CN108088672A - A kind of aircraft nose landing gear outer barrel suspension joint slow test fixture - Google Patents
A kind of aircraft nose landing gear outer barrel suspension joint slow test fixture Download PDFInfo
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- CN108088672A CN108088672A CN201711229922.XA CN201711229922A CN108088672A CN 108088672 A CN108088672 A CN 108088672A CN 201711229922 A CN201711229922 A CN 201711229922A CN 108088672 A CN108088672 A CN 108088672A
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- outer barrel
- suspension joint
- barrel suspension
- fixed plate
- landing gear
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- 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
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- 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 barrel suspension joint slow test fixture, including rack, outer barrel suspension joint component, connection component, diagonal brace bar assembly and two pressurized struts, rack is cuboid framework, it is positioned over by backing plate on horizontal plane, a pair of of girder is set on the rack, and the second floor stringer is rabbeted to trabecular interior at this, in first floor stringer placed to girder top overlap joint for multilayer fixed plate component, outer barrel suspension joint is set in fixed plate, the outer barrel suspension joint pressurized strut with being arranged on backing plate respectively, the load(ing) point being plugged in loading lever draws auricle, and it is installed on the hound member hinges on the second floor stringer, wherein loading lever one end is hinged to small connector by XY with mounting 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 connection and loaded state of the actual response testpieces on undercarriage and can bear the static(al) under big load and fatigue test.
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 barrel suspension joint slow test fixture.
Background technology
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 cycle length, Test-bed Design manufacturing cycles
Long, the shortcomings of test period is long, development cost is high, the aircraft nose landing gear outer barrel strut connector of launch carries under marine environment
Lotus is big, and existing test fixture can not be met the requirements.
The content of the invention
It is an object of the invention to provide a kind of aircraft nose landing gear outer barrel suspension joint slow test fixtures, overcome or subtract
At least one drawbacks described above of the light prior art, enables connection and stand under load of the actual response testpieces on undercarriage
State and the static(al) under big load and fatigue test can be born, it is safe and reliable under the loading 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 barrel suspension joint slow test
Fixture, for testing outer barrel suspension joint, including,
Rack, which is the cuboid framework formed by more beam item docking, and passes through backing plate and be positioned on horizontal plane,
A pair of parallel arranged first floor stringer is wherein overlapped by a pair of of girder of setting with respect on beam item in rack bottom two, and
And rabbet second floor stringer between two girders；
Outer barrel suspension joint component, including the multilayer fixed plate component being overlapped between two first floor stringers and installation
Outer barrel suspension joint on multilayer fixed plate component, wherein setting the locking dress of its restricted movement on outer barrel suspension joint
It puts；
Connection component draws auricle including loading lever, pulling-on piece and load(ing) point, and loading lever both sides have double ear knot
Structure, wherein one 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 bearing is hinged；It is that the monaural structure other end is ears structure that load(ing) point, which draws auricle one end, and monaural one end is plugged in loading thick stick
Bar centre position, ears one end are installed by bolt assembly and the cooperation of outer barrel suspension joint；
Diagonal brace bar assembly, it is hinged another including the diagonal brace bearing being arranged on the second floor stringer and one end and diagonal brace bearing
The diagonal brace exemplar that one end is connected with outer barrel suspension joint；
Pressurized strut sets two, is respectively Z-direction pressurized strut and XY to pressurized strut, wherein Z-direction pressurized strut both ends respectively with outside
Cylinder suspension joint and backing plate are hinged and connected；XY is cut with scissors to pressurized strut one end by docking XY to small connector and loading lever opposite side
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 loading lever is amplified loading to the XY to pressurized strut, according to 1:2 magnification ratio system
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, which is stacked, to be connected, wherein offering the through hole of the embedded outer barrel suspension joint in the first fixed plate, and is set on hole wall
It is equipped with multiple protrusions that limitation outer barrel suspension joint rotates.
Preferably, the locking device includes cylinder fixture and the fixing nut with cylinder fixture cooperation installation,
Wherein cylinder fixture is installed on through the through hole in first fixed plate in second fixed plate, and the outer barrel is hung
Fitting sleeve on the cylinder fixture, wherein inside fixing nut insertion outer barrel suspension joint and with cylinder fixture thread fitting phase
It connects.
Preferably, the load(ing) point draw auricle, the loading lever, the pulling-on piece, the XY to small connector and
The XY is placed to pressurized strut with Y-direction in 10.36 °, is loaded with ensureing that X synthesizes a power to power and Y-direction power.
Preferably, to ensure load angle, the load(ing) point draws auricle ears one end front and rear sides and passes through stay bolt
Two panels clamp clip is clamped, the auricle in clamp clip one end fitting ears structure is set, and the other end is then bonded the outer barrel and hangs
Hanging joint is set；Wherein stay bolt sets three groups altogether.
