CN110589022A - Loading device and multi-support undercarriage variable stroke replacement-free loading system - Google Patents
Loading device and multi-support undercarriage variable stroke replacement-free loading system Download PDFInfo
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- CN110589022A CN110589022A CN201910919177.4A CN201910919177A CN110589022A CN 110589022 A CN110589022 A CN 110589022A CN 201910919177 A CN201910919177 A CN 201910919177A CN 110589022 A CN110589022 A CN 110589022A
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/60—Testing or inspecting aircraft components or systems
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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
- G01M17/00—Testing of vehicles
- G01M17/007—Wheeled or endless-tracked vehicles
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Abstract
The application belongs to the technical field of variable-stroke loading tests of aircraft undercarriages, and particularly relates to a loading device and a variable-stroke reloading-free loading system of a multi-strut undercarriage, wherein the loading device comprises: a rocker arm including a strut connecting portion, a hub mounting shaft, and a damper connecting portion; the two hub simulation pieces are fixedly sleeved on the hub mounting shafts on the two sides through the double-lug structures of the two hub simulation pieces respectively; and the two three-way joints are respectively rotatably arranged on the hub mounting shafts on the two sides, are in a double-lug structure on the same side and comprise two course loading lugs and a vertical loading lug. The loading device and the multi-support undercarriage variable stroke reloading-free loading system solve the problem that the multi-support undercarriage cannot realize independent loading of all supports in a narrow space, can realize multi-point coordination loading of the multi-support undercarriage, guarantees loading precision, improves working efficiency and effectively shortens test period.
Description
Technical Field
The application belongs to the technical field of variable-stroke loading tests of aircraft undercarriages, and particularly relates to a loading device and a multi-strut undercarriage variable-stroke replacement-free loading system.
Background
Conventional landing gear range loading methods are generally only applicable to single strut landing gears. To prevent the deformation from spreading, the isotropic loading should be stretched unidirectionally as much as possible, so that the loading space is required to a large extent. With multi-strut landing gears, the limited space between the struts necessarily results in the inability to independently load a single strut. Moreover, for the rocker arm type undercarriage, in order to meet the requirements of different strokes of the buffer, frequent replacement and installation of a plurality of loading points of the loading device are inevitable, and the test progress is influenced.
At present, a loading device and a method for a part of variable stroke tests of landing gears are only suitable for strut type landing gears. For the strut type landing gear, the change of the compression amount of the buffer does not affect the position of a high stress point, and only causes the moment on the main intersection point to generate linear change, so that the influence of most of the compression amount change on a test result can be eliminated in a mode of balancing additional moment; however, for the rocker arm type landing gear, the change of the compression amount of the buffer not only changes the position of a high stress point (the bearing angle of the rocker arm changes), but also causes the nonlinear change of moment and concentrated force on a main intersection point, and the existing loading device and method cannot truly reflect the bearing condition of a test piece.
Disclosure of Invention
In order to solve at least one of the technical problems, the application provides a loading device and a multi-strut landing gear variable stroke replacement-free loading system.
In a first aspect, the present application discloses a loading device, comprising:
the rocker arm comprises a rocker arm body, one end of the rocker arm body is a strut connecting part, the other end of the rocker arm body is bilaterally symmetrically provided with two hub mounting shafts perpendicular to the rocker arm body, and the top of the rocker arm body is provided with a buffer connecting part;
the top of each hub simulation piece is provided with a double-lug structure, a mounting hole penetrates through the double-lug structure, and the bottom of each hub simulation piece is provided with a braking point loading lug and a side loading lug;
two are platelike three-way joints, every three-way joint middle part is opened and is worn to be provided with the mounting hole the peripheral position of mounting hole the three-way joint is last to be provided with two course loading auricles and a vertical loading auricle, wherein, two the three-way joint rotates through its mounting hole respectively and installs the wheel hub of the rocking arm left and right sides is installed epaxially, and is located the left and right sides respectively in the ears structure of wheel hub simulation piece.
According to at least one embodiment of the application, convex fixing parts are symmetrically arranged on the left side and the right side of one end, close to a hub mounting shaft, of the rocker arm body; wherein
And one side of the top of each wheel hub simulation piece, which is close to the rocker arm body, is provided with a fixed lug, the fixed lug is provided with a through hole matched with the fixed part on the corresponding side, and the fixed lug is fixedly sleeved on the fixed part.
According to at least one embodiment of the present application, the mounting hole of the double-lug structure is fixedly sleeved on the hub mounting shaft through a sleeve.
According to at least one embodiment of this application, be platelike on the three-way joint, vertical loading auricle is located the top of mounting hole, two course loading auricles are located the both sides of vertical loading auricle.
According to at least one embodiment of the application, two brake point loading lugs are arranged at the bottom of each hub simulation piece and are arranged at positions corresponding to the arrangement positions of the two heading loading lugs.
According to at least one embodiment of this application, every wheel hub simulation piece bottom with on the hub installation axis vertical plane, be provided with two sets of brake point loading auricles, and every group includes two brake point loading auricles that are parallel to each other, and the loading axis of two sets of brake point loading auricles is located the coplanar, and is predetermined contained angle.
According to at least one embodiment of the present application, the brake point loading lug, the lateral loading lug, the course loading lug, and the vertical loading lug are each provided with a spherical hinge connecting member.
In a second aspect, the present application further discloses a multi-strut landing gear variable stroke replacement-free loading system, comprising:
at least two loading devices arranged side by side, the loading devices being as described in any of the above first aspects;
the connecting rods can connect two course loading lugs or two brake point loading lugs at the relative positions between two adjacent loading devices, wherein the connecting rods are hinged with the course loading lugs or the brake point loading lugs.
The application has at least the following beneficial technical effects:
the application discloses loading device and many spinal branchs post undercarriage become stroke and exempt from to change dress loading system, the difficult problem that many spinal branchs post undercarriage can't realize each pillar loaded alone in narrow and small space has been solved for the first time, not only can eliminate the additional moment that the pillar warp and relative displacement leads to between each pillar and then guarantee experimental loading precision, can also avoid frequent multiple spot changing dress to influence the difficult problem of job schedule, in static strength test and fatigue strength test very much, the multiple spot harmony loading of many spinal branchs post undercarriage all can be realized, and guarantee the loading precision, and improve work efficiency simultaneously, effectively shorten test period.
Drawings
FIG. 1 is a front view of a loading device of the present application;
FIG. 2 is a left side view of the loading device of the present application;
FIG. 3 is a cross-sectional view B-B of FIG. 1;
FIG. 4 is a schematic structural view of one of the connection states of the preferred embodiment of the variable stroke, non-reloading and loading system of the multi-strut landing gear of the present application;
FIG. 5 is a schematic structural view of another connection state of a preferred embodiment of the multi-strut landing gear variable stroke reloading-free loading system of the present application;
FIG. 6 is a schematic view of a rocker arm landing gear (left side in the figure) and a strut landing gear (right side in the figure);
FIG. 7 is a schematic representation of the wheel grounding point positions of rocker arm landing gear (left side in the figure) and strut landing gear (right side in the figure);
FIG. 8 is a schematic view of the loading between the struts;
FIG. 9 is a schematic view of a landing gear in one embodiment.
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the drawings in the embodiments of the present application. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are a subset of the embodiments in the present application and not all embodiments in the present application. The embodiments described below with reference to the drawings are exemplary and intended to be used for explaining the present application and should not be construed as limiting the present application. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present application. Embodiments of the present application will be described in detail below with reference to the accompanying drawings.
In the description of the present application, it is to be understood that the terms "middle", "left", "right", "horizontal", "top", "bottom", and the like, indicate orientations and positional relationships based on those shown in the drawings, are only used for convenience in describing the present application and simplifying the description, and do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore, should not be taken as limiting the scope of the present application.
The loading device and the multi-strut landing gear variable stroke replacement-free loading system of the present application are further described in detail below with reference to fig. 1-9.
