CN215865764U - Aircraft landing gear strut loading device - Google Patents
Aircraft landing gear strut loading device Download PDFInfo
- Publication number
- CN215865764U CN215865764U CN202121360442.9U CN202121360442U CN215865764U CN 215865764 U CN215865764 U CN 215865764U CN 202121360442 U CN202121360442 U CN 202121360442U CN 215865764 U CN215865764 U CN 215865764U
- Authority
- CN
- China
- Prior art keywords
- landing gear
- aircraft landing
- gear support
- clamping block
- loading device
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Images
Landscapes
- Investigating Strength Of Materials By Application Of Mechanical Stress (AREA)
Abstract
The application belongs to the technical field of the aircraft structural strength test, concretely relates to undercarriage pillar loading device, include: the two aircraft landing gear strut clamping blocks are oppositely arranged; an arc-shaped groove is formed in the wall surface of each aircraft landing gear support clamping block, which faces to the other aircraft landing gear support clamping block; the two arc-shaped grooves can be attached to the outer surface of the landing gear strut of the airplane; one end of each pulling plate is connected with one aircraft landing gear support clamping block, and the other end of each pulling plate is connected with the other aircraft landing gear support clamping block, so that the two aircraft landing gear support clamping blocks can clamp the aircraft landing gear support; and one end of the pull rod is connected to the wall surface of one aircraft landing gear support clamping block, which is back to the other aircraft landing gear support clamping block, and the other end of the pull rod is connected with an actuating device so as to apply a pulling load or a pressing load to the aircraft landing gear support.
Description
Technical Field
The application belongs to the technical field of aircraft structural strength tests, and particularly relates to an aircraft landing gear strut loading device.
Background
In the aircraft structural strength test, the situation of loading the landing gear strut is involved, based on the existing landing gear strut loading device, the loading to the load can be only carried out to the landing gear strut in the test, the alternate loading to the load and the load can not be carried out to the landing gear strut, the true situation of the landing gear stress can not be accurately simulated, and the accuracy of the test result is influenced.
The present application has been made in view of the above-mentioned technical drawbacks.
It should be noted that the above background disclosure is only for the purpose of assisting understanding of the inventive concept and technical solutions of the present invention, and does not necessarily belong to the prior art of the present patent application, and the above background disclosure should not be used for evaluating the novelty and inventive step of the present application without explicit evidence to suggest that the above content is already disclosed at the filing date of the present application.
Disclosure of Invention
It is an object of the present application to provide an aircraft landing gear strut loading device which overcomes or mitigates at least one aspect of the technical disadvantages known to exist.
The technical scheme of the application is as follows:
an aircraft landing gear strut loading device comprising:
the two aircraft landing gear strut clamping blocks are oppositely arranged; an arc-shaped groove is formed in the wall surface of each aircraft landing gear support clamping block, which faces to the other aircraft landing gear support clamping block; the two arc-shaped grooves can be attached to the outer surface of the landing gear strut of the airplane;
one end of each pulling plate is connected with one aircraft landing gear support clamping block, and the other end of each pulling plate is connected with the other aircraft landing gear support clamping block, so that the two aircraft landing gear support clamping blocks can clamp the aircraft landing gear support;
and one end of the pull rod is connected to the wall surface of one aircraft landing gear support clamping block, which is back to the other aircraft landing gear support clamping block, and the other end of the pull rod is connected with an actuating device so as to apply a pulling load or a pressing load to the aircraft landing gear support.
According to at least one embodiment of the present application, in the above-described aircraft landing gear strut loading device, both ends of each pulling plate are detachably connected to the corresponding aircraft landing gear strut clamping blocks.
According to at least one embodiment of the application, in the aircraft landing gear strut loading device, two ends of each pulling plate are connected with the corresponding aircraft landing gear strut clamping block through bolts.
According to at least one embodiment of the present application, in the above-described aircraft landing gear strut loading device, a dynamometer is connected between the pull rod and the actuator.
According to at least one embodiment of the present application, the above-mentioned aircraft landing gear strut loading device further includes:
two rubber pads, every rubber pad corresponds and sets up in an arc groove.
According to at least one embodiment of the present application, in the aircraft landing gear strut loading device described above, each rubber pad is bonded in a corresponding arcuate slot.
Drawings
FIG. 1 is a schematic structural diagram of an aircraft landing gear strut loading device provided in an embodiment of the present application;
FIG. 2 is a side view of FIG. 1;
wherein:
1-an aircraft landing gear strut clamp block; 2-pulling a plate; 3-a pull rod; 4-rubber pad.
For the purpose of better illustrating the embodiments, certain features of the drawings may be omitted, enlarged or reduced, and do not represent the size of an actual product; further, the drawings are for illustrative purposes, and terms describing positional relationships are limited to illustrative illustrations only and are not to be construed as limiting the patent.
