CN112373725A - Be used for undercarriage multi-angle loaded device - Google Patents
Be used for undercarriage multi-angle loaded device Download PDFInfo
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- CN112373725A CN112373725A CN202011452500.0A CN202011452500A CN112373725A CN 112373725 A CN112373725 A CN 112373725A CN 202011452500 A CN202011452500 A CN 202011452500A CN 112373725 A CN112373725 A CN 112373725A
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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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Abstract
The invention discloses a device for multi-angle loading of an undercarriage, which comprises an axle fixing part, a movable loading plate and a fixed loading plate, wherein an opening is formed in the middle of the movable loading plate, the axle fixing part penetrates through the opening to be connected with the movable loading plate, and the movable loading plate freely rotates around the axle fixing part through the opening; the fixed loading plate comprises a first plate and a second plate, the first plate and the second plate are fixed on the wheel axle fixing part, a gap is reserved between the first plate and the second plate, the movable loading plate is fixed in the gap, and the fixed loading plate limits the movable loading plate at the position of a wheel center corresponding to the wheel axle fixing part; the movable loading plate is provided with a wheel center loading hole, and the fixed loading plate is provided with a touch point loading hole. A device for undercarriage multi-angle loading in this application realizes undercarriage fatigue test's variable stroke loading, at two experimental state transform processes, and the automatic adjustment is loaded to corresponding loading position to the testpieces.
Description
Technical Field
The invention relates to the technical field of fatigue tests of aircraft landing gears, in particular to a device and a measuring method for multi-angle loading of landing gears.
Background
In a fatigue test of a main landing gear of an airplane, a test load consists of four loads of Px, Py, Fx and Fz, wherein Px and Py are the wheel center loads of the landing gear, Fx and Fz are the contact point loads of tires of the landing gear, and the distance between the contact point and the wheel center is R. The test load spectrum of the main landing gear comprises twelve spectrum types, each spectrum type is formed by mixing four loads of Px, Py, Fx and Fz, and meanwhile, the compression stroke of a buffer of the main landing gear is continuously changed between 18mm and 80 mm. The load of the fatigue test of the main landing gear is applied by designing a loading dummy wheel, designing a corresponding loading hole on the loading dummy wheel, and applying the load to the main landing gear by connecting a corresponding loading device to the loading hole.
In the static test of the landing gear, the compression stroke of the buffer is a certain fixed value, the loading positions in all states can be directly and sequentially designed in the loading dummy wheel when the loading dummy wheel is designed, and when the static test is carried out, loading equipment is connected with the corresponding loading holes according to the compression stroke state of the corresponding buffer, so that a test piece can be loaded. The design method of the loading dummy wheel is not feasible in the fatigue test with variable stroke, and cannot be applied to freely and alternatively loading in two or more test states. In order to realize variable stroke loading of a fatigue test of a certain aircraft main landing gear, a loading fake wheel suitable for multi-angle position changing needs to be designed, and in the two state changing processes of the test, the loading fake wheel is automatically adjusted to a corresponding loading position to load a test piece, so that the test requirement is met.
Disclosure of Invention
The invention aims to solve the problems and provides a device for multi-angle loading of an undercarriage, which is automatically adjusted to a corresponding loading position to load a test piece in two state transformation processes of a test so as to meet the test requirements.
In order to solve the technical problem, the invention provides a device for multi-angle loading of an undercarriage, which comprises an axle fixing part, a movable loading plate and a fixed loading plate, wherein an opening is formed in the middle of the movable loading plate, the axle fixing part penetrates through the opening to be connected with the movable loading plate, and the movable loading plate freely rotates around the axle fixing part through the opening; the fixed loading plate comprises a first plate and a second plate, the first plate and the second plate are both fixed on the wheel axle fixing part, a gap is reserved between the first plate and the second plate, the movable loading plate is fixed in the gap, and the fixed loading plate limits the movable loading plate at the position of a wheel center corresponding to the wheel axle fixing part; the movable loading plate is provided with wheel center loading holes for loading wheel center loads Px and Py, and the fixed loading plate is provided with touch point loading holes for loading touch point loads Fx and Fz.
In an optional embodiment of the present application, the axle fixing component includes a shaft sleeve and an undercarriage connecting component, the shaft sleeve is matched with the axle of the undercarriage, and the cross section of the shaft sleeve is circular; the wheel shaft penetrates through the opening to be connected with the movable loading plate, and the movable loading plate freely rotates around the wheel shaft through the opening.
