CN209921605U - Aircraft front wheel rotation stopping device - Google Patents
Aircraft front wheel rotation stopping device Download PDFInfo
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- CN209921605U CN209921605U CN201920498852.6U CN201920498852U CN209921605U CN 209921605 U CN209921605 U CN 209921605U CN 201920498852 U CN201920498852 U CN 201920498852U CN 209921605 U CN209921605 U CN 209921605U
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Abstract
A front wheel rotation stopping device of an airplane comprises a friction plate, a support plate, a guide rod and springs, wherein the outer side of the friction plate is a friction plane, the inner side of the friction plate is provided with a plurality of mutually parallel convex step holes, the guide rod is vertically embedded in the step holes, a flange of the guide rod is in contact with the inner end face of each step hole for limiting, the other end of the guide rod is connected with the support plate through a connecting piece, the support plate is mutually parallel to the friction plate, and each guide rod is sleeved with one spring between the support plate and the friction plate; fixing a connecting plate of the rotation stopping device on a machine body in an aircraft landing gear cabin, wherein the mounting position of the rotation stopping device ensures that when a front wheel of an aircraft is folded in place, the surface of a front wheel tire is pressed at the middle position of a friction plate, and the width symmetric surface of the front wheel tire is superposed with the width symmetric surface of the friction plate; when the front wheel tire of the airplane is folded, the surface of the tire extrudes the friction plate, the friction plate overcomes the resistance of the spring to push the spring to compress, and the compression damping of the spring counteracts the friction plate to provide friction resistance for the front wheel tire, so that the rotating speed of the front wheel tire is stably reduced, and the front wheel tire reaches a static state within a preset time.
Description
Technical Field
The application relates to the design and manufacturing technology of an airplane, in particular to a front wheel rotation stopping device of an airplane.
Background
After the airplane takes off, the front wheel can be retracted into the nose landing gear cabin, under the common condition, the front wheel of the airplane is a driven wheel, a rotation stopping brake mechanism is not arranged on the front wheel, and the continuous rotation of the front wheel in the nose landing gear cabin can cause potential safety hazards to the airplane. The requirement of front wheel rotation stopping has become a necessary requirement of various types of military and civil aircrafts in China. The prior front wheel rotation stopping device in China has two types of rigid rotation stopping and flexible rotation stopping. The existing rigid rotation stopping device provides resistance by using the bending elasticity of a metal sheet, and has the advantages of simple structure, convenience in installation and higher damping efficiency; however, the damping characteristic of the metal sheet is difficult to analyze, the processing and forming difficulty is high, the design precision is not easy to guarantee, and a large amount of test data is required to be provided for correction; and the metal sheet does not have the characteristics of vibration reduction and energy absorption, and cannot absorb vibration energy generated during rotation stopping. The existing flexible rotation stopping device absorbs vibration energy by utilizing the flexible characteristic of a stopping belt, and the rotation stopping is stable; the defects are that the required damping force is larger, the performance requirement on an elastic component for providing damping is higher, and the damping efficiency is low; and the structure is more complicated, the processing and the assembly are difficult, the space requirement is more limited, and the device can only be used under the condition of larger forebay space.
Disclosure of Invention
The application aims to provide a method and a device for stopping rotation of a front wheel of an airplane aiming at the requirements and the defects in the prior art.
The utility model provides an aircraft front wheel device that splines, the device contains friction plate, backup pad, guide arm and spring, the outside of friction plate is the friction plane, and the inboard of friction plate is equipped with a plurality of convex step holes that are parallel to each other, and a plurality of step hole symmetric distribution inlay a guide arm in each step hole, the one end of guide arm is equipped with the flange that corresponds with the step hole, and the guide arm is inlayed perpendicularly in the step hole, and the guide arm flange is spacing with the interior terminal surface contact in the step hole, and the other end of guide arm is connected with the backup pad through the connecting piece, and a plurality of guide arms are parallel to each other to be fixed in the backup pad, and the backup pad is parallel to each other with the friction plate, and between backup pad.
When the anti-rotation device is used, the connecting plate of the anti-rotation device is fixed on a machine body in an aircraft landing gear cabin, the installation position of the anti-rotation device ensures that when a front wheel of an aircraft is folded in place, the surface of a front wheel tire is pressed at the middle position of the friction plate, and the width symmetric surface of the front wheel tire is superposed with the width symmetric surface of the friction plate; when the front wheel tire of the airplane is folded, the surface of the tire extrudes the friction plate, the friction plate overcomes the resistance of the spring to push the spring to compress, and the compression damping of the spring counteracts the friction plate to provide friction resistance for the front wheel tire, so that the rotating speed of the front wheel tire is stably reduced, and the front wheel tire reaches a static state within a preset time.
In the preferred scheme, four parallel convex step holes are formed in the inner side of the friction plate and are symmetrically distributed, a guide rod is embedded in each step hole, and the four guide rods are fixed on the supporting plate in parallel.
The beneficial effect of this application lies in: 1) the device utilizes the damping characteristic of the spring to provide frictional resistance for the front wheel belt when the front wheel belt is rolled up. 2) The device can effectively absorb vibration energy, reduce vibration damage to the body structure caused by the front wheel rotation stopping, enable the front wheel rotation stopping to be stable, and further improve the operation stability of the airplane. 3) The invention has simple structure and composition, the materials of all parts can be selected from conventional materials which are easy to purchase, all parts are designed by using conventional structures and are easy to manufacture, and the processing cost is effectively reduced; and the structure is small in volume and has stronger space adaptability. 4) The elastic damping of the device is provided by the spring, the damping characteristic is simple and easy to analyze, the contact pressure between the tire and the friction plate is consistent with the resistance direction of the spring, the performance requirement on the elastic component is reduced, and the design precision and the damping efficiency are obviously improved.
