CN104773306A - Main landing gear three-way loading test device - Google Patents
Main landing gear three-way loading test device Download PDFInfo
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- CN104773306A CN104773306A CN201510160774.5A CN201510160774A CN104773306A CN 104773306 A CN104773306 A CN 104773306A CN 201510160774 A CN201510160774 A CN 201510160774A CN 104773306 A CN104773306 A CN 104773306A
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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 alighting gear fatigue test technology, particularly a kind of main landing gear three-dimensional load testing machine.
Background technology
Alighting gear is the crucial hydraulic unit on helicopter, will bear very large load in the landing of helicopter with in sliding.Helicopter fly at every turn all experiencing from fly to the process of the periodicity reverse load effect of landing, the quality of its performance directly has influence on Helicopter Strength and flight safety.Therefore need strained condition during simulated flight when fatigue test, apply three directional loads to main landing gear.
A usual master fall frame wheel shaft on a tire is housed.For the simulation of single tire, size and the installation requirement of two pieces of dull and stereotyped simulation tires can be designed, replace the installing condition of wheel hub on wheel shaft.But for large-tonnage type, symmetrical on the wheel shaft of its main landing gear two tires are housed, how the wheel of its single shaft two-shipper wheeled construction simulates also does not have experience to use for reference.
Summary of the invention
The present invention will provide a kind of main landing gear three-dimensional load testing machine, can solve current experimental set-up cannot carry out three-dimensional load test problem to the main landing gear with two tires.
Technical scheme of the present invention:
A kind of main landing gear three-dimensional load testing machine, comprise the wheel shaft being arranged on vertical damper leg bottom, described wheel shaft is provided with the wheel bogusware for helicopter simulating tire, it is characterized in that, described wheel bogusware to comprise centered by the axle center of described damper leg and the first wheel bogusware be symmetrical set at described wheel shaft two ends and the second wheel bogusware;
Described main landing gear three-dimensional load testing machine also comprises:
First loaded member, by bolt simultaneously and be equidistantly connected with described second wheel bogusware with described first wheel bogusware, and be positioned at the vertical below of described damper leg, the loading direction of the power of described first loaded member is vertical direction;
Second loaded member, by bolt simultaneously and be equidistantly connected with described second wheel bogusware with described first wheel bogusware, and being positioned at the same side of described first wheel bogusware and described second wheel bogusware, the loading direction of the power of described second loaded member is contrary with the travel direction of described helicopter tire;
3rd loaded member, arranges along described axle axis, and fixes with described first wheel bogusware and described second wheel bogusware simultaneously, and the loading direction of described 3rd loaded member power overlaps with the axis direction of described wheel shaft.
Alternatively, described first wheel bogusware comprises:
Be parallel to each other and all with the first outside plate and first inner panel of horizontal plane, and the area of described first outside plate is greater than the area of described first inner panel;
Described second wheel bogusware comprises:
Be parallel to each other and all with the second outside plate and second inner panel of horizontal plane, and described second outside plate is identical with described first outside plate shape, and described second inner panel is identical with described first inner panel shape;
Simultaneously described second loaded member runs through described first inner panel and described second inner panel by described bolt, is being separately fixed on described first outside plate and described second outside plate.
Alternatively, described 3rd loaded member runs through described first outside plate and described second outside plate successively along described axle axis direction, and fix with described first outside plate and described second outside plate simultaneously.
Alternatively, described first wheel bogusware also comprises:
First intermediate plate, is arranged on described wheel shaft with horizontal plane, between described first outside plate and the first inner panel;
Described second wheel bogusware also comprises:
Second intermediate plate, identical with described first intermediate plate shape, be arranged on described wheel shaft with horizontal plane, and between described second outside plate and the second inner panel;
Simultaneously described first loaded member is fixed on described first intermediate plate and described second intermediate plate by described bolt.
Alternatively, comprise two for the described bolt arranging described second loaded member, be vertically arranged in parallel;
In the side of described first outside plate and described second outside plate that are not provided with described second loaded member, also be provided with two bolts, two described bolts are vertically arranged in parallel, and two described bolts also run through described first inner panel of homonymy and described second inner panel simultaneously, in addition, two described bolts and for described second loaded member is set two described bolts between symmetrical between two.
Alternatively, comprise two for the described bolt arranging described first loaded member, be arranged in parallel in the horizontal direction.
Alternatively, be provided with the side of described second loaded member, described first outside plate and described first inner panel, described first inner panel and described second loaded member, described second loaded member and described second inner panel and the described bolt between described second inner panel and described second outside plate are all being arranged with lining;
In the side relative with described second loaded member, described first outside plate and described first inner panel, described first inner panel and described second inner panel and the described bolt between described second inner panel and described second outside plate are all arranged with described lining;
Described first intermediate plate and described first loaded member and the described bolt between described first loaded member and the second intermediate plate are all arranged with lining.
Alternatively, described second loaded member is connected by the first oscillating bearing with between described bolt.
Alternatively, described first intermediate plate is connected with described wheel shaft respectively by second joint axle with the second intermediate plate.
Alternatively, described first loaded member offers through hole, described through hole is positioned at the vertical lower of the described bolt for arranging described first loaded member, and described 3rd loaded member is through described through hole.
Beneficial effect of the present invention:
Main landing gear three-dimensional load testing machine of the present invention, simplify the design of three-dimensional loading structure, simple and practical, more true and accurate simulation can have structure and the stand under load feature of the wheel of the main landing gear of two tires, the loading in three directions is non-interference, mutual coordination, make test combined error little, test figures is more accurate.
Accompanying drawing explanation
Fig. 1 is the block diagram according to one embodiment of the invention main landing gear three-dimensional load testing machine;
Fig. 2 is the front view (part is cutd open) according to one embodiment of the invention main landing gear three-dimensional load testing machine.
Detailed description of the invention
Below in conjunction with accompanying drawing, main landing gear three-dimensional load testing machine involved in the present invention is described in further details.
According to test requirements document, vertical load is to be just upwards, and drag loads is just with inverse course, and lateral loading is just to point on the right side of fuselage.During helicopter landing, three directional loads mean effort is on two tires, and the power suffered by two tires passes to damper leg.If two tires are regarded as independent stress point, just need two cover load maintainers, respectively two wheel boguswares are loaded.
Namely utilize two actuator to apply vertical load to two wheel boguswares respectively, lateral loading, drag loads are also like this.Which not only adds test apparatus equipment, at double add cost, and the design of loading structure is by complexity, clumsy.
In order to simplified structure and equipment, wheel bogusware that can be reasonable in design, is evenly distributed to applied force in an actuator on the wheel shaft of both sides.Due to alighting gear load spectrum block process in, the fluid be full of in damper leg inevitably mixes air, its can along with the change of magnitude of load Repeated Compression extend, so also need consider three load loaded plant in structure coordination loading.
As shown in Figure 1 to Figure 2, a kind of main landing gear three-dimensional load testing machine of the present invention, comprises the wheel shaft 12 being arranged on vertical damper leg 13 bottom, wheel shaft 12 is provided with the wheel bogusware for helicopter simulating tire.Wheel bogusware to comprise centered by the axle center of damper leg 13 and the first wheel bogusware be symmetrical set at wheel shaft 12 two ends and the second wheel bogusware.
Main landing gear three-dimensional load testing machine also comprises the first loaded member 9, second loaded member 10 and the 3rd loaded member 11.
First loaded member 9 by bolt 5 simultaneously and be equidistantly connected with the second wheel bogusware with the first wheel bogusware, ensure that the load(ing) point of vertical load is positioned at the center-point of wheel.And the first loaded member 9 is positioned at the vertical below 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 the bolt 5 that is connected drives the first wheel bogusware and the second wheel bogusware, then be passed to wheel shaft 12.
Second loaded member 10 by bolt 5 simultaneously and be equidistantly connected with the second wheel bogusware with the first wheel bogusware, and being positioned at the same side of the first wheel bogusware and the second wheel bogusware, the loading direction of the power of the second loaded member 10 is contrary with the travel direction of helicopter tire.Wherein, drag loads is applied through the second loaded member 10 and connected bolt 5 drives the first wheel bogusware and described second wheel bogusware, then is passed to wheel shaft 12.
3rd loaded member 11 along wheel shaft 12 axis arranged, and is fixed with the first wheel bogusware and the second wheel bogusware simultaneously, and the loading direction of the 3rd loaded member 11 power overlaps with the axis direction of wheel shaft 12.The stress point of lateral loading is positioned at the side of tire, and this device drives the first wheel bogusware and the second wheel bogusware by the 3rd loaded member 11 of the outermost side of wheel bogusware dexterously, eliminates the work of redesign, simplifies force-input device.
Main landing gear three-dimensional load testing machine of the present invention, simplifies the design of three-dimensional loading structure, simple and practical, more true and accurate simulation can have structure and the stand under load feature of the wheel of the main landing gear of two tires, meet test requirements document.
The loading in three directions is non-interference, coordinates mutually, and make test combined error little, test figures is more accurate.
In the present embodiment, in order to better simulate the wheel axial thickness of wheel, the amount of compression of tire and tire out of center distance.First wheel bogusware can comprise be parallel to each other and all with the first outside plate 1 and the first inner panel 2 of horizontal plane, and the area of the first outside plate 1 is greater than the area of the first inner panel 2.Second wheel bogusware can comprise be parallel to each other and all with the second outside plate 3 and the second inner panel 4 of horizontal plane, and the second outside plate 3 is identical with the first outside plate 1 shape, and the second inner panel 4 is identical with the first inner panel 2 shape.It should be noted that, the first concrete outside plate 1 and the concrete shape of the second outside plate 3 and the first inner panel 2 and the second inner panel 4 can carry out according to the wheel of physical simulation the design that is applicable to, repeat no more herein.
Simultaneously second loaded member 10 runs through the first inner panel 2 and the second inner panel 4 by bolt 5, is being separately fixed on the first outside plate 1 and the second outside plate 3.
3rd loaded member 11 runs through the first outside plate 1 and the second outside plate 3 successively along wheel shaft 12 axis direction, and fix with the first outside plate 1 and the second outside plate 3 simultaneously.
In the present embodiment, the first wheel bogusware also comprises the first intermediate plate 7.First intermediate plate 7 is arranged on wheel shaft 12, between the first outside plate 1 and the first inner panel 2 with horizontal plane.Equally, the second wheel bogusware also comprises the second intermediate plate 8, identical with the first intermediate plate 7 shape, is arranged on wheel shaft 12 with horizontal plane, and between the second outside plate 3 and the second inner panel 4.Simultaneously first loaded member 9 is fixed on the first intermediate plate 7 and the second intermediate plate 8 by bolt 5.
Bolt 5 for arranging the second loaded member 10 comprises two, is vertically arranged in parallel.And in the side of the first outside plate 1 and the second outside plate 3 that are not provided with the second loaded member 10, being also provided with two bolts, 5, two bolts 5 is vertically arranged in parallel, and two bolts 5 also run through the first inner panel 2 and the second inner panel 4 of homonymy simultaneously.In addition, above-mentioned two bolts 5 and for the second loaded member 10 is set two bolts 5 between symmetrical between two, can ensure in the second loaded member 10 force process, the stability between each inner and outer plates.
Equally, comprise two for the bolt 5 arranging the first loaded member 9, be arranged in parallel in the horizontal direction, make structure firm stable more, force evenly.
Be provided with the side of the second loaded member 10, the first outside plate 1 and the first inner panel 2, first inner panel 2 and the second loaded member 10, second loaded member 10 and the second inner panel 4 and the bolt 5 between the second inner panel 4 and the second outside plate 3 are all being arranged with lining 6.Further, in the side relative with the second loaded member 10, the first outside plate 1 and the first inner panel 2, first inner panel 2 and the second inner panel 4 and the bolt 5 between the second inner panel 4 and the second outside plate 3 are all arranged with lining 6.In addition, the first intermediate plate 7 and the first loaded member 9 and the bolt 5 between the first loaded member 9 and the second intermediate plate 8 are all arranged with lining 6.Lining 6 for being spaced from each other between above-mentioned parts, and can simulate the wheel axial thickness of wheel, the amount of compression of tire better, tire out of center distance.
Second loaded member 10 is connected by the first oscillating bearing 101 with between bolt 5, can eliminate the interference to it when vertical load and lateral loading load.Be connected with wheel shaft 12 respectively by second joint bearing 701 with the second intermediate plate 8 at the first intermediate plate 7, the interference to it when drag loads and lateral loading load can be eliminated.Further, also oscillating bearing (not shown) can be arranged between the 3rd loaded member 11 and corresponding hold-down bolt 5, thus the interference to it when eliminating vertical load and drag loads loading.
First loaded member 9 offers through hole 901, and through hole 901 is positioned at the vertical lower of the bolt 5 for arranging the first loaded member 9, and the 3rd loaded member 11, through through hole 901, makes the integral structure of experiment loading unit simpler.
Main landing gear three-dimensional load testing machine of the present invention, the loading in three directions is non-interference, coordinates mutually, and make test combined error little, tested by this experimental set-up, test combined error can be controlled within 3%, and test figures is more accurate.
The above is only the preferred embodiment of the present invention; it should be pointed out that for those skilled in the art, do not departing under the original prerequisite of the present invention; can also make some improvements and modifications, these improvements and modifications also should be considered as protection scope of the present invention.
Claims (10)
1. a main landing gear three-dimensional load testing machine, comprise the wheel shaft (12) being arranged on vertical damper leg (13) bottom, described wheel shaft (12) is provided with the wheel bogusware for helicopter simulating tire, it is characterized in that, described wheel bogusware to comprise centered by the axle center of described damper leg (13) and the first wheel bogusware be symmetrical set at described wheel shaft (12) two ends and the second wheel bogusware;
Described main landing gear three-dimensional load testing machine also comprises:
First loaded member (9), by bolt (5) simultaneously and be equidistantly connected with described second wheel bogusware with described first wheel bogusware, and being positioned at the vertical below of described damper leg (13), the loading direction of the power of described first loaded member (9) is vertical direction;
Second loaded member (10), by bolt (5) simultaneously and be equidistantly connected with described second wheel bogusware with described first wheel bogusware, and being positioned at the same side of described first wheel bogusware and described second wheel bogusware, the loading direction of the power of described second loaded member (10) is contrary with the travel direction of described helicopter tire;
3rd loaded member (11), along described wheel shaft (12) axis arranged, and fix with described first wheel bogusware and described second wheel bogusware, the loading direction of described 3rd loaded member (11) power overlaps with the axis direction of described wheel shaft (12). simultaneously
2. main landing gear three-dimensional load testing machine according to claim 1, is characterized in that, described first wheel bogusware comprises:
Be parallel to each other and all with the first outside plate (1) and first inner panel (2) of horizontal plane, and the area of described first outside plate (1) is greater than the area of described first inner panel (2);
Described second wheel bogusware comprises:
Be parallel to each other and all with the second outside plate (3) and second inner panel (4) of horizontal plane, and described second outside plate (3) is identical with described first outside plate (1) shape, described second inner panel (4) is identical with described first inner panel (2) shape;
Simultaneously described second loaded member (10) runs through described first inner panel (2) and described second inner panel (4) by described bolt (5), is being separately fixed at described first outside plate (1) with on described second outside plate (3).
3. main landing gear three-dimensional load testing machine according to claim 2, it is characterized in that, described 3rd loaded member (11) runs through described first outside plate (1) and described second outside plate (3) successively along described wheel shaft (12) axis direction, and fix with described first outside plate (1) and described second outside plate (3) simultaneously.
4. main landing gear three-dimensional load testing machine according to claim 3, is characterized in that, described first wheel bogusware also comprises:
First intermediate plate (7), is arranged on described wheel shaft (12) with horizontal plane, is positioned between described first outside plate (1) and the first inner panel (2);
Described second wheel bogusware also comprises:
Second intermediate plate (8), identical with described first intermediate plate (7) shape, be arranged on described wheel shaft (12) with horizontal plane, and be positioned between described second outside plate (3) and the second inner panel (4);
Simultaneously described first loaded member (9) is fixed on described first intermediate plate (7) with on described second intermediate plate (8) by described bolt (5).
5. main landing gear three-dimensional load testing machine according to claim 4, is characterized in that, comprises two, be vertically arranged in parallel for the described bolt (5) arranging described second loaded member (10);
In the side of described first outside plate (1) Yu described second outside plate (3) that are not provided with described second loaded member (10), also be provided with two bolts (5), two described bolts (5) are vertically arranged in parallel, and two described bolts (5) also run through described first inner panel (2) of homonymy and described second inner panel (4) simultaneously, in addition, two described bolts (5) and for described second loaded member (10) is set two described bolts (5) between symmetrical between two.
6. main landing gear three-dimensional load testing machine according to claim 4, is characterized in that, comprises two, be arranged in parallel in the horizontal direction for the described bolt (5) arranging described first loaded member (9).
7. the main landing gear three-dimensional load testing machine according to claim 5 or 6, it is characterized in that, be provided with the side of described second loaded member (10), described first outside plate (1) and described first inner panel (2), described first inner panel (2) and described second loaded member (10), described second loaded member (10) and described second inner panel (4) and the described bolt (5) between described second inner panel (4) and described second outside plate (3) are all being arranged with lining (6);
In the side relative with described second loaded member (10), described first outside plate (1) and described first inner panel (2), described first inner panel (2) and described second inner panel (4) and the described bolt (5) between described second inner panel (4) and described second outside plate (3) are all arranged with described lining (6);
Described first intermediate plate (7) and described first loaded member (9) and the described bolt (5) between described first loaded member (9) and the second intermediate plate (8) are all arranged with lining (6).
8. main landing gear three-dimensional load testing machine according to claim 7, is characterized in that, described second loaded member (10) is connected by the first oscillating bearing (101) with between described bolt (5).
9. main landing gear three-dimensional load testing machine according to claim 7, it is characterized in that, described first intermediate plate (7) is connected with described wheel shaft (12) respectively by second joint bearing (701) with the second intermediate plate (8).
10. main landing gear three-dimensional load testing machine according to claim 7, it is characterized in that, described first loaded member (9) offers through hole (901), described through hole (901) is positioned at the vertical lower of the described bolt (5) for arranging described first loaded member (9), and described 3rd loaded member (11) is through described through hole (901).
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| CN201510160774.5A CN104773306B (en) | 2015-04-07 | 2015-04-07 | Main landing gear three-way loading test device |
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| CN201510160774.5A CN104773306B (en) | 2015-04-07 | 2015-04-07 | Main landing gear three-way loading test device |
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| CN104773306A true CN104773306A (en) | 2015-07-15 |
| CN104773306B CN104773306B (en) | 2017-02-01 |
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| CN105173117A (en) * | 2015-10-10 | 2015-12-23 | 中国航空工业集团公司沈阳飞机设计研究所 | Fuselage crossing point simulating device for airplane main landing gear ground test |
| CN106428623A (en) * | 2016-08-29 | 2017-02-22 | 中国航空工业集团公司西安飞机设计研究所 | Loading method of variable stroke test for undercarriage |
| 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 |
| CN109506909A (en) * | 2018-11-09 | 2019-03-22 | 中国直升机设计研究所 | Endpiece testpieces fatigue test tail undercarriage load charger |
| 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 |
| CN109733638A (en) * | 2018-09-07 | 2019-05-10 | 中国飞机强度研究所 | Load applying method in the case of a kind of long struts undercarriage large deformation |
| CN109850184A (en) * | 2019-04-08 | 2019-06-07 | 中航飞机起落架有限责任公司 | A kind of supporting adn fixing device integrally delivered for undercarriage and application method |
| CN110595755A (en) * | 2019-09-29 | 2019-12-20 | 中国直升机设计研究所 | Main landing gear loading test device with single wheel and inclined angle |
| CN110589022A (en) * | 2019-09-26 | 2019-12-20 | 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 |
| CN110815078A (en) * | 2019-11-14 | 2020-02-21 | 昌河飞机工业（集团）有限责任公司 | Undercarriage strut test clamping device and method |
| CN112461515A (en) * | 2020-10-30 | 2021-03-09 | 中国直升机设计研究所 | Helicopter undercarriage loading device |
| CN117382909A (en) * | 2023-12-07 | 2024-01-12 | 山西助我飞科技有限公司 | Fatigue characteristic testing assembly for undercarriage |
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| CN105173117A (en) * | 2015-10-10 | 2015-12-23 | 中国航空工业集团公司沈阳飞机设计研究所 | Fuselage crossing point simulating device for airplane main landing gear ground test |
| CN106428623A (en) * | 2016-08-29 | 2017-02-22 | 中国航空工业集团公司西安飞机设计研究所 | Loading method of variable stroke test for undercarriage |
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| 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 |
| CN109733638A (en) * | 2018-09-07 | 2019-05-10 | 中国飞机强度研究所 | Load applying method in the case of a kind of long struts undercarriage large deformation |
| CN109506909A (en) * | 2018-11-09 | 2019-03-22 | 中国直升机设计研究所 | Endpiece testpieces fatigue test tail undercarriage load charger |
| 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 |
| CN109850184A (en) * | 2019-04-08 | 2019-06-07 | 中航飞机起落架有限责任公司 | A kind of supporting adn fixing device integrally delivered for undercarriage and application method |
| CN110589022A (en) * | 2019-09-26 | 2019-12-20 | 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 |
| 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 |
| CN110595755A (en) * | 2019-09-29 | 2019-12-20 | 中国直升机设计研究所 | Main landing gear loading test device with single wheel and inclined angle |
| CN110815078A (en) * | 2019-11-14 | 2020-02-21 | 昌河飞机工业（集团）有限责任公司 | Undercarriage strut test clamping device and method |
| 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 |
| CN117382909A (en) * | 2023-12-07 | 2024-01-12 | 山西助我飞科技有限公司 | Fatigue characteristic testing assembly for undercarriage |
| 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 |
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