CN117513907A - Aircraft cabin door opening and retaining mechanism - Google Patents
Aircraft cabin door opening and retaining mechanism Download PDFInfo
- Publication number
- CN117513907A CN117513907A CN202311530865.4A CN202311530865A CN117513907A CN 117513907 A CN117513907 A CN 117513907A CN 202311530865 A CN202311530865 A CN 202311530865A CN 117513907 A CN117513907 A CN 117513907A
- Authority
- CN
- China
- Prior art keywords
- support
- cabin door
- transmission
- lock hook
- mandrel
- 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 27
- 230000005540 biological transmission Effects 0.000 claims description 58
- 125000006850 spacer group Chemical group 0.000 claims description 14
- 238000000034 method Methods 0.000 claims description 4
- 230000008569 process Effects 0.000 claims description 4
- 230000000903 blocking effect Effects 0.000 claims 1
- 230000007774 longterm Effects 0.000 abstract description 4
- 230000000694 effects Effects 0.000 abstract description 3
- 238000001125 extrusion Methods 0.000 abstract description 3
- 230000007704 transition Effects 0.000 abstract description 3
- 238000012423 maintenance Methods 0.000 abstract 1
- 230000014759 maintenance of location Effects 0.000 description 3
- 238000005299 abrasion Methods 0.000 description 2
- 230000009471 action Effects 0.000 description 2
- 238000003754 machining Methods 0.000 description 2
- 238000006467 substitution reaction Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 239000013585 weight reducing agent Substances 0.000 description 1
Classifications
-
- E—FIXED CONSTRUCTIONS
- E05—LOCKS; KEYS; WINDOW OR DOOR FITTINGS; SAFES
- E05D—HINGES OR SUSPENSION DEVICES FOR DOORS, WINDOWS OR WINGS
- E05D11/00—Additional features or accessories of hinges
- E05D11/10—Devices for preventing movement between relatively-movable hinge parts
- E05D11/1014—Devices for preventing movement between relatively-movable hinge parts for maintaining the hinge in only one position, e.g. closed
-
- 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
-
- E—FIXED CONSTRUCTIONS
- E05—LOCKS; KEYS; WINDOW OR DOOR FITTINGS; SAFES
- E05D—HINGES OR SUSPENSION DEVICES FOR DOORS, WINDOWS OR WINGS
- E05D5/00—Construction of single parts, e.g. the parts for attachment
- E05D5/02—Parts for attachment, e.g. flaps
Abstract
The application belongs to the technical field of aircraft cabin door opening and holding mechanism design, concretely relates to aircraft cabin door opening and holding mechanism, the design utilizes torsion spring to carry out the position maintenance, when the hatch door is opened, with the help of the extrusion of second support, make the head of latch hook in the locked groove, realize the automatic locking to the hatch door, when closing the hatch door, with the control handle operation, make the head of latch hook break away from the locked groove, and in the drive mechanism, with the gyro wheel, the slotted hole carries out the transition, have the activity margin, can reduce the precision requirement to processing and assembly, avoid opening, closing the hatch door and interfere, and can compensate the wearing and tearing that long-term use takes place between the part, can be with the reliable locking of hatch door in the open position.
Description
Technical Field
The application belongs to the technical field of aircraft cabin door opening and holding mechanism design, and particularly relates to an aircraft cabin door opening and holding mechanism.
Background
The transportation type aircraft cabin door is hinged on the door frame through the cabin door, and is opened in an outward translation mode, so that the cabin door is prevented from shaking and colliding with the machine body and being closed accidentally after being opened, and an opening retaining mechanism is designed to lock the cabin door at an opening position.
Currently, the holding mechanism is opened, the cooperation between the cabin door and the door frame is designed through the lock pin and the lock hook, the handle is controlled through the transmission mechanism, and the cabin door is locked after being opened, so that the following defects exist:
1) The cabin door cannot be automatically locked after being opened, and in practice, the situation that the cabin door is forgotten to be locked often exists;
2) The lock pin and the lock hook are complex in matching profile, have extremely high precision requirements on machining and assembling, in practice, machining and assembling errors are difficult to avoid, interference with opening and closing of the cabin door is easy to occur, abrasion is easy to occur among long-term use components, and reliable locking of the cabin door at an opening position is difficult to achieve;
3) The aircraft has the advantages of complex structure and numerous parts, and increases the weight of the aircraft as a whole, which is not in line with the current weight reduction requirement of the aircraft.
The present application has been made in view of the existence of the above-mentioned technical drawbacks.
It should be noted that the above disclosure of the background art is only for aiding in understanding the inventive concept and technical solution of the present application, which is not necessarily prior art to the present application, and should not be used for evaluating the novelty and creativity of the present application in the case where no clear evidence indicates that the above content has been disclosed at the filing date of the present application.
Disclosure of Invention
It is an object of the present application to provide an aircraft door opening and retaining mechanism that overcomes or alleviates at least one of the known technical drawbacks.
The technical scheme of the application is as follows:
an aircraft door opening retention mechanism comprising: the device comprises a cabin door hinge, a first support, a second support, a handle support, a control handle, a transmission rocker arm, a transmission shaft, a transmission pull rod, a lock hook, a torsion spring, a support shaft and a mandrel;
the first support and the second support are connected to the door frame, wherein the second support is provided with a locking groove;
the cabin door hinge is hinged to the first support and the second support;
the handle support is connected to the cabin door hinge;
the transmission shaft is arranged on the handle support;
the control handle is connected to the transmission shaft;
the transmission rocker arm is connected to the transmission shaft;
the mandrel is arranged on the cabin door hinge and is provided with a protruding part, and the protruding part is provided with a slotted hole;
one end of the transmission pull rod is hinged on the transmission rocker arm, and the other end of the transmission pull rod is provided with a roller which is clamped in the oblong hole;
the lock hook is connected to the mandrel and is provided with a stop protrusion;
two ends of the supporting shaft are arranged on the cabin door hinge through the support;
the torsion spring is wound on the lock hook, two ends of the torsion spring are connected to the support shaft, the stop protrusion is abutted against the support shaft by virtue of elastic force, and one end of the oblong hole is contacted with the roller;
in the opening process of the cabin door, the cabin door hinge rotates to enable the lock hook to touch the second support, the lock hook is blocked by the second support and rotates, when the cabin door reaches the opening position, the head of the lock hook bypasses the surface of the second support, and under the action of the elastic force of the torsion spring, the lock hook is hooked into the lock groove to lock the cabin door at the opening position;
when the cabin door is closed, the control handle is pulled, the transmission rocker arm is driven to rotate through the transmission shaft, the mandrel is driven to rotate through the transmission pull rod and the idler wheels of the transmission pull rod, the lock hook is driven to rotate, the head of the lock hook is separated from the lock groove, and the cabin door can be closed.
Optionally, in the above aircraft door opening and holding mechanism, the aircraft door opening and holding mechanism further includes a first spacer and a second spacer;
the first spacer bush and the second spacer bush are sleeved on the periphery of the mandrel and are positioned on two sides of the lock hook.
Optionally, in the above-mentioned aircraft cabin door opening and holding mechanism, a knuckle bearing is disposed between the transmission pull rod and the transmission rocker arm.
Optionally, in the above-mentioned aircraft cabin door opening and holding mechanism, the latch hook and the core shaft are connected in a spline fit.
