CN109629937B - Synchronous linkage locking device of general airplane cabin door - Google Patents
Synchronous linkage locking device of general airplane cabin door Download PDFInfo
- Publication number
- CN109629937B CN109629937B CN201910057519.6A CN201910057519A CN109629937B CN 109629937 B CN109629937 B CN 109629937B CN 201910057519 A CN201910057519 A CN 201910057519A CN 109629937 B CN109629937 B CN 109629937B
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- Prior art keywords
- cabin
- locking
- linkage
- locking mechanism
- handle
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Classifications
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- E—FIXED CONSTRUCTIONS
- E05—LOCKS; KEYS; WINDOW OR DOOR FITTINGS; SAFES
- E05C—BOLTS OR FASTENING DEVICES FOR WINGS, SPECIALLY FOR DOORS OR WINDOWS
- E05C9/00—Arrangements of simultaneously actuated bolts or other securing devices at well-separated positions on the same wing
- E05C9/02—Arrangements of simultaneously actuated bolts or other securing devices at well-separated positions on the same wing with one sliding bar for fastening when moved in one direction and unfastening when moved in opposite direction; with two sliding bars moved in the same direction when fastening or unfastening
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- 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
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- E—FIXED CONSTRUCTIONS
- E05—LOCKS; KEYS; WINDOW OR DOOR FITTINGS; SAFES
- E05B—LOCKS; ACCESSORIES THEREFOR; HANDCUFFS
- E05B63/00—Locks or fastenings with special structural characteristics
- E05B63/14—Arrangement of several locks or locks with several bolts, e.g. arranged one behind the other
- E05B63/143—Arrangement of several locks, e.g. in parallel or series, on one or more wings
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- E—FIXED CONSTRUCTIONS
- E05—LOCKS; KEYS; WINDOW OR DOOR FITTINGS; SAFES
- E05C—BOLTS OR FASTENING DEVICES FOR WINGS, SPECIALLY FOR DOORS OR WINDOWS
- E05C19/00—Other devices specially designed for securing wings, e.g. with suction cups
- E05C19/001—Other devices specially designed for securing wings, e.g. with suction cups with bolts extending over a considerable extent, e.g. nearly along the whole length of at least one side of the wing
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- E—FIXED CONSTRUCTIONS
- E05—LOCKS; KEYS; WINDOW OR DOOR FITTINGS; SAFES
- E05C—BOLTS OR FASTENING DEVICES FOR WINGS, SPECIALLY FOR DOORS OR WINDOWS
- E05C9/00—Arrangements of simultaneously actuated bolts or other securing devices at well-separated positions on the same wing
- E05C9/006—Details of bars
-
- E—FIXED CONSTRUCTIONS
- E05—LOCKS; KEYS; WINDOW OR DOOR FITTINGS; SAFES
- E05C—BOLTS OR FASTENING DEVICES FOR WINGS, SPECIALLY FOR DOORS OR WINDOWS
- E05C9/00—Arrangements of simultaneously actuated bolts or other securing devices at well-separated positions on the same wing
- E05C9/10—Actuating mechanisms for bars
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Structural Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Lock And Its Accessories (AREA)
Abstract
The invention belongs to the technical field of aircraft production, in particular to a synchronous linkage locking device of a universal aircraft cabin door, which comprises a fuselage, wherein the fuselage comprises a front cabin, a rear cabin and cabin doors for closing the front cabin and the rear cabin simultaneously, the synchronous linkage locking device also comprises a linkage locking mechanism and a rear cabin locking mechanism, the linkage locking mechanism comprises a locking part arranged at the edge of the cabin door, a front cabin locking assembly and a rear cabin locking assembly, the rear cabin locking mechanism comprises a locking assembly and a handle assembly, the locking assembly comprises a plug rod group, the locking part comprises a connecting batten and a plurality of buckles, the synchronous linkage locking device ensures that a flight trainee and a coach can enter and exit the front cabin and the rear cabin simultaneously, the trainee can not have flung and jumping, and when the trainee has a faint condition, the trainee can not operate an emergency condition of an aircraft in the rear cabin, the coach can lift the cabin door independently, strive for the time of saving oneself for coach and student, reduce serious loss.
Description
Technical Field
The invention belongs to the technical field of aircraft production, and particularly relates to a synchronous linkage locking device of a universal aircraft cabin door.
Background
When flight trainees carry out flight training, flight trainees can take over the flight trainees to operate the airplane by generally sitting in the rear cabins of the flight trainees, the front cabins and the rear cabins of the existing airplanes for training are opened independently, but meet unexpected conditions, the psychological quality of the flight trainees is not over, the front cabins are opened, the flight trainees can hurry and jump parachutes, the safety of the trainees is difficult to guarantee, and for some conditions, the trainees can deal with the situations, but the psychological quality of the flight trainees is not over, so that serious loss and even potential hazards of life are caused.
Disclosure of Invention
The invention aims to provide a synchronous linkage locking device of a general airplane cabin door, aiming at overcoming the defects of the prior art.
In order to solve the above problems, the present invention provides the following technical solutions:
a synchronous linkage locking device of a general machine body cabin door comprises a machine body, wherein the machine body comprises a front cabin, a rear cabin and a cabin door for closing the front cabin and the rear cabin simultaneously, the synchronous linkage locking device also comprises a linkage locking mechanism and a rear cabin locking mechanism, the linkage locking mechanism comprises a locking part arranged at the edge of the cabin door, a front cabin locking assembly and a rear cabin locking assembly, the front cabin locking assembly and the rear cabin locking assembly can be matched with the locking part in an inserting way, the rear cabin locking mechanism comprises a locking assembly arranged at the bottom of the linkage locking mechanism and a handle assembly arranged on the locking assembly, the locking component comprises an inserting rod group which can be inserted on the machine body, one side of the cabin door is hinged with the machine body through a hinge shaft, the locking portion is including the buckle that is connected the slat and a plurality of equidistant setting along the articulated shaft axis parallel with the axis of articulated shaft.
Preferably, the linkage locking mechanism further comprises a U-shaped slat with a strip structure, a plurality of sliding rails for sliding the front cabin locking assembly and the rear cabin locking assembly are arranged in the U-shaped slat, the locking assembly is mounted at the bottom of the U-shaped slat, the front cabin locking assembly comprises a first linkage bar parallel to the axis of the hinge shaft and a plurality of first latches which are vertically arranged at equal intervals along the axis of the hinge shaft, first plug connectors are arranged at the upper half parts of the first latches, all the first latches are mounted on the first linkage bar, and the first linkage bar is in sliding fit with one of the sliding rails.
Preferably, the rear cabin locking assembly comprises a second linkage bar parallel to the axis of the hinge shaft and a plurality of vertically arranged second lock catches arranged at equal intervals along the axis of the hinge shaft, the lower half parts of all the second lock catches are provided with second plug connectors, all the second lock catches are mounted on the second linkage bar, and the second linkage bar is in sliding fit with one of the slide rails.
Preferably, all be provided with two respectively on the buckle and supply first bayonet joint and second bayonet joint grafting complex spliced eye, all first hasp all sets up the one side that corresponds the buckle, and all second hasps all sets up the opposite side that corresponds the buckle at the articulated shaft axis.
Preferably, be provided with the first handle that can stimulate self to remove along self length direction on the first linkage barre, be provided with the second handle that can stimulate self to remove along self length direction on the second linkage barre, U type slat can be run through to first handle and second handle homoenergetic.
Preferably, the locking assembly comprises a plurality of guide plates which are arranged along the length direction of the U-shaped strip plate at equal intervals, the insertion rod group comprises a first insertion rod and a second insertion rod which are parallel and arranged in parallel, the locking assembly further comprises two insertion parts which are respectively arranged at two ends of the insertion rod group, and the first insertion rod and the second insertion rod can be inserted into all the insertion parts one by one.
Preferably, the handle assembly comprises a first handle mounted on the first plug-in lever and a second handle mounted on the second plug-in lever.
Preferably, one side of the buckle is a cylindrical surface with the hinge shaft as an axis.
The beneficial effect of adopting above technical scheme is: when the cabin door needs to be opened, the first handle and the second handle are pulled to move in the opposite directions, so that all the first plug connectors and all the second plug connectors leave from the plug holes, all the buckles are released, at the moment, the cabin door can be lifted, otherwise, the cabin door is locked, a flight student and a coach can simultaneously enter and exit from the front cabin and the rear cabin, the situation that the student hurdles and jumps the cabin cannot occur, when the student is faint, the coach cannot operate the airplane in the rear cabin in emergency, the coach pulls the handle assembly, the first plug rod and the second plug rod are pulled out from the plug part, the lifted cabin door drives the linkage locking mechanism to rotate together, the self-rescue time of the coach and the student is shortened, and the serious loss is reduced.
Drawings
FIG. 1 is a first perspective view of the present invention;
FIG. 2 is a schematic perspective view of the present invention;
FIG. 3 is a schematic perspective view of a linkage locking mechanism and a rear cabin locking mechanism according to the present invention;
FIG. 4 is a schematic perspective view of a linkage locking mechanism and a rear cabin locking mechanism according to the present invention;
FIG. 5 is a schematic perspective view of the latch portion and rear hatch latch assembly of the present invention;
FIG. 6 is a schematic perspective view of the latch portion of the present invention;
FIG. 7 is a side view of the U-shaped slat of the present invention;
FIG. 8 is a schematic perspective view of the front hatch locking assembly of the present invention;
FIG. 9 is a schematic perspective view of the rear hatch locking assembly of the present invention;
FIG. 10 is a schematic perspective view of the rear hatch locking mechanism of the present invention;
description of reference numerals: the locking mechanism comprises a machine body 1, a front cabin 11, a rear cabin 12, a cabin door 13, a linkage locking mechanism 2, a rear cabin locking mechanism 3, a front cabin locking assembly 4, a first linkage bar 41, a first lock catch 42, a first plug connector 43, a first handle 44, a rear cabin locking assembly 5, a second linkage bar 51, a second lock catch 52, a second plug connector 53, a second handle 54, a locking assembly 6, a guide plate 61, a first plug connector 62, a plug connector 63, a locking part 7, a connecting strip plate 71, a buckle 72, a plug hole 73, a handle assembly 8, a first handle 81, a second handle 82, a U-shaped strip plate 9, a sliding rail 91 and a hinged shaft 10.
Detailed Description
The following detailed description of the embodiments of the present invention will be given with reference to the accompanying drawings for a purpose of helping those skilled in the art to more fully, accurately and deeply understand the concept and technical solution of the present invention and to facilitate its implementation.
Referring to fig. 1 to 10, the invention relates to a synchronous linkage locking device of a universal machine body cabin door, which comprises a machine body 1, wherein the machine body 1 comprises a front cabin 11, a rear cabin 12 and a cabin door 13 for closing the front cabin 11 and the rear cabin 12 simultaneously, the synchronous linkage locking device further comprises a linkage locking mechanism 2 and a rear cabin locking mechanism 3, the linkage locking mechanism 2 comprises a locking part 7 arranged at the edge of the cabin door 13, a front cabin locking component 4 and a rear cabin locking component 5, the front cabin locking component 4 and the rear cabin locking component 5 can be in inserted fit with the locking part 7, the rear cabin locking mechanism 3 comprises a locking component 6 arranged at the bottom of the linkage locking mechanism 2 and a handle component 8 arranged on the locking component 6, the locking component 6 comprises an insertion rod group which can be inserted on the machine body 1, one side of the cabin door 13 is hinged with the machine body 1 through a hinge shaft 10, locking portion 7 is including the buckle 72 that is connected slat 71 and a plurality of along articulated shaft 10 equidistant setting of axis with the axis parallel of articulated shaft 10, when hatch door 13 is opened to needs, stimulate forecabin locking subassembly 4 and backstay locking subassembly 5 reverse movement simultaneously, locking portion 7 is released, at this moment, can lift hatch door 13, when the faint condition appears in the student, the emergency of coach at the 12 unable operation aircraft in backstay, coach pulling handle subassembly 8, make the grafting pole group all extract from grafting portion 63, lift hatch door 13 and drive linkage locking mechanism 2 and rotate together and open, time of saving oneself for coach and student strive for.
The linkage locking mechanism 2 further comprises a U-shaped strip 9 with a long strip structure, a plurality of slide rails 91 for the sliding of the front cabin locking assembly 4 and the rear cabin locking assembly 5 are arranged in the U-shaped strip 9, the locking assembly 6 is installed at the bottom of the U-shaped strip 9, the front cabin locking assembly 4 comprises a first linkage strip rod 41 parallel to the axis of the hinge shaft 10 and a plurality of first lock catches 42 which are vertically arranged at equal intervals along the axis of the hinge shaft 10, the upper half parts of all the first lock catches 42 are provided with first plug-in connectors 43, all the first lock catches 42 are installed on the first linkage strip rod 41, the first linkage strip rod 41 is in sliding fit with one of the slide rails 91, the first pull handle 44 is pulled to drive the first linkage strip rod 41 to move along the length direction of the first lock catch 42 to move, so that all the first plug-in connectors 43 can synchronously enter and exit all the buckles 72, the lock portion 7 is locked or released.
The rear cabin locking assembly 5 comprises a second linkage bar 51 parallel to the axis of the hinge shaft 10 and a plurality of vertically arranged second lock catches 52 at equal intervals along the axis of the hinge shaft 10, the lower half parts of all the second lock catches 52 are provided with second plug connectors 53, all the second lock catches 52 are installed on the second linkage bar 51, the second linkage bar 51 is in sliding fit with one of the slide rails 91, the second handle 54 is pulled to drive the second linkage bar 51 to move along the length direction of the second linkage bar 51, all the second lock catches 52 are driven to move, all the second plug connectors 53 can synchronously enter and exit all the buckles 72, the locking part 7 is locked or released, and the front cabin locking assembly 4 and the rear cabin locking assembly 5 are simultaneously released, so that the cabin door 13 can be opened simultaneously.
All the buckles 72 are provided with two insertion holes 73 which are respectively used for the first insertion-connection head 43 and the second insertion-connection head 53 to be inserted and matched, all the first lock catches 42 are arranged on one side corresponding to the buckles 72, all the second lock catches 52 are arranged on the other side of the corresponding buckles 72 on the axis of the hinge shaft, the first pull handles 44 and the second pull handles 54 are oppositely pulled, so that the first insertion-connection head 43 and the second insertion-connection head 53 are both inserted into the buckles 72, and the first pull handles 44 and the second pull handles 54 are simultaneously pulled reversely, so that the first insertion-connection head 43 and the second insertion-connection head 53 are both separated from the buckles 72.
The first linkage bar 41 is provided with a first handle 44 capable of pulling the first linkage bar to move along the length direction of the first linkage bar, the second linkage bar 51 is provided with a second handle 54 capable of pulling the second linkage bar to move along the length direction of the second linkage bar, the first handle 44 and the second handle 54 can penetrate through the U-shaped strip 9, the first handle 44 and the second handle 54 are pulled simultaneously from the inside of the fuselage 1, the cabin door 13 can be locked or the cabin door 13 can be opened, the first handle 44 and the second handle 54 are pulled simultaneously from the outside of the fuselage 1, the cabin door 13 can be accessed and released, and the cabin door 13 can be locked or the cabin door 13 can be opened.
The locking assembly 6 comprises a plurality of guide plates 61 which are arranged along the length direction of the U-shaped strip plate 9 at equal intervals, the insertion rod group comprises a first insertion rod 62 and a second insertion rod which are arranged in parallel and in parallel, the locking assembly 6 further comprises two insertion parts 63 which are respectively arranged at two ends of the insertion rod group, the first insertion rod 62 and the second insertion rod can be inserted into all the insertion parts 63 one by one, the coach pulls the handle assembly 8 in opposite directions, so that the first insertion rod 62 and the second insertion rod are all pulled out from the insertion parts 63, the hatchdoor 13 is lifted to drive the linkage locking mechanism 2 to rotate together, the handle assembly 8 is pulled in opposite directions, and the first insertion rod 62 and the second insertion rod are respectively inserted into the insertion parts 63.
The handle assembly 8 comprises a first handle 81 mounted on the first inserting rod 62 and a second handle 82 mounted on the second inserting rod, the coach pulls the first handle 81 and the second handle 82 oppositely to enable the first inserting rod 62 and the second inserting rod to be pulled out from the inserting part 63, the hatchdoor 13 is lifted to drive the linkage locking mechanism 2 to rotate together, and the first handle 81 and the second handle 82 are pulled reversely to enable the first inserting rod 62 and the second inserting rod to be respectively inserted into the inserting part 63.
One side of the buckle 72 is a cylindrical surface with the hinge shaft 10 as an axis, so that the buckle 72 is prevented from being clamped in the U-shaped strip 9 when the cabin door 13 is opened.
The working principle is as follows: when the cabin door 13 needs to be opened, the first pull handle 44 and the second pull handle 54 are pulled to move reversely, so that all the first plug connectors 43 and all the second plug connectors 53 leave from the plug holes 73, all the buckles 72 are released, at this time, the cabin door 13 can be lifted, otherwise, the cabin door 13 is locked, a flight trainee and a coach can enter and exit the front cabin 11 and the rear cabin 12 simultaneously, the trainee cannot hurry and jump the cabin, when the trainee is in a faint situation, the coach cannot operate the airplane in the rear cabin 12 in an emergency, the coach pulls the handle assembly 8, so that the first plug rod 62 and the second plug rod are pulled out from the plug part 63, and the lifted cabin door 13 drives the linkage locking mechanism 2 to rotate together.
The present invention has been described in connection with the accompanying drawings, and it is to be understood that the invention is not limited to the specific embodiments described above, but is intended to cover various insubstantial modifications of the invention based on the principles and technical solutions of the invention; the present invention is not limited to the above embodiments, and can be modified in various ways.
Claims (8)
1. The utility model provides a synchronous linkage locking means of general fuselage hatch door, including fuselage (1), fuselage (1) is including front deck (11), after-deck (12) and be used for closing hatch door (13) of front deck (11) and after-deck (12) simultaneously, its characterized in that: the synchronous linkage locking device further comprises a linkage locking mechanism (2) and a rear cabin locking mechanism (3), the linkage locking mechanism (2) comprises a locking part (7) installed at the edge of the cabin door (13), a front cabin locking assembly (4) and a rear cabin locking assembly (5), the front cabin locking assembly (4) and the rear cabin locking assembly (5) can be matched with the locking part (7) in an inserting mode, the rear cabin locking mechanism (3) comprises a locking assembly (6) installed at the bottom of the linkage locking mechanism (2) and a handle assembly (8) installed on the locking assembly (6), the locking assembly (6) comprises an inserting rod group capable of being inserted on the body (1), one side of the cabin door (13) is hinged to the body (1) through an articulated shaft (10), the locking part (7) comprises a connecting strip plate (71) parallel to the axis of the articulated shaft (10) and a plurality of buckles (3) arranged at equal intervals along the axis of the articulated shaft (10) 72).
2. The synchronized locking mechanism for a universal fuselage door of claim 1, wherein: the linkage locking mechanism (2) further comprises a U-shaped slat (9) with a strip-shaped structure, a plurality of sliding rails (91) for a front cabin locking assembly (4) and a rear cabin locking assembly (5) to slide are arranged in the U-shaped slat (9), the locking assemblies (6) are installed at the bottom of the U-shaped slat (9), the front cabin locking assembly (4) comprises first linkage bars (41) parallel to the axis of a hinged shaft (10) and a plurality of first lock catches (42) which are vertically arranged along the axis of the hinged shaft (10) at equal intervals, first inserting joints (43) are arranged at the upper half parts of all the first lock catches (42), all the first lock catches (42) are installed on the first linkage bars (41), and the first linkage bars (41) are in sliding fit with one of the sliding rails (91).
