CN112483509A - Aircraft cabin door actuator cylinder with internal locking mechanism - Google Patents
Aircraft cabin door actuator cylinder with internal locking mechanism Download PDFInfo
- Publication number
- CN112483509A CN112483509A CN202011452488.3A CN202011452488A CN112483509A CN 112483509 A CN112483509 A CN 112483509A CN 202011452488 A CN202011452488 A CN 202011452488A CN 112483509 A CN112483509 A CN 112483509A
- Authority
- CN
- China
- Prior art keywords
- piston
- snap ring
- steel ball
- clamping ring
- actuator cylinder
- 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
- 230000007246 mechanism Effects 0.000 title claims abstract description 18
- 229910000831 Steel Inorganic materials 0.000 claims abstract description 27
- 239000010959 steel Substances 0.000 claims abstract description 27
- 239000010720 hydraulic oil Substances 0.000 claims abstract description 7
- 238000009434 installation Methods 0.000 claims description 5
- 230000000670 limiting effect Effects 0.000 claims description 3
- 239000003921 oil Substances 0.000 description 3
- 230000009471 action Effects 0.000 description 2
- 230000008602 contraction Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 230000009467 reduction Effects 0.000 description 1
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F15—FLUID-PRESSURE ACTUATORS; HYDRAULICS OR PNEUMATICS IN GENERAL
- F15B—SYSTEMS ACTING BY MEANS OF FLUIDS IN GENERAL; FLUID-PRESSURE ACTUATORS, e.g. SERVOMOTORS; DETAILS OF FLUID-PRESSURE SYSTEMS, NOT OTHERWISE PROVIDED FOR
- F15B15/00—Fluid-actuated devices for displacing a member from one position to another; Gearing associated therewith
- F15B15/08—Characterised by the construction of the motor unit
- F15B15/14—Characterised by the construction of the motor unit of the straight-cylinder type
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/14—Windows; Doors; Hatch covers or access panels; Surrounding frame structures; Canopies; Windscreens accessories therefor, e.g. pressure sensors, water deflectors, hinges, seals, handles, latches, windscreen wipers
- B64C1/1407—Doors; surrounding frames
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F15—FLUID-PRESSURE ACTUATORS; HYDRAULICS OR PNEUMATICS IN GENERAL
- F15B—SYSTEMS ACTING BY MEANS OF FLUIDS IN GENERAL; FLUID-PRESSURE ACTUATORS, e.g. SERVOMOTORS; DETAILS OF FLUID-PRESSURE SYSTEMS, NOT OTHERWISE PROVIDED FOR
- F15B15/00—Fluid-actuated devices for displacing a member from one position to another; Gearing associated therewith
- F15B15/20—Other details, e.g. assembly with regulating devices
- F15B15/26—Locking mechanisms
- F15B15/261—Locking mechanisms using positive interengagement, e.g. balls and grooves, for locking in the end positions
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- General Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Actuator (AREA)
Abstract
The invention provides an aircraft cabin door actuator cylinder with an internal locking mechanism, which comprises a steel ball (3), an upper clamping ring (14), a lower clamping ring (15), a piston (11) and matched parts, wherein the steel ball (3) is positioned in the middle of the piston (11), the upper clamping ring (14) and the lower clamping ring (15) are respectively arranged at two ends of the piston (11), the steel ball (3) is pressed to contract along the radial direction through the movement of the piston (11), the piston (11) is withdrawn from the inner wall of the upper clamping ring (14) or the lower clamping ring (15), the upper clamping ring (14) or the lower clamping ring (15) automatically rebounds to complete unlocking, the steel ball (3) contracts under the pressure of hydraulic oil, and the piston (11) realizes the reciprocating motion of the actuator cylinder under the driving of the hydraulic oil. The aircraft cabin door actuator cylinder with the internal lock mechanism has the advantages of simple and reliable structure, stable unlocking pressure and stable telescopic motion.
Description
Technical Field
The invention belongs to the field of mechanical design, and particularly relates to an aircraft cabin door actuator cylinder with an internal locking mechanism.
Background
The common use of the aircraft landing device with internal lock actuator cylinder is steel ball lock, finger lock and snap ring lock. Finger locks and snap ring locks are commonly used for large barrel diameter rams. Due to the limitation of installation and use space size, the aircraft cabin door actuator cylinder generally adopts a steel ball type internal lock structure.
The steel ball actuator cylinder adopts the steel ball motion driven by the piston to achieve the purpose of locking the piston rod, the contact form of the steel ball and the point-to-surface of the inner wall of the actuator cylinder easily causes the unevenness of the inner wall and the obvious increase of the friction resistance, and further causes the problems of the actuator cylinder such as the tightness of the telescopic motion, the instability of the unlocking pressure, the reduction of the service life of the actuator cylinder and the like.
Disclosure of Invention
The invention provides an airplane cabin door actuator cylinder with an internal locking mechanism, aiming at solving the problems of tight telescopic motion, unstable unlocking pressure and the like of the airplane cabin door actuator cylinder.
The aircraft cabin door actuator cylinder with the inner lock mechanism comprises a steel ball, an upper clamping ring, a lower clamping ring, a piston and matched parts, wherein the steel ball is located in the middle of the piston, the upper clamping ring and the lower clamping ring are respectively arranged at two ends of the piston, the steel ball is pressed to radially contract through the movement of the piston, the piston is withdrawn from the inner wall of the upper clamping ring or the lower clamping ring, and the upper clamping ring or the lower clamping ring automatically rebounds, so that unlocking is completed. The steel ball contracts under the pressure of hydraulic oil, and the piston realizes the reciprocating motion of the actuating cylinder under the drive of the hydraulic oil.
Furthermore, the aircraft cabin door actuator cylinder matched parts with the internal lock mechanism comprise an upper end cover, a pressure spring, an outer cylinder, a support bushing, an earring bolt, a lower end cover, a piston rod, a nut, a top ring, a bolt and a nut. The piston can move left and right on the piston rod, is limited by the nut and is anti-loose by a set screw after being installed, and finally, the installation of other parts is completed.
Furthermore, the inner sides of the upper snap ring and the lower snap ring of the aircraft cabin door actuator cylinder with the inner lock mechanism are provided with convex ribs, so that the rigidity of the snap ring is improved, the unlocking contact area is increased, and the unlocking stability is improved.
The aircraft cabin door actuator cylinder with the inner lock mechanism has the advantages of simple and reliable structure, stable unlocking pressure and stable telescopic motion, and effectively solves the problems of the steel ball lock actuator cylinder.
Drawings
Figure 1 is a sectional view of an aircraft door actuator with an internal lock mechanism.
Fig. 2 is an enlarged view of a portion of an aircraft door ram structure with an internal lock mechanism.
Fig. 3 is a structure diagram of an upper snap ring and a lower snap ring with convex ribs.
In FIGS. 1-3: 1. the device comprises an upper end cover, 2, a pressure spring, 3, a steel ball, 4, an outer cylinder, 5, a support bush, 6, an earring bolt, 7, a lower end cover, 8, a piston rod, 9, a nut, 10, a top ring, 11, a piston, 12, a bolt, 13, a nut, 14, an upper clamping ring, 15 and a lower clamping ring.
Detailed Description
The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to fig. 1 to 3, and it is obvious that the described embodiment is only a specific embodiment of the present invention, and not all embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
As shown in fig. 1 and 2, an aircraft door actuator cylinder with an inner lock mechanism includes an upper end cover 1, a pressure spring 2, a steel ball 3, an outer cylinder 4, a support bushing 5, an ear bolt 6, a lower end cover 7, a piston rod 8, a nut 9, a top ring 10, a piston 11, a bolt 12, a nut 13, an upper snap ring 14 and a lower snap ring 15.
The pressure spring 2, the steel ball 3, the top ring 10, the bolt 12 and the nut 13 are installed in the piston rod 8, the upper clamping ring 14 and the lower clamping ring 15 are respectively arranged on two sides of the piston 11, the piston 11 can move left and right on the piston rod 8, the piston is limited by the nut 9 after being installed and is anti-loose by a set screw, and finally, installation of other parts is completed.
When the piston rod 8 of the actuating cylinder retracts to the left side, the upper clamping ring 14 is positioned in a groove in the left side of the inner wall of the outer cylinder 4, and due to the limiting effect of the pressure spring 2 and the steel ball 3, the piston 11 is pressed into the inner side of the upper clamping ring 14 to expand the upper clamping ring, so that the piston rod 8 is locked at the retracting position.
When hydraulic oil enters from an oil inlet of the upper end cover 1, the boss on the inner wall of the piston 11 presses the steel ball 3 to contract inwards along the radial direction under the action of hydraulic force, the piston 11 moves rightwards after being unlocked, the upper clamping ring 14 rebounds, the piston rod 8 can smoothly drive the upper clamping ring 14 to cross the groove on the left side of the outer barrel 4 to complete the extending process, and the steel ball 3 crosses the step and then recovers to contact with the inner wall of the piston 11 under the action of the pretightening force of the pressure spring 2.
When the piston rod 8 of the actuating cylinder extends to the right side, the lower clamping ring 5 is driven into the groove on the right side of the outer cylinder 4, the piston 11 is pressed into the inner side of the lower clamping ring 15 due to the limiting effect of the steel ball 3, the lower clamping ring 15 expands in the groove, and the piston rod 8 is locked at the extending position.
The limit of the piston 11 can be released when oil entering from the oil port of the lower end cover 7 reaches the inward contraction pressure of the steel ball 3, and the unlocking and retraction of the piston rod 8 are realized.
As shown in fig. 3, the inner sides of the upper snap ring 14 and the lower snap ring 15 are provided with convex ribs, which are used for improving the rigidity of the snap rings, increasing the unlocking contact area and improving the unlocking stability.
Claims (3)
1. The utility model provides an aircraft hatch door pressurized strut of in-band locking mechanism which characterized by: the aircraft cabin door actuator cylinder with the inner lock mechanism comprises a steel ball (3), an upper snap ring (14), a lower snap ring (15), a piston (11) and matched parts, wherein the steel ball (3) is located in the middle of the piston (11), the upper snap ring (14) and the lower snap ring (15) are respectively arranged at two ends of the piston (11), the steel ball (3) is pressed to contract along the radial direction through the movement of the piston (11), the piston (11) exits from the inner wall of the upper snap ring (14) or the lower snap ring (15), and the upper snap ring (14) or the lower snap ring (15) automatically rebounds to complete unlocking; the steel ball (3) contracts under the pressure of hydraulic oil, and the piston (11) realizes the reciprocating motion of the actuating cylinder under the driving of the hydraulic oil.
2. The aircraft door ram with an internal lock mechanism of claim 1, wherein: the aircraft cabin door actuator cylinder matched parts with the internal lock mechanism comprise an upper end cover (1), a pressure spring (2), an outer cylinder (4), a support bushing (5), an earring bolt (6), a lower end cover (7), a piston rod (8), a nut (9), a top ring (10), a bolt (12) and a nut (13); the pressure spring (2), the steel ball (3), the top ring (10), the bolt (12) and the nut (13) are installed in the piston rod (8), the upper clamping ring (14) and the lower clamping ring (15) are respectively arranged on two sides of the piston (11), the piston (11) can move left and right on the piston rod (8), the nut (9) is used for limiting after installation, the set screw is adopted for preventing looseness, and installation of other parts is completed at last.
3. The aircraft door ram with an internal lock mechanism of claim 1, wherein: and convex ribs are arranged on the inner sides of the upper snap ring (14) and the lower snap ring (15).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011452488.3A CN112483509A (en) | 2020-12-12 | 2020-12-12 | Aircraft cabin door actuator cylinder with internal locking mechanism |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011452488.3A CN112483509A (en) | 2020-12-12 | 2020-12-12 | Aircraft cabin door actuator cylinder with internal locking mechanism |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN112483509A true CN112483509A (en) | 2021-03-12 |
Family
ID=74940167
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202011452488.3A Pending CN112483509A (en) | 2020-12-12 | 2020-12-12 | Aircraft cabin door actuator cylinder with internal locking mechanism |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN112483509A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114046286A (en) * | 2021-11-10 | 2022-02-15 | 湖北三江航天红阳机电有限公司 | Cold air unlocking actuator and use method thereof |
| CN114313228A (en) * | 2021-12-23 | 2022-04-12 | 中国航空工业集团公司金城南京机电液压工程研究中心 | Mechanical locking device for external hydraulic actuator cylinder |
| DE202021105127U1 (en) | 2021-09-23 | 2023-01-03 | Liebherr-Aerospace Lindenberg Gmbh | Multi-stage lockable actuator |
Citations (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB898260A (en) * | 1960-06-01 | 1962-06-06 | Automotive Prod Co Ltd | Improvements in or relating to fluid pressure remote control systems |
| GB928609A (en) * | 1961-01-10 | 1963-06-12 | Lionel Pacific Inc | Midstroke locking device |
| DE29908312U1 (en) * | 1999-05-10 | 1999-07-29 | Wulke | Working cylinder |
| US6173969B1 (en) * | 1997-12-10 | 2001-01-16 | Festo Ag & Co. | Sealing ring |
| DE10140561A1 (en) * | 2001-08-17 | 2003-02-27 | Ina Schaeffler Kg | Releasable clamping lock has one clamp track on fixed part and other in form of run-up ramp for clamping body on other part |
| CN203035655U (en) * | 2012-11-30 | 2013-07-03 | 江苏恒立高压油缸股份有限公司 | Buffering type locking structure of self-locking oil cylinder |
| US20140271040A1 (en) * | 2013-03-15 | 2014-09-18 | GM Global Technology Operations LLC | Balanced snap ring |
| CN106275392A (en) * | 2016-09-08 | 2017-01-04 | 南京航空航天大学 | A kind of multistage pressurized strut locking device |
| CN108757630A (en) * | 2018-06-19 | 2018-11-06 | 中航飞机起落架有限责任公司 | A kind of quick-release pressurized strut |
| CN208348207U (en) * | 2018-06-19 | 2019-01-08 | 中航飞机起落架有限责任公司 | Hydraulic actuator outer cylinder and end cap connection structure |
| CN109987220A (en) * | 2017-12-29 | 2019-07-09 | 北京精密机电控制设备研究所 | A kind of ball-type lead screw locking mechanism in place |
| CN110005692A (en) * | 2018-01-04 | 2019-07-12 | 美建建筑系统(中国)有限公司 | A kind of venting of dust explosion washer suitable for profiled sheet |
| CN210599667U (en) * | 2019-09-24 | 2020-05-22 | 贵州龙飞航空附件有限公司 | Actuator cylinder with built-in mechanical locks at two ends |
| CN111379760A (en) * | 2018-12-28 | 2020-07-07 | 比亚迪股份有限公司 | Oil cylinder, hydraulic system and lifting equipment |
-
2020
- 2020-12-12 CN CN202011452488.3A patent/CN112483509A/en active Pending
Patent Citations (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB898260A (en) * | 1960-06-01 | 1962-06-06 | Automotive Prod Co Ltd | Improvements in or relating to fluid pressure remote control systems |
| GB928609A (en) * | 1961-01-10 | 1963-06-12 | Lionel Pacific Inc | Midstroke locking device |
| US6173969B1 (en) * | 1997-12-10 | 2001-01-16 | Festo Ag & Co. | Sealing ring |
| DE29908312U1 (en) * | 1999-05-10 | 1999-07-29 | Wulke | Working cylinder |
| DE10140561A1 (en) * | 2001-08-17 | 2003-02-27 | Ina Schaeffler Kg | Releasable clamping lock has one clamp track on fixed part and other in form of run-up ramp for clamping body on other part |
| CN203035655U (en) * | 2012-11-30 | 2013-07-03 | 江苏恒立高压油缸股份有限公司 | Buffering type locking structure of self-locking oil cylinder |
| US20140271040A1 (en) * | 2013-03-15 | 2014-09-18 | GM Global Technology Operations LLC | Balanced snap ring |
| CN106275392A (en) * | 2016-09-08 | 2017-01-04 | 南京航空航天大学 | A kind of multistage pressurized strut locking device |
| CN109987220A (en) * | 2017-12-29 | 2019-07-09 | 北京精密机电控制设备研究所 | A kind of ball-type lead screw locking mechanism in place |
| CN110005692A (en) * | 2018-01-04 | 2019-07-12 | 美建建筑系统(中国)有限公司 | A kind of venting of dust explosion washer suitable for profiled sheet |
| CN108757630A (en) * | 2018-06-19 | 2018-11-06 | 中航飞机起落架有限责任公司 | A kind of quick-release pressurized strut |
| CN208348207U (en) * | 2018-06-19 | 2019-01-08 | 中航飞机起落架有限责任公司 | Hydraulic actuator outer cylinder and end cap connection structure |
| CN111379760A (en) * | 2018-12-28 | 2020-07-07 | 比亚迪股份有限公司 | Oil cylinder, hydraulic system and lifting equipment |
| CN210599667U (en) * | 2019-09-24 | 2020-05-22 | 贵州龙飞航空附件有限公司 | Actuator cylinder with built-in mechanical locks at two ends |
Non-Patent Citations (3)
| Title |
|---|
| 机械设计手册编委会: "《机械设计手册 第2卷》", 31 August 2004, 机械工业出版社 * |
| 李艳军: "《飞机液压传动与控制》", 28 February 2009, 科学出版社 * |
| 郑长胜: "《液压动力头岩心钻机设计与使用》", 31 August 2011, 地质出版社 * |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE202021105127U1 (en) | 2021-09-23 | 2023-01-03 | Liebherr-Aerospace Lindenberg Gmbh | Multi-stage lockable actuator |
| CN114046286A (en) * | 2021-11-10 | 2022-02-15 | 湖北三江航天红阳机电有限公司 | Cold air unlocking actuator and use method thereof |
| CN114046286B (en) * | 2021-11-10 | 2023-10-20 | 湖北三江航天红阳机电有限公司 | Cold air unlocking actuator and using method thereof |
| CN114313228A (en) * | 2021-12-23 | 2022-04-12 | 中国航空工业集团公司金城南京机电液压工程研究中心 | Mechanical locking device for external hydraulic actuator cylinder |
| CN114313228B (en) * | 2021-12-23 | 2023-05-30 | 中国航空工业集团公司金城南京机电液压工程研究中心 | External hydraulic actuator mechanical locking device |
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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 | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20210312 |