CN108100239B - Double-shaft rotating bearing device with anti-swing function - Google Patents
Double-shaft rotating bearing device with anti-swing function Download PDFInfo
- Publication number
- CN108100239B CN108100239B CN201711240441.9A CN201711240441A CN108100239B CN 108100239 B CN108100239 B CN 108100239B CN 201711240441 A CN201711240441 A CN 201711240441A CN 108100239 B CN108100239 B CN 108100239B
- Authority
- CN
- China
- Prior art keywords
- steel cable
- rotor
- limiting pin
- wheel shaft
- shaft
- 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
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/32—Alighting gear characterised by elements which contact the ground or similar surface
- B64C25/34—Alighting gear characterised by elements which contact the ground or similar surface wheeled type, e.g. multi-wheeled bogies
- B64C25/36—Arrangements or adaptations of wheels, tyres or axles in general
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Pivots And Pivotal Connections (AREA)
Abstract
The invention discloses a double-shaft rotating bearing device with an anti-swing function, which comprises a lining, an outer ring, a roller pin, an inner ring and a wheel shaft, wherein the outer ring is arranged on the periphery of the roller pin; the invention has the advantages of convenient production, good practicability, easy popularization and application and great value.
Description
Technical Field
The invention belongs to the technical field of airplane design, particularly relates to an airplane undercarriage bearing design and an undercarriage anti-swing and anti-vibration device, and particularly relates to a double-shaft rotating bearing device with an anti-swing and anti-vibration function.
Background
The airplane needs to be steered when entering or returning from the runway from the hangar, which requires the nose landing gear of the airplane to have a steering function, and the steering mechanism of the airplane is usually complex and needs to pay a large weight cost, so that the airplane is not cost-effective for small airplanes or unmanned planes. Aircraft landing gear bearings generally can only rotate around a horizontal axis and cannot rotate around a vertical axis, and common universal bearings cannot be used on landing gear wheels. Therefore, in some small-sized airplanes, the front landing gear can be used for eliminating a torsion arm, so that the airplane wheels can rotate around the actuating cylinders, and the steering problem during airplane transfer is solved. The torsion arm is eliminated, and when the speed of the airplane runs and exceeds a critical value, the nose landing gear can generate shimmy, and the structural damage of the landing gear and even the damage of the airplane to people can be caused in serious conditions. The invention designs a novel bearing which can rotate around a horizontal shaft and a vertical shaft, and when the wheel rotates at high speed, the anti-shimmy device can be locked by using centrifugal force to limit the rotation of the wheel of the landing gear around the vertical shaft so as to realize the function of preventing shimmy.
Disclosure of Invention
Object of the Invention
In order to solve the problems that the steering of the airplane is limited due to the installation of a torsion arm, and the shimmy is caused by the cancellation of the torsion arm, the invention provides the shimmy-proof bearing which can freely rotate around a horizontal shaft and a vertical shaft during low-speed running of the airplane and automatically lock and limit the rotation of the vertical shaft during high-speed running of the airplane.
In order to achieve the purpose, the invention adopts the technical scheme that: the utility model provides a biax rotating bearing device with anti-sway function, includes bush, outer lane, kingpin, inner circle, shaft, the outer lane is installed on the kingpin periphery, the kingpin is installed on the inner circle periphery, the inner circle is installed on the shaft periphery, the bush is installed in the shaft hole, the shaft links to each other with the undercarriage pressurized strut, two opposite surfaces of inner wall of inner circle are slick and sly curved surface, and its other two opposite surfaces are the plane, two opposite surfaces in the shaft outside are slick and sly curved surface, and its other two opposite surfaces are the plane, and this structural shape and the inboard structural shape of inner circle are corresponding, be equipped with the draw-in groove on the bush.
Further, the biaxial rotation bearing device with the anti-shimmy function further comprises an anti-shimmy device, wherein the anti-shimmy device comprises a limiting pin, a rotor steel cable, a limiting pin steel cable, a reset spring, a rotor, an undercarriage wheel and a spherical hinge, the undercarriage wheel is installed on the periphery of the outer ring, the rotor is installed in a runner of the undercarriage wheel, one end of the rotor is connected with one end of the rotor steel cable, and the other end of the rotor steel cable penetrates through a clamping groove of the bushing and is connected with one end of the spherical hinge; the other end of the spherical hinge is connected with one end of the limiting pin steel cable, and the other end of the limiting pin steel cable is connected with one end of the limiting pin; the other end of the limiting pin is connected with one end of the return spring, the other end of the return spring is connected with the wheel shaft, and the rotor steel cable and the spherical hinge are arranged in an opening of the wheel shaft along the axis; the limiting pin steel cable, the limiting pin and the reset spring are arranged in the open groove of the wheel shaft.
Further, the outer ring rotates around a horizontal shaft relative to the inner ring, and the inner ring rotates around a vertical shaft relative to the wheel shaft.
Further, the bushing may rotate along with the rotor cable.
Advantageous effects of the invention
The invention has the beneficial effects that: the outer side of the bearing device is a common needle bearing of the landing gear, so that the function of high-speed rotation of the bearing around a horizontal shaft is realized; the two sides of the wheel shaft at the inner side of the bearing are spherical surfaces, and the upper plane and the lower plane realize the function of the bearing rotating around a vertical shaft at low speed, so that the problem of airplane steering is solved; the bearing device utilizes the centrifugal force generated by the rotor when the airplane runs to automatically lock the bearing through the steel cable to limit the rotation of the bearing around a vertical shaft, thereby effectively limiting the shimmy; when the device limits shimmy, the locking force is vertical to the shimmy direction of the airplane wheel, so that the device can be locked by a small force; the rotor steel cable passes through the bush draw-in groove, drives the bush and rotates, can effectually avoid the wearing and tearing of steel cable, and then reduces the emergence of accident. The bearing device is convenient to produce, good in practicability, easy to popularize and apply and high in value.
Drawings
FIG. 1 is an exploded view of the present invention;
FIG. 2 is a schematic view of the assembly structure of the anti-swing lock apparatus of the present invention;
FIG. 3 is a schematic view of the construction of the centrifugal rotor apparatus of the present invention;
FIG. 4 is a schematic view of a spherical hinge structure of the present invention;
FIG. 5 is a schematic diagram of a structure of the bearing device of the present invention before locking;
FIG. 6 is a schematic view of a locked bearing device according to the present invention;
FIG. 7 is a sectional view showing a position structure of a lock front stopper pin of the bearing device of the present invention;
fig. 8 is a sectional view showing a position structure of a lock pin in the bearing device of the present invention.
The wheel comprises a bush 1, a bush 2, an outer ring 3, a needle roller 4, an inner ring 5, a wheel shaft 6, a limit pin 7, a rotor steel cable 8, a limit pin steel cable 9, a return spring 10, a rotor 11, a landing gear wheel 11 and a spherical hinge 12.
Detailed Description
The present invention will be described in further detail with reference to the following examples and the accompanying drawings.
As shown in fig. 1 to 8, the present invention provides a biaxial rotation bearing device with a vibration damping function, including a bushing 1, an outer ring 2, a needle roller 3, an inner ring 4, and a hub 5, wherein the outer ring 2 is mounted on the outer periphery of the needle roller 3, the needle roller 2 is mounted on the outer periphery of the inner ring 4, the inner ring 4 is mounted on the outer periphery of the hub 5, the bushing 1 is mounted in a hole of the hub 5, the hub 5 is connected to an undercarriage actuator, two opposite side surfaces of the inner wall of the inner ring 4 are smooth curved surfaces, the other two opposite side surfaces are flat surfaces, two opposite side surfaces outside the hub 5 are smooth curved surfaces, the other two opposite side surfaces are flat surfaces, the structural shape corresponds to the structural shape of the inner side of the inner ring 4, and the bushing 1 is provided with a slot.
Further, the biaxial rotation bearing device with the anti-shimmy function further comprises an anti-shimmy device, the anti-shimmy device comprises a limit pin 6, a rotor steel cable 7, a limit pin steel cable 8, a reset spring 9, a rotor 10, an undercarriage wheel 11 and a spherical hinge 12, the undercarriage wheel 11 is installed on the periphery of the outer ring 2, the rotor 10 is installed in a sliding groove of the undercarriage wheel 11, one end of the rotor 10 is connected with one end of the rotor steel cable 7, and the other end of the rotor steel cable 7 penetrates through a clamping groove of the bushing 1 to be connected with one end of the spherical hinge 12; the other end of the spherical hinge 12 is connected with one end of the limiting pin steel cable 8, and the other end of the limiting pin steel cable 8 is connected with one end of the limiting pin 6; the other end of the limiting pin 6 is connected with one end of a return spring 9, the other end of the return spring 9 is connected with the wheel shaft 5, and the rotor steel cable 7 and the spherical hinge 12 are arranged in an opening of the wheel shaft 5 along the axis; the limiting pin steel cable 8, the limiting pin 6 and the return spring 9 are arranged in the open groove of the wheel shaft 5.
Further, the outer ring 2 rotates about a horizontal axis relative to the inner ring 4, and the inner ring 4 rotates about a vertical axis relative to the wheel shaft 5.
Further, the bushing 1 can rotate together with the rotor cable 7.
In the shimmy-damping device, the rotor 10 is arranged at the edge of an undercarriage wheel 11 and transmits centrifugal force to the limiting pin 6 through the rotor steel cable 7 and the limiting pin steel cable 8, the limiting pin steel cable 8 can push out the limiting pin 6 when the rotation speed of the undercarriage wheel is high, so that the rotation around a vertical shaft is limited, and the reset spring 9 can pull back the limiting pin 6 when the rotation speed of the undercarriage wheel is low, so that the steering function of the undercarriage wheel is realized.
The invention relates to a double-shaft rotating bearing device with an anti-swing function, wherein an outer ring 2, a needle roller 3 and an inner ring 4 of the device form a high-speed bearing capable of rotating around a horizontal shaft. The inner ring 4 and the wheel shaft 5 of the device form a low-speed bearing capable of rotating around a vertical shaft, the upper surface and the lower surface of the outer side of the wheel shaft 5 are planes which limit the rotation of the inner ring 4 relative to the wheel shaft 5 around the horizontal direction and the heading direction, and the spherical surfaces on the two sides of the outer side of the wheel shaft 5 allow the inner ring 4 to rotate around the vertical shaft relative to the wheel shaft 5.
When the airplane runs on the runway, the wheel rotates at high speed, large centrifugal force is generated on the rotor 10, the centrifugal force is transmitted to the limiting pin 6 through the steel cable, and when the airplane runs at high speed, the centrifugal force is enough to push the limiting pin 6 out to limit the rotation of the bearing around the vertical shaft.
The rotor steel cable 7 can rotate along with the rotor 10, and the steel cable drives the lining 1 to rotate through the clamping groove of the lining 1, so that the abrasion of the steel cable can be effectively avoided, and the occurrence of accidents is reduced. The rotor steel cable 7 and the limit pin steel cable 8 are connected through a spherical hinge 12, so that the limit pin steel cable 8 can not rotate along with the rotor steel cable 7. When the centrifugal force is larger, the limiting pin steel rope 8 can push out the limiting pin 6 to realize locking. When the sliding speed of the airplane is reduced and the centrifugal force is reduced, the reset spring 9 can pull back the limiting pin 6 to realize unlocking.
It should be noted that the specific embodiments are merely representative examples of the present invention, and it is obvious that the technical solution of the present invention is not limited to the above examples, and many variations are possible. Those skilled in the art, having the benefit of this disclosure, and the benefit of this description, will appreciate the scope of the present invention as it is expressly disclosed herein or as it may appear from the written description of such documents.
Claims (3)
1. A double-shaft rotating bearing device with the function of preventing the oscillation comprises a bush (1), an outer ring (2), a roller pin (3), an inner ring (4) and a wheel shaft (5), the outer ring (2) is mounted on the outer periphery of the needle rollers (3), the needle rollers (3) are mounted on the outer periphery of the inner ring (4), the inner ring (4) is arranged on the periphery of the wheel shaft (5), the bushing (1) is arranged in a hole of the wheel shaft (5), the wheel shaft (5) is connected with the undercarriage actuator cylinder, two opposite side surfaces of the inner wall of the inner ring (4) are smooth curved surfaces, the other two opposite side surfaces are planes, the two opposite side surfaces at the outer side of the wheel shaft (5) are smooth curved surfaces, its other two opposite side surfaces are the planes, and this structural shape with the inboard structural shape of inner circle (4) is corresponding, be equipped with draw-in groove, its characterized in that on bush (1): the anti-shimmy landing gear comprises a limiting pin (6), a rotor steel cable (7), a limiting pin steel cable (8), a reset spring (9), a rotor (10), a landing gear wheel (11) and a spherical hinge (12), wherein the landing gear wheel (11) is installed on the periphery of the outer ring (2), the rotor (10) is installed in a sliding groove of the landing gear wheel (11), one end of the rotor (10) is connected with one end of the rotor steel cable (7), and the other end of the rotor steel cable (7) penetrates through a clamping groove of the bushing (1) to be connected with one end of the spherical hinge (12); the other end of the spherical hinge (12) is connected with one end of the limiting pin steel cable (8), and the other end of the limiting pin steel cable (8) is connected with one end of the limiting pin (6); the other end of the limiting pin (6) is connected with one end of a return spring (9), the other end of the return spring (9) is connected with the wheel shaft (5), and the rotor steel cable (7) and the spherical hinge (12) are arranged in an opening of the wheel shaft (5) along the axis; the limiting pin steel cable (8), the limiting pin (6) and the reset spring (9) are arranged in the open groove of the wheel shaft (5).