In a first aspect, as shown in fig. 1-3, the application discloses a loading device that may include a rocker arm 1, a hub simulator 2, and a three-way joint 3.
The rocker arm 1 can adopt a rocker arm structure of a landing gear which is known at present; specifically, the rocker arm 1 includes a rocker arm body 11 having a cylindrical shape, and one end (left end in fig. 1) of the rocker arm body 11 is a pillar connecting portion 12 for being hinged to a pillar; two hub mounting shafts 13 perpendicular to the rocker arm body 11 are arranged at the other end (the right end in fig. 1) of the rocker arm body 11 in bilateral symmetry; in addition, the top of the rocker arm body 11 is provided with a damper connecting portion 14 for being hinged with a damper. Further, at one end of the rocker arm body 11 close to the hub mounting shaft 13, protruding fixing portions 15 are symmetrically arranged on the left side and the right side, and the fixing portions 15 are used for being connected with a brake shaft.
The number of the wheel hub simulation parts 2 (also called false wheel hubs) is two; the top of each wheel hub simulation part 2 is provided with a double-lug structure 21, a U-shaped open slot is formed in the middle of the double-lug structure 21, and mounting holes are formed in the double-lug structure 21 in a penetrating mode (two lugs are simultaneously penetrated), so that the two wheel hub simulation parts 2 are fixedly arranged on the wheel hub mounting shafts 13 on the left side and the right side of the rocker arm 1 through the mounting holes in the double-lug structure 21 respectively. In addition, in order to make the connection structure more stable, the mounting hole of the preferred double-lug structure 21 is fixedly sleeved on the hub mounting shaft 13 through the sleeve 4. Further, the bottom of each hub simulator 2 is provided with a braking point loading tab 22 and a side loading tab 23.
The three-way joints 3 are plate-shaped, and the number of the three-way joints is two; a mounting hole is formed in the middle of each three-way joint 3 in a penetrating manner, two heading loading lugs 31 and a vertical loading lug 32 are arranged on the three-way joint 3 at the peripheral position of the mounting hole, wherein the two three-way joints 3 are respectively rotatably mounted on the hub mounting shafts 13 at the left side and the right side of the rocker arm 1 through the mounting holes and are respectively located in the two-lug structures 21 of the hub simulation pieces 2 at the left side and the right side, namely in the U-shaped open grooves of the two-lug structures 21.
In this embodiment, on the plate-shaped three-way joint 3, the vertical loading lug 32 is located at the top of the mounting hole, and the two heading loading lugs 31 are located at two sides (left and right sides in fig. 1) of the vertical loading lug 32.
Similarly, the number and the arrangement positions of the braking point loading lugs 22 and the side loading lugs 23 on the hub simulating member 2 can be also set appropriately according to the test requirements; in this embodiment, it is preferable that the bottom of each hub simulator 2 is provided with two braking point loading tabs 22, which are arranged at positions corresponding to the positions of the two heading loading tabs 31, i.e., a left-right arrangement in fig. 1. Further, preferably, two sets of braking point loading lugs 22 are arranged on a plane perpendicular to the axis of the hub mounting shaft 13 at the bottom of each hub simulation member 2, each set includes two braking point loading lugs 22 parallel to each other, and the loading axes of the two sets of braking point loading lugs 22 are located on the same plane and form a predetermined included angle.
Further, in the loading device of the present application, a fixing lug 24 is further fixedly disposed on one side of the top of each hub simulation piece 2 close to the rocker arm body 11, a through hole matched with the fixing portion 15 on the corresponding side is formed in the fixing lug 24, and the fixing lug is fixedly sleeved on the fixing portion 15 through the through hole.
Furthermore, in the hub simulation part 2 and the three-way joint 3, the brake point loading lug 22, the lateral loading lug 23, the course loading lug 31 and the vertical loading lug 32 are all provided with spherical hinge connecting pieces, that is, the spherical hinge connecting pieces are connected with other corresponding parts in a spherical hinge manner, so that the rotational freedom degree is favorably released.
In a second aspect, as shown in fig. 4 and 5, the application further discloses a multi-strut landing gear stroke-changing-free loading system, which may include a loading device and a connecting rod 5.
The loading devices include at least two loading devices, the specific number of the loading devices can be set appropriately according to the test object, and the at least two loading devices are arranged in a side-by-side mode as shown in fig. 4 and 5.
The connecting rods 5 can be a plurality of suitable rod-shaped structural members, the number of the connecting rods is multiple, and each connecting rod 5 can connect two course loading lugs 31 or two brake point loading lugs 22 at the relative positions between two adjacent loading devices so as to adapt to different test requirements; wherein, the connecting rod 5 is hinged with the course loading lug 31 or the braking point loading lug 22.
To sum up, the loading device and many spinal branchs post undercarriage become stroke and exempt from to change outfit loading system of this application have solved many spinal branchs post undercarriage and can't realize the loaded difficult problem alone of each pillar in narrow and small space for the first time, not only can eliminate the additional moment that the relative displacement leads to between pillar deformation and each pillar and then guarantee experimental loading precision, can also avoid frequent multiple spot to change outfit the difficult problem that influences the job schedule, in static strength test and fatigue strength are experimental very much, the multiple spot harmony loading of many spinal branchs post undercarriage all can be realized, and guarantee the loading precision, improve work efficiency simultaneously, effectively shorten test period.
Further, the design steps and design concept of the loading device and the multi-strut undercarriage variable-stroke replacement-free loading system are as follows:
step one, parameterizing the position of the wheel grounding point.
As shown in fig. 6 and 7, the landing gear load points include wheel center point O and wheel ground point a.
1) For rocker arm landing gear, the parameters determining the position of the wheel ground point A are the wheel radius R and the rocker arm angleWherein the wheel radius R can be obtained according to the specification of CCAR25, and the turning angleThe solution process of (2) is as follows:
when the buffer is compressed to delta S, the grounding point of the wheel is changed from A to A', and the rocker arm rotates by an angleThe relationship with Δ S is:
2) for strut landing gear, the parameter for determining the wheel contact patch position is only the wheel radius R, and can be determined according to the specifications of CCAR 25.
When the bumper is compressed to Δ S, the structural inclination of the strut does not change, so the wheel ground point a does not change.
And step two, differential loading is adopted, so that the problems that the space among a plurality of pillars is narrow and independent loading on a single pillar cannot be realized are solved.
Taking a rocker arm type undercarriage with a large number of loading point parameters as an example, because the undercarriage is an open structure, the problem of narrow space between every two support columns is mainly reflected in the course loading, namely the independent loading of the course loads of every support column cannot be realized.
The invention realizes the requirement of unidirectional stretching and loading among all struts in a differential loading mode through the design of a group of wheel center loading points and a group of wheel grounding loading points. As shown in fig. 8, the 1# bidirectional actuator applies a heading load Fx1 to the wheel center point of the 1 st strut, and applies a heading load-Fx 1 to the 2 nd strut, so that the 2# bidirectional actuator applies a heading load Fx1+ Fx2 to the 2 nd strut to ensure that the heading total load borne by the wheel center point is the actual load Σ F ═ Fx1+ Fx2-Fx1 ═ Fx 2. By analogy, the reverse heading load applied to the center point of the n-th strut wheel isThe applied heading load should beThe reverse directional load applied to the wheel ground point should beThe applied heading load should be
And step three, solving the additional moment caused by the relative displacement between the struts.
Firstly, releasing rotational freedom of each loading point through a mounting bearing so as to eliminate additional moment generated by relative displacement among struts to the loading points; secondly, the loading devices of the course and the vertical loading points can rotate around the wheel shaft, so that the vertical and course load action lines can pass through the center of the wheel under any buffer compression amount, and the influence of loading deformation is eliminated; finally, in order to prevent the loading device of the wheel grounding loading point from rotating around the wheel shaft, the loading device needs to be connected with a brake shaft to restrict the rotational degree of freedom.
According to the CCAR25, the braking load corresponds to the stopping compression amount only, so the positions of the braking load loading points correspond to one group of parameters only, and the positions of the side load loading points correspond to multiple groups of parameters. When the compression amount of the buffer changes, the loading device does not need to be replaced, the lateral loading point and the loading equipment only need to be reconnected, and the connection points of the rest points and the loading equipment do not need to be disassembled.
Finally, the loading device and the variable stroke non-reloading loading system of the multi-strut landing gear of the present application will be further described by taking the specific test steps of a certain type of machine as an example, wherein the landing gear of the certain type of machine is schematically illustrated in fig. 9.
Step one, determining position parameters of each strut grounding loading point.
The test conditions of a certain type of machine are shown in the following table 1:
TABLE 1 test conditions and compression
For the multi-support undercarriage, the structures of all the supports are completely consistent, so that the position parameters of the wheel grounding point of one support are determined. Wherein, each initial parameter is shown in the following table 2:
TABLE 2 initial parameters of wheel grounding point position
Further, the wheel-contact-point position parameters of a single strut are shown in table 3:
in the loading state 1, as shown in fig. 4, the vertical loading point is selected as point J1 in the figure, and the heading load point is selected as point J2 in the figure. When transitioning to the loaded state 2, as shown in FIG. 4, its vertical load point is selected as point J1, its heading load point is selected as point J2, and its lateral load point is selected as point J3 (i.e., the right one of the two sets of brake point loading tabs 22). When transitioning to the loaded state 3, as shown in FIG. 5, its vertical load point is selected as point J1, its heading load point is selected as point J2, its lateral load point is selected as point J4 (i.e., the left of the two sets of brake point loading tabs 22) and its brake load point is selected as point J5. That is to say, through the loading device and the multi-strut undercarriage variable stroke replacement-free loading system, when switching is carried out among various loading states, components such as the hub simulation part 2 and the three-way joint 3 do not need to be replaced, the required loading conditions can be met, the working efficiency is improved, and the test period is effectively shortened.
And step two, designing a loading device according to the position parameters given in the table 3, and realizing differential loading among the struts.
As shown in fig. 1, a spherical hinge is arranged in each loading lug hole to release the rotational freedom; the three-way joint can rotate around the wheel shaft, and the degree of freedom of the three-way joint along the axial direction of the wheel shaft is limited by the wheel hub (namely, the wheel hub simulation piece 2) of the false wheel. The dummy wheel hub is limited in each direction by a tab (i.e., the fixing tab 24) connected to the brake shaft, the hub mounting shaft 13 and the sleeve 4. The amount of tire compression is ensured by the position of the side loading tabs 23 and the brake loading tabs 22.
The differential loading structure between the struts realized by the application is shown in the figure. The loading poses correspond one-to-one to the parametric quantities given in table 3.
The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (8)
1. A loading device, comprising:
the rocker arm (1), the rocker arm (1) comprises a rocker arm body (11), one end of the rocker arm body (11) is a pillar connecting part (12), the other end of the rocker arm body is provided with two hub mounting shafts (13) which are bilaterally symmetrical and perpendicular to the rocker arm body (11), and the top of the rocker arm body (11) is provided with a buffer connecting part (14);
the top of each hub simulation piece (2) is provided with a double-lug structure (21), a mounting hole penetrates through the double-lug structure (21), the bottom of each hub simulation piece (2) is provided with a brake point loading lug (22) and a lateral loading lug (23), and the two hub simulation pieces (2) are fixedly sleeved on hub mounting shafts (13) on the left side and the right side of the rocker arm (1) through the mounting holes in the double-lug structures (21);
two are platelike three-way joints (3), every three-way joint (3) middle part is opened and is worn to be provided with the mounting hole the peripheral position of mounting hole three-way joint (3) are gone up and are provided with two course loading auricles (31) and a vertical loading auricle (32), wherein, two three-way joint (3) rotate through its mounting hole respectively and install on the wheel hub installation axle (13) of rocking arm (1) left and right sides, and be located the left and right sides respectively in the ears structure (21) of wheel hub simulation piece (2).
2. The loading device according to claim 1, wherein a protruding fixing part (15) is symmetrically arranged at the left side and the right side of one end of the rocker arm body (11) close to the hub mounting shaft (13); wherein
A fixing lug (24) is arranged on one side, close to the rocker arm body (11), of the top of each hub simulation piece (2), a through hole matched with the fixing portion (15) on the corresponding side is formed in the fixing lug (24), and the fixing lug is fixedly sleeved on the fixing portion (15).
3. The loading device according to claim 2, wherein the mounting hole of the double-lug structure (21) is fixedly sleeved on the hub mounting shaft (13) through a sleeve (4).
4. The loading device according to claim 1, characterized in that on the three-way joint (3) in the form of a plate, a vertical loading tab (32) is located at the top of the mounting hole, two heading loading tabs (31) being located on either side of the vertical loading tab (32).
5. The loading device according to claim 4, characterized in that the bottom of each hub simulator (2) is provided with two braking point loading lugs (22) which are arranged in positions corresponding to the arrangement positions of the two heading loading lugs (31).
6. The loading device according to claim 5, characterized in that two sets of brake point loading lugs (22) are arranged on a plane perpendicular to the axis of the hub mounting shaft (13) at the bottom of each hub simulator (2), each set comprises two brake point loading lugs (22) parallel to each other, and the loading axes of the two sets of brake point loading lugs (22) are located on the same plane and form a predetermined included angle.
7. The loading device according to claim 1, wherein the braking point loading tab (22), the lateral loading tab (23), the course loading tab (31) and the vertical loading tab (32) are provided with spherical hinge connections therein.
8. A multi-strut landing gear variable stroke replacement-free loading system is characterized by comprising:
at least two loading devices arranged side by side, wherein the loading devices adopt the loading device as claimed in any one of claims 1 to 7;
the connecting rods (5) can connect two course loading lugs (31) or two brake point loading lugs (22) at the relative positions between two adjacent loading devices, wherein the connecting rods (5) are hinged with the course loading lugs (31) or the brake point loading lugs (22).
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| CN201910919177.4A CN110589022B (en) | 2019-09-26 | 2019-09-26 | Loading device and multi-support undercarriage variable stroke replacement-free loading system |
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| CN201910919177.4A CN110589022B (en) | 2019-09-26 | 2019-09-26 | Loading device and multi-support undercarriage variable stroke replacement-free loading system |
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| CN111452994A (en) * | 2020-04-22 | 2020-07-28 | 中国飞机强度研究所 | Aircraft nose landing gear supporting device |
| CN111977019A (en) * | 2020-07-06 | 2020-11-24 | 西安飞机工业（集团）有限责任公司 | Aircraft landing gear test loading device and test method |
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| CN113212795A (en) * | 2021-06-04 | 2021-08-06 | 中国飞机强度研究所 | Loading false wheel for undercarriage strength test |
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Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111452994A (en) * | 2020-04-22 | 2020-07-28 | 中国飞机强度研究所 | Aircraft nose landing gear supporting device |
| CN111452994B (en) * | 2020-04-22 | 2023-03-24 | 中国飞机强度研究所 | Aircraft nose landing gear supporting device |
| CN111977019A (en) * | 2020-07-06 | 2020-11-24 | 西安飞机工业（集团）有限责任公司 | Aircraft landing gear test loading device and test method |
| CN111977019B (en) * | 2020-07-06 | 2022-07-12 | 西安飞机工业（集团）有限责任公司 | Aircraft landing gear test loading device and test method |
| CN112373725A (en) * | 2020-12-12 | 2021-02-19 | 江西洪都航空工业集团有限责任公司 | Be used for undercarriage multi-angle loaded device |
| CN113212795A (en) * | 2021-06-04 | 2021-08-06 | 中国飞机强度研究所 | Loading false wheel for undercarriage strength test |
| CN113212795B (en) * | 2021-06-04 | 2024-04-09 | 中国飞机强度研究所 | Landing gear strength test loading false wheel |
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