CN110844043A - Retraction mechanism of aircraft maintenance cabin door - Google Patents
Retraction mechanism of aircraft maintenance cabin door Download PDFInfo
- Publication number
- CN110844043A CN110844043A CN201911023119.XA CN201911023119A CN110844043A CN 110844043 A CN110844043 A CN 110844043A CN 201911023119 A CN201911023119 A CN 201911023119A CN 110844043 A CN110844043 A CN 110844043A
- Authority
- CN
- China
- Prior art keywords
- door
- rocker arm
- hinged
- door frame
- rod
- 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
- 238000012423 maintenance Methods 0.000 title claims abstract description 23
- 230000037237 body shape Effects 0.000 claims description 3
- 230000006835 compression Effects 0.000 claims description 3
- 238000007906 compression Methods 0.000 claims description 3
- 238000004804 winding Methods 0.000 abstract 3
- 230000000694 effects Effects 0.000 description 4
- 238000013016 damping Methods 0.000 description 3
- 238000000034 method Methods 0.000 description 3
- 210000001015 abdomen Anatomy 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000002035 prolonged effect Effects 0.000 description 1
Images
Classifications
-
- 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
- B64C1/1446—Inspection hatches
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/40—Maintaining or repairing aircraft
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Manufacturing & Machinery (AREA)
- Transportation (AREA)
- Mechanical Engineering (AREA)
- Closing And Opening Devices For Wings, And Checks For Wings (AREA)
Abstract
The utility model provides a jack of aircraft maintenance hatch door, contain the hatch door, the door frame and winding and unwinding devices, the one end of hatch door is articulated with the one end of door frame, the other end of hatch door is connected with the other end of door frame through winding and unwinding devices, the door frame is fixed on the aircraft organism, winding and unwinding devices's first rocking arm is articulated with the front end pole of second rocking arm, the other end of first rocking arm articulates the other end at the hatch door, the turning department of second rocking arm and third rocking arm articulates on the end frame of door frame through an intersection point joint, the other end of third rocking arm is articulated with the one end of air spring, the other end of air spring articulates on the side frame of door frame through.
Description
Technical Field
The invention relates to the technical field of airplane design, in particular to a retraction mechanism of an airplane maintenance door, which is used for realizing the opening and closing of the airplane maintenance door and keeping the stability of the door when personnel trample the door.
Background
The aircraft cabin door is an openable and closable structure arranged on an aircraft body, generally, the cabin door used by passengers is mostly arranged on the side surface of the aircraft body, and the cabin door used for aircraft maintenance and overhaul is mostly arranged on the lower part of the belly. In order to facilitate the access of maintenance personnel to the cabin, the maintenance cabin door mostly adopts a downward-turning door-ladder combined cabin door. Among the prior art, the maintenance of the state of opening of maintenance hatch door leans on the cable wire pulling, personnel trample poor stability when passing in and out, there is not damping effect in the current maintenance hatch door opening process simultaneously, the hatch door is opened and is relied on self weight free fall, cause the damage to personnel and organism easily, lead to organism mechanism damage when preventing the hatch door free fall, need whole the supporting hatch door of operating personnel slow whereabouts after the hatch door unblock, the same hatch door is closed the in-process and also is not had the helping hand effect, the operating performance is relatively poor.
Disclosure of Invention
To the problems in the prior art, the present application aims to provide a retraction mechanism for an aircraft maintenance door.
A retraction mechanism of an aircraft maintenance hatch door comprises a hatch door, a door frame and a retraction device, wherein one end of the hatch door is hinged with one end of the door frame, the other end of the hatch door is connected with the other end of the door frame through the retraction device, the door frame is fixed on an aircraft body, the retraction device comprises an air spring, a first rocker arm and a second rocker arm, the first rocker arm is of a rod-shaped structure, the first rocker arm is hinged with a front end rod of the second rocker arm, the other end of the first rocker arm is hinged with the other end of the hatch door, a rear end rod of the second rocker arm is of a triangular body shape, the front end rod of the second rocker arm extends to the long side of the triangular body, a third rocker arm with an included angle with the front end rod of the second rocker arm is formed on the outer side edge of the triangular body, the turning part of the second rocker arm and the third rocker arm is hinged on an end frame of the door frame through, the other end of the gas spring is hinged on the side frame of the door frame through a joint.
The two retraction devices are respectively arranged on the left side and the right side of the door frame and the cabin door, the ends of the first rocker arms of the two retraction devices are fixedly connected with the two ends of a torsion tube through joints, and the torsion tube is transversely hinged and fixed at the near end of the cabin door.
And one end of the self-locking pull rod is hinged on the first rocker arm, and the other end of the self-locking pull rod is hinged on the cabin door.
When the cabin door is in a closed state, the gas spring is in a free state and has a certain included angle with the third rocker arm, the first rocker arm and the second rocker arm are folded, the compression amount of the gas spring reaches the maximum when the cabin door is in an open state, the gas spring and the third rocker arm are positioned on the same straight line, and the first rocker arm and the second rocker arm are unfolded on the same straight line.
The beneficial effect of this application lies in: the buffer damping/assistance for opening/closing the cabin door is realized through the air spring, the defect that the maintenance cabin door of an airplane in the prior art falls freely or has no assistance when being opened or closed can be effectively overcome, the retraction device is simple and reliable in structure and small in arrangement space, the pedaling stability of the maintenance cabin door is ensured by utilizing the triangular stability principle, the assistance/damping effect can be provided in the closing/opening process of the cabin door, the burden of operators is reduced, the operation safety is improved, the downward-turning type door ladder combined type cabin door can be widely applied to the cabin door with different sizes and weights by only adjusting the sizes of related parts and the nominal force value of the air spring, and the use can be realized.
The present application will be described in further detail with reference to the accompanying drawings.
Drawings
Fig. 1 is a schematic structural diagram of the retraction device.
Figure 2 is a schematic view of the aircraft maintenance door closed position retraction mechanism.
Fig. 3 is a schematic view of the aircraft maintenance door opening state retracting mechanism.
The numbering in the figures illustrates: 1 gas spring, 2 second rocker arms, 3 third rocker arms, 4 intersection joints, 5 pull rod joints, 6 toothed plates, 7 self-locking pull rods, 8 torsion tubes, 9 end joints, 10 first rocker arms, 11 steering joints, 12 fixed joints, 13 cabin doors, 14 door frames, 15 retraction devices, 16 connecting shafts and 17 connecting pins
Detailed Description
Referring to the drawings, the retraction device of the retraction mechanism of the aircraft maintenance door of the embodiment is shown in fig. 1 and comprises a gas spring 1, a second rocker arm 2, a third rocker arm 3, an intersection joint 4, a pull rod joint 5, a toothed plate 6, a self-locking pull rod 7, a torsion tube 8, an end joint 9, a first rocker arm 10, a steering joint 11 and a fixed joint 12. Except that the self-locking pull rod 7 is arranged on one side of the cabin door, the other gas springs 1, the second rocker arm 2, the third rocker arm 3, the first rocker arm 10 and the like are symmetrically arranged.
One end of the cabin door 13 is hinged with one end of the door frame 14 through a connecting shaft 16, the other end of the cabin door 13 is connected with the other end of the door frame 14 through a retracting device 15, the door frame 14 is fixed on the airplane body, in the embodiment, the retracting device 15 is respectively arranged on the left side and the right side of the door frame 14 and the cabin door 13, the ends of the first rocker arms 10 of the two retracting devices are fixedly connected with the two ends of the torsion tube 8 through end connectors 9, and the torsion tube 8 is transversely hinged and fixed at the near end of the cabin door 13. As shown in fig. 1, the retraction device 15 comprises a gas spring 1, a first rocker arm 10 and a second rocker arm 2, wherein the first rocker arm 10 is a rod-shaped structure, the first rocker arm 10 is hinged with the front end rod of the second rocker arm 2 through a connecting pin 17, and the other end of the first rocker arm 10 is hinged with the other end of the cabin door through a torsion tube 8. The rear end rod of the second rocker arm 2 is in a triangular body shape, the front end rod of the second rocker arm 2 extends to be a long edge of the triangular body, a third rocker arm 3 which forms an included angle with the front end rod of the second rocker arm 2 is formed on the outer side edge of the triangular body, the turning part of the second rocker arm 2 and the third rocker arm 3 is hinged to an end frame of the door frame 14 through a cross point joint 4, the other end of the third rocker arm 3 is hinged to one end of the gas spring 1, and the other end of the gas spring 1 is hinged to a side frame of the door frame 14 through a steering joint 11.
Referring to fig. 2, the torque tube 8 is hinged to the lower part of the door and is fixedly connected to the first swing arm 10 through an end joint 9. The torsion tube 8 is rotatable about the hatch door. The second rocker arm 2 and the third rocker arm 3 are respectively hinged with the first rocker arm 10, the gas spring 1 and the intersection joint 4 fixed on the door frame through bolts and groove-shaped nuts. The other end of the gas spring 1 is hinged with a steering joint 11 fixed on the doorframe. By adjusting the nominal force value of the air spring 1, the cabin door can not freely fall down after being unlocked.
In addition, a self-locking pull rod 7 is arranged between the cabin door 13 and the first rocker arm 10, one end of the self-locking pull rod 7 is hinged on the first rocker arm 10 through a fixed joint 12, the other end of the self-locking pull rod is connected to the cabin door through a pull rod joint 5 and a toothed plate 6, and the lower surface of the pull rod joint 5 is in a toothed structure and is matched and connected with the toothed plate 6 fixed on the cabin door. The adjustment of the angle between the first rocker arm 10 and the second rocker arm 2 after the hatch door is opened can be realized by adjusting the relative matching position of the pull rod joint 5 on the toothed plate 6.
When the cabin door 13 is closed, as shown in fig. 2, the gas spring 1 is in a free state and forms a certain included angle with the third rocker arm 3, and the first rocker arm 10 and the second rocker arm 2 are folded; when the cabin door is gradually opened, the gas spring 1 is gradually compressed to provide resistance for the opening of the cabin door, so that the cabin door is slowly opened. Conversely, when the hatch door is closed, the air spring 1 gradually extends to provide assistance for the closing of the hatch door.
When the door 13 is opened, as shown in fig. three, the compression of the gas spring 1 is maximized, and the gas spring 1 and the third rocker arm 3 are located on a straight line, and at this time, the gas spring 1 has no acting force on the door. The first rocker arm 10 is unfolded in line with the second rocker arm 2. At the moment, the cabin door retracting mechanism, the cabin door and the door frame are in a triangular structure, so that the stability is strong, and the treading performance is good.
The design has the advantages that the opening state of the cabin door is kept independent of the self-locking pull rod 7, other acting forces are not applied to the self-locking pull rod 7, the effect of preventing the state of the cabin door from changing due to manual misoperation is achieved, and the service life of the self-locking pull rod 7 can be effectively prolonged.
Claims (5)
1. A retraction mechanism of an aircraft maintenance hatch door comprises a hatch door, a door frame and a retraction device, wherein one end of the hatch door is hinged with one end of the door frame, the other end of the hatch door is connected with the other end of the door frame through the retraction device, the door frame is fixed on an aircraft body, the retraction device comprises an air spring, a first rocker arm and a second rocker arm, the first rocker arm is of a rod-shaped structure, the first rocker arm is hinged with a front end rod of the second rocker arm, the other end of the first rocker arm is hinged with the other end of the hatch door, a rear end rod of the second rocker arm is of a triangular body shape, the front end rod of the second rocker arm extends to the long side of the triangular body, a third rocker arm with an included angle with the front end rod of the second rocker arm is formed on the outer side edge of the triangular body, the turning part of the second rocker arm and the third rocker arm is hinged on an end frame of the door frame through, the other end of the gas spring is hinged on the side frame of the door frame through a joint.
2. An aircraft maintenance door retraction mechanism according to claim 1 wherein a retraction device is provided on each of the left and right sides of the door frame and the door, the first rocker ends of the two retraction devices being secured by joints to the ends of a torsion tube which is transversely hinged to the proximal end of the door.
3. An aircraft maintenance door retraction mechanism according to claim 1, further comprising a self-locking pull rod, one end of which is hinged to the first rocker arm and the other end of which is hinged to the door.
4. An aircraft maintenance door retraction mechanism according to claim 1, 2 or 3, wherein the gas spring is free and angled relative to the third rocker arm when the door is in the closed position, the first and second rocker arms fold, the maximum compression of the gas spring is achieved when the door is in the open position, and the gas spring and the third rocker arm are aligned and the first and second rocker arms extend in a straight line.
5. An aircraft maintenance door retraction mechanism according to claim 1 wherein said self locking tension rod is connected to the door by a tension rod connection and a castellated plate.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911023119.XA CN110844043A (en) | 2019-10-25 | 2019-10-25 | Retraction mechanism of aircraft maintenance cabin door |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911023119.XA CN110844043A (en) | 2019-10-25 | 2019-10-25 | Retraction mechanism of aircraft maintenance cabin door |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN110844043A true CN110844043A (en) | 2020-02-28 |
Family
ID=69597775
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201911023119.XA Pending CN110844043A (en) | 2019-10-25 | 2019-10-25 | Retraction mechanism of aircraft maintenance cabin door |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN110844043A (en) |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111977022A (en) * | 2020-07-06 | 2020-11-24 | 西安飞机工业（集团）有限责任公司 | Method and test stand for testing functions of aircraft maintenance cabin door |
| CN112208770A (en) * | 2020-10-10 | 2021-01-12 | 江西洪都航空工业集团有限责任公司 | Linkage retraction device for cabin door of exposed equipment of airplane |
| CN112265630A (en) * | 2020-10-27 | 2021-01-26 | 西安航空职业技术学院 | Retraction mechanism of aircraft maintenance cabin door |
| CN112478128A (en) * | 2020-12-02 | 2021-03-12 | 中国航空工业集团公司沈阳飞机设计研究所 | Retraction mechanism and cabin door structure thereof |
| CN115506674A (en) * | 2022-10-09 | 2022-12-23 | 中国航空工业集团公司西安飞机设计研究所 | Cabin door structure |
| CN117550059A (en) * | 2023-10-24 | 2024-02-13 | 湖南山河华宇航空科技有限公司 | Aircraft tail hatch door |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4601446A (en) * | 1983-09-29 | 1986-07-22 | The Boeing Company | Aircraft door counterbalance system |
| DE3806688A1 (en) * | 1988-03-02 | 1989-09-14 | Messerschmitt Boelkow Blohm | OPENING DEVICE FOR AN AIRCRAFT FREIGHT GATE |
| SU1827972A1 (en) * | 1991-04-10 | 1995-11-20 | Ухтомский вертолетный завод им.Н.И.Камова | Retractable footboard of flying vehicle |
| CN2648036Y (en) * | 2003-06-30 | 2004-10-13 | 南京康尼机电新技术有限公司 | Folding ladder for emergent dispersion |
| US20100001136A1 (en) * | 2007-07-31 | 2010-01-07 | B/E Aerospace, Inc. | Aircraft door and method for using the same |
| CN103306598A (en) * | 2012-03-09 | 2013-09-18 | 法克罗Pp公司 | Folding stairs, especially light wooden stairs |
| CN105501431A (en) * | 2015-11-30 | 2016-04-20 | 中航飞机股份有限公司西安飞机分公司 | Retracting and releasing structure for maintenance cabin door at bottom of plane |
| CN109667532A (en) * | 2019-01-03 | 2019-04-23 | 信义超薄玻璃(东莞)有限公司 | Glass production line maintenance platform |
-
2019
- 2019-10-25 CN CN201911023119.XA patent/CN110844043A/en active Pending
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4601446A (en) * | 1983-09-29 | 1986-07-22 | The Boeing Company | Aircraft door counterbalance system |
| DE3806688A1 (en) * | 1988-03-02 | 1989-09-14 | Messerschmitt Boelkow Blohm | OPENING DEVICE FOR AN AIRCRAFT FREIGHT GATE |
| SU1827972A1 (en) * | 1991-04-10 | 1995-11-20 | Ухтомский вертолетный завод им.Н.И.Камова | Retractable footboard of flying vehicle |
| CN2648036Y (en) * | 2003-06-30 | 2004-10-13 | 南京康尼机电新技术有限公司 | Folding ladder for emergent dispersion |
| US20100001136A1 (en) * | 2007-07-31 | 2010-01-07 | B/E Aerospace, Inc. | Aircraft door and method for using the same |
| CN103306598A (en) * | 2012-03-09 | 2013-09-18 | 法克罗Pp公司 | Folding stairs, especially light wooden stairs |
| CN105501431A (en) * | 2015-11-30 | 2016-04-20 | 中航飞机股份有限公司西安飞机分公司 | Retracting and releasing structure for maintenance cabin door at bottom of plane |
| CN109667532A (en) * | 2019-01-03 | 2019-04-23 | 信义超薄玻璃(东莞)有限公司 | Glass production line maintenance platform |
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111977022A (en) * | 2020-07-06 | 2020-11-24 | 西安飞机工业（集团）有限责任公司 | Method and test stand for testing functions of aircraft maintenance cabin door |
| CN111977022B (en) * | 2020-07-06 | 2023-02-10 | 西安飞机工业（集团）有限责任公司 | Airplane maintenance cabin door function test method and test bench |
| CN112208770A (en) * | 2020-10-10 | 2021-01-12 | 江西洪都航空工业集团有限责任公司 | Linkage retraction device for cabin door of exposed equipment of airplane |
| CN112208770B (en) * | 2020-10-10 | 2022-08-26 | 江西洪都航空工业集团有限责任公司 | Cabin door linkage retracting and releasing device for exposed equipment of airplane |
| CN112265630A (en) * | 2020-10-27 | 2021-01-26 | 西安航空职业技术学院 | Retraction mechanism of aircraft maintenance cabin door |
| CN112478128A (en) * | 2020-12-02 | 2021-03-12 | 中国航空工业集团公司沈阳飞机设计研究所 | Retraction mechanism and cabin door structure thereof |
| CN115506674A (en) * | 2022-10-09 | 2022-12-23 | 中国航空工业集团公司西安飞机设计研究所 | Cabin door structure |
| CN115506674B (en) * | 2022-10-09 | 2024-07-05 | 中国航空工业集团公司西安飞机设计研究所 | Cabin door structure |
| CN117550059A (en) * | 2023-10-24 | 2024-02-13 | 湖南山河华宇航空科技有限公司 | Aircraft tail hatch door |
| CN117550059B (en) * | 2023-10-24 | 2024-06-11 | 湖南山河华宇航空科技有限公司 | Aircraft tail hatch door |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN110844043A (en) | Retraction mechanism of aircraft maintenance cabin door | |
| CN107605307B (en) | Switching mechanism, locking mechanism and front self-locking device | |
| CN210391159U (en) | Folding coupler and vehicle | |
| JPH01254488A (en) | Releasing device for freight gate of aircraft | |
| CN218907591U (en) | Folding cabin door driven by actuating cylinder to open and close | |
| CN105056543B (en) | A kind of five connecting rod nose-gears | |
| US11697962B2 (en) | Opening and closing mechanism and train having the same | |
| CN209479659U (en) | Water conservancy diversion cover opening/closing mechanism and pod | |
| CN109736661A (en) | A kind of gull wing door tooling verifying system | |
| CN109184416B (en) | Power hatch cover lifting mechanism of armored car | |
| US4787578A (en) | Weight compensating mechanism particularly for aircraft hatches, doors or gates | |
| CN110439416B (en) | Electric luggage compartment door | |
| WO1998030445A1 (en) | Flapping flying apparatus | |
| CN109050879A (en) | A kind of folding support rod formula wingfold mechanism | |
| CN114165119A (en) | Damping rotating assembly for connecting automobile body and automobile door | |
| CN209534753U (en) | A kind of floating driving lifting bow device of magnetic | |
| CN209469190U (en) | Fold flat-pushing hinge and Flat sliding window | |
| CN209289263U (en) | Operating stick lifting device | |
| CN108035629B (en) | Door lock device of blanking door of tea rolling machine | |
| CN215169243U (en) | Special anti-drop structure of high-rise building horizontal sliding door and window | |
| CN208337019U (en) | A kind of suspension clamp replacement tool | |
| CN206141863U (en) | Connecting bridge stretches out and draws back and hides fluffy mechanism | |
| CN220504818U (en) | Tower crane cab door injury prevention device | |
| CN220687150U (en) | Safety protection device for deflection of rotary wing | |
| CN216491582U (en) | Double-door type flip 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 | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20200228 |
|
| WD01 | Invention patent application deemed withdrawn after publication |