3. The synchronized locking mechanism for a universal fuselage door of claim 2, wherein: the rear cabin locking assembly (5) comprises a second linkage bar (51) parallel to the axis of the hinge shaft (10) and a plurality of second lock catches (52) which are arranged vertically along the axis of the hinge shaft (10) at equal intervals, the lower half parts of all the second lock catches (52) are provided with second plug connectors (53), all the second lock catches (52) are arranged on the second linkage bar (51), and the second linkage bar (51) is in sliding fit with one of the sliding rails (91).
4. The synchronized locking mechanism for a universal fuselage door of claim 3, wherein: all buckle (72) are last all to be provided with two and to supply first bayonet joint (43) and second bayonet joint (53) grafting complex spliced eye (73) respectively, and all first hasp (42) all set up the one side that corresponds buckle (72), and all second hasp (52) all set up the opposite side that corresponds buckle (72) at the articulated shaft axis.
5. The synchronized locking mechanism for a universal fuselage door of claim 4, wherein: be provided with on first linkage barre (41) and can stimulate self along self length direction removal first handle (44), be provided with on second linkage barre (51) and can stimulate self along self length direction removal second handle (54), U type slat (9) can be run through in first handle (44) and second handle (54) homoenergetic.
6. The synchronized locking mechanism for a universal fuselage door of claim 5, wherein: the locking assembly (6) comprises a plurality of guide plates (61) which are arranged along the length direction of the U-shaped strip plate (9) at equal intervals, the inserting rod group comprises a first inserting rod (62) and a second inserting rod which are parallel and arranged in parallel, the locking assembly (6) further comprises two inserting parts (63) which are respectively arranged at two ends of the inserting rod group, and the first inserting rod (62) and the second inserting rod can be inserted into all the inserting parts (63) one by one.
7. The synchronized locking mechanism for a universal fuselage door of claim 6, wherein: the handle assembly (8) comprises a first handle (81) mounted on the first plug-in lever (62) and a second handle (82) mounted on the second plug-in lever.
8. The synchronized locking mechanism for a universal fuselage door of claim 7, wherein: one side of the buckle (72) is a cylindrical surface taking the hinge shaft (10) as an axis.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910057519.6A CN109629937B (en) | 2019-01-22 | 2019-01-22 | Synchronous linkage locking device of general airplane cabin door |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910057519.6A CN109629937B (en) | 2019-01-22 | 2019-01-22 | Synchronous linkage locking device of general airplane cabin door |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN109629937A CN109629937A (en) | 2019-04-16 |
| CN109629937B true CN109629937B (en) | 2020-08-25 |
Family
ID=66063007
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910057519.6A Active CN109629937B (en) | 2019-01-22 | 2019-01-22 | Synchronous linkage locking device of general airplane cabin door |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109629937B (en) |
Family Cites Families (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2492336A1 (en) * | 1980-10-20 | 1982-04-23 | Aerospatiale | Explosive cockpit release for aircraft - has explosive cord around edge of glazing and along top to split it into two halves |
| US5259576A (en) * | 1992-05-18 | 1993-11-09 | Howard D U | External sliding aircraft door |
| US5931415A (en) * | 1997-05-09 | 1999-08-03 | The Boeing Company | Plug-type overwing emergency exit door assembly |
| IT1302159B1 (en) * | 1997-09-03 | 2000-07-31 | Eurocopter Deutschland | DOOR SYSTEM FOR A PASSENGER AIRCRAFT |
| CN204002183U (en) * | 2014-05-27 | 2014-12-10 | 江西洪都航空工业集团有限责任公司 | The buckle structure that a kind of aircraft is special |
| CN208137713U (en) * | 2018-03-26 | 2018-11-23 | 珠海市海卫科技有限公司 | A kind of light-duty sport plane canopy safety lock |
-
2019
- 2019-01-22 CN CN201910057519.6A patent/CN109629937B/en active Active
Also Published As
| Publication number | Publication date |
|---|---|
| CN109629937A (en) | 2019-04-16 |
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