The present application is described in further detail below with reference to the accompanying drawings of embodiments.
Drawings
Fig. 1 is a schematic view of a front wheel rotation stopping structure of an airplane.
Fig. 2 is a cross-sectional schematic view of a front wheel rotation stopping structure of the airplane.
FIG. 3 is a schematic diagram of a method for stopping rotation of a nose wheel of an aircraft.
The numbering in the figures illustrates: 1 friction plate, 2 support plates, 3 guide rods, 4 springs, 5 bosses, 6 machine bodies, 7 stepped holes, 8 flanges and 9 front wheels.
Detailed Description
Referring to the drawings, the present device utilises the damping characteristics of the spring 4 to provide frictional resistance to the aircraft nose wheel 9 as it is rolled up. The device can effectively absorb vibration energy, reduce vibration damage to the body structure caused by the rotation stopping of the front wheel, improve damping efficiency, reduce the performance requirement on the elastic component and obviously improve design precision.
As shown in fig. 1 and 2, the rotation stopping device of the present application includes friction plate 1, support plate 2, guide rod 3 and spring 4. The outer side of the friction plate is a friction plane, the inner side of the friction plate is provided with four convex step holes 7, each step hole forms a boss 5, the four step holes 7 are symmetrically distributed, and a guide rod 3 is embedded in each step hole 7. One end of each guide rod is provided with a flange 8 corresponding to the step hole 7, the guide rods 3 are vertically embedded in the step holes 7, the flanges 8 of the guide rods are in contact with the inner end faces of the step holes 7 for limiting, the other ends of the guide rods 3 are connected with the supporting plate 2 through connecting pieces, the four guide rods are fixed on the supporting plate 2 in parallel, and the supporting plate 2 is parallel to the friction plate 1. Between the support plate 2 and the friction plate 1, each guide rod 3 is sleeved with a spring 4.
When the anti-rotation device is used, the connecting plate 2 of the anti-rotation device is fixed on the body 5 in the landing gear cabin of the airplane, the installation position of the anti-rotation device ensures that when the front wheel 9 of the airplane is folded in place, the tire surface of the front wheel 9 is pressed at the middle position of the friction plate, and the tire width symmetrical plane of the front wheel 9 is superposed with the width symmetrical plane of the friction plate, as shown in fig. 3.
When the airplane front wheel 9 tire is folded, the surface of the tire extrudes the friction plate 1, the friction plate 1 overcomes the resistance of the spring 4 to push the spring 4 to compress, the compression damping of the spring 4 reacts on the friction plate 1 to provide friction resistance for the front wheel tire, so that the rotating speed of the front wheel tire is stably reduced, and the front wheel tire reaches a static state within a preset time.
The invention has simple structure and composition, the materials of all parts can be selected from conventional materials which are easy to purchase, all parts are designed by using conventional structures and are easy to manufacture, and the processing cost is effectively reduced; and the structure is small in volume and has stronger space adaptability.
The elastic damping of the device is provided by the spring, the damping characteristic is simple and easy to analyze, the spring resistance and the contact pressure direction between the tire and the friction plate are consistent, and the design precision and the damping efficiency are improved. Meanwhile, the damping characteristic of the spring is utilized by the device, the vibration energy generated by the rotation stopping is absorbed, the vibration damage to the body structure caused by the rotation stopping of the front wheel is reduced, the rotation stopping of the front wheel is stable, and the operation stability of the airplane is further improved.
Claims (2)
1. The utility model provides an aircraft nose wheel device that splines, installs on the organism in the aircraft undercarriage cabin, its characterized in that, the device contains friction plate, backup pad, guide arm and spring, the outside of friction plate is the friction plane, and the inboard of friction plate is equipped with a plurality of convex step holes that are parallel to each other, and a plurality of step hole symmetric distribution, the downthehole guide arm of inlaying of each step, the one end of guide arm is equipped with the flange that corresponds with the step hole, and the guide arm is inlayed perpendicularly in the step hole, and the guide arm flange is spacing with the terminal surface contact in the step hole, and the other end of guide arm passes through the connecting piece and is connected with the backup pad, and a plurality of guide arms are parallel to each other fixed in the backup pad, and backup pad and friction plate are parallel to each other.
2. The aircraft nose wheel anti-rotation device of claim 1, wherein the friction plate has four parallel protruding step holes on its inner side, the four step holes are symmetrically distributed, each step hole is embedded with a guide rod, and the four guide rods are parallel fixed on the support plate.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920498852.6U CN209921605U (en) | 2019-04-12 | 2019-04-12 | Aircraft front wheel rotation stopping device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920498852.6U CN209921605U (en) | 2019-04-12 | 2019-04-12 | Aircraft front wheel rotation stopping device |
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| Publication Number | Publication Date |
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| CN209921605U true CN209921605U (en) | 2020-01-10 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201920498852.6U Active CN209921605U (en) | 2019-04-12 | 2019-04-12 | Aircraft front wheel rotation stopping device |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110065625A (en) * | 2019-04-12 | 2019-07-30 | 西安飞机工业（集团）有限责任公司 | A kind of aircraft nose wheel rotation stop method and rotation stop device |
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2019
- 2019-04-12 CN CN201920498852.6U patent/CN209921605U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110065625A (en) * | 2019-04-12 | 2019-07-30 | 西安飞机工业（集团）有限责任公司 | A kind of aircraft nose wheel rotation stop method and rotation stop device |
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