CN102235125A - Limiting mechanism for airplane cabin doors - Google Patents
Limiting mechanism for airplane cabin doors Download PDFInfo
- Publication number
- CN102235125A CN102235125A CN2010101684113A CN201010168411A CN102235125A CN 102235125 A CN102235125 A CN 102235125A CN 2010101684113 A CN2010101684113 A CN 2010101684113A CN 201010168411 A CN201010168411 A CN 201010168411A CN 102235125 A CN102235125 A CN 102235125A
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- hatch door
- bracing frame
- stopper arms
- limit mechanism
- ear
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Abstract
The invention provides a limiting mechanism for airplane cabin doors, which can be used in airplane electronic cabins incapable of providing a larger layout space. The limiting mechanism comprises a stop arm, an opening handle, a torsional spring, a limiting element, a plug-in ear, a supporting bracket, an anchoring element and the like, wherein the stop arm and the opening handle are respectively pivotally arranged on two parallelly-spaced vertical webs of the supporting bracket, and can pivotally rotate around a pivot crossly arranged on the two vertical webs; and the torsional spring is sleeved on the pivot and arranged between the stop arm and the opening handle, thereby driving the stop arm and the opening handle to move synchronously. The limiting mechanism disclosed by the invention is simple in structure, and has no high requirements for mounting spaces while the automatic limiting and fixation of opening of cabin doors are ensured.
Description
Technical field
The present invention relates to a kind of aircraft door position-limit mechanism, especially the structural position-limit mechanism of civil aircraft electronic equipment cabin door.
Background technology
Be provided with electronics bay below the driving cabin of aircraft, equipment compartment is equipped with hatch door to make things convenient for maintainer's access device cabin.Usually, the hatch door of equipment compartment need be equipped with position-limit mechanism, causes the damage of door and equipment frame to avoid hatch door to bump against equipment frame in unrestricted rotation process; Accident falls and closes in the time of also can avoiding simultaneously hatch door to only depend on deadweight to rest on the equipment frame, and maintenance personal and hatch door structure are damaged.
At present, the position-limit mechanism that generally uses on each civil aircraft mostly is installed in aircraft door away from rotating shaft place, and this structure can make that the arm of force was bigger when mechanism acted on the hatch door, only need propose less requirement of strength to this mechanism by the big arm of force.Yet, can provide this position-limit mechanism of the big arm of force all need provide bigger arrangement space away from rotating shaft one end at hatch door.Yet, be not that each aircraft can both be arranged for the hatch door position-limit mechanism provide big space, if in case in the cabin of aircraft environment can not give the spacing headspace of hatch door, just can't design traditional fixed limit mechanism for hatch door.
Summary of the invention
The object of the present invention is to provide a kind of simple in structure, aircraft door position-limit mechanism that requirements of installation space is not high.
For achieving the above object, aircraft door according to the present invention with position-limit mechanism by utilizing same axis to pivot to be installed on the stopper arms on the bracing frame and opening handle and an end is fixedlyed connected the other end and the torsionspring of unlatching handle flexible connection and realized the opening and closing of hatch door with bracing frame.In the hatch door opening procedure, hatch door limits it by locating part and continues motion when moving near vertical position, and subsequently by stopper arms be positioned at hatch door on slotting ear and the spacing bearing pin that is positioned on the bracing frame cooperate to come stop; When need were closed hatch door, as long as rotarily open handle, stopper arms rotated synchronously with handle, and stopper arms upwards lifts simultaneously, threw off with slotting ear, and rotate hatch door this moment, can realize closing.
According to an aspect of the present invention, aircraft door position-limit mechanism of the present invention, it comprises the bracing frame that is fixedly mounted on the hatch door doorframe, this bracing frame is equipped with the rotating shaft of aircraft door so that hatch door can rotate around this rotating shaft, wherein, this position-limit mechanism also comprises: a stopper arms, its bottom are installed on the bracing frame pivotly, and another free end forms hook portion; One opens handle, and its bottom is installed on the bracing frame pivotly, and another free end forms grip part, and the installation that pivots around the two ends of same pivot of described unlatching handle and described stopper arms; One torsionspring, it is set on the described pivot, and the one end is fixedlyed connected the other end and the flexible connection of unlatching handle with bracing frame; One locating part, it is positioned on the fixed mount, is used for limiting when hatch door moves upward to the precalculated position being moved further of hatch door; One inserts ear, and it is positioned on the hatch door, should insert ear and engage with the hook portion of stopper arms after hatch door moves up limited stop; One anchor, it is fixed on the bracing frame, is used for supporting stopper arms from downside when stopper arms combines with slotting ear.
Further, under the hatch door open mode, the hook portion of described stopper arms equals to insert the distance of ear to the hatch door rotating shaft to the distance of hatch door rotating shaft.
Described torsionspring one end hook is connected with unlatching handle formation activity, other end hook is fixedly coupled with the bracing frame formation, and the axis pin of the spring that protrusion is arranged respectively being set in a side of opening close torsionspring on handle and the bracing frame, described hook is articulated on the axis pin of the spring.
Described locating part is preferably stop screw.
Support frame as described above has two parallel spaced vertical web, and described pivot is installed across these two vertical web.
Locking mechanism of the present invention is owing to be to overlap position-limit mechanism in the root rotating shaft place design and installation one of hatch door hinge arms, so can be reserved the less aircraft in space uses, utilize the rebound effect of torsionspring, the stop and the locking of hatch door can be finished in same operating process, by insert on stopper arms and the hatch door ear cooperate and stopper arms with guarantee the automatic spacing that hatch door is opened cooperating of spacing bearing pin and fix, collision injury equipment frame can be avoided, the hatch door obscission that do not meet accident can be guaranteed again.
Description of drawings
Fig. 1 is the stereogram that hatch door position-limit mechanism according to the present invention is in the hatch door buttoned-up status;
Fig. 2 is that hatch door position-limit mechanism according to the present invention is in the stereogram that hatch door is opened the back state fully;
Fig. 3 is the view of another angle of the hatch door position-limit mechanism among Fig. 2;
Fig. 4 inserts ear to move into progress figure with the stopper arms engagement state on the hatch door.
Wherein, the label declaration among the figure is as follows:
The 1-stopper arms; The 101-hook portion
2-opens handle; The 201-grip part; The 202-axis pin of the spring
The 3-torsionspring; The 301-hook
The 4-locating part
5-inserts ear
The 6-hatch door; 601-hatch door hinge arms
The 7-bracing frame; 701, the 702-vertical web
The spacing bearing pin of 8-
The rotating shaft of 9-hatch door
The 10-pivot
The dividing plate of 11-hatch door doorframe
The specific embodiment
Fig. 1-4 shows the preferred implementation of aircraft door of the present invention with position-limit mechanism.
At first, shown in Fig. 1-2, aircraft door of the present invention comprises stopper arms 1 with position-limit mechanism, open handle 2, torsionspring 3, locating part 4, insert ear 5, bracing frame 7, anchor 8 etc., wherein stopper arms 1 and unlatching handle 2 are installed in two parallel spaced vertical web 71 of bracing frame 7 respectively pivotally, on 72, can be around being crossed on two vertical web 71, pivot 10 on 72 pivots, torsionspring 3 is sleeved on the pivot 10 and at stopper arms 1 with open between the handle 2, the one end is fixedly attached on the bracing frame 7, and the other end hangs over by the hook 301 that forms and opens on the handle 1 inboard bearing pin 202 that protrudes.
From Fig. 1-2 as can be seen, a whole set of position-limit mechanism is positioned at hatch door rotating shaft 9 places near hinge arms 601 roots of hatch door 6, wherein, bracing frame 7 is fixedly mounted on the dividing plate 11 of doorframe of hatch door 6, hatch door rotating shaft 9 is fixed on this bracing frame 7, thereby hatch door 6 can rotate around this rotating shaft 9, move to subvertical unlatching from the fastening position of level till, perhaps be turned back to the fastening position of level from subvertical enable possition.
Need to prove, be moved upward in the process of open position at hatch door 6, hatch door is not unrestrictedly to move upward, but near the upright position time by being positioned at the locating part 4 of hatch door one side on the bracing frame 7, for example can be that the continuation that stop screw stops hatch door 6 is moved.Subsequently, the slotting ear 5 on hatch door 6 hook portion 101 that relies on stopper arms 1 and the hatch door hinge arms 601 combine and anchor 8 (for example spacing bearing pin) is still in open mode near the upright position from downside to the support of stopper arms 1.
Refer again to Fig. 1-2, because pivot 10 passes the web 71,72 of bracing frame (7), two ends are affixed with stopper arms 1 and handle 2 respectively, can stopper arms 1 and the synchronous rotation of handle 2; In addition, owing to twining torsionspring 3 on the pivot 10, the one end hook 301 of spring and axis pin of the spring 202 overlap joints on the handle 2, other end hook (figure does not show) is overlapped on the axis pin of the spring (figure does not show) of bracing frame 7, when upwards stirring stopper arms 1, the unlatching handle 2 of pivot 10 other ends and then rotates synchronously; Axis pin of the spring 202 pulling torsionsprings 3 on the handle 2, camber of spring.If unclamp stopper arms 1 this moment, under the restoring force effect of spring 3, stopper arms 1 can downward resilience.
Because spacing bearing pin 8 passes bracing frame 7 and is fixed on the bracing frame 7, and when being positioned at stopper arms 1 and clockwise rotating near on the downside of hatch door 6, stopper arms 1 is stopped by this bearing pin 8 in springback process, and rests on the position shown in Fig. 1.
The operating principle of hatch door position-limit mechanism in the opening and closing process is once described below with reference to accompanying drawings.
When the electronics bay of aircraft need overhaul, the operator upwards promoted hatch door 6 by horizontal level with hand.In the hatch door opening procedure, hatch door 6 and hatch door hinge arms 601 upwards promote around hatch door rotating shaft 9.Be fixed in cylindrical slotting ear 5 on the hinge arms 6 along with being synchronized with the movement.The distance of inserting between ear 5 and the hatch door rotating shaft 9 is equal to the distance of stopper arms 1 free-ended hook portion 101 to hatch door rotating shaft 9.After hatch door 6 rotated certain angle, the slotting ear 5 on the hinge arms 601 at first contacted with the end of the hook portion 101 of stopper arms 1, and stopper arms is flicked; Be rotated further hatch door, insert ear 5 stopper arms 1 is lifted, turn over smaller angle, stopper arms resilience under the restoring force of torsionspring, and ride on the slotting ear 5.Be rotated further hatch door, with till locating part 4 contacts, hatch door can not continue upwards to rotate until hinge arms 6.In this process, under the effect of torsion spring, the downside of stopper arms 1 remains with slotting ear 5 and contacts.
Fig. 4 shows the movement locus of cylindrical slotting ear 5 relative stopper arms hook portions 101.The following side contacts of cylindrical slotting ear 5 and stopper arms hook portion 101 after stopper arms 1 resilience, after this insert ear 5 along 101 times lateral movements of stopper arms hook portion up to end; Finally insert ear 5 and continue motion by the terminal inboard restriction of stopper arms hook portion 101.
In the hatch door opening procedure, after the downside of stopper arms 1 and slotting ear 5 keep in touch, continue upwards to rotate hatch door, thereby can bumping against locating part 4 subsequently, hatch door 6 stop door further to be opened.And after inserting 101 times side contacts of hook portion of ear 5 and stopper arms 1, can be along the curved surface of stopper arms downside towards stopper arms central motion one segment distance.At this moment, the operator rotates hatch door less angle again, for example can be about 2 °-5 °, can allow the hook portion 101 of stopper arms hook fully like this and insert ear 5, the center of gravity that also can avoid hatch door 6 simultaneously is on the peak and cause hatch door unstability on the position of opening fully.
After rotating the less angle of hatch door 6, stopper arms 1 limited bearing pin 8 restrictions continue to rotate.Insert ear 5 and fastened fully by the hook portion 101 of stopper arms 1 immediately, and be limited to continue to rotate.Whole hatch door is fixed on this position, as shown in Figure 2.The hatch door opening procedure finishes.
Fastened by stopper arms 1 owing to insert ear 5, whole hatch door 6 and hatch door hinge arms 601 can't rotate, and keep this state until needs hatch door to be closed behind the hatch door complete opening.
Below in conjunction with Fig. 2 the process that hatch door is closed is described.When closing hatch door, the operator buttresses hatch door door body on the other hand, upwards lifts hatch door to small angle, and the hook portion 101 of stopper arms 1 and slotting ear 5 are thrown off; Another holds the grip part 201 of opening handle 2, rotates counterclockwise handle 2, and stopper arms 1 is lifted simultaneously, lifts certain angle, till slotting ear 5 exposes from the hook portion 101 of stopper arms 1 fully; After slotting ear 5 exposes the hook portion 101 of stopper arms 1 fully, rotate hatch door 6, release handle 2 after a while, and stopper arms 1 recoils to the initial position shown in Fig. 1 under the effect of torsionspring 3; At this moment, rotate hatch door, close hatch door to complete fastening position.
Claims (6)
1. aircraft door position-limit mechanism, it comprises the bracing frame (7) that is fixedly mounted on the hatch door doorframe, this bracing frame (7) is equipped with the rotating shaft (9) of aircraft door so that hatch door can rotate around this rotating shaft, it is characterized in that this position-limit mechanism also comprises:
One stopper arms (1), its bottom are installed on the bracing frame (7) pivotly, and another free end forms hook portion (101);
One opens handle (2), and its bottom is installed on the bracing frame (7) pivotly, and another free end forms grip part (201), and the installation that pivots around the two ends of same pivot (10) of described unlatching handle and described stopper arms;
One torsionspring (3), it is set on the described pivot (10), and the one end is fixedlyed connected the other end and unlatching handle (1) flexible connection with bracing frame (7);
One locating part (4), it is positioned on the fixed mount (7), is used for limiting when hatch door moves upward to the precalculated position being moved further of hatch door;
One inserts ear (5), and it is positioned on the hatch door, should insert ear (5) and engage with the hook portion (101) of stopper arms (1) after hatch door moves up limited (4) stop;
One anchor (8), it is fixed on the bracing frame (7), is used for from downside supporting stopper arms (1) with slotting ear (5) when combining at stopper arms (1).
2. aircraft door position-limit mechanism as claimed in claim 1 is characterized in that, under the hatch door open mode, the hook portion (101) of described stopper arms (1) equals to insert the distance of ear (5) to hatch door rotating shaft (9) to the distance of hatch door rotating shaft (9).
3. aircraft door position-limit mechanism as claimed in claim 1 is characterized in that, described torsionspring (3) one ends hooks (301) are connected with the formation activity of unlatching handle (2), and other end hook is fixedly coupled with bracing frame (7) formation.
4. aircraft door position-limit mechanism as claimed in claim 3 is characterized in that, goes up the bearing pin that is respectively arranged with protrusion near a side of torsionspring (3) at described unlatching handle (2) and bracing frame (7), and described hook is overlapped on the described bearing pin.
5. aircraft door position-limit mechanism as claimed in claim 1 is characterized in that, described locating part (4) is a stop screw.
6. as each described aircraft door position-limit mechanism of claim 1-5, it is characterized in that support frame as described above (7) has two parallel spaced vertical web (701,702), described pivot (10) is installed across these two vertical web (701,702).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201010168411.3A CN102235125B (en) | 2010-05-06 | 2010-05-06 | Limiting mechanism for airplane cabin doors |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201010168411.3A CN102235125B (en) | 2010-05-06 | 2010-05-06 | Limiting mechanism for airplane cabin doors |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN102235125A true CN102235125A (en) | 2011-11-09 |
| CN102235125B CN102235125B (en) | 2014-04-16 |
Family
ID=44886191
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201010168411.3A Active CN102235125B (en) | 2010-05-06 | 2010-05-06 | Limiting mechanism for airplane cabin doors |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN102235125B (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2015010271A1 (en) * | 2013-07-24 | 2015-01-29 | Mra Systems, Inc. | Engine door and latch assembly |
| CN106639701A (en) * | 2016-12-14 | 2017-05-10 | 中航通飞研究院有限公司 | Cabin door limiting and locking mechanism |
| CN107271160A (en) * | 2017-06-02 | 2017-10-20 | 中国商用飞机有限责任公司 | A kind of test method for verifying aircraft door durability switching function |
| CN107271161A (en) * | 2017-06-02 | 2017-10-20 | 中国商用飞机有限责任公司 | A kind of aircraft door durability test device |
| CN107605285A (en) * | 2017-11-09 | 2018-01-19 | 徐工集团工程机械股份有限公司科技分公司 | A kind of side door limiting fixing mechanism of engine shroud |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1167182A2 (en) * | 2000-06-29 | 2002-01-02 | ESW-EXTEL SYSTEMS WEDEL Gesellschaft für Ausrüstung mbH | Device for electrically operating an aircraft door |
| US7070016B1 (en) * | 2005-03-18 | 2006-07-04 | Paccar Inc | Apparatus for vehicle hood |
| CN2799782Y (en) * | 2005-05-30 | 2006-07-26 | 许振荣 | Door stopper for cash truck |
| CN201220748Y (en) * | 2008-05-28 | 2009-04-15 | 江西洪都航空工业集团有限责任公司 | Balancing unit is opened to formula cabin cover that turns on one's side |
| US20090113954A1 (en) * | 2006-03-22 | 2009-05-07 | Latecoere | Locking system for an aircraft door, especially for an airplane passenger door |
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2010
- 2010-05-06 CN CN201010168411.3A patent/CN102235125B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1167182A2 (en) * | 2000-06-29 | 2002-01-02 | ESW-EXTEL SYSTEMS WEDEL Gesellschaft für Ausrüstung mbH | Device for electrically operating an aircraft door |
| US7070016B1 (en) * | 2005-03-18 | 2006-07-04 | Paccar Inc | Apparatus for vehicle hood |
| CN2799782Y (en) * | 2005-05-30 | 2006-07-26 | 许振荣 | Door stopper for cash truck |
| US20090113954A1 (en) * | 2006-03-22 | 2009-05-07 | Latecoere | Locking system for an aircraft door, especially for an airplane passenger door |
| CN201220748Y (en) * | 2008-05-28 | 2009-04-15 | 江西洪都航空工业集团有限责任公司 | Balancing unit is opened to formula cabin cover that turns on one's side |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2015010271A1 (en) * | 2013-07-24 | 2015-01-29 | Mra Systems, Inc. | Engine door and latch assembly |
| US11060331B2 (en) | 2013-07-24 | 2021-07-13 | Mra Systems, Llc | Engine door and latch assembly |
| CN106639701A (en) * | 2016-12-14 | 2017-05-10 | 中航通飞研究院有限公司 | Cabin door limiting and locking mechanism |
| CN107271160A (en) * | 2017-06-02 | 2017-10-20 | 中国商用飞机有限责任公司 | A kind of test method for verifying aircraft door durability switching function |
| CN107271161A (en) * | 2017-06-02 | 2017-10-20 | 中国商用飞机有限责任公司 | A kind of aircraft door durability test device |
| CN107605285A (en) * | 2017-11-09 | 2018-01-19 | 徐工集团工程机械股份有限公司科技分公司 | A kind of side door limiting fixing mechanism of engine shroud |
Also Published As
| Publication number | Publication date |
|---|---|
| CN102235125B (en) | 2014-04-16 |
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