In an optional embodiment of the present application, the opening is in clearance fit with the bushing, so that the movable loading plate freely rotates on the bushing.
In an optional embodiment of the present application, the movable loading plate is a three-jaw structure, the opening is disposed in the middle of the three-jaw structure, and three jaws of the three-jaw structure are respectively provided with a wheel center loading hole, two of the wheel center loading holes are used for loading the wheel center load Px, and a third loading hole is used for loading the wheel center load Py.
In an optional embodiment of the present application, a first touchdown point loading hole and a second touchdown point loading hole are provided on the fixed loading plate, and the distance from the first touchdown point loading hole to the wheel center is the distance from the touchdown point of the undercarriage to the wheel center; each touchdown point loading hole corresponds to a respective compression stroke of the buffer.
In an optional embodiment of the present application, the first plate and the second plate are respectively provided with a fixing hole, the shaft sleeve passes through the fixing hole, and the first plate and the second plate are welded and fixed to the axle fixing member.
In an optional embodiment of the present application, the fixed loading plate further includes a fixed connection block, and the first plate and the second plate are welded into a whole by the fixed connection block.
In an optional embodiment of the present application, the first plate and the second plate are provided with fixing plate reinforcing ribs.
In an alternative embodiment of the present application, a gap is left between the first and second plates and the movable load plate, and the movable load plate is free to rotate on the axle fixing member.
The device for multi-angle loading of the landing gear comprises an axle fixing part, a movable loading plate and a fixed loading plate, wherein an opening is formed in the middle of the movable loading plate, the axle fixing part penetrates through the opening to be connected with the movable loading plate, and the movable loading plate freely rotates around the axle fixing part through the opening; the fixed loading plate comprises a first plate and a second plate, the first plate and the second plate are both fixed on the wheel axle fixing part, a gap is reserved between the first plate and the second plate, the movable loading plate is fixed in the gap, and the fixed loading plate limits the movable loading plate at the position of a wheel center corresponding to the wheel axle fixing part; the movable loading plate is provided with wheel center loading holes for loading wheel center loads Px and Py, and the fixed loading plate is provided with touch point loading holes for loading touch point loads Fx and Fz.
According to the device for multi-angle loading of the undercarriage, the movable loading plate and the fixed loading plate are designed, so that the wheel center load and the touch point load of the undercarriage are separated, the wheel center load loading hole is designed in the movable loading plate, the position of the movable loading plate is limited at the wheel center, the movable loading plate can freely rotate on the shaft sleeve, and the device can be suitable for the loading state of the undercarriage under any compression stroke, and the variable stroke loading of the undercarriage fatigue test is realized; the touch point loading points are designed on the fixed loading plate, the fixed loading plate and the wheel axle fixing part are welded together, the torque of the landing gear and the bending moment generated by the side load due to the touch point load can be transmitted, meanwhile, the number of the touch point loading holes and the included angle theta can be associated with the test requirements and are in one-to-one correspondence with the test, the variable stroke loading of the landing gear fatigue test is realized, and the difficult problem of the variable stroke loading of the landing gear fatigue test, particularly the rocker arm type landing gear, is solved.
Further, the fixed loading plate is provided with a fixed plate reinforcing rib for enhancing the bending resistance of the fixed loading plate when the side load of the landing gear is applied.
Drawings
In order to more clearly illustrate the embodiments or technical solutions of the present invention, the drawings used in the description of the embodiments or the prior art will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and it is obvious for those skilled in the art that other drawings can be obtained based on these drawings without creative efforts.
FIG. 1 is a schematic structural diagram of a multi-angle landing gear loading device according to an embodiment of the present application.
FIG. 2 is a front view of the distribution of loading holes of a multi-angle loading device of a landing gear according to an embodiment of the present application.
FIG. 3 is a left side view of the distribution of loading holes of a multi-angle loading device of a landing gear according to an embodiment of the present application.
Fig. 4 is a schematic structural diagram of an axle fixing part according to an embodiment of the present application.
FIG. 5 is a plan view of a movable load plate in accordance with an embodiment of the present application.
FIG. 6 is a plan view of a fixed load plate in an embodiment of the present application.
FIG. 7 is a graphical illustration of touchdown point loading hole versus landing gear compressive travel.
Detailed Description
In the fatigue test of the main landing gear of the airplane, the test load consists of Px, Py, Fx and Fz, wherein Px and Py are the wheel center loads of the landing gear, Fx and Fz are the contact point loads of the tires of the landing gear, and the contact point is away from the wheel center by R. The bumper compression stroke of the main landing gear is constantly changed between 18mm and 80 mm. The load of the fatigue test of the main landing gear is applied by designing a loading dummy wheel, designing a corresponding loading hole on the loading dummy wheel, and applying the load to the main landing gear by connecting a corresponding loading device to the loading hole.
In the static test of the landing gear, the compression stroke of the buffer is a certain fixed value, the loading positions in all states can be directly and sequentially designed in the loading dummy wheel when the loading dummy wheel is designed, and when the static test is carried out, loading equipment is connected with the corresponding loading holes according to the compression stroke state of the corresponding buffer, so that a test piece can be loaded. The design method of the loading dummy wheel is not feasible in the fatigue test with variable stroke, and cannot be applied to freely and alternatively loading in two or more test states.
Therefore, the technical scheme is provided, wherein the technical scheme is suitable for the variable-stroke fatigue test, can be freely and changeably loaded in two or more test states, and can be automatically adjusted to the corresponding loading positions to load the test piece.
In order that those skilled in the art will better understand the disclosure, the invention will be described in further detail with reference to the accompanying drawings and specific embodiments. It is to be understood that the described embodiments are merely exemplary of the invention, and not restrictive of the full scope of the invention. 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 invention.
The components of embodiments of the present invention generally described and illustrated in the figures herein may be arranged and designed in a wide variety of different configurations.
Thus, the following detailed description of the embodiments of the present invention, presented in the figures, is not intended to limit the scope of the invention, as claimed, but is merely representative of selected embodiments of the invention. 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 invention.
It should be noted that: like reference numbers and letters refer to like items in the following figures, and thus, once an item is defined in one figure, it need not be further defined and explained in subsequent figures.
Fig. 1 to 6 show a schematic structural diagram of a multi-angle loading device of an undercarriage according to an embodiment of the present application, and fig. 2 shows a front view of loading hole distribution of the multi-angle loading device of the undercarriage according to an embodiment of the present application. FIG. 3 is a left side view of the distribution of loading holes of a multi-angle loading device of a landing gear according to an embodiment of the present application. Fig. 4 is a schematic structural diagram of an axle fixing part according to an embodiment of the present application. FIG. 5 is a plan view of a movable load plate in accordance with an embodiment of the present application. FIG. 6 is a plan view of a fixed load plate in an embodiment of the present application. The device for multi-angle loading of the landing gear comprises: the wheel shaft fixing part comprises a wheel shaft fixing part 1, a movable loading plate 2 and a fixed loading plate 3, wherein an opening 21 is formed in the middle of the movable loading plate 2, the wheel shaft fixing part 1 penetrates through the opening 21 to be connected with the movable loading plate 2, and the movable loading plate 2 freely rotates around the wheel shaft fixing part 1 through the opening 21; the fixed loading plate 3 comprises a first plate 31 and a second plate 32, the first plate 31 and the second plate 32 are both fixed on the axle fixing part 1, a gap is left between the first plate 31 and the second plate 32, the movable loading plate 2 is fixed in the gap, and the fixed loading plate 3 limits the movable loading plate 2 at a position of a wheel center corresponding to the axle fixing part 1; the movable loading plate 2 is provided with wheel center loading holes for loading wheel center loads Px and Py, and the fixed loading plate 3 is provided with touchdown point loading holes for loading touchdown point loads Fx and Fz.
The airplane wheel is an important component of a landing gear and carries impact load when the airplane is taken off from the shoulder to take off at high speed and run and land. The wheel center in this application is the wheel center of wheel in the aircraft undercarriage.