The application has at least the following beneficial technical effects:
the utility model provides a hold mechanism is opened to aircraft hatch door, the design utilizes torsion spring to carry out the position retention, when the hatch door is opened, with the help of the extrusion of second support, make the head of latch hook in the locked groove, realize the automatic locking to the hatch door, when closing the hatch door, with the control handle operation, make the head of latch hook break away from the locked groove, and simple overall structure, and in the drive mechanism, with gyro wheel, the slotted hole carries out the transition, have the activity allowance, can reduce the precision requirement to processing and assembly, avoid opening, closing to the hatch door and take place to interfere, and can compensate the wearing and tearing that long-term use takes place between the part, can reliably lock the hatch door in the open position.
Drawings
Fig. 1 is a schematic structural view of an aircraft door opening and retaining mechanism provided in an embodiment of the present application;
FIG. 2 is an assembled schematic view of an aircraft door opening and retaining mechanism provided in an embodiment of the present application;
fig. 3 is a schematic view of a door provided in an embodiment of the present application when opened;
fig. 4 is a schematic view of a door provided in an embodiment of the present application when closed;
wherein:
1-cabin door hinge; 2-a first support; 3-a second support; 4-a handle support; 5-manipulating the handle; 6-driving rocker arms; 7-a transmission shaft; 8-a transmission pull rod; 9-latch hooks; 10-a first spacer; 11-torsion springs; 12-a second spacer; 13-a support shaft; 14-mandrel.
For the purpose of better illustrating the present embodiments, certain elements of the drawings may be omitted, enlarged or reduced and do not represent the actual product dimensions, and furthermore, the drawings are for illustrative purposes only and are not to be construed as limiting the present patent.
Detailed Description
In order to make the technical solution of the present application and the advantages thereof more apparent, the technical solution of the present application will be more fully described in detail below with reference to the accompanying drawings, it being understood that the specific embodiments described herein are only some of the embodiments of the present application, which are for explanation of the present application, not for limitation of the present application. It should be noted that, for convenience of description, only the portion relevant to the present application is shown in the drawings, and other relevant portions may refer to a general design, and without conflict, the embodiments and technical features in the embodiments may be combined with each other to obtain new embodiments.
Furthermore, unless defined otherwise, technical or scientific terms used in the description of this application should be given the ordinary meaning as understood by one of ordinary skill in the art to which this application belongs. The terms "upper," "lower," "left," "right," "center," "vertical," "horizontal," "inner," "outer," and the like as used in this description are merely used to indicate relative directions or positional relationships, and do not imply that a device or element must have a particular orientation, be configured and operated in a particular orientation, and that the relative positional relationships may be changed when the absolute position of the object being described is changed, and thus should not be construed as limiting the present application. The terms "first," "second," "third," and the like, as used in the description herein, are used for descriptive purposes only and are not to be construed as indicating or implying any particular importance to the various components. The use of the terms "a," "an," or "the" and similar referents in the description of the invention are not to be construed as limited in number to the precise location of at least one. As used in this description, the terms "comprises," "comprising," or the like are intended to cover an element or article that appears before the term and that is listed after the term and its equivalents, without excluding other elements or articles.
Furthermore, unless specifically stated and limited otherwise, the terms "mounted," "connected," and the like in the description herein are to be construed broadly and refer to either a fixed connection, a removable connection, or an integral connection, for example; can be mechanically or electrically connected; can be directly connected or indirectly connected through an intermediate medium, and can also be communicated with the inside of two elements, and the specific meaning of the two elements can be understood by a person skilled in the art according to specific situations.
The present application is described in further detail below with reference to fig. 1-4.
An aircraft door opening retention mechanism comprising: the cabin door hinge 1, the first support 2, the second support 3, the handle support 4, the control handle 5, the transmission rocker 6, the transmission shaft 7, the transmission pull rod 8, the lock hook 9, the first spacer bush 10, the torsion spring 11, the second spacer bush 12, the support shaft 13 and the mandrel 14 are shown in fig. 1-2.
The first support 2 and the second support 3 are connected to the door frame, and particularly can be connected through bolts, wherein the second support 3 is provided with a locking groove.