Detailed Description
In order to make the technical solutions and advantages of the present application clearer, the technical solutions of the present application will be further clearly and completely described in the following detailed description with reference to the accompanying drawings, and it should be understood that the specific embodiments described herein are only some of the embodiments of the present application, and are only used for explaining the present application, but not limiting the present application. It should be noted that, for convenience of description, only the parts related to the present application are shown in the drawings, other related parts may refer to general designs, and the embodiments and technical features in the embodiments in the present application may be combined with each other to obtain a new embodiment without conflict.
In addition, unless otherwise defined, technical or scientific terms used in the description of the present application shall have the ordinary meaning as understood by one of ordinary skill in the art to which the present application belongs. The terms "upper", "lower", "left", "right", "center", "vertical", "horizontal", "inner", "outer", and the like used in the description of the present application, which indicate orientations, are used only to indicate relative directions or positional relationships, and do not imply that the devices or elements must have a specific orientation, be constructed and operated in a specific orientation, and when the absolute position of the object to be described is changed, the relative positional relationships may be changed accordingly, and thus, should not be construed as limiting the present application. The use of "first," "second," "third," and the like in the description of the present application is for descriptive purposes only to distinguish between different components and is not to be construed as indicating or implying relative importance. The use of the terms "a," "an," or "the" and similar referents in the context of describing the application is not to be construed as an absolute limitation on the number, but rather as the presence of at least one. The word "comprising" or "comprises", and the like, when used in this description, is intended to specify the presence of stated elements or items, but not the exclusion of other elements or items.
Further, it is noted that, unless expressly stated or limited otherwise, the terms "mounted," "connected," and the like are used in the description of the invention in a generic sense, e.g., connected as either a fixed connection or a removable connection or integrally connected; can be mechanically or electrically connected; they may be directly connected or indirectly connected through an intermediate medium, or they may be connected through the inside of two elements, and those skilled in the art can understand their specific meaning in this application according to the specific situation.
The present application is described in further detail below with reference to fig. 1-2.
An aircraft landing gear strut loading device comprising:
the two aircraft landing gear strut clamping blocks 1 are oppositely arranged; an arc-shaped groove is formed in the wall surface of each aircraft landing gear support clamping block 1 facing to the other aircraft landing gear support clamping block 1; the two arc-shaped grooves can be attached to the outer surface of the landing gear strut of the airplane;
one end of each pulling plate 2 is connected with one aircraft landing gear support clamping block 1, and the other end of each pulling plate 2 is connected with the other aircraft landing gear support clamping block 1, so that the two aircraft landing gear support clamping blocks 1 can clamp the aircraft landing gear support;
one end of the pull rod 3 is connected to the wall surface of one aircraft landing gear support clamping block 1, which is opposite to the other aircraft landing gear support clamping block 1, and the other end of the pull rod is connected with an actuating device so as to apply pulling load or pressing load to the aircraft landing gear support.
For the aircraft landing gear strut loading device disclosed in the above embodiment, as can be understood by those skilled in the art, the arc-shaped grooves of the two aircraft landing gear strut clamping blocks 1 connected by the two pulling plates 2 clamp the aircraft landing gear strut, and the actuation device alternately loads the aircraft landing gear strut in the pulling direction and the pressing direction through the pull rod 3 connected with one aircraft landing gear strut clamping block 1, so that the real situation of the stress of the aircraft landing gear can be accurately simulated, and the accuracy of the test result is ensured.
In some alternative embodiments, in the above-described aircraft landing gear strut loading device, both ends of each pulling plate 2 are detachably connected to the corresponding aircraft landing gear strut clamping block 1.
For the aircraft landing gear strut loading device disclosed in the above embodiment, it can be understood by those skilled in the art that two ends of the pulling plate 2 are detachably connected to the corresponding aircraft landing gear strut clamping blocks 1, so that the two aircraft landing gear strut clamping blocks 1 can be conveniently detached from and installed on the aircraft landing gear strut.
In some alternative embodiments, in the above-described aircraft landing gear strut loading device, both ends of each pulling plate 2 are connected with the corresponding aircraft landing gear strut clamping blocks 1 through bolts.
In some alternative embodiments, in the above-described aircraft landing gear strut loading device, a dynamometer is connected between the pull rod 3 and the actuator.
In some optional embodiments, the above aircraft landing gear strut loading device further comprises:
two rubber pads 4, every rubber pad 4 corresponds the setting in an arc wall to this avoids aircraft landing gear pillar grip block 1 and aircraft landing gear pillar direct contact, causes the damage to the aircraft landing gear pillar, and can increase the friction between aircraft landing gear pillar grip block 1 and the aircraft landing gear pillar, takes place the phenomenon of skidding when avoiding carrying out the load loading to the aircraft landing gear pillar.
In some alternative embodiments, in the above-described aircraft landing gear strut loading device, each rubber pad 4 is bonded in the corresponding arc-shaped groove to prevent the rubber pad 4 from falling off from the corresponding arc-shaped groove.
The embodiments are described in a progressive manner in the specification, each embodiment focuses on differences from other embodiments, and the same and similar parts among the embodiments are referred to each other.
Having thus described the present application in connection with the preferred embodiments illustrated in the accompanying drawings, it will be understood by those skilled in the art that the scope of the present application is not limited to those specific embodiments, and that equivalent modifications or substitutions of related technical features may be made by those skilled in the art without departing from the principle of the present application, and those modifications or substitutions will fall within the scope of the present application.
Claims (6)
1. An aircraft landing gear strut loading device, comprising:
the two aircraft landing gear strut clamping blocks (1) are oppositely arranged; an arc-shaped groove is formed in the wall surface of each aircraft landing gear support clamping block (1) facing to the other aircraft landing gear support clamping block (1); the two arc-shaped grooves can be attached to the outer surface of the landing gear strut of the airplane;
two pulling plates (2), one end of each pulling plate (2) is connected with one aircraft landing gear support clamping block (1), and the other end of each pulling plate is connected with the other aircraft landing gear support clamping block (1), so that the two aircraft landing gear support clamping blocks (1) can clamp the aircraft landing gear support;
and one end of the pull rod (3) is connected to the wall surface of one aircraft landing gear support clamping block (1) back to the other aircraft landing gear support clamping block (1), and the other end of the pull rod is connected with an actuating device so as to apply pulling load or pressing load to the aircraft landing gear support.
2. An aircraft landing gear strut loading device according to claim 1,
the two ends of each pulling plate (2) are detachably connected with the corresponding aircraft landing gear strut clamping blocks (1).
3. An aircraft landing gear strut loading device according to claim 2,
and the two ends of each pulling plate (2) are connected with the corresponding aircraft landing gear strut clamping blocks (1) through bolts.
4. An aircraft landing gear strut loading device according to claim 1,
and a dynamometer is connected between the pull rod (3) and the actuating device.
5. An aircraft landing gear strut loading device according to claim 1,
further comprising:
two rubber pads (4), every rubber pad (4) correspond and set up in one the arc wall.
6. An aircraft landing gear strut loading device according to claim 5,
each rubber pad (4) is bonded in the corresponding arc-shaped groove.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202121360442.9U CN215865764U (en) | 2021-06-18 | 2021-06-18 | Aircraft landing gear strut loading device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202121360442.9U CN215865764U (en) | 2021-06-18 | 2021-06-18 | Aircraft landing gear strut loading device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN215865764U true CN215865764U (en) | 2022-02-18 |
Family
ID=80334256
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202121360442.9U Active CN215865764U (en) | 2021-06-18 | 2021-06-18 | Aircraft landing gear strut loading device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN215865764U (en) |
-
2021
- 2021-06-18 CN CN202121360442.9U patent/CN215865764U/en active Active
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN109029811B (en) | Car coupler force test method and calibration tool | |
| CN206891718U (en) | A kind of automobile control arm assembly durability test apparatus | |
| CN104237015B (en) | The device of high speed dynamic compressive test | |
| CN105258929B (en) | A kind of test method of PE rope and cord clip ball switching performance | |
| CN215865764U (en) | Aircraft landing gear strut loading device | |
| CN114509250B (en) | Conventional fatigue and vibration load combined loading device for aviation wallboard | |
| CN207689121U (en) | A kind of axle fatigue test board | |
| CN106314474B (en) | The braking equipment of walking mechanism for suspension type monorail | |
| CN103101555B (en) | Mechanical type hand braking gripping device of railway vehicle steering frame | |
| KR100934766B1 (en) | A testing apparatus for a lightweight bogie frame | |
| KR200494385Y1 (en) | A Test Apparatus Of Leaf Spring For Automotive Available of Convinient Testing | |
| CN104237016B (en) | High speed dynamic compressive test device | |
| CN113119834A (en) | Special trailer of coil of strip transportation that security performance is high | |
| CN114235375B (en) | Unmanned aerial vehicle wing girder intensity test structure | |
| CN205607635U (en) | A device for car front axle leaf spring assembly fatigue test | |
| CN105417304A (en) | Weight measuring method and weight measuring device for lifting body of lift | |
| CN106644685A (en) | Pressure loading device for pressing test | |
| KR102255891B1 (en) | A Test Apparatus Of Leaf Spring For Automotive | |
| KR20130105318A (en) | Lug test apparatus | |
| US3696663A (en) | Force applying apparatus | |
| CN218317394U (en) | Experimental loading structure | |
| CN113772509A (en) | Overload switch detection device for no-load elevator based on hydraulic drive | |
| CN107817120B (en) | A kind of vehicle static strength test device for simulating bogie shock loading | |
| CN204116147U (en) | A kind of device of high speed dynamic compressive test | |
| CN214200653U (en) | Automobile hand brake simulation testing device |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant |