CN110576967A - Undercarriage centering device - Google Patents
Undercarriage centering device Download PDFInfo
- Publication number
- CN110576967A CN110576967A CN201910931892.XA CN201910931892A CN110576967A CN 110576967 A CN110576967 A CN 110576967A CN 201910931892 A CN201910931892 A CN 201910931892A CN 110576967 A CN110576967 A CN 110576967A
- Authority
- CN
- China
- Prior art keywords
- torsion spring
- fixed seat
- arc
- landing gear
- support sleeve
- 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.)
- Pending
Links
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
-
- 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
Abstract
The invention discloses a centering device of an undercarriage, wherein a fixed seat (10) is connected with a rocker arm of the undercarriage, and the outer side of a round hole on the lower end surface is provided with an arc-shaped groove; the lower end of the rotating shaft (20) is connected with a wheel fork of the undercarriage, and the upper end of the rotating shaft penetrates through a round hole in the lower end face of the fixed seat (10), penetrates out of a hole in the bottom of the supporting sleeve (60) and is fixed; the supporting sleeve (60) is arranged in the top of the fixed seat (10), and the upper end surface of the supporting sleeve is provided with an arc-shaped groove; the upper end of the upper torsion spring (30) is connected with the support sleeve (60) and is allowed to slide in the circular arc groove of the support sleeve (60), and the lower end of the upper torsion spring is fixed on the anti-rotation cushion block (50); the upper end of the lower torsion spring (40) is fixed on the anti-rotation cushion block (50), the lower end of the lower torsion spring is connected with the fixed seat (10) and allowed to slide in the arc-shaped groove of the fixed seat (10), and the sliding direction of the lower torsion spring is opposite to that of the upper torsion spring. After the landing gear is turned over or deflected by external interference, the centering device of the invention can make the wheel return to the neutral position by the restoring force of the torsion spring.
Description
Technical Field
The invention belongs to the technical field of undercarriage design, and particularly relates to an undercarriage centering device.
Background
In order to meet the turning requirement of ground taxiing, a front undercarriage or a tail undercarriage of the helicopter is of a structure capable of rotating around a fuselage. The centering mechanism can enable the wheel to return to a neutral position after the turning is finished or external disturbance is applied. The commonly adopted solution is to provide a pair of centering cams. One of the centering cams is fixed relative to the outer cylinder and the other is fixed relative to the rotary cylinder or the piston rod. When the aircraft flies off the ground, the buffer extends, the upper cam and the lower cam are meshed and centered, and the front wheel or the tail wheel returns to the neutral position. In the stop state, the buffer is compressed, and the upper cam and the lower cam are in a disengaged state and have no centering capability.
Disclosure of Invention
In view of the above-mentioned state of the art, it is an object of the present invention to provide a landing gear centering device that meets the landing gear centering requirements of helicopters during ground taxiing as well as airborne flight.
The above object of the present invention is achieved by the following technical solutions:
A landing gear centering device comprises a fixed seat, a rotating shaft, an upper torsion spring, a lower torsion spring, an anti-rotation cushion block and a support sleeve, wherein the fixed seat is connected with a landing gear rocker arm, the center of the lower end face of the fixed seat is provided with a round hole, and the outer side of the round hole is provided with an arc-shaped groove; the lower end of the rotating shaft is connected with a wheel fork of the undercarriage, the upper end of the rotating shaft penetrates through a round hole on the lower end face of the fixed seat, penetrates out of a hole in the bottom of the supporting sleeve and is fixed, and a notch which is matched and connected with an inner hole of the anti-rotation cushion block is arranged on a cylinder at the upper end; the supporting sleeve is arranged in the top of the fixed seat, and the upper end surface of the supporting sleeve is provided with an arc-shaped groove and falls on the upper end surface of the fixed seat; the upper torsion spring is arranged between the support sleeve and the fixed seat, the upper end of the upper torsion spring is connected with the support sleeve and is allowed to slide in the arc-shaped groove of the support sleeve, and the lower end of the upper torsion spring is fixed on the anti-rotation cushion block; the lower torsion spring is arranged between the rotating shaft and the fixing seat, the upper end of the lower torsion spring is fixed on the anti-rotation cushion block, the lower end of the lower torsion spring is connected with the fixing seat and allowed to slide in the arc-shaped groove of the fixing seat, and the sliding direction of the lower torsion spring is opposite to the sliding direction of the upper torsion spring.
Wherein, the outer side edge of the anti-rotation cushion block is provided with a notch, and the lower end of the upper torsion spring and the upper end of the lower torsion spring are clamped in the notch, thereby fixing the upper and lower torsion springs.
The center of the upper end face of the support sleeve is provided with a round hole, the arc-shaped groove is formed in the outer side of the hole, and the rotating shaft is fixed by a bolt which penetrates through a gasket clamped in the round hole and is connected with a threaded hole of the rotating shaft in the center round hole of the upper end face of the support sleeve.
By adopting the undercarriage centering device, when the wheel rotates in the anticlockwise direction, the rotating shaft and the anti-rotation cushion block are driven to rotate together, the lower torsion spring is twisted to store energy, and the upper torsion spring freely slides along the arc-shaped groove; when the external interference force is reduced, the lower torsion spring releases energy to generate restoring force so that the airplane wheel returns to the neutral position; and in the same way, the upper torsion spring is twisted to store energy, the lower torsion spring freely slides along the groove, and the upper torsion spring releases energy to generate restoring force so that the airplane wheel returns to the neutral position.
after the helicopter landing gear is turned or deflected by external interference, the centering device can enable the helicopter wheels to return to the neutral position through the restoring force of the torsion spring.
Drawings
Fig. 1 is a schematic view of the installation of the landing gear centering device.
Fig. 2 is a schematic diagram of the internal structure of the centering device of the present invention.
Fig. 3 is an exploded view of the centering device of the present invention.
Detailed Description
The technical scheme of the invention is clearly and completely described in combination with the embodiment of the invention by referring to the attached drawings.
Fig. 1 is a schematic view of the installation of the landing gear centering device, and as shown in the figure, the centering device is installed at the joint of a rocker arm of the landing gear and a wheel fork, and the wheel fork can rotate left and right around the axis of the centering device.
Fig. 2 is a schematic view of the internal structure of the centering device of the present invention, and fig. 3 is an exploded view of the centering device of the present invention. As shown in the figures, the centering device of the present invention includes a fixing base 10, a rotating shaft 20, an upper torsion spring 30, a lower torsion spring 40, an anti-rotation pad 50, and a support sleeve 60.
Wherein, fixing base 10 is fixed with the undercarriage rocking arm, and the lower terminal surface center is provided with the circular port, and the hole outside is provided with the arc-shaped groove. The lower end of the rotating shaft 20 is fixed with the wheel fork of the landing gear, the upper end of the rotating shaft 20 penetrates through a round hole in the lower end face of the fixing seat 10, a notch is formed in the upper end cylinder, the inner hole of the anti-rotation cushion block 50 is connected, and the rotating shaft penetrates out of and is fixed to a hole in the bottom of the supporting sleeve 60. The supporting sleeve 60 is installed in the top of the fixing seat 10, the upper end surface of the supporting sleeve 60 is provided with an arc-shaped groove and falls on the upper end surface of the fixing seat 10, and the supporting sleeve 60 is installed and fixed in the top of the fixing seat 10 through a threaded hole in the upper end surface by using a screw 70. The upper torsion spring 30 is arranged between the support sleeve 60 and the fixing seat 10, the upper end of the upper torsion spring 30 is connected with the support sleeve 60, the upper end of the upper torsion spring 30 is allowed to slide in the arc-shaped groove of the support sleeve 60 along the anticlockwise direction, and the lower end of the upper torsion spring is fixed on the anti-rotation cushion block 50. The lower torsion spring 40 is disposed between the rotating shaft 20 and the fixing base 10, the upper end of the lower torsion spring 40 is fixed on the anti-rotation cushion block 50, and the lower end of the lower torsion spring 40 is connected to the fixing base 10, so as to allow the lower end of the lower torsion spring 40 to slide clockwise in the annular groove of the fixing base 10. In the embodiment, the upper and lower torsion springs are made of 50CrVA, the torsional rigidity is required to be 5N/deg, and they can be selected and adjusted according to specific situations, and in addition, the upper torsion spring 30 and the lower torsion spring 40 can be two independent torsion springs, or can be composed of two parts of one torsion spring, that is, the upper torsion spring 30 and the lower torsion spring 40 can be integrated. The inner hole of the anti-rotation pad 50 is composed of a circular arc surface and a plane, and is matched with the notch of the cylindrical part at the upper end of the rotating shaft 20, and can be in other shapes capable of realizing corresponding functions. A notch is formed in the outer edge of the anti-rotation pad 50, and the lower end of the upper torsion spring and the upper end of the lower torsion spring are clamped in the notch, so that the upper torsion spring and the lower torsion spring are fixed.
In this embodiment, a circular hole is further formed in the center of the upper end surface of the support sleeve 60, an arc-shaped groove in the upper end surface of the support sleeve 60 is formed outside the circular hole, and the rotating shaft 20 is fixed in the circular hole in the center of the upper end surface of the support sleeve 60 by a bolt 90 passing through a gasket 80 clamped in the circular hole and connected to a threaded hole of the rotating shaft 20.
In addition, the width of the arc-shaped grooves on the fixed seat 10 and the supporting sleeve 60 is 5.2mm, which can be adjusted according to the specific situation. The central angle corresponding to the neutral line arc of the arc-shaped groove is 10 degrees to 180 degrees, and in this embodiment, 120 degrees. The projections of the arc-shaped grooves on the fixed seat 10 and the support sleeve 60 on the end surface of the support sleeve 60 are symmetrical about the symmetry plane of the airplane wheel.
The working principle of the landing gear centering device is as follows: when the airplane wheel rotates in the anticlockwise direction, the rotating shaft and the anti-rotation cushion block are driven to rotate together, the lower torsion spring is twisted to store energy, and the upper torsion spring freely slides along the arc-shaped groove; when the external interference force is reduced, the lower torsion spring releases energy to generate restoring force so that the airplane wheel returns to the neutral position; and in the same way, the upper torsion spring is twisted to store energy, the lower torsion spring freely slides along the groove, and the upper torsion spring releases energy to generate restoring force so that the airplane wheel returns to the neutral position. Therefore, when the helicopter landing gear deflects after the turning is finished or when the helicopter landing gear deflects due to external interference, the centering device can enable the airplane wheel to return to the neutral position through the restoring force of the torsion spring, and the centering requirement of the landing gear during ground sliding and aerial flight of the helicopter is met.
Claims (9)
1. A landing gear centering device comprises a fixed seat (10), a rotating shaft (20), an upper torsion spring (30), a lower torsion spring (40), an anti-rotation cushion block (50) and a support sleeve (60), wherein the fixed seat (10) is connected with a landing gear rocker arm, a round hole is formed in the center of the lower end face of the fixed seat, and an arc-shaped groove is formed in the outer side of the round hole; the lower end of the rotating shaft (20) is connected with a wheel fork of the undercarriage, the upper end of the rotating shaft penetrates through a round hole on the lower end face of the fixed seat (10), penetrates out of a hole at the bottom of the supporting sleeve (60) and is fixed, and a notch which is matched and connected with an inner hole of the anti-rotation cushion block (50) is arranged on a cylinder at the upper end; the supporting sleeve (60) is arranged in the top of the fixed seat (10), and the upper end surface of the supporting sleeve is provided with an arc-shaped groove and falls on the upper end surface of the fixed seat (10); the upper torsion spring (30) is arranged between the support sleeve (60) and the fixed seat (10), the upper end of the upper torsion spring is connected with the support sleeve (60) and allowed to slide in the arc-shaped groove of the support sleeve (60), and the lower end of the upper torsion spring is fixed on the anti-rotation cushion block (50); the lower torsion spring (40) is arranged between the rotating shaft (20) and the fixed seat (10), the upper end of the lower torsion spring is fixed on the anti-rotation cushion block (50), the lower end of the lower torsion spring is connected with the fixed seat (10) and allowed to slide in the arc-shaped groove of the fixed seat (10), and the sliding direction of the lower torsion spring is opposite to that of the upper torsion spring.
2. Landing gear centering device according to claim 1, wherein notches for fixing the upper torsion spring (30) and the lower torsion spring (40) are provided on the outer side edges of the anti-rotation spacer (50).
3. The landing gear centering device according to claim 1, wherein a circular hole is formed in the center of the upper end surface of the support sleeve (60), a circular arc groove is formed outside the circular hole, and the rotary shaft (20) is fixed by a bolt (90) which is inserted through a washer (80) fitted in the circular hole and connected to a threaded hole of the rotary shaft (20) in the circular hole in the center of the upper end surface of the support sleeve (60).
4. Landing gear centering device according to claim 1, wherein the projections of the circular arc grooves on the fastening base (10) and the support sleeve (60) onto the end face of the support sleeve (60) are symmetrical with respect to the plane of symmetry of the fuselage.
5. Landing gear centralising device according to claim 1, wherein the material of the upper torsion spring (30) and the lower torsion spring (40) is 50CrVA and the torsional stiffness requires 5N/deg.
6. Landing gear centering device according to claim 1, wherein the upper torsion spring (30) and the lower torsion spring (40) are two separate torsion springs.
7. Landing gear centering device according to claim 1, wherein the upper torsion spring (30) and the lower torsion spring (40) are integral.
8. Landing gear centering device according to claim 1, wherein the central angle of the neutral arc of the arc-shaped groove in the holder (10) and in the support sleeve (60) corresponds to 120 °.
9. A landing gear centralising apparatus as claimed in claim 1, wherein the upper torsion spring slides in a counter-clockwise direction.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910931892.XA CN110576967A (en) | 2019-09-29 | 2019-09-29 | Undercarriage centering device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910931892.XA CN110576967A (en) | 2019-09-29 | 2019-09-29 | Undercarriage centering device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN110576967A true CN110576967A (en) | 2019-12-17 |
Family
ID=68814009
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910931892.XA Pending CN110576967A (en) | 2019-09-29 | 2019-09-29 | Undercarriage centering device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN110576967A (en) |
Citations (12)
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|---|---|---|---|---|
| GB713356A (en) * | 1951-12-11 | 1954-08-11 | Gloster Aircraft Company Ltd | Improvements in or relating to undercarriage controllers for aircraft |
| CN1269757A (en) * | 1997-09-13 | 2000-10-11 | 腓特烈斯港齿轮工厂股份公司 | Method for mounting steering valve with centring unt |
| CN102320324A (en) * | 2011-06-30 | 2012-01-18 | 浙江大学宁波理工学院 | Wire control steering automobile road sensing simulation executing device |
| CN202481305U (en) * | 2011-12-22 | 2012-10-10 | 中国直升机设计研究所 | Automatic aligning mechanism |
| JP2013067258A (en) * | 2011-09-22 | 2013-04-18 | Mitsubishi Electric Corp | Electric power steering system |
| US20140231584A1 (en) * | 2011-09-02 | 2014-08-21 | Messier-Bugatti-Dowty | Anti-lofting deflector for aircraft landing gear |
| US20140239119A1 (en) * | 2013-02-22 | 2014-08-28 | Goodrich Corporation | Main landing gear compact axle steering |
| CN204755572U (en) * | 2015-06-18 | 2015-11-11 | 深圳市斯蒙奇科技有限公司 | Automatic rotation type damping pivot |
| CN106585962A (en) * | 2016-11-30 | 2017-04-26 | 中国直升机设计研究所 | External automatic reset device of landing gear |
| CN206437201U (en) * | 2016-12-14 | 2017-08-25 | 中航通飞研究院有限公司 | Device in a kind of new time |
| CN207517214U (en) * | 2017-09-27 | 2018-06-19 | 瑞安市奔翔教学设备有限公司 | A kind of vehicle driving simulator steering wheel self-aligning device |
| KR20190023400A (en) * | 2017-08-29 | 2019-03-08 | 현대위아 주식회사 | Steerimg device of landing gear of airplane and torsional coil spring setting method thereof |
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2019
- 2019-09-29 CN CN201910931892.XA patent/CN110576967A/en active Pending
Patent Citations (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB713356A (en) * | 1951-12-11 | 1954-08-11 | Gloster Aircraft Company Ltd | Improvements in or relating to undercarriage controllers for aircraft |
| CN1269757A (en) * | 1997-09-13 | 2000-10-11 | 腓特烈斯港齿轮工厂股份公司 | Method for mounting steering valve with centring unt |
| CN102320324A (en) * | 2011-06-30 | 2012-01-18 | 浙江大学宁波理工学院 | Wire control steering automobile road sensing simulation executing device |
| US20140231584A1 (en) * | 2011-09-02 | 2014-08-21 | Messier-Bugatti-Dowty | Anti-lofting deflector for aircraft landing gear |
| JP2013067258A (en) * | 2011-09-22 | 2013-04-18 | Mitsubishi Electric Corp | Electric power steering system |
| CN202481305U (en) * | 2011-12-22 | 2012-10-10 | 中国直升机设计研究所 | Automatic aligning mechanism |
| US20140239119A1 (en) * | 2013-02-22 | 2014-08-28 | Goodrich Corporation | Main landing gear compact axle steering |
| CN204755572U (en) * | 2015-06-18 | 2015-11-11 | 深圳市斯蒙奇科技有限公司 | Automatic rotation type damping pivot |
| CN106585962A (en) * | 2016-11-30 | 2017-04-26 | 中国直升机设计研究所 | External automatic reset device of landing gear |
| CN206437201U (en) * | 2016-12-14 | 2017-08-25 | 中航通飞研究院有限公司 | Device in a kind of new time |
| KR20190023400A (en) * | 2017-08-29 | 2019-03-08 | 현대위아 주식회사 | Steerimg device of landing gear of airplane and torsional coil spring setting method thereof |
| CN207517214U (en) * | 2017-09-27 | 2018-06-19 | 瑞安市奔翔教学设备有限公司 | A kind of vehicle driving simulator steering wheel self-aligning device |
Non-Patent Citations (1)
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Legal Events
| Date | Code | Title | Description |
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| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20191217 |
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| RJ01 | Rejection of invention patent application after publication |