The cabin door hinge 1 is hinged on the first support 2 and the second support 3, and can be particularly hinged through a pin shaft by matching with a single-double-lug structure.
The handle support 4 is connected to the hatch door hinge 1, in particular by means of a screw connection.
The transmission shaft 7 is mounted on the handle support 4, and the handle support 4 can be specifically designed to be in a double-ear structure, and the transmission shaft 7 is mounted in the double-ear hole.
The control handle 5 is connected to the transmission shaft 7, and can be specifically sleeved on the transmission shaft 7 through a through hole.
The transmission rocker arm 6 is connected to the transmission shaft 7, and can be sleeved on the transmission shaft 7 through a through hole.
The two ends of the mandrel 14 are arranged on the cabin door hinge 1 through the support, and the mandrel is provided with a protruding part, and the protruding part is provided with a long round hole.
One end of the transmission pull rod 8 is hinged to the transmission rocker arm 6, the transmission pull rod is matched with the transmission rocker arm through a single-double-lug structure, the transmission rocker arm is hinged through a pin shaft, a joint bearing can be arranged, a roller is arranged at the other end of the transmission pull rod, the transmission pull rod can be specifically designed into a double-lug structure, the roller is installed between two lugs through the pin shaft, and the roller is clamped in a long round hole.
The latch hook 9 is connected to the spindle 14, in particular by means of a through-hole which is sleeved on the spindle 14 and can be connected in a spline fit, on which a stop projection is provided.
The first spacer bush 10 and the second spacer bush 12 are sleeved on the periphery of the mandrel 14 and are positioned on two sides of the lock hook 9.
The two ends of the supporting shaft 13 are arranged on the cabin door hinge 1 through the supporting seats.
The torsion spring 11 is wound on the lock hook 9, two ends of the torsion spring are connected to the support shaft 13, the torsion spring can be sleeved on the support shaft 13 through a through hole, and an anticlockwise rotation trend is generated on the lock hook 9 and the mandrel 14 by means of elastic force, so that the stop protrusion is abutted to the support shaft 13, and one end of the oblong hole is contacted with the roller.
In the opening process of the cabin door, the cabin door hinge 1 rotates clockwise, so that the lock hook 9 touches the second support 3, the lock hook 9 is blocked by the second support 3 to rotate anticlockwise, when the cabin door reaches the opening position, the head of the lock hook 9 bypasses the surface of the second support 3, and rotates clockwise under the elastic force of the torsion spring 11 to be hooked into the locking groove, thereby locking the cabin door at the opening position, as shown in fig. 3, in the process, the mandrel 14 and the lock hook 9 rotate synchronously, the roller rolls in the oblong hole, and the transmission pull rod 8, the transmission rocker 6, the transmission shaft 7 and the control handle 5 do not act.
When the cabin door is closed, the control handle 5 is pulled anticlockwise, the transmission rocker arm 6 is driven to rotate anticlockwise through the transmission shaft 7, the mandrel 14 is pushed to rotate anticlockwise through the transmission pull rod 8 and the idler wheels of the transmission pull rod, the lock hook 9 is driven to rotate anticlockwise, the head of the lock hook 9 is separated from the lock groove, the cabin door can be further closed, after the control handle 5 is loosened, all components are automatically reset under the action of the elastic force of the torsion spring 11, and the cabin door is shown in fig. 4.
The aircraft cabin door opening and holding mechanism disclosed in the above embodiment uses the torsion spring 11 to perform position holding, when the cabin door is opened, the head of the lock hook 9 is hooked into the lock groove by means of extrusion of the second support 3, automatic locking of the cabin door is realized, when the cabin door is closed, the head of the lock hook 9 is controlled by the control handle 5, the head of the lock hook 9 is separated from the lock groove, the whole structure is simple, in the transmission mechanism, the roller and the oblong hole are used for transition, the movement allowance is provided, the precision requirements on processing and assembly of the cabin door can be reduced, interference on opening and closing of the cabin door is avoided, abrasion caused by long-term use among components can be compensated, and the cabin door can be reliably locked at the opening position.
Having thus described the technical aspects of the present application with reference to the preferred embodiments illustrated in the accompanying drawings, it should be understood by those skilled in the art that the scope of the present application is not limited to the specific embodiments, and those skilled in the art may make equivalent changes or substitutions to the relevant technical features without departing from the principles of the present application, and those changes or substitutions will now fall within the scope of the present application.
Claims (4)
1. An aircraft door opening and retaining mechanism comprising: the cabin door hinge (1), the first support (2), the second support (3), the handle support (4), the control handle (5), the transmission rocker arm (6), the transmission shaft (7), the transmission pull rod (8), the lock hook (9), the torsion spring (11), the support shaft (13) and the mandrel (14);
the first support (2) and the second support (3) are connected to the door frame, wherein the second support (3) is provided with a locking groove;
the cabin door hinge (1) is hinged on the first support (2) and the second support (3);
the handle support (4) is connected to the cabin door hinge (1);
the transmission shaft (7) is arranged on the handle support (4);
the control handle (5) is connected to the transmission shaft (7);
the transmission rocker arm (6) is connected to the transmission shaft (7);
the mandrel (14) is arranged on the cabin door hinge (1) and is provided with a protruding part, and the protruding part is provided with a slotted hole;
one end of a transmission pull rod (8) is hinged on the transmission rocker arm (6), and the other end is provided with a roller which is clamped in the oblong hole;
the latch hook (9) is connected to the mandrel (14) and is provided with a stop protrusion;
two ends of the supporting shaft (13) are arranged on the cabin door hinge (1) through the support;
the torsion spring (11) is wound on the lock hook (9), two ends of the torsion spring are connected to the support shaft (13), the stop protrusion is abutted on the support shaft (13) by virtue of elastic force, and one end of the oblong hole is contacted with the roller;
in the opening process of the cabin door, the cabin door hinge (1) rotates to enable the lock hook (9) to touch the second support (3), the lock hook (9) rotates under the blocking of the second support (3), when the cabin door reaches the opening position, the head of the lock hook (9) bypasses the surface of the second support (3), and under the elastic force of the torsion spring (11), the lock hook is hooked into the lock groove to lock the cabin door at the opening position;
when the cabin door is closed, the control handle (5) is pulled, the transmission rocker arm (6) is driven to rotate through the transmission shaft (7), the mandrel (14) is pushed to rotate through the transmission pull rod (8) and the idler wheels thereof, the lock hook (9) is driven to rotate, the head of the lock hook (9) is separated from the lock groove, and then the cabin door can be closed.
2. The aircraft door opening and retaining mechanism according to claim 1, further comprising a first spacer (10), a second spacer (12);
the first spacer bush (10) and the second spacer bush (12) are sleeved on the periphery of the mandrel (14) and are positioned on two sides of the lock hook (9).
3. The aircraft door opening and retaining mechanism according to claim 1, wherein,
a joint bearing is arranged between the transmission pull rod (8) and the transmission rocker arm (6).
4. The aircraft door opening and retaining mechanism according to claim 1, wherein,
the lock hook (9) and the mandrel (14) are connected in a spline fit mode.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311530865.4A CN117513907A (en) | 2023-11-16 | 2023-11-16 | Aircraft cabin door opening and retaining mechanism |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311530865.4A CN117513907A (en) | 2023-11-16 | 2023-11-16 | Aircraft cabin door opening and retaining mechanism |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN117513907A true CN117513907A (en) | 2024-02-06 |
Family
ID=89760312
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202311530865.4A Pending CN117513907A (en) | 2023-11-16 | 2023-11-16 | Aircraft cabin door opening and retaining mechanism |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN117513907A (en) |
-
2023
- 2023-11-16 CN CN202311530865.4A patent/CN117513907A/en active Pending
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