CN219192567U - Simulation aircraft nose landing gear test device - Google Patents
Simulation aircraft nose landing gear test device Download PDFInfo
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- CN219192567U CN219192567U CN202223181366.2U CN202223181366U CN219192567U CN 219192567 U CN219192567 U CN 219192567U CN 202223181366 U CN202223181366 U CN 202223181366U CN 219192567 U CN219192567 U CN 219192567U
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- mounting
- landing gear
- nose landing
- aircraft nose
- support mechanism
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation
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Abstract
The utility model provides a simulated aircraft nose landing gear test device, which relates to the technical field of test load vehicles, and comprises a mounting support mechanism and a real aircraft nose landing gear, wherein the mounting support mechanism is provided with a mounting hole, a threaded fastener penetrates through the mounting hole so as to enable the mounting support mechanism to be detachably connected with the test load vehicle, the mounting support mechanism is provided with a mounting structure, and the real aircraft nose landing gear is detachably arranged on the mounting structure; the utility model adopts the real aircraft nose landing gear, can effectively ensure the simulation effect, and can replace the corresponding real aircraft nose landing gear according to the specific model of the aircraft to be tested in the actual use process by the installation supporting mechanism with the installation holes and the installation structure, thereby being suitable for different aircraft models and having wide application range.
Description
Technical Field
The utility model relates to the technical field of load testing vehicles, in particular to a test device for simulating a nose landing gear of an airplane.
Background
The aircraft tractor is a guarantee device for towing an aircraft on the airport ground, can be used for moving large aircraft parts or aircraft in the aircraft manufacturing process, and generally comprises a rod type tractor and a rodless type tractor, wherein the rodless type tractor is of a wheel-holding type structure, and does not need to use a traction rod for traction operation, so that the need of the aircraft on the traction rod is eliminated, the labor intensity of staff is relieved, the working efficiency of aircraft traction is greatly improved, and meanwhile, the risk hidden danger when the tractor is in butt joint with the traction rod can be effectively avoided, so that the aircraft tractor is widely used. Since a wheel-holding type rodless tractor usually directly contacts the nose landing gear of an aircraft when the aircraft is towed, the reliability and the safety of the wheel-holding type rodless tractor are important.
The existing test load car that has appeared to embracing wheeled rodless tractor, it generally includes the bearing platform, be provided with the driver's cabin on the bearing platform, power control system, hydraulic control system and electrical control system, the bearing platform upper end is equipped with the counter weight assembly, the lower extreme is provided with the support wheelset, the front end is provided with nose wheel device, nose wheel device is including simulation undercarriage, simulation undercarriage is usually as an organic whole with bearing platform welded fastening, can't realize changing, current test load car can only simulate single aircraft model, application scope is narrower, it is troublesome to use, and is with high costs.
Disclosure of Invention
The utility model aims to provide a test device for simulating an aircraft nose landing gear, which is used for solving the technical problems that the existing test load vehicle adopting an integral structure nose landing gear in the prior art is only suitable for an aircraft with a corresponding model and has a narrow application range; the preferred technical scheme of the technical schemes provided by the utility model has a plurality of technical effects; details are set forth below.
In order to achieve the above purpose, the present utility model provides the following technical solutions:
the utility model provides a simulated aircraft nose landing gear test device, which comprises an installation supporting mechanism and a real aircraft nose landing gear, wherein: the mounting support mechanism is provided with a mounting hole, and a threaded fastener penetrates through the mounting hole so that the mounting support mechanism is detachably connected with the test load vehicle; the mounting support mechanism is provided with a mounting structure, and the nose landing gear of the real aircraft is detachably arranged on the mounting structure.
Preferably, the mounting support mechanism comprises a mounting plate, and the mounting hole is formed in the mounting plate.
Preferably, the mounting support mechanism comprises a mounting bracket, and the mounting bracket is arranged on one side of the bottom of the mounting plate; the mounting structure is disposed on the mounting plate and the mounting bracket.
Preferably, the mounting structure comprises two first mounting seats, the two first mounting seats are arranged on the other side of the bottom of the mounting plate, and the support arm of the nose landing gear of the real aircraft is mounted on the two first mounting seats.
Preferably, a first pin hole is formed in the first mounting seat, and the support arm is mounted on the first mounting seat through a first pin shaft.
Preferably, the mounting structure comprises a second mount provided on the underside of the mounting bracket, the drag bar of the real aircraft nose landing gear being mounted to the second mount.
Preferably, the second mounting seat comprises two ear plates which are oppositely arranged, and a second pin hole is formed in the ear plates in a penetrating manner; the end of the resistance rod is positioned between the two lug plates and is mounted on the lug plates through a second pin shaft.
Preferably, the second mount comprises a fixed plate, wherein: the fixing plate is provided with a first connecting hole, a second connecting hole is formed in the mounting bracket at a position corresponding to the first connecting hole, and a threaded fastener penetrates through the first connecting hole and the second connecting hole so as to mount the fixing plate to the bottom side of the mounting bracket; the lug plate is arranged at the bottom side of the fixed plate.
Preferably, the second mounting seat is integrally provided with the mounting bracket.
Preferably, the mounting bracket is provided with a weight reducing groove.
The test device for simulating the nose landing gear of the aircraft has at least the following beneficial effects:
the test load vehicle comprises a mounting support mechanism and a real aircraft nose landing gear, wherein the mounting support mechanism is used for mounting the real aircraft nose landing gear and the test load vehicle, and the real aircraft nose landing gear is adopted to ensure the simulation effect.
The mounting support mechanism is provided with mounting holes, the mounting support mechanism and the test load vehicle can be detachably mounted through threaded fasteners, the mounting support mechanism is provided with a mounting structure, the real aircraft nose landing gear and the mounting support mechanism can be detachably mounted, and the mounting support mechanism adopts a double detachable structure, so that the real aircraft nose landing gear can be conveniently replaced.
The utility model adopts the real aircraft nose landing gear, can effectively ensure the simulation effect, and can replace the corresponding real aircraft nose landing gear according to the specific model of the aircraft to be tested in the actual use process by the installation supporting mechanism with the installation holes and the installation structure, thereby being suitable for different aircraft models and having wide application range.
Drawings
In order to more clearly illustrate the embodiments of the utility model or the technical solutions in the prior art, the drawings that are required in the embodiments or the description of the prior art will be briefly described, it being obvious that the drawings in the following description are only some embodiments of the utility model, and that other drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.
FIG. 1 is a schematic diagram of the structure of the present utility model;
FIG. 2 is a schematic top view of the present utility model;
FIG. 3 is a schematic front view of the present utility model;
FIG. 4 is a schematic side view of the present utility model;
fig. 5 is an enlarged view of the portion a of the present utility model.
Reference numerals
1. Installing a supporting mechanism; 11. a mounting plate; 111. a mounting hole; 12. a mounting structure; 121. a first mount; 122. a second mounting base; 1221. a fixing plate; 1222. ear plates; 1223. a first connection hole; 13. a mounting bracket; 131. a second connection hole; 132. a weight reduction groove; 2. a real aircraft nose landing gear; 21. a resistance rod; 22. a support arm; 3. a first pin; 4. and a second pin.
Detailed Description
In order to make the objects, technical solutions and advantages of the present utility model more apparent, the technical solutions of the present utility model will be described in detail below. It will be apparent that the described embodiments are only some, but not all, embodiments of the utility model. All other embodiments, based on the examples herein, which are within the scope of the utility model as defined by the claims, will be within the scope of the utility model as defined by the claims.
Example 1:
the utility model provides a simulated aircraft nose landing gear test device, which is shown by referring to fig. 1 and comprises a mounting support mechanism 1 and a real aircraft nose landing gear 2.
The mounting support mechanism 1 is provided with a plurality of mounting holes 111, and the test load vehicle is provided with fixing holes corresponding to the mounting holes 111.
The mounting support mechanism 1 is provided with a mounting structure 12, the mounting structure 12 being used for detachable mounting of the nose landing gear 2 of a real aircraft.
In use, a user selects the real aircraft nose landing gear 2 corresponding to the aircraft nose landing gear according to the specific aircraft model to be simulated, the aircraft nose landing gear is mounted on the mounting structure 12, and the mounting support mechanism 1 is mounted on the test load vehicle by penetrating the mounting holes 111 and the fixing holes through threaded fasteners.
The utility model adopts the real aircraft nose landing gear 2, can effectively ensure the simulation effect, and can replace the corresponding real aircraft nose landing gear 2 according to the actual aircraft model to be simulated by the installation supporting mechanism 1 with the installation hole 111 and the installation structure 12, thereby enabling one test load vehicle to be suitable for various different aircraft models, having wide application range, convenient operation and effectively saving cost.
Example 2:
example 2 is based on example 1:
as shown in fig. 1 and 2, the mounting support mechanism 1 comprises a mounting plate 11, mounting holes 111 are formed in the mounting plate 11, and when the mounting plate 11 is mounted, the mounting plate is attached to a test load car, the mounting is firm, and the stress is uniform.
As an alternative embodiment, as shown in fig. 3, the mounting support mechanism 1 includes a mounting bracket 13, and the mounting bracket 13 is fixedly disposed at one side of the bottom of the mounting plate 11.
The mounting structure 12 is provided on the mounting plate 11 and the mounting bracket 13.
The mounting structure 12 is adapted to the particular aircraft model, and is capable of effectively simulating the mounting attitude of the real aircraft nose landing gear 2.
As an alternative embodiment, as shown in fig. 3 and 4, the mounting structure 12 includes the first mounting seats 121, the number of the first mounting seats 121 is two, the two first mounting seats 121 are disposed at the other side of the bottom of the mounting plate 11, and the two first mounting seats 121 are symmetrically disposed.
The support arm 22 of the real aircraft nose landing gear 2 is mounted to two first mounts 121, the support arm 22 being firmly mounted.
As an alternative embodiment, the first mounting seat 121 is provided with a first pin hole, the support arm 22 is mounted on the first mounting seat 121 through the first pin shaft 3, and a pin shaft mounting structure is adopted, so that the mounting posture of the support arm 22 is effectively simulated in accordance with the mounting structure of the nose landing gear of the aircraft.
As an alternative embodiment, as shown in fig. 5, the mounting structure 12 includes a second mounting seat 122, the second mounting seat 122 is disposed on the bottom side of the mounting bracket 13, and the drag link 21 of the nose landing gear 2 of the real aircraft is mounted to the second mounting seat 122, and the drag link 21 is firmly mounted.
As an alternative embodiment, the second mounting seat 122 includes two ear plates 1222 disposed opposite to each other, the ear plates 1222 are provided with second pin holes therethrough, and the end of the resistance rod 21 is located between the two ear plates 1222 and is mounted to the ear plates 1222 through the second pin shaft 4.
Because the nose landing gear of the aircraft is not completely vertically arranged in actual installation, and has a certain inclination angle relative to the aircraft, the second mounting seat 122 is arranged on the mounting bracket 13, and the mounting posture corresponding to the mounting posture is matched with the mounting posture of the simulation support arm 22, so that the stress condition of the nose landing gear of the aircraft when the nose landing gear is subjected to the wheel-holding type aircraft tractor can be simulated to the greatest extent.
As an alternative embodiment, the second mounting seat 122 includes a fixing plate 1221, two ear plates 1222 are vertically disposed at a middle position of a bottom side of the fixing plate 1221, and are integrally disposed with the fixing plate 1221, first connection holes 1223 are disposed on the fixing plate 1221 and located on outer sides of the two ear plates 1222, and second connection holes 131 are disposed on the mounting bracket 13 corresponding to the first connection holes 1223.
When the second mounting seat 122 is mounted, the screw fastener passes through the first and second connection holes 1223 and 131, thereby mounting the fixing plate 1221 to the bottom side of the mounting bracket 13.
As an alternative embodiment, as shown in fig. 5, the mounting bracket 13 is provided with a weight-reducing groove 132.
The weight reduction groove 132 can play a role in weight reduction under the premise of ensuring the structural strength of the mounting bracket 13, and is lighter.
The installing support 13 is including connecting gradually three riser and being located the bottom plate of riser bottom, and the second connecting hole 131 sets up on the bottom plate, three all be provided with on the riser and subtract heavy groove 132.
Example 3
Example 3 differs from example 2 in that:
the second mount 122 is integrally provided with the mounting bracket 13.
The mounting plate 11 and the mounting bracket 13 of the utility model form various structures according to different shapes and specifications, are suitable for different real aircraft nose landing gears 2, and can be used for selecting to independently replace the real aircraft nose landing gear 2 or integrally replace the mounting support mechanism 1 and the real aircraft nose landing gear 2 according to the actual model of the aircraft in the replacement process, thereby further expanding the application range.
In the description of the present application, it should be understood that the terms "upper," "lower," "inner," "outer," "top," "bottom," and the like indicate an orientation or a positional relationship based on that shown in the drawings, and are merely for convenience of description and simplicity of description, and do not indicate or imply that the devices or elements referred to must have a specific orientation, be configured and operated in a specific orientation, and thus should not be construed as limiting the present application.
Furthermore, the terms "first," "second," and the like, are used for descriptive purposes only and are not to be construed as indicating or implying a relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defining "a first" or "a second" may explicitly or implicitly include at least one such feature. In the description of the present application, the meaning of "a plurality", "a number" or "a plurality" is at least two, such as two, three, etc., unless explicitly defined otherwise.
In this application, unless specifically stated and limited otherwise, the terms "mounted," "connected," "secured," and the like are to be construed broadly, and may be, for example, fixedly connected, detachably connected, or integrally formed; either directly or indirectly, through intermediaries, or both, may be in communication with each other or in interaction with each other, unless expressly defined otherwise. The specific meaning of the terms in this application will be understood by those of ordinary skill in the art as the case may be.
The foregoing is merely illustrative of the present utility model, and the present utility model is not limited thereto, and any person skilled in the art will readily recognize that variations or substitutions are within the scope of the present utility model. Therefore, the protection scope of the present utility model shall be subject to the protection scope of the claims.
Claims (10)
1. An aircraft nose landing gear simulation test device, comprising a mounting support mechanism and a real aircraft nose landing gear, wherein:
the mounting support mechanism is provided with a mounting hole, and a threaded fastener penetrates through the mounting hole so that the mounting support mechanism is detachably connected with the test load vehicle;
the mounting support mechanism is provided with a mounting structure, and the nose landing gear of the real aircraft is detachably arranged on the mounting structure.
2. A simulated aircraft nose landing gear testing device as claimed in claim 1, wherein said mounting support mechanism comprises a mounting plate, said mounting holes being provided in said mounting plate.
3. The simulated aircraft nose landing gear test device of claim 2, wherein said mounting support mechanism comprises a mounting bracket disposed on one side of the bottom of said mounting plate;
the mounting structure is disposed on the mounting plate and the mounting bracket.
4. A simulated aircraft nose landing gear testing device as claimed in claim 3, wherein said mounting structure comprises two first mounting seats, two of said first mounting seats being provided on the other side of the bottom of said mounting plate, and said support arm of said real aircraft nose landing gear being mounted to both of said first mounting seats.
5. The simulated aircraft nose landing gear testing device of claim 4, wherein said first mounting base is provided with a first pin aperture, said support arm being mounted to said first mounting base by a first pin.
6. A simulated aircraft nose landing gear testing device as claimed in claim 3, wherein said mounting structure comprises a second mount provided on an underside of said mounting bracket, a drag lever of said real aircraft nose landing gear being mounted to said second mount.
7. The simulated aircraft nose landing gear testing device of claim 6, wherein said second mount comprises two oppositely disposed ear plates having second pin holes therethrough;
the end of the resistance rod is positioned between the two lug plates and is mounted on the lug plates through a second pin shaft.
8. The simulated aircraft nose landing gear testing device of claim 7, wherein said second mount comprises a fixed plate, wherein:
the fixing plate is provided with a first connecting hole, a second connecting hole is formed in the mounting bracket at a position corresponding to the first connecting hole, and a threaded fastener penetrates through the first connecting hole and the second connecting hole so as to mount the fixing plate to the bottom side of the mounting bracket;
the lug plate is arranged at the bottom side of the fixed plate.
9. The simulated aircraft nose landing gear testing device of claim 7, wherein said second mount is integrally provided with said mounting bracket.
10. A simulated aircraft nose landing gear testing device as claimed in claim 3, wherein said mounting bracket is provided with a weight-reducing slot.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202223181366.2U CN219192567U (en) | 2022-11-28 | 2022-11-28 | Simulation aircraft nose landing gear test device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202223181366.2U CN219192567U (en) | 2022-11-28 | 2022-11-28 | Simulation aircraft nose landing gear test device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN219192567U true CN219192567U (en) | 2023-06-16 |
Family
ID=86706739
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202223181366.2U Active CN219192567U (en) | 2022-11-28 | 2022-11-28 | Simulation aircraft nose landing gear test device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN219192567U (en) |
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2022
- 2022-11-28 CN CN202223181366.2U patent/CN219192567U/en active Active
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