Preferably, the bolt assembly includes the pin set through the loading lever with the outer barrel suspension joint
Axis and respectively the Z-direction fixed plate and Z-direction fixing nut with axis pin both ends cooperation installation, Z-direction fixed plate and Z-direction fixation spiral shell
It is both female to clamp loading lever, prevent its Z-direction from moving.
A kind of advantageous effect of aircraft nose landing gear outer barrel suspension joint slow test fixture provided by the present invention is,
Wherein structural weak link is selected according to undercarriage carrying situation or carries larger key position, by being risen before a kind of ultrafort steel
Fall frame laser forming typical structure part, to substitute full-scale undercarriage, content of the test is concentrated on typical structure part carry out it is 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, are provided effectively for other Project R＆Ds
Test method and means.
Description of the drawings
Fig. 1 is the overall structure diagram of the present invention；
Fig. 2 is the structure diagram of outer barrel suspension joint component in the present invention；
Fig. 3 is the structure diagram of connection component in the present invention；
Fig. 4 is the structure 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 structure diagram that lever is loaded in the present invention；
Fig. 7 is the structure diagram that load(ing) point draws auricle in the present invention；
Fig. 8 is the structure diagram of the first fixed plate in the present invention；
Fig. 9 is the structure diagram of cylinder fixture in the present invention；
Figure 10 is the structure diagram of fixing nut in the present invention；
Figure 11 be the present invention in structure diagram from XY to small connector.
Reference numeral：
1- racks, 2- outer barrel suspension joints component, 3- connection components, 4- diagonal braces bar assembly, 5-Z to pressurized strut, 6-XY to
Pressurized strut, 11- girders, the first floor stringers of 12-, 13- backing plates, the second floor stringers of 14-, 21- outer barrels suspension joint, 22- first are solid
Fixed board, the second fixed plates of 23-, 24- cylinders fixture, 25- fixing nuts, 31- loadings lever, 32- pulling-on pieces, 33- load(ing) points are drawn
Auricle, 34- pulling-on pieces bearing, 35- clamp clips, 36-Z load auricle, 41- to fixed plate, 37-Z to fixing nut, 38- pressurized struts
Diagonal brace bearing, 42- diagonal braces exemplar, 61-XY are to small connector.
Specific embodiment
The aircraft nose landing gear outer barrel suspension joint slow test fixture of the present invention is done further below in conjunction with the accompanying drawings in detail
It describes in detail bright.
As shown in Fig. 1 to 11, a kind of aircraft nose landing gear outer barrel suspension joint slow test fixture hangs for testing outer barrel
Hanging joint, including rack 1, outer barrel suspension joint component 2, connection component 3, diagonal brace bar assembly 4 and two pressurized struts.
As shown in Figure 1, rack 1 is the cuboid framework formed by more beam item docking, and passes through backing plate 13 and be positioned over water
In plane, wherein by the way that a pair of of girder 11 is set to overlap a pair of parallel arranged the on the opposite beam article in 1 bottom two of rack
One floor stringer 12, and rabbet second floor stringer 14 between two girders 11.
As shown in Fig. 2, outer barrel suspension joint component 2 includes multilayer fixed plate component and the outer barrel suspension of required experiment connects
First 21.The multilayer fixed plate component includes the first fixed plate 22 and the second fixed plate 23, two fixed plates are stacked phase by bolt
Even, wherein offering the through hole of embedded outer barrel suspension joint 21 in the first fixed plate 22, and set on hole wall outside restricted
Multiple protrusions that cylinder suspension joint rotates, the first fixed plate 22 are shown in Fig. 8.Two fixed plates for being stacked connected by bolt are taken and are loaded on
On two first floor stringers 12, wherein 23 one side of the second fixed plate is in contact with the first floor stringer 12,22 one side of the first fixed plate leads to
Outer barrel suspension joint 21 at hole is installed, is moved to limit the outer barrel suspension joint 21, locking device is set inside it, the lock
Tight device includes cylinder fixture 24 (as shown in Figure 9) and the fixing nut 25 installed with cylinder fixture cooperation (see Figure 10 institutes
Show), wherein cylinder fixture 24 is installed on through the through hole in the first fixed plate 22 in the second fixed plate 23, and outer barrel suspension is connect
First 21 are sleeved on the cylinder fixture 24, wherein fixing nut 25 be embedded in 21 inside of outer barrel suspension joint 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 barrel suspension joint 21, the fixing nut 25
For preventing the upward play of outer barrel suspension joint 21, fixing nut 25 clamps outer barrel suspension with cylinder fixture and connects about 24 for setting
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 barrel suspension joint 21, but in view of loading
X is synthesized a power loading by point position and testpieces spatial position and size factor to Y-direction, and Z-direction individually loads.From
And pressurized strut sets two, to pressurized strut 6, wherein 5 one end of Z-direction pressurized strut is added respectively Z-direction pressurized strut 5 and XY by pressurized strut
It carries auricle 38 to be hinged and connected with outer barrel 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 experiment loading
The uniformity of system, XY select 30 tons of hydraulic actuators to pressurized strut 6.
As shown in figure 3, connection component 3, which includes loading lever 31 (as shown in Figure 6), pulling-on piece 32 and load(ing) point, draws auricle
33 (as shown in Figure 7).Loading 31 both sides of lever has ears structure, wherein one 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 bearing 34 on girder 11 between two first floor stringers 12, opposite side ears
Structure is hinged and connected to small connector 61 (as shown in Figure 11) by docking XY with XY to pressurized strut 6, since the loading lever 31 is used
In being amplified loading to pressurized strut 6 to XY, preferably according to 1:2 magnification ratio manufacture.Load(ing) point draws 33 one end of auricle
The monaural structure other end is ears structure, and monaural one end is plugged in 31 centre position of loading lever, and ears one end passes through bolt group
Part is installed with the cooperation of outer barrel suspension joint 21.The bolt assembly includes what is set through loading lever 31 with outer barrel suspension joint 21
Axis pin and respectively the Z-direction fixed plate 36 and Z-direction fixing nut 37, Z-direction fixed plate 36 and Z with axis pin both ends cooperation installation
Loading lever 31 is clamped to both fixing nuts 37, prevents its Z-direction from moving.
It is loaded to ensure that X synthesizes a power to power and Y-direction power, so as to select load(ing) point drawing auricle 33 and Y
To in 10.36 ° of placements, placed correspondingly, loading lever 31, XY are also in 10.36 ° to small connector 61, pulling-on piece 32 with Y-direction.XY to
Pressurized strut 6 is also fixed in 10.36 ° on rack 1 with Y-direction.It should be noted that 34 one end of pulling-on piece bearing passes through spiral shell with pulling-on piece 32
It tethers and connects, the other end is connected with rack girder 11, and pulling-on piece bearing 34 is horizontal positioned, but 34 ears piece of pulling-on piece bearing and pulling-on piece 32
Parallel tilting, i.e., 34 ears piece of pulling-on piece bearing and 34 bearing of pulling-on piece bearing are tilting at an angle.Since load(ing) point draws auricle
33 need slant setting to ensure load angle, select to pass through stay bolt in 33 ears one end front and rear sides of load(ing) point extraction auricle
Two panels clamp clip 35 is clamped, the auricle in 35 one end of clamp clip fitting ears structure is set, and the other end is then bonded outer barrel and hangs
Hanging joint 21 is set, and wherein stay bolt sets three groups altogether.
As shown in figure 4, diagonal brace bar assembly 4 include being arranged at diagonal brace bearing 41 on the second floor stringer 14 and one end with
Diagonal brace bearing 41 is hinged the diagonal brace exemplar 42 that the other end is connected with outer barrel suspension joint 21.
The fixture of the present invention connection and loaded state of the actual response testpieces on undercarriage and can be held
It is safe and reliable under the loading of guarantee test part by the static(al) under big load and fatigue test.
The above description is merely a specific embodiment, but protection scope of the present invention is not limited thereto, any
Those familiar with the art in the technical scope disclosed by the present invention, all should by the change or replacement that can be readily occurred in
It is included within the scope of the present invention.Therefore, protection scope of the present invention should using the scope of the claims as
It is accurate.
Claims (8)
1. a kind of aircraft nose landing gear outer barrel suspension joint slow test fixture, for testing outer barrel suspension joint, feature exists
In, including,
Rack (1), which is the cuboid framework formed by more beam item docking, and passes through backing plate (13) and be positioned over water
In plane, wherein a pair of arranged parallel to each other by the way that a pair of of girder (11) is set to overlap with respect on beam item in rack (1) bottom two
The first floor stringer (12), and between two girders (11) rabbet second floor stringer (14)；
Outer barrel suspension joint component (2), including multilayer fixed plate component, the Yi Jian being overlapped between two first floor stringers (12)
Loaded on the outer barrel suspension joint (21) on multilayer fixed plate component, wherein setting its restricted shifting on outer barrel suspension joint (21)
Dynamic locking device；
Connection component (3) draws auricle (33), loading lever (31) including loading lever (31), pulling-on piece (32) and load(ing) point
Both sides have ears structure, wherein one 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 bearing (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 loading lever (31) centre position, and ears one end is by bolt assembly and outside
Cylinder suspension joint (21) coordinates installation；
Diagonal brace bar assembly (4), including the diagonal brace bearing (41) being arranged on the second floor stringer (14) and one end and diagonal brace bearing
(41) the diagonal brace exemplar (42) that the hinged other end is connected with outer barrel suspension joint (21)；
Pressurized strut sets two, and respectively Z-direction pressurized strut (5) and XY divides to pressurized strut (6), wherein Z-direction pressurized strut (5) both ends
It is not hinged and connected with outer barrel suspension joint (21) and backing plate (13)；XY is to pressurized strut (6) one end by docking XY to small connector
(61) hinged with loading lever (31) opposite side, the other end is mounted on rack (1) roof beam item.
2. aircraft nose landing gear outer barrel suspension joint slow test fixture according to claim 1, which is characterized in that described
XY to pressurized strut (6) be 30 tons of hydraulic actuators.
3. aircraft nose landing gear outer barrel suspension joint slow test fixture according to claim 2, which is characterized in that described
Loading lever (31) is amplified loading to the XY to pressurized strut (6), according to 1:2 magnification ratio manufacture.
4. aircraft nose landing gear outer barrel 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 stacked by bolt to be connected,
The through hole of the embedded outer barrel suspension joint (21) is offered in wherein the first fixed plate (22), and is set on hole wall limited
Multiple protrusions that outer barrel suspension joint processed rotates.
5. aircraft nose landing gear outer barrel suspension joint slow test fixture according to claim 4, which is characterized in that described
Locking device includes cylinder fixture (24) and the fixing nut (25) with cylinder fixture cooperation installation, wherein cylinder fixture
(24) it is installed on through the through hole on first fixed plate (22) on second fixed plate (23), and the outer barrel is hung
Connector (21) is sleeved on the cylinder fixture (24), wherein the embedded outer barrel suspension joint (21) of fixing nut (25) it is internal and with circle
Column fixture (24) thread fitting connects.
6. aircraft nose landing gear outer barrel suspension joint slow test fixture according to claim 5, which is characterized in that described
Load(ing) point draws auricle (33), the loading lever (31), the pulling-on piece (32), the XY to small connector (61) and the XY
It is loaded to pressurized strut (6) with Y-direction in 10.36 ° of placements with ensureing that X synthesizes a power to power and Y-direction power.
7. aircraft nose landing gear outer barrel 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 in clamp clip (35) one end fitting ears structure is set, and the other end is then bonded the outer barrel suspension joint
(21) set；Wherein stay bolt sets three groups altogether.
8. aircraft nose landing gear outer barrel suspension joint slow test fixture according to claim 7, which is characterized in that described
Bolt assembly include through it is described loading lever (31) with the outer barrel suspension joint (21) set axis pin and respectively with this
The Z-direction fixed plate (36) and Z-direction fixing nut (37), Z-direction fixed plate (36) and Z-direction fixing nut of axis pin both ends cooperation installation
(37) the two clamps loading lever (31), prevents its Z-direction from moving.
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 |
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| 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 |
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| CN108088672A true CN108088672A (en) | 2018-05-29 |
| CN108088672B CN108088672B (en) | 2019-06-28 |
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| CN109357852A (en) * | 2018-10-22 | 2019-02-19 | 成都理工大学 | A kind of static(al) rack and Quintic system shock test device |
| CN110220690A (en) * | 2019-07-10 | 2019-09-10 | 中航飞机起落架有限责任公司 | A kind of symmetrical balance loading mechanism and its test method |
| WO2019242104A1 (en) * | 2018-06-22 | 2019-12-26 | 潍柴动力股份有限公司 | Fatigue test assessment method |
| CN110654568A (en) * | 2019-09-29 | 2020-01-07 | 中国直升机设计研究所 | Hub couple loading device |
| CN111099036A (en) * | 2019-11-22 | 2020-05-05 | 南京航空航天大学 | Fatigue test device and method for landing gear ejection main force transfer structure |
| CN111452994A (en) * | 2020-04-22 | 2020-07-28 | 中国飞机强度研究所 | Aircraft nose landing gear supporting device |
| CN112461515A (en) * | 2020-10-30 | 2021-03-09 | 中国直升机设计研究所 | Helicopter undercarriage loading device |
| CN112762779A (en) * | 2020-12-11 | 2021-05-07 | 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 |
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| CN112461515A (en) * | 2020-10-30 | 2021-03-09 | 中国直升机设计研究所 | Helicopter undercarriage loading device |
| CN112461515B (en) * | 2020-10-30 | 2022-07-01 | 中国直升机设计研究所 | Helicopter undercarriage loading device |
| CN112762779A (en) * | 2020-12-11 | 2021-05-07 | 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 |
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| CN108088672B (en) | 2019-06-28 |
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