In the landing gear fatigue test, different compression strokes of the buffer and the position included angle theta of the touch point are in one-to-one correspondence, and when the landing gear fatigue test is in the conversion process under different compression strokes, the loading fake wheel of the landing gear must meet the test loading requirement. As shown in fig. 2, the included angles θ 1 and θ 2 in fig. 2 correspond to the landing gear state conditions of the buffer compression strokes a and b, respectively, that is, the buffer compression strokes correspond to the position included angles θ of the touchdown points one by one. The loading device is designed in combination with the above requirements, and is designed into three parts, namely, an axle fixing part 1, a movable loading plate 2 and a fixed loading plate 3. The movable loading plate 2 is sleeved on the wheel axle fixing part 1, can freely rotate, and can be suitable for the loading state of the landing gear under any compression stroke, so that the variable stroke loading of the landing gear fatigue test is realized; the fixed loading plate 3 is designed into two plates with the same specific shape, the movable loading plate 2 is limited at the wheel center of the wheel axle fixing part 1, the movable loading plate 2 can freely rotate, meanwhile, contact point loading holes are designed in the fixed loading plate 3, the number of the contact point loading holes and the included angle theta can be related to the test requirement and are in one-to-one correspondence with the test, and the variable stroke loading of the fatigue test of the undercarriage is realized.
It should be noted that the number of the contact point loading holes on the fixed loading plate 3 is at least two, the number of the contact point loading holes is related to the compression stroke of the buffer, the compression stroke of the buffer is a variable stroke, and if the compression stroke is 2 strokes, 2 contact point loading holes are arranged; if 3 strokes are used, 3 touchdown point loading holes are set, and the like. Furthermore, the included angle theta is the included angle between the connecting line of the grounding point and the wheel center and the brake key. Through the design of the number of the contact point loading holes and the included angle theta, the requirement corresponding to the test is met, and the variable stroke loading of the landing gear fatigue test is realized.
The structure of the axle fixing part 1 is shown in fig. 4, the axle fixing part 1 comprises a shaft sleeve 11 and an undercarriage connecting part 12, the shaft sleeve 11 is matched with an axle of an undercarriage, and the section of the shaft sleeve is circular; the wheel shaft 11 passes through the opening 21 to be connected with the movable loading plate 2, and the movable loading plate 2 freely rotates around the wheel shaft 11. The landing gear connecting component 12 and the landing gear are connected into a whole, and it needs to be explained that the connection form and structure of the landing gear connecting component 12 and the landing gear are not specifically limited, and preferably, the connection form is a connection key and a key groove or a flange plate, and the like.
The structure of the movable loading plate is shown in fig. 5, the movable loading plate 2 is a three-jaw structure, an opening 21 connected with the axle fixing part 1 is designed in the center of the movable loading plate, and the opening 21 is matched with the shaft sleeve 11 of the axle fixing part 1, so that the movable loading plate 2 can freely rotate on the shaft sleeve 11 of the axle fixing part 1, and the movable loading plate can be applied to the loading state of the landing gear under any compression stroke, and the variable stroke loading of the landing gear fatigue test is realized. And loading holes 6, 7 and 8 are respectively designed in the three-jaw direction of the movable loading plate 2, wherein the loading holes 6 and 7 are used for applying a wheel center load Px, and the loading holes 8 are used for applying a wheel center load Py.
It should be noted that the fitting relationship between the opening 21 and the sleeve 11 is not particularly limited, but is preferably a clearance fit, so that the movable loading plate 2 can freely rotate on the sleeve 11 of the wheel axle fixing member 1.
The structure of the fixed loading plate is shown in fig. 6, and the fixed loading plate 3 is used for limiting the movable loading plate 2 at the wheel center of the wheel axle fixing part 1 and keeping the movable loading plate 2 to rotate freely around the shaft sleeve 11. Therefore, the fixed loading plate 3 is designed into two identical plates with specific shapes, including a first plate 31 and a second plate 32, the first plate 31 and the second plate 32 sandwich the movable loading plate 2 and limit the movable loading plate at the wheel center position corresponding to the wheel axle fixing part 1, and a gap is left between the movable loading plate 2, so that the movable loading plate 2 can freely rotate on the shaft sleeve 11. The fixed loading plate 3 further comprises a fixed connecting block 4, and the first plate 31 and the second plate 32 are welded into a whole through the fixed connecting block 4.
A first touchdown point loading hole 9 and a second touchdown point loading hole 10 are formed in the fixed loading plate 3, and the distance between the first touchdown point loading hole 9 and the second touchdown point loading hole 10 and the wheel center is the distance R between the touchdown point of the undercarriage and the wheel center; each touchdown point loading hole corresponds to a respective compression stroke of the buffer. The included angles theta 1 and theta 2 correspond to the states of the buffer compression strokes a and b, respectively. As shown in fig. 2, an angle θ 2 between a line connecting the first touchdown point loading hole 9 and the wheel center and the brake key, that is, an angle θ 2 between the line segment PO and the SO, corresponds to the buffer compression stroke a; an included angle theta 2 between a connecting line of the second touchdown point loading hole 10 and the wheel center and the brake key, namely an included angle theta 1 between the line segments TO and SO corresponds TO the buffer compression stroke b.
As can be seen from fig. 7, the rocker arm of the landing gear can rotate around the fulcrum a, the fixed point B of the buffer is constrained, and the compression stroke L of the buffer corresponds to the position included angle θ of the touchdown point one by one; the number of the contact point loading holes on the fixed loading plate 3 is at least two, the number of the contact point loading holes is related to the compression stroke of the buffer, the compression stroke L of the buffer is a variable stroke, namely L is a variable, and if L is 2 strokes, 2 contact point loading holes are arranged; if L is 3 strokes, then 3 touchdown point loading holes are provided, and so on. Furthermore, the included angle theta is the included angle between the connecting line of the grounding point and the wheel center and the brake key. Through the design of the number of the contact point loading holes and the included angle theta, the requirement corresponding to the test is met, and the variable stroke loading of the landing gear fatigue test is realized. The first plate 31 and the second plate 32 are provided with fixing plate reinforcing ribs 5, and the fixing plate reinforcing ribs 5 are used for reinforcing the bending resistance of the fixing loading plate 3 when the side load of the landing gear is applied, and the size of the fixing loading plate is related to the contact point side load of the landing gear.
According to the multi-angle loading device for the undercarriage, the movable loading plate 2 and the fixed loading plate 3 are designed, so that the wheel center load and the touchdown point load of the undercarriage are separated, the wheel center load loading hole is designed in the movable loading plate 2, the position of the movable loading plate is limited at the wheel center, the movable loading plate freely rotates on the shaft sleeve 11, and the multi-angle loading device is suitable for the loading state of the undercarriage under any compression stroke, and the variable stroke loading of the undercarriage fatigue test is realized. The touchdown point loading holes are designed on the fixed loading plate 3, the fixed loading plate 3 and the wheel axle fixing part 1 are welded together, the torque of the landing gear and the bending moment generated by the side load due to the touchdown point load can be transmitted, meanwhile, the number and the included angle theta of the touchdown point loading holes can be related to the test requirements and are in one-to-one correspondence with the test, the variable stroke loading of the landing gear fatigue test is realized, and the difficult problem of the variable stroke loading of the landing gear fatigue test, particularly the rocker arm type landing gear, is solved.
It should be noted that, in this document, the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc. indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings or the orientations or positional relationships that the products of the present invention usually place when in use, and are only used for convenience of describing the present invention and simplifying the description, but do not indicate or imply that the devices or elements referred to must have specific orientations, be constructed in specific orientations, and operate, and thus, should not be construed as limiting the present invention. Furthermore, the terms "first," "second," "third," and the like are used solely to distinguish one from another and are not to be construed as indicating or implying relative importance.
Furthermore, the terms "horizontal", "vertical" and the like do not imply that the components are required to be absolutely horizontal or pendant, but rather may be slightly inclined. For example, "horizontal" merely means that the direction is more horizontal than "vertical" and does not mean that the structure must be perfectly horizontal, but may be slightly inclined.
It should also be noted that, unless expressly stated or limited otherwise, the terms "disposed," "mounted," "connected," and "connected" are intended to be construed broadly, as they may be fixedly connected, detachably connected, or integrally connected, for example; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meanings of the above terms in the present invention can be understood in specific cases to those skilled in the art.
Relational terms such as first and second, and the like may be used solely to distinguish one entity or action from another entity or action without necessarily requiring or implying any actual such relationship or order between such entities or actions. Furthermore, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include elements inherent in the list. Without further limitation, an element defined by the phrase "comprising an … …" does not exclude the presence of other identical elements in a process, method, article, or apparatus that comprises the element. In addition, parts of the above technical solutions provided in the embodiments of the present application, which are consistent with the implementation principles of corresponding technical solutions in the prior art, are not described in detail so as to avoid redundant description.
The principles and embodiments of the present invention are explained herein using specific examples, which are presented only to assist in understanding the method and its core concepts. It should be noted that, for those skilled in the art, it is possible to make various improvements and modifications to the present invention without departing from the principle of the present invention, and those improvements and modifications also fall within the scope of the claims of the present invention.
Claims (9)
1. The device for multi-angle loading of the landing gear is characterized by comprising an axle fixing part, a movable loading plate and a fixed loading plate, wherein an opening is formed in the middle of the movable loading plate, the axle fixing part penetrates through the opening to be connected with the movable loading plate, and the movable loading plate freely rotates around the axle fixing part through the opening; the fixed loading plate comprises a first plate and a second plate, the first plate and the second plate are both fixed on the wheel axle fixing part, a gap is reserved between the first plate and the second plate, the movable loading plate is fixed in the gap, and the fixed loading plate limits the movable loading plate at the position of a wheel center corresponding to the wheel axle fixing part; the movable loading plate is provided with wheel center loading holes for loading wheel center loads Px and Py, and the fixed loading plate is provided with touch point loading holes for loading touch point loads Fx and Fz.
2. The device for multi-angle loading of landing gear according to claim 1, wherein the axle fixing member comprises a bushing and a landing gear attachment member, the bushing cooperating with the axle of the landing gear; the wheel shaft penetrates through the opening to be connected with the movable loading plate, and the movable loading plate freely rotates around the wheel shaft through the opening.
3. A device for multi-angle loading of a landing gear according to claim 2, wherein the aperture is a clearance fit with the boss such that the mobile load plate is free to rotate on the boss.
4. A device for multi-angle loading of landing gear according to claim 1, wherein said movable loading plate is a three-jaw structure, said opening is provided in the middle of the three-jaw structure, and each of the three jaws of said three-jaw structure is provided with a wheel center loading hole, two of said loading holes are used for loading the wheel center load Px, and the third loading hole is used for loading the wheel center load Py.
5. The device for multi-angle loading of the landing gear according to claim 1, wherein the fixed loading plate is provided with a first touchdown point loading hole and a second touchdown point loading hole, and the distance between the first touchdown point loading hole and the second touchdown point loading hole and the wheel center is the distance between the touchdown point of the landing gear and the wheel center; each touchdown point loading hole corresponds to a respective compression stroke of the buffer.
6. The device for multi-angle loading of the landing gear according to claim 2, wherein the first plate and the second plate are respectively provided with fixing holes, the shaft sleeve penetrates through the fixing holes, and the first plate and the second plate are welded and fixed on the axle fixing component.
7. The device for multi-angle loading of landing gears according to claim 6, wherein the fixed loading plate further comprises a fixed connection block, and the first plate and the second plate are welded into a whole through the fixed connection block.
8. The device for multi-angle loading of a landing gear according to claim 1, wherein the first plate and the second plate are provided with fixing plate reinforcing ribs.
9. A device for multi-angle loading of landing gear according to claim 1, wherein the first and second plates are spaced from the mobile load plate, the mobile load plate being free to rotate on the axle securing member.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011452500.0A CN112373725A (en) | 2020-12-12 | 2020-12-12 | Be used for undercarriage multi-angle loaded device |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011452500.0A CN112373725A (en) | 2020-12-12 | 2020-12-12 | Be used for undercarriage multi-angle loaded device |
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| Publication Number | Publication Date |
|---|---|
| CN112373725A true CN112373725A (en) | 2021-02-19 |
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| CN202011452500.0A Pending CN112373725A (en) | 2020-12-12 | 2020-12-12 | Be used for undercarriage multi-angle loaded device |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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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| 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 |
| CN111409853A (en) * | 2020-04-12 | 2020-07-14 | 中国飞机强度研究所 | Structure is applyed to undercarriage intensity test tire ground point load |
| 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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- 2020-12-12 CN CN202011452500.0A patent/CN112373725A/en active Pending
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN107264835A (en) * | 2017-07-13 | 2017-10-20 | 江西洪都航空工业集团有限责任公司 | A kind of gear test load charger |
| 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 |
| CN111409853A (en) * | 2020-04-12 | 2020-07-14 | 中国飞机强度研究所 | Structure is applyed to undercarriage intensity test tire ground point load |
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| Publication number | Priority date | Publication date | Assignee | Title |
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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 |
| 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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Application publication date: 20210219 |
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