2. The biaxial rotation bearing device having a wobbling-proof function as claimed in claim 1, wherein: the outer ring (2) rotates around a horizontal shaft relative to the inner ring (4), and the inner ring (4) rotates around a vertical shaft relative to the wheel shaft (5).
3. The biaxial rotation bearing device having a wobbling-proof function as claimed in claim 1, wherein: the bushing (1) can rotate along with the rotor steel cable (7).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711240441.9A CN108100239B (en) | 2017-11-30 | 2017-11-30 | Double-shaft rotating bearing device with anti-swing function |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711240441.9A CN108100239B (en) | 2017-11-30 | 2017-11-30 | Double-shaft rotating bearing device with anti-swing function |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN108100239A CN108100239A (en) | 2018-06-01 |
| CN108100239B true CN108100239B (en) | 2021-03-05 |
Family
ID=62207920
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201711240441.9A Active CN108100239B (en) | 2017-11-30 | 2017-11-30 | Double-shaft rotating bearing device with anti-swing function |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108100239B (en) |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN201747776U (en) * | 2010-08-11 | 2011-02-16 | 福建龙溪轴承(集团)股份有限公司 | Cracking-type radial spherical plain bearing unit |
| CN201800917U (en) * | 2010-09-30 | 2011-04-20 | 湖南山河科技股份有限公司 | Anti-shimmy mechanism of landing wheel |
| CN203169956U (en) * | 2013-01-22 | 2013-09-04 | 赵燕 | Moving device of basketball stand base |
| CN204253612U (en) * | 2014-10-11 | 2015-04-08 | 中国航空工业集团公司西安飞机设计研究所 | A kind of aligning needle roller roller bearing |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6729763B2 (en) * | 2001-11-16 | 2004-05-04 | Kamatics Corporation | Hybrid bearing system |
-
2017
- 2017-11-30 CN CN201711240441.9A patent/CN108100239B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN201747776U (en) * | 2010-08-11 | 2011-02-16 | 福建龙溪轴承(集团)股份有限公司 | Cracking-type radial spherical plain bearing unit |
| CN201800917U (en) * | 2010-09-30 | 2011-04-20 | 湖南山河科技股份有限公司 | Anti-shimmy mechanism of landing wheel |
| CN203169956U (en) * | 2013-01-22 | 2013-09-04 | 赵燕 | Moving device of basketball stand base |
| CN204253612U (en) * | 2014-10-11 | 2015-04-08 | 中国航空工业集团公司西安飞机设计研究所 | A kind of aligning needle roller roller bearing |
Also Published As
| Publication number | Publication date |
|---|---|
| CN108100239A (en) | 2018-06-01 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| EP3038901B1 (en) | Drive system for landing gear | |
| EP2882644B1 (en) | Landing gear drive systems | |
| EP2982603B1 (en) | Landing gear drive system | |
| EP3539864B1 (en) | Auxiliary support system for a flap of an aircraft wing | |
| CN106477040B (en) | A kind of axis is interior to manipulate rotor driver | |
| CN103303472B (en) | Free deflection lag-damping type nose landing gear of small unmanned air vehicle | |
| CN103786882B (en) | The rotor head of rotor craft and manufacture thereof and assemble method | |
| EP0031602A1 (en) | Airplane main landing gear assembly | |
| CN109774922B (en) | Main land playing device of variable grounding point | |
| US10640199B2 (en) | Wheel and gear assembly | |
| CN204775995U (en) | Elevator actuator antihunting control structure | |
| US9346539B2 (en) | Self-orienting aircraft landing gear | |
| CN108082449B (en) | Large aircraft control surface suspension structure | |
| Young | Aircraft landing gears—the past, present and future | |
| CN114030597B (en) | Landing gear cabin door linkage mechanism, landing gear cabin door linkage system and unmanned aerial vehicle | |
| CN106218872A (en) | A kind of turn to shimmy damping device for the all-electric of unmanned plane nose-gear | |
| CN201863861U (en) | Side-rolling resistant torsion rod system for railway vehicle | |
| CN108100239B (en) | Double-shaft rotating bearing device with anti-swing function | |
| CN107140019A (en) | One kind turn to vice president into and its automobile | |
| CN108945400A (en) | A kind of small drone undercarriage locking structure | |
| CN211731795U (en) | Undercarriage uplock structure for aviation emergency | |
| US9802697B2 (en) | Aircraft landing gear | |
| CN112722251B (en) | Multi-stage buffering anti-crosswind skid landing device and working method thereof | |
| US3133717A (en) | Aircraft landing gear | |
| CN204433036U (en) | Without bulge aircraft aileron structure |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |