressurized strut 6
In on 1 roof beam item of rack, since XY is larger to stress, it is contemplated that laboratory pressurized strut load capability and entire test load
The consistency of system, XY select 30 tons of hydraulic actuators to pressurized strut 6.
As shown in figure 3, connection component 3 includes that load lever 31 (as shown in Figure 6), pulling-on piece 32 and load(ing) point draw auricle
33 (as shown in Figure 7).Loading 31 two sides of lever has ears structure, wherein side ears structure and 32 one end grafting of pulling-on piece, should
32 other end of pulling-on piece is then hinged and connected with the pulling-on piece support 34 on girder 11 between two first floor stringers 12, other side ears
Structure is hinged and connected by docking XY to small connector 61 (as shown in Figure 11) and XY to pressurized strut 6, since the load lever 31 is used
In amplifying load to pressurized strut 6 to XY, preferably manufactured according to the magnification ratio of 1:2.Load(ing) point draws 33 one end of auricle
The monaural structure other end is ears structure, and monaural one end is plugged in load 31 middle position of lever, and ears one end passes through bolt group
Part is coupled with outer cylinder suspension joint 21.The bolt assembly includes being arranged through load lever 31 and outer cylinder suspension joint 21
Pin shaft and the Z-direction fixed plate 36 and Z-direction fixture nut 37 being coupled respectively with the pin shaft both ends, Z-direction fixed plate 36 and Z
Load lever 31 is clamped to both fixture nuts 37, prevents its Z-direction mobile.
It is loaded to guarantee that X synthesizes a power to power and Y-direction power, so that load(ing) point is drawn auricle 33 and Y by selection
To in 10.36 ° of placements, placed correspondingly, load lever 31, XY are also in 10.36 ° with Y-direction to small connector 61, pulling-on piece 32.XY to
Pressurized strut 6 is also fixed on rack 1 with Y-direction in 10.36 °.It should be noted that 34 one end of pulling-on piece support and pulling-on piece 32 pass through spiral shell
It tethers and connects, the other end is connect with rack girder 11, and pulling-on piece support 34 is horizontal positioned, but 34 ears piece of pulling-on piece support and pulling-on piece 32
Parallel tilting, i.e., 34 ears piece of pulling-on piece support and 34 support of pulling-on piece support are tilting at an angle.Since load(ing) point draws auricle
33 need slant setting to guarantee load angle, and selection draws 33 ears one end front and rear sides of auricle in load(ing) point and passes through stay bolt
Two panels clamp clip 35 is clamped, which is bonded the auricle setting in ears structure, and it is outstanding that the other end is then bonded outer cylinder
Hanging joint 21 is arranged, and wherein stay bolt is arranged three groups altogether.
As shown in figure 4, diagonal brace bar assembly 4 include the diagonal brace support 41 that is set on the second floor stringer 14 and one end with
The diagonal brace exemplar 42 that the hinged other end of diagonal brace support 41 is connected with outer cylinder suspension joint 21.
Fixture of the invention connection and loaded state of the actual response testpieces on undercarriage and can be held
By under big load static(al) and fatigue test, guarantee test part load under it is safe and reliable.
The above description is merely a specific embodiment, but scope of protection of the present invention is not limited thereto, any
In the technical scope disclosed by the present invention, any changes or substitutions that can be easily thought of by those familiar with the art, all answers
It is included within the scope of the present invention.Therefore, protection scope of the present invention should be with the scope of protection of the claims
It is quasi-.
Claims (8)
1. a kind of aircraft nose landing gear outer cylinder suspension joint slow test fixture, for testing outer cylinder suspension joint, feature exists
In, including,
Rack (1), which is cuboid framework made of being docked as more beam items, and is placed in water by backing plate (13)
In plane, wherein a pair of arranged parallel to each other by the way that a pair of of girder (11) overlap joint is arranged with respect on beam item in rack (1) bottom end two
The first floor stringer (12), and between two girders (11) rabbet second floor stringer (14)；
Outer cylinder suspension joint component (2), including multilayer fixed plate component, the Yi Jian being overlapped between two first floor stringers (12)
Loaded on the outer cylinder suspension joint (21) on multilayer fixed plate component, wherein its restricted shifting is arranged on outer cylinder suspension joint (21)
Dynamic locking device；
Connection component (3), including load lever (31), pulling-on piece (32) and load(ing) point draw auricle (33), load lever (31)
Two sides have ears structure, wherein side ears structure and pulling-on piece (32) one end grafting, pulling-on piece (32) other end and girder (11)
The upper pulling-on piece support (34) between two first floor stringers (12) is hinged；It is monaural structure that load(ing) point, which draws auricle (33) one end,
The other end is ears structure, and monaural one end is plugged in load lever (31) middle position, and ears one end is by bolt assembly and outside
Cylinder suspension joint (21) is coupled；
Diagonal brace bar assembly (4), including the diagonal brace support (41) being set on the second floor stringer (14) and one end and diagonal brace support
(41) the diagonal brace exemplar (42) that the hinged other end is connected with outer cylinder suspension joint (21)；
Pressurized strut is arranged two, and respectively Z-direction pressurized strut (5) and XY are to pressurized strut (6), and wherein Z-direction pressurized strut (5) both ends are divided
It is not hinged and connected with outer cylinder suspension joint (21) and backing plate (13)；XY is to pressurized strut (6) one end by docking XY to small connector
(61) hinged with load lever (31) other side, the other end is mounted on rack (1) roof beam item.
2. aircraft nose landing gear outer cylinder suspension joint slow test fixture according to claim 1, which is characterized in that described
XY is 30 tons of hydraulic actuators to pressurized strut (6).
3. aircraft nose landing gear outer cylinder suspension joint slow test fixture according to claim 2, which is characterized in that described
Load lever (31) amplifies load to pressurized strut (6) to the XY, manufactures according to the magnification ratio of 1:2.
4. aircraft nose landing gear outer cylinder suspension joint slow test fixture according to claim 3, which is characterized in that described
Multilayer fixed plate component includes the first fixed plate (22) and the second fixed plate (23), and two fixed plates are laminated by bolt to be connected,
The through-hole for being embedded in the outer cylinder suspension joint (21) wherein is offered in the first fixed plate (22), and is arranged on hole wall limited
Multiple protrusions of outer cylinder suspension joint rotation processed.
5. aircraft nose landing gear outer cylinder suspension joint slow test fixture according to claim 4, which is characterized in that described
Locking device includes cylinder fixture (24) and the fixture nut (25) being coupled with the cylinder fixture, wherein cylinder fixture
(24) through-hole passed through on first fixed plate (22) is installed on second fixed plate (23), and the outer cylinder is hung
Connector (21) is sleeved on the cylinder fixture (24), wherein fixture nut (25) insertion outer cylinder suspension joint (21) it is internal and with circle
Column fixture (24), which is threadedly engaged, to connect.
6. aircraft nose landing gear outer cylinder suspension joint slow test fixture according to claim 5, which is characterized in that described
Load(ing) point draws auricle (33), the load lever (31), the pulling-on piece (32), the XY to small connector (61) and the XY
To pressurized strut (6) with Y-direction in 10.36 ° of placements, loaded with guaranteeing that X synthesizes a power to power and Y-direction power.
7. aircraft nose landing gear outer cylinder suspension joint slow test fixture according to claim 6, which is characterized in that protect
Load angle is demonstrate,proved, the load(ing) point draws auricle (33) ears one end front and rear sides and clamps two panels clamp clip by stay bolt
(35), the auricle setting in clamp clip (35) one end fitting ears structure, the other end are then bonded the outer cylinder suspension joint
(21) it is arranged；Wherein stay bolt is arranged three groups altogether.
8. aircraft nose landing gear outer cylinder suspension joint slow test fixture according to claim 7, which is characterized in that described
Bolt assembly include through it is described load lever (31) and the outer cylinder suspension joint (21) setting pin shaft and respectively with this
The Z-direction fixed plate (36) and Z-direction fixture nut (37) that pin shaft both ends are coupled, Z-direction fixed plate (36) and Z-direction fixture nut
(37) the two clamps load lever (31), prevents its Z-direction mobile.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711229922.XA CN108088672B (en) | 2017-11-29 | 2017-11-29 | A kind of aircraft nose landing gear outer cylinder suspension joint slow test fixture |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711229922.XA CN108088672B (en) | 2017-11-29 | 2017-11-29 | A kind of aircraft nose landing gear outer cylinder suspension joint slow test fixture |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN108088672A CN108088672A (en) | 2018-05-29 |
| CN108088672B true CN108088672B (en) | 2019-06-28 |
Family
ID=62173142
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201711229922.XA Active CN108088672B (en) | 2017-11-29 | 2017-11-29 | A kind of aircraft nose landing gear outer cylinder suspension joint slow test fixture |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108088672B (en) |
Families Citing this family (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108444694A (en) | 2018-06-22 | 2018-08-24 | 潍柴动力股份有限公司 | A kind of fatigue test wire examination method |
| CN109357852B (en) * | 2018-10-22 | 2020-03-20 | 成都理工大学 | Static force rack and pseudo-static force anti-seismic testing device |
| CN110220690B (en) * | 2019-07-10 | 2021-02-26 | 中航飞机起落架有限责任公司 | Symmetrical balanced loading mechanism and test method thereof |
| CN110654568B (en) * | 2019-09-29 | 2022-09-06 | 中国直升机设计研究所 | Hub couple loading device |
| CN111099036B (en) * | 2019-11-22 | 2021-09-17 | 南京航空航天大学 | Fatigue test device and method for landing gear ejection main force transfer structure |
| CN111452994B (en) * | 2020-04-22 | 2023-03-24 | 中国飞机强度研究所 | Aircraft nose landing gear supporting device |
| CN112461515B (en) * | 2020-10-30 | 2022-07-01 | 中国直升机设计研究所 | Helicopter undercarriage loading device |
| CN112762779B (en) * | 2020-12-11 | 2023-01-03 | 北京航天飞腾装备技术有限责任公司 | Lever loading-based static test device and method for guided bomb |
Family Cites Families (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| KR20100108991A (en) * | 2009-03-31 | 2010-10-08 | 한재도 | Test equipment and method of air vehicle landing gear |
| CN103604619B (en) * | 2013-11-21 | 2016-01-20 | 南京航空航天大学 | Frame-type catapult-assisted take-off carrier-borne aircraft nose-gear slow test charger |
| CN204988712U (en) * | 2015-09-30 | 2016-01-20 | 中国航空工业集团公司沈阳飞机设计研究所 | Undercarriage test load loading device |
| CN205819590U (en) * | 2016-07-01 | 2016-12-21 | 陕西飞机工业（集团）有限公司 | A kind of aircraft slow test main landing gear loading simulation part |
| CN106240841B (en) * | 2016-07-07 | 2019-01-18 | 中国飞机强度研究所 | A kind of gear test loading device |
| CN106768921A (en) * | 2016-11-29 | 2017-05-31 | 中国直升机设计研究所 | A kind of tail undercarriage rocking arm erection joint fatigue experimental device |
-
2017
- 2017-11-29 CN CN201711229922.XA patent/CN108088672B/en active Active
Also Published As
| Publication number | Publication date |
|---|---|
| CN108088672A (en) | 2018-05-29 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN108088672B (en) | A kind of aircraft nose landing gear outer cylinder suspension joint slow test fixture | |
| CN108168854B (en) | Static test fixture for outer cylinder stay bar joint of nose landing gear of airplane | |
| CN108238282B (en) | Central wing box test equipment | |
| CN103604593B (en) | Plane type ejection launch carrier-borne aircraft front undercarriage static force test charger | |
| CN106248322B (en) | A kind of wing-box experimental rig of curved scissors loading | |
| CN102680236B (en) | Structural strength test loading device for aircraft wing-mounted engine | |
| CN106043662A (en) | Aircraft rear structure | |
| CN104807627B (en) | Central wing test supporting device | |
| CN103983463A (en) | Method for verification test of combined loading of airframe and undercarriage | |
| CN103723285A (en) | Empennage load applying device used for plane structure strength tests | |
| CN109060511A (en) | A kind of multifunction structure engineering load test system | |
| JP6625351B2 (en) | Fuselage with structural and non-structural struts | |
| CN104163250A (en) | Reliability test device for aircraft landing gear cabin door lock system | |
| CN105675290B (en) | For the detecting tool of automobile control arm ball pin fatigue test | |
| CN108045597A (en) | Modularization, sectional satellite structure | |
| US7380463B2 (en) | Assembly for testing panels under shear-compression loads | |
| CN103407579A (en) | Major-diameter airframe test loading clamp | |
| CN104019983B (en) | A kind of device for testing reliability of cabin door lock for aircrafts | |
| CN210882689U (en) | Static test supporting piece for spoiler of airplane | |
| CN202710399U (en) | Composite-material laminate bolt connection extruding strength single-lap joint test fixture | |
| CN105836155B (en) | A kind of aircraft structure strength tests double floor beam loading device | |
| CN203965239U (en) | A kind of rivet pure shear dynamic mechanical test supportive device | |
| CN207607664U (en) | A kind of experiment load and support bogusware | |
| CN213516588U (en) | Loading device for airplane stabilizer control load test | |
| CN205719509U (en) | Detecting tool for automobile control arm ball pin fatigue test |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |