CN114348233A - Aircraft cabin locking device - Google Patents
Aircraft cabin locking device Download PDFInfo
- Publication number
- CN114348233A CN114348233A CN202111545466.6A CN202111545466A CN114348233A CN 114348233 A CN114348233 A CN 114348233A CN 202111545466 A CN202111545466 A CN 202111545466A CN 114348233 A CN114348233 A CN 114348233A
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- main shaft
- mounting hole
- handle seat
- boss
- handle
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
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- Lock And Its Accessories (AREA)
Abstract
The invention discloses an aircraft cabin lock device, which comprises a screw, a handle, a main shaft, a handle seat, a spring clamp, a rocker arm, a switching rocker arm, a nut, a split pin and a lock pull rod, wherein the handle seat is provided with a main shaft mounting hole, the handle seat is arranged on a frame at the mouth of an aircraft body, the main shaft is a stepped shaft with three sections of gradually-reduced outer diameters, the main shaft is provided with a boss A and a boss B, the main shaft passes through the main shaft mounting hole on the handle seat and is arranged on the handle seat, and is fixed on a handle seat through a nut, a spring clip is arranged at the bottom of the handle seat, the spring clip is positioned at the rear side of the rocker arm and is used for fixing the rocker arm during locking, one end of the handle is sleeved on a boss A of the main shaft, the locking device is fixed on a boss A of the main shaft through a screw, one end of the rocker arm is sleeved on a boss B of the main shaft, the other end of the rocker arm is rotatably connected with one end of the switching rocker arm, the other end of the switching rocker arm is connected with the locking pull rod, and the cotter pin penetrates through a through hole in the main shaft and is screwed tightly; the invention has the advantages that: simple structure, the processing of being convenient for has reduced the part, has alleviateed weight.
Description
Technical Field
The invention belongs to the technical field of locking mechanisms, and particularly relates to an aircraft cabin lock device.
Background
The aircraft cockpit lock mechanism is the main structure who guarantees the normal switch of cockpit lock system, makes the linkage of lock pull rod through the push-and-pull handle, realizes unblanking and locking of cockpit lid lock system, if the lock mechanism appears accidentally unblanking at the flight in-process, can make the cockpit lid open by accident, makes the cockpit lid lose the protect function to the pilot, causes the pilot to receive the air current and blows, influences the flight safety of aircraft.
Disclosure of Invention
In view of the above prior art, the present invention aims to overcome the disadvantages of the prior art and to meet the practical needs, thereby providing an aircraft cabin lock device with simple structure, convenient installation and maintenance and strong reliability.
In order to achieve the purpose, the invention adopts the technical scheme that: an aircraft cabin locking device comprises a screw, a handle, a main shaft, a handle seat, a spring clamp, a rocker arm, a switching rocker arm, a nut, a cotter pin and a lock pull rod, wherein a main shaft mounting hole is formed in the handle seat, the handle seat is mounted on a frame of an aircraft body, the main shaft is a stepped shaft with three sections of gradually-reduced outer diameters, a boss A and a boss B are arranged on the main shaft, the boss A is positioned on the left side of an outer diameter shaft of a first section, the boss B is positioned on the right side of a second section, an external thread matched with the nut is arranged on a third section of shaft, a through hole is formed in the outer wall of the right side of the section of shaft, the main shaft penetrates through the main shaft mounting hole in the handle seat and is fixed on the handle seat through a nut sleeved on the exposed end of the third section of shaft of the main shaft, the spring clamp is mounted at the bottom of the handle seat and is positioned on the rear side of the rocker arm and used for fixing the rocker arm during locking, the false unlocking is avoided during the action, one end of the handle is sleeved on the boss A of the main shaft, and is fixed on the boss A of the main shaft through a screw, the other end of the handle is a holding end, one end of the rocker arm is sleeved on the boss B of the main shaft, the other end of the rocker arm is rotatably connected with one end of the switching rocker arm, the other end of the switching rocker arm is connected with the locking pull rod, and the split pin penetrates through a through hole in the main shaft and is screwed down to prevent the nut from falling off.
Furthermore, one end of the handle is sleeved on the boss A of the main shaft, the handle is fixed on the boss A of the main shaft by sequentially penetrating the elastic pad and the gasket through screws, the other end of the rocker arm is rotatably connected with one end of the switching rocker arm through a cylindrical pin, and the main shaft penetrates through a main shaft mounting hole in the handle seat and is fixed on the handle seat through a nut and the gasket, wherein the exposed end of the third section of shaft of the main shaft is sleeved on the exposed end of the main shaft.
Further, the handle seat is an L-shaped support, two lug plates vertically protrude upwards from the right end of the horizontal support at the bottom of the L-shaped support, a gap is reserved between the two lug plates, a main shaft mounting hole A is formed in the lower end of the vertical support at the left side of the L-shaped support, a main shaft mounting hole B and a main shaft mounting hole C are formed in the two lug plates respectively, the main shaft mounting hole B is located between the main shaft mounting hole A and the main shaft mounting hole C, 4 bolt mounting holes are further formed in the bottom of the handle seat, the handle seat is mounted on the frame of the machine body through the bolt mounting holes, the main shaft sequentially penetrates through the main shaft mounting hole A in the handle seat through a third section shaft of the main shaft, the main shaft mounting hole B and the main shaft mounting hole C are mounted on the handle seat, and the boss B on the main shaft is located in the gap between the two lug plates.
Further, the main shaft mounting hole A, the main shaft mounting hole B and the main shaft mounting hole C are located on the same horizontal height, the aperture of the main shaft mounting hole A and the aperture of the main shaft mounting hole B are matched with the outer diameter of the second section shaft of the main shaft, and the aperture of the main shaft mounting hole C is matched with the outer diameter of the third section shaft of the main shaft.
Further, bushings are arranged in the main shaft mounting hole A, the main shaft mounting hole B and the main shaft mounting hole C, and the main shaft is prevented from rotating to wear the handle seat.
Further, the handle seat is of an integrally formed structure, and a lightening hole is further formed in the upper end of the vertical support in the left side of the handle seat.
Furthermore, the spring clip is of a U-shaped structure and is narrowed at the U-shaped opening, the bottom of the spring clip is riveted on a transverse support at the bottom between two lugs on the handle seat, the U-shaped opening of the spring clip is positioned at the rear side of the rocker arm, and the rocker arm can be clamped in the U-shaped opening after being locked.
Further, the opening width of the U-shaped opening narrowing part of the spring clamp is smaller than the outer diameter of the rocker arm.
Furthermore, the bottom of the spring clamp is fixed on the handle seat through two rivets.
According to the invention, the main shaft mounting holes in the handle seat are all provided with bushings to prevent the main shaft from rotating to abrade the handle seat, the main shaft is fixed on the handle seat through nuts, the main shaft is provided with a boss A and a boss B, the boss A and the boss B are respectively used for mounting the handle and the rocker arm, the handle is fixed on the boss A of the main shaft through screws, a gasket and an elastic pad are arranged at the positions of the screws to prevent loosening, the rocker arm is fixed on the boss B of the main shaft, one end of the switching rocker arm is connected with the rocker arm through a cylindrical pin, the other end of the switching rocker arm is connected with a locking pull rod, a spring clamp is riveted on the handle seat and used for fixing the rocker arm during locking, the mistaken unlocking during the manual action is avoided, and a gap between two lug pieces on the handle seat can accommodate the boss B, the rocker arm and the spring clamp of the main shaft.
In the invention, the invention is used for unlocking and locking the aircraft canopy. The handle seat adopts the integrated design, and the main shaft passes on the handle seat and links to each other with handle and rocking arm simultaneously, pushes away, draws the handle to make the rocking arm take place to rotate, drives the motion of locking pull rod, realizes unblanking and closing the lock of passenger cabin, installs the spring card on the handle seat, locks the back rocking arm and arranges the effect that prevents the mistake and unblank in the spring card in, and the device simple structure, the reliability is high.
The invention has the beneficial effects that: the lock device provided by the invention is simple in structure and convenient to process, the handle seat is made of aluminum alloy materials, lightening holes are formed in the handle seat, the weight requirement of the lock device is met, and the main shaft mounting hole in the handle seat is provided with the steel bushing, so that the abrasion of the handle seat body is avoided; the main shaft adopts a variable cross-section form and is provided with two bosses which are respectively used for fixing the handle and the rocker arm, so that the mode of fixing by using a bolt is avoided, installation parts are reduced, and the weight of the system is reduced; the spring clamp is fixed on the handle seat through two rivets, the locking device can be effectively prevented from being mistakenly unlocked in flight, and the spring clamp is simple in structure and convenient to install.
Drawings
FIG. 1 is a schematic structural view of the present invention;
FIG. 2 is an exploded view of the present invention;
FIG. 3 is a partial cross-sectional view of the present invention;
fig. 4 is a schematic diagram of a locking structure according to the present invention.
Wherein: the locking device comprises a bolt 1, a spring pad 2, a washer 3, a handle 4, a spindle 5, a bushing 6, a handle seat 7, a spring clip 8, a rocker arm 9, a cylindrical pin 10, a switching rocker arm 11, a nut 12, a split pin 13, a lock pull rod 14, a boss A15, a boss B16, a spindle mounting hole A17, a spindle mounting hole B18, a lightening hole 19, a lug plate 20 and a spindle mounting hole C21.
Detailed Description
The following detailed description of embodiments of the invention refers to the accompanying drawings. It should be understood that the detailed description and specific examples, while indicating the present invention, are given by way of illustration and explanation only, not limitation.
In the description of the present application, it is to be understood that the terms "upper", "lower", "front", "rear", "left", "right", "vertical", "lateral", "top", "bottom", "inner", "outer", and the like, indicate orientations or positional relationships based on those shown in the drawings, are merely for convenience in describing the present application and simplifying the description, and do not indicate or imply that the referred device or element must have a particular orientation, be constructed in a particular orientation, and be operated, and thus, should not be construed as limiting the present application.
As shown in fig. 1 to 4, the invention provides an aircraft cabin lock device, which comprises a screw 1, a handle 4, a main shaft 5, a handle seat 7, a spring clip 8, a rocker arm 9, a switching rocker arm 11, a nut 12, a split pin 13 and a lock pull rod 14, wherein the handle seat 7 is provided with a main shaft mounting hole, the handle seat 7 is arranged on a frame of an aircraft body opening, the main shaft 5 is a stepped shaft with three sections of gradually reduced outer diameters, the main shaft is provided with a boss a15 and a boss B16, the boss a15 is positioned at the left side of a first section of outer diameter shaft, the boss B16 is positioned at the right side of a second section of shaft, a third section of shaft is provided with an external thread matched with the nut 12, the outer wall of the right side of the section of shaft is provided with a through hole, the main shaft 5 passes through the main shaft mounting hole on the handle seat 7 and is fixed on the handle seat 7 by sleeving the nut 12 on the exposed end of the third section of the main shaft, the spring clip 8 is arranged at the bottom of the handle seat 7, the spring clip 8 is located the rocking arm 9 rear side and is used for fixed rocking arm 9 when locking, avoid taking place the mistake when the motor action and unblank, handle 4 one end cup joints on boss A15 of main shaft 5, and be fixed in on the boss A15 of main shaft 5 through screw 1, the handle 4 other end is for holding the end, 9 one end of rocking arm cup joints on the boss B16 of main shaft 5, the rocking arm 9 other end rotates with switching rocking arm 11 one end to be connected, the switching rocking arm 11 other end is connected with lock pull rod 14, split pin 13 passes the through-hole on the main shaft 5 and screws up, in order to prevent droing of nut 12.
Preferably, one end of the handle 4 is sleeved on the boss a15 of the spindle 5, the screw 1 sequentially penetrates through the spring washer 2 and the washer 3 to fix the handle 4 on the boss a15 of the spindle 5, the other end of the rocker arm 9 is rotatably connected with one end of the switching rocker arm 11 through the cylindrical pin 10, and the spindle 5 penetrates through a spindle mounting hole in the handle seat 7 and is sleeved on an exposed end of a third section of the spindle 5 through the nut 12 and the washer 3 to be fixed on the handle seat 7.
Preferably, the handle seat 7 is an L-shaped seat, two lugs 20 are vertically and upwardly protruded from the right end of the horizontal seat at the bottom of the L-shaped seat, a gap is formed between the two lugs 20, a spindle mounting hole a17 is arranged at the lower end of the vertical seat at the left side of the L-shaped seat, a spindle mounting hole B18 and a spindle mounting hole C21 are respectively arranged on the two lugs, the spindle mounting hole B18 is located between the spindle mounting hole a17 and the spindle mounting hole C21, 4 bolt mounting holes are further arranged at the bottom of the handle seat 7, the handle seat 7 is mounted on the frame of the machine body through the bolt mounting holes, the spindle 5 sequentially penetrates through the spindle mounting hole a17, the spindle mounting hole B18 and the spindle mounting hole C21 on the handle seat 7 through a third section shaft of the spindle 5, and the boss B16 on the spindle 5 is located in the gap between the two lugs 20.
Preferably, the main shaft mounting hole a17, the main shaft mounting hole B18 and the main shaft mounting hole C21 are located at the same horizontal height, the diameters of the main shaft mounting hole a17 and the main shaft mounting hole B18 are both matched with the outer diameter of the second section shaft of the main shaft 5, and the diameter of the main shaft mounting hole C21 is matched with the outer diameter of the third section shaft of the main shaft 5.
Preferably, the bushings 6 are arranged in the spindle mounting hole A17, the spindle mounting hole B18 and the spindle mounting hole C21, so that the spindle 5 is prevented from rotating to wear the handle seat 7.
Preferably, the handle seat 7 is of an integrally formed structure, and the upper end of the vertical support at the left side of the handle seat 7 is also provided with a lightening hole 19.
Preferably, the spring clip 8 is formed into a U-shaped structure by sheet metal, and is narrowed at the U-shaped opening, the bottom of the spring clip 8 is riveted on a bottom transverse support between two lugs 20 on the handle seat 7, the U-shaped opening of the spring clip 8 is positioned at the rear side of the rocker arm 9, and the rocker arm 9 can be clamped into the U-shaped opening after being locked.
Preferably, the mouth width of the U-shaped mouth narrowing of the spring clip 8 is smaller than the outer diameter of the rocker arm 9.
Preferably, the bottom of the spring clip 8 is fixed on the handle seat 7 through two rivets.
In the invention, the main shaft 5 is fixed on the handle seat 7 through the nut 12, the handle 4 and the rocker arm 9 are respectively fixed on two bosses of the main shaft 5, the main shaft 5 is rotated by pushing and pulling the handle 5, and the rocker arm 9 drives the lock pull rod 14 to move along with the rotation of the main shaft 5, thereby realizing locking and unlocking.
The working principle of the invention is as follows: when the handle 4 is pulled, the handle 4 is matched with the spindle 5 to drive the spindle 5 to rotate clockwise around the axis of the spindle, the spindle 5 rotates to drive the rocker arm 9 matched with the spindle to rotate, the rocker arm 9 slides out of the spring clamp 8 to finish unlocking, and the