CN104773306B - Main landing gear three-way loading test device - Google Patents
Main landing gear three-way loading test device Download PDFInfo
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- CN104773306B CN104773306B CN201510160774.5A CN201510160774A CN104773306B CN 104773306 B CN104773306 B CN 104773306B CN 201510160774 A CN201510160774 A CN 201510160774A CN 104773306 B CN104773306 B CN 104773306B
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- inner panel
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Abstract
The invention belongs to the technology of helicopter main landing gear fatigue tests, and relates to a main landing gear three-way loading test device. The main landing gear three-way loading test device can solve the problem that a current test device cannot carry out a three-way loading test on a main landing gear with two tires. The main landing gear three-way loading test device disclosed by the invention comprises a wheel shaft arranged at the bottom end of a vertical buffer support, wherein airplane wheel artificial pieces for simulating helicopter tires are arranged on the rotating shaft; the airplane wheel artificial pieces comprise a first airplane wheel artificial piece and a second airplane wheel artificial piece which are symmetrically arranged on the left side and the right side by taking the axis of the buffer support as the center. The main landing gear three-way loading test device further comprises a first loading piece, a second loading piece and a third loading piece. According to the main landing gear three-way loading test device disclosed by the invention, the design of a three-way loading structure is simplified, the device is simple and practical, and the structure and loaded characteristic of the airplane wheels of the main landing gear with two tires can be simulated more truly and accurately.
Description
Technical field
The invention belongs to Helicopter Main undercarriage fatigue test technology, particularly to a kind of main landing gear three-dimensional load test
Device.
Background technology
Undercarriage is the crucial hydraulic unit on helicopter, will bear very big load in the landing of helicopter with sliding
Lotus.The each flight of helicopter all experiencing from fly to landing periodicity alternate load effect process, the quality of its performance
Directly influence Helicopter Strength and flight safety.Stress when therefore needing simulated flight in fatigue test, gives
Main landing gear applies three directional loads.
A usual master fall frame wheel shaft on equipped with a tire.For the simulation of single tire, two pieces can be designed and put down
Template die intends size and the installation requirement of tire, replaces installment state on wheel shaft for the wheel hub.But for large-tonnage type, its
On the wheel shaft of main landing gear symmetrical equipped with two tires, how the wheel of its single shaft two-shipper wheeled construction simulates also does not have warp
Test and can use for reference.
Content of the invention
The present invention will provide a kind of main landing gear three-dimensional load testing machine, can solve the problem that current assay device cannot be to tool
The main landing gear having two tires carries out the problem of three-dimensional load test.
Technical scheme:
A kind of main landing gear three-dimensional load testing machine, including the wheel shaft being arranged on vertical damper leg bottom, described wheel
Wheel bogusware for helicopter simulating tire is provided with axle it is characterised in that described wheel bogusware is included with described buffering
Centered on the axle center of pillar and be symmetrical set the first wheel bogusware at described wheel shaft two ends and the second wheel bogusware；
Described main landing gear three-dimensional load testing machine also includes:
First loaded member, simultaneously and equidistantly false with described first wheel bogusware and described second wheel by the first bolt
Part is connected, and is located at the vertical lower section of described damper leg, and the loading direction of the power of described first loaded member is vertical direction；
Second loaded member, simultaneously and equidistantly false with described first wheel bogusware and described second wheel by the second bolt
Part is connected, and is located at the same side of described first wheel bogusware and described second wheel bogusware, the power of described second loaded member
Loading direction is contrary with the travel direction of described helicopter tire；
3rd loaded member, along described axle axis arrangement, and simultaneously with described first wheel bogusware and described second wheel
Bogusware is fixed, and the loading direction of described 3rd loaded member power is overlapped with the axis direction of described wheel shaft.
Alternatively, described first wheel bogusware includes:
It is parallel to each other and the first outside plate and the first inner panel all with horizontal plane, and the area of described first outside plate is more than
The area of described first inner panel；
Described second wheel bogusware includes:
It is parallel to each other and the second outside plate and the second inner panel all with horizontal plane, and described second outside plate and described first
Outer plate shape is identical, and described second inner panel is identical with plate shape in described first；
Described second loaded member is to run through described first inner panel and described second inner panel by described second bolt simultaneously, then
It is separately fixed on described first outside plate and described second outside plate.
Alternatively, described 3rd loaded member is to sequentially pass through described first outside plate and described the along described axle axis direction
Two outside plates, and fix with described first outside plate and described second outside plate simultaneously.
Alternatively, described first wheel bogusware also includes:
First intermediate plate, is arranged on described wheel shaft with horizontal plane, positioned at described first outside plate and the first inner panel it
Between；
Described second wheel bogusware also includes:
Second intermediate plate, identical with the described first middle plate shape, it is arranged on described wheel shaft with horizontal plane, and position
Between described second outside plate and the second inner panel；
Described first loaded member is to be also secured in described first intermediate plate and described second by described first bolt
Between on plate.
Alternatively, described second bolt for arranging described second loaded member includes two, vertically parallel cloth
Put；
It is being not provided with described first outside plate of described second loaded member and the side of described second outside plate, be additionally provided with two
Root second bolt, two described second bolts are vertically arranged in parallel, and two described second bolts also run through same simultaneously
Described first inner panel of side and described second inner panel, in addition, two described second bolts with for arranging described second loaded member
Two described second bolts between symmetrical two-by-two.
Alternatively, described first bolt for arranging described first loaded member includes two, parallel cloth in the horizontal direction
Put.
Alternatively, in the side being provided with described second loaded member, described first outside plate and described first inner panel, described the
One inner panel and described second loaded member, described second loaded member and described second inner panel and described second inner panel and described second
All it is arranged with bushing on described second bolt between outside plate；
In the side relative with described second loaded member, described first outside plate and described first inner panel, described first inner panel
All it is arranged with described on described second bolt and described second inner panel and described second inner panel and described second outside plate between
Bushing；
Institute between described first intermediate plate and described first loaded member and described first loaded member and the second intermediate plate
State and bushing is all arranged with the first bolt.
Alternatively, it is connected by the first oscillating bearing between described second loaded member and described second bolt.
Alternatively, described first intermediate plate and the second intermediate plate are connected with described wheel shaft by second joint axle respectively.
Alternatively, described first loaded member offers through hole, described through hole is located at for arranging described first loaded member
Described first bolt vertical lower, described 3rd loaded member pass through described through hole.
Beneficial effects of the present invention:
The main landing gear three-dimensional load testing machine of the present invention, simplifies the design of three-dimensional loading structure, simple and practical, energy
More true and accurate simulation has structure and the stand under load feature of the wheel of the main landing gear of two tires, and the loading in three directions is mutual
Do not interfere, coordinate mutually so that test total error is little, test data is more accurate.
Brief description
Fig. 1 is the axonometric chart according to one embodiment of the invention main landing gear three-dimensional load testing machine；
Fig. 2 is the front view (partly cuing open) according to one embodiment of the invention main landing gear three-dimensional load testing machine.
Specific embodiment
Below in conjunction with the accompanying drawings main landing gear three-dimensional load testing machine involved in the present invention is described in further details.
According to test requirements document, for just, with inverse course for just, lateral load is to point to machine for drag loads with upwards for vertical load
Just it is on the right side of body.During helicopter landing, on two tires, the power suffered by two tires passes to slow for three directional loads mean effort
Rush pillar.If two tires are regarded as single stress point it is necessary to two sets of load maintainers, respectively two wheel boguswares are entered
Row loads.
Two actuator are utilized to apply vertical load to two wheel boguswares respectively, lateral load, drag loads are also
So.Which not only adds test apparatuses equipment, at double increased cost, and the design of loading structure will be complicated, stupid
Clumsy.
In order to simplify structure and equipment, wheel bogusware that can be reasonable in design, the power that an actuator is applied is put down
All it is assigned on the wheel shaft of both sides.During loading spectrum block due to undercarriage, the fluid being full of in damper leg is inevitable
Mix air, it Repeated Compression can extend with the change of magnitude of load, so three load also needing to consider load
The coordination crossing structure in planting loads.
As shown in Figure 1 to Figure 2, a kind of main landing gear three-dimensional load testing machine of the present invention, vertically delays including being arranged on
Rush the wheel shaft 12 of pillar 13 bottom, wheel shaft 12 is provided with the wheel bogusware for helicopter simulating tire.Wheel bogusware includes
Centered on the axle center of damper leg 13 and be symmetrical set the first wheel bogusware at wheel shaft 12 two ends and the second wheel is false
Part.
Main landing gear three-dimensional load testing machine also includes the first loaded member 9, the second loaded member 10 and the 3rd loaded member
11.
First loaded member 9 is connected by the first bolt simultaneously and equidistantly with the first wheel bogusware and the second wheel bogusware,
Ensure that the load(ing) point of vertical load is located at the central point of wheel.And first loaded member 9 be located at the vertical lower section of damper leg 13,
The loading direction of the power of the first loaded member 9 is vertical direction.Wherein, vertical load be applied through the first loaded member 9 and phase
The first bolt even is driving the first wheel bogusware and the second wheel bogusware, then is transferred to wheel shaft 12.
Second loaded member 10 is connected by the second bolt simultaneously and equidistantly with the first wheel bogusware and the second wheel bogusware,
And be located at the same side of the first wheel bogusware and the second wheel bogusware, the loading direction of power of the second loaded member 10 with go straight up to wheel
The travel direction of tire is contrary.Wherein, drag loads are applied through the second loaded member 10 and the second bolt of being connected to drive the
One wheel bogusware and described second wheel bogusware, then it is transferred to wheel shaft 12.
3rd loaded member 11 is arranged along wheel shaft 12 axis, and fixes with the first wheel bogusware and the second wheel bogusware simultaneously,
The loading direction of the 3rd loaded member 11 power is overlapped with the axis direction of wheel shaft 12.The stress point of lateral load is located at the side of tire
Face, this device dexterously drives the first wheel bogusware and the second machine by the 3rd loaded member 11 of the outermost side of wheel bogusware
Wheel bogusware, eliminates the work of redesign, simplifies charger.
The main landing gear three-dimensional load testing machine of the present invention, simplifies the design of three-dimensional loading structure, simple and practical, energy
More true and accurate simulation has structure and the stand under load feature of the wheel of the main landing gear of two tires, meets test requirements document.
The loading in three directions is non-interference, coordinates mutually so that test total error is little, test data is more accurate.
In the present embodiment, wheel axial thickness, the decrement of tire and tire in order to preferably simulate wheel are excentric
Distance.First wheel bogusware can include being parallel to each other and the first outside plate 1 and the first inner panel 2 all with horizontal plane, and the
The area of one outside plate 1 is more than the area of the first inner panel 2.Second wheel bogusware can include being parallel to each other and equal and horizontal plane
The second outside plate 3 and the second inner panel 4, and the second outside plate 3 is identical with the first outside plate 1 shape, the second inner panel 4 and the first inner panel 2 shape
Shape is identical.It should be noted that specific first outside plate 1 and the second outside plate 3 and the first inner panel 2 and the second inner panel 4 is concrete
Shape can carry out suitable design according to the wheel of physical simulation, and here is omitted.
Second loaded member 10 is to run through the first inner panel 2 and the second inner panel 4 by the second bolt simultaneously, is being separately fixed at
On one outside plate 1 and the second outside plate 3.
3rd loaded member 11 is to sequentially pass through the first outside plate 1 and the second outside plate 3 along wheel shaft 12 axis direction, and simultaneously with
One outside plate 1 and the second outside plate 3 are fixing.
In the present embodiment, the first wheel bogusware also includes the first intermediate plate 7.First intermediate plate 7 and horizontal plane setting
On wheel shaft 12, between the first outside plate 1 and the first inner panel 2.Equally, the second wheel bogusware also includes the second intermediate plate 8, with
First intermediate plate 7 shape is identical, is arranged on wheel shaft 12 with horizontal plane, and be located at the second outside plate 3 and the second inner panel 4 it
Between.First loaded member 9 is to be also secured on the first intermediate plate 7 and the second intermediate plate 8 by the first bolt.
The second bolt for arranging the second loaded member 10 includes two, is vertically arranged in parallel.And be not provided with
There are the first outside plate 1 of the second loaded member 10 and the side of the second outside plate 3, be additionally provided with two second bolts, two second bolts
Vertically it is arranged in parallel, and two second bolts also run through the first inner panel 2 and second inner panel 4 of homonymy simultaneously.In addition, on
State between two second bolts and two second bolts being used for setting the second loaded member 10 two-by-two symmetrically it is ensured that second adds
Stability during holder 10 force, between each inner and outer plates.
Equally, the first bolt for arranging the first loaded member 9 includes two, is arranged in parallel in the horizontal direction so that tying
Structure more firm stable, force is evenly.
In the side being provided with the second loaded member 10, the first outside plate 1 and the first inner panel 2, the first inner panel 2 and the second loaded member
10th, all it is arranged with lining on the second bolt between the second loaded member 10 and the second inner panel 4 and the second inner panel 4 and the second outside plate 3
Set 6.And, in the side relative with the second loaded member 10, the first outside plate 1 and the first inner panel 2, the first inner panel 2 and the second inner panel 4
And second be all arranged with bushing 6 on the second bolt between inner panel 4 and the second outside plate 3.In addition, the first intermediate plate 7 and first
All it is arranged with bushing 6 on the first bolt between loaded member 9 and the first loaded member 9 and the second intermediate plate 8.Bushing 6 is used for will
It is spaced from each other between above-mentioned part, and can preferably simulate the wheel axial thickness of wheel, the decrement of tire, tire is from center
Distance.
Be connected by the first oscillating bearing 101 between second loaded member 10 and the second bolt, can eliminate vertical load and
Interference to it when lateral load loads.The first intermediate plate 7 and the second intermediate plate 8 pass through respectively second joint bearing 701 with
Wheel shaft 12 connects, and can eliminate the interference to it when drag loads and lateral load loading.Further it is also possible to load the 3rd
It is arranged on oscillating bearing (not shown), thus eliminating vertical load and drag loads between part 11 and corresponding installation the second bolt
Interference to it during loading.
Through hole 901 is offered on the first loaded member 9, through hole 901 is located at the first bolt for arranging the first loaded member 9
Vertical lower, the 3rd loaded member 11 passes through through hole 901 so that the overall structure of experiment loading unit is simpler.
The main landing gear three-dimensional load testing machine of the present invention, the loading in three directions is non-interference, coordinate mutually so that
Test total error is little, is tested by this assay device, and test total error can be controlled within 3%, and test data is more accurate.
The above is only the preferred embodiment of the present invention it is noted that ordinary skill people for the art
For member, on the premise of original without departing from the present invention, some improvements and modifications can also be made, these improvements and modifications also should
It is considered as protection scope of the present invention.
Claims (10)
1. a kind of main landing gear three-dimensional load testing machine, including the wheel shaft (12) being arranged on vertical damper leg (13) bottom,
Wheel bogusware for helicopter simulating tire is provided with described wheel shaft (12) it is characterised in that described wheel bogusware includes
Centered on the axle center of described damper leg (13) and be symmetrical set the first wheel bogusware at described wheel shaft (12) two ends
With the second wheel bogusware；
Described main landing gear three-dimensional load testing machine also includes:
First loaded member (9), simultaneously and equidistantly false with described first wheel bogusware and described second wheel by the first bolt
Part is connected, and is located at the vertical lower section of described damper leg (13), and the loading direction of the power of described first loaded member (9) is vertical
Direction；
Second loaded member (10), simultaneously and equidistantly false with described first wheel bogusware and described second wheel by the second bolt
Part is connected, and is located at the same side of described first wheel bogusware and described second wheel bogusware, described second loaded member (10)
The loading direction of power is contrary with the travel direction of described helicopter tire；
3rd loaded member (11), along described wheel shaft (12) axis arrangement, and simultaneously with described first wheel bogusware and described second
Wheel bogusware is fixed, and the loading direction of described 3rd loaded member (11) power is overlapped with the axis direction of described wheel shaft (12).
2. main landing gear three-dimensional load testing machine according to claim 1 is it is characterised in that described first wheel bogusware
Including:
It is parallel to each other and the first outside plate (1) and the first inner panel (2) all with horizontal plane, and the face of described first outside plate (1)
The long-pending area more than described first inner panel (2)；
Described second wheel bogusware includes:
It is parallel to each other and the second outside plate (3) and the second inner panel (4) all with horizontal plane, and described second outside plate (3) and institute
State the first outside plate (1) shape identical, described second inner panel (4) is identical with described first inner panel (2) shape；
Described second loaded member (10) is to run through described first inner panel (2) and described second inner panel by described second bolt simultaneously
, then be separately fixed on described first outside plate (1) and described second outside plate (3) (4).
3. main landing gear three-dimensional load testing machine according to claim 2 is it is characterised in that described 3rd loaded member
(11) be to sequentially pass through described first outside plate (1) and described second outside plate (3) along described wheel shaft (12) axis direction, and simultaneously with
Described first outside plate (1) and described second outside plate (3) are fixing.
4. main landing gear three-dimensional load testing machine according to claim 3 is it is characterised in that described first wheel bogusware
Also include:
First intermediate plate (7), is arranged on described wheel shaft (12) with horizontal plane, positioned at described first outside plate (1) and first
Between inner panel (2)；
Described second wheel bogusware also includes:
Second intermediate plate (8), identical with described first intermediate plate (7) shape, it is arranged on described wheel shaft (12) with horizontal plane
On, and be located between described second outside plate (3) and the second inner panel (4)；
Described first loaded member (9) is to be also secured to described first intermediate plate (7) and described second by described first bolt
On intermediate plate (8).
5. main landing gear three-dimensional load testing machine according to claim 4 is it is characterised in that be used for arranging described second
Described second bolt of loaded member (10) includes two, is vertically arranged in parallel；
It is being not provided with described first outside plate (1) of described second loaded member (10) and the side of described second outside plate (3), also setting
It is equipped with two second bolts, two described second bolts are vertically arranged in parallel, and two described second bolts are also simultaneously
Run through described first inner panel (2) of homonymy and described second inner panel (4), in addition, two described second bolts with for arranging
State symmetrical two-by-two between two described second bolts of the second loaded member (10).
6. main landing gear three-dimensional load testing machine according to claim 4 is it is characterised in that be used for arranging described first
Described first bolt of loaded member (9) includes two, is arranged in parallel in the horizontal direction.
7. the main landing gear three-dimensional load testing machine according to claim 5 or 6 is it is characterised in that described being provided with
The side of the second loaded member (10), described first outside plate (1) and described first inner panel (2), described first inner panel (2) and described the
Two loaded member (10), described second loaded member (10) and described second inner panel (4) and described second inner panel (4) and described second
All it is arranged with bushing (6) on described second bolt between outside plate (3)；
In the side relative with described second loaded member (10), described first outside plate (1) and described first inner panel (2), described the
Between one inner panel (2) and described second inner panel (4) and described second inner panel (4) and described second outside plate (3) described second
Described bushing (6) is all arranged with bolt；
Described first intermediate plate (7) and described first loaded member (9) and described first loaded member (9) and the second intermediate plate (8)
Between described first bolt on be all arranged with bushing (6).
8. main landing gear three-dimensional load testing machine according to claim 7 is it is characterised in that described second loaded member
(10) it is connected by the first oscillating bearing (101) between described second bolt.
9. main landing gear three-dimensional load testing machine according to claim 7 is it is characterised in that described first intermediate plate
(7) and the second intermediate plate (8) is connected with described wheel shaft (12) by second joint bearing (701) respectively.
10. main landing gear three-dimensional load testing machine according to claim 7 is it is characterised in that described first loaded member
(9) offer through hole (901) on, described through hole (901) is located at for arranging described first bolt of described first loaded member (9)
Vertical lower, described 3rd loaded member (11) pass through described through hole (901).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510160774.5A CN104773306B (en) | 2015-04-07 | 2015-04-07 | Main landing gear three-way loading test device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510160774.5A CN104773306B (en) | 2015-04-07 | 2015-04-07 | Main landing gear three-way loading test device |
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| Publication Number | Publication Date |
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| CN104773306A CN104773306A (en) | 2015-07-15 |
| CN104773306B true CN104773306B (en) | 2017-02-01 |
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| CN201510160774.5A Active CN104773306B (en) | 2015-04-07 | 2015-04-07 | Main landing gear three-way loading test device |
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Families Citing this family (15)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105173117B (en) * | 2015-10-10 | 2018-06-05 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of fuselage intersection point simulator of aircraft main landing gear ground experiment |
| CN106428623B (en) * | 2016-08-29 | 2019-01-18 | 中国航空工业集团公司西安飞机设计研究所 | A kind of undercarriage becomes the load loading method of stroke test |
| CN106275502B (en) * | 2016-08-29 | 2018-06-05 | 中国航空工业集团公司西安飞机设计研究所 | A kind of false wheel of gear test loading |
| CN108163226A (en) * | 2017-11-29 | 2018-06-15 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of aircraft nose landing gear outer barrel strut connector launch fatigue test method |
| CN108163225A (en) * | 2017-11-29 | 2018-06-15 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of aircraft nose landing gear outer barrel suspension joint launch fatigue test method |
| CN109733638B (en) * | 2018-09-07 | 2022-05-06 | 中国飞机强度研究所 | Load application method under large deformation condition of long strut undercarriage |
| CN109506909B (en) * | 2018-11-09 | 2020-08-14 | 中国直升机设计研究所 | Tail landing gear load loading device for fatigue test of tail section test piece |
| CN109533386A (en) * | 2018-11-13 | 2019-03-29 | 中国直升机设计研究所 | Connection structure strength test device on a kind of undercarriage machine |
| CN109850184B (en) * | 2019-04-08 | 2020-07-17 | 中航飞机起落架有限责任公司 | Supporting and fixing device for integral delivery of undercarriage and using method |
| CN110589022B (en) * | 2019-09-26 | 2022-08-19 | 中国航空工业集团公司西安飞机设计研究所 | Loading device and multi-support undercarriage variable stroke replacement-free loading system |
| CN110595755B (en) * | 2019-09-29 | 2021-07-23 | 中国直升机设计研究所 | Main landing gear loading test device with single wheel and inclined angle |
| CN110815078B (en) * | 2019-11-14 | 2021-06-29 | 昌河飞机工业（集团）有限责任公司 | Undercarriage strut test clamping device and method |
| CN112461515B (en) * | 2020-10-30 | 2022-07-01 | 中国直升机设计研究所 | Helicopter undercarriage loading device |
| CN114919773B (en) * | 2022-06-10 | 2024-08-02 | 中国航空工业集团公司西安飞机设计研究所 | Undercarriage loading device and loading method based on moment balance |
| CN117382909B (en) * | 2023-12-07 | 2024-02-09 | 山西助我飞科技有限公司 | Fatigue characteristic testing assembly for undercarriage |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN202156542U (en) * | 2011-06-21 | 2012-03-07 | 南京航空航天大学 | Variable load loading test device |
| CN104048880A (en) * | 2014-07-01 | 2014-09-17 | 北京航空航天大学 | Three-directional load experiment system for airport pavement |
| CN104354855A (en) * | 2009-08-28 | 2015-02-18 | 空中客车英国运营有限责任公司 | Aircraft landing gear |
Family Cites Families (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB0523069D0 (en) * | 2005-11-11 | 2005-12-21 | Airbus Uk Ltd | Aircraft braking system |
| US8220740B2 (en) * | 2007-11-06 | 2012-07-17 | Borealis Technical Limited | Motor for driving aircraft, located adjacent to undercarriage wheel |
| FR2987441B1 (en) * | 2012-02-24 | 2014-12-19 | Airbus Operations Sas | DEVICE FOR EXCITATION TO THE GROUND OF A LANDING TRAIN OF AN AIRCRAFT. |
-
2015
- 2015-04-07 CN CN201510160774.5A patent/CN104773306B/en active Active
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104354855A (en) * | 2009-08-28 | 2015-02-18 | 空中客车英国运营有限责任公司 | Aircraft landing gear |
| CN202156542U (en) * | 2011-06-21 | 2012-03-07 | 南京航空航天大学 | Variable load loading test device |
| CN104048880A (en) * | 2014-07-01 | 2014-09-17 | 北京航空航天大学 | Three-directional load experiment system for airport pavement |
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| CN104773306A (en) | 2015-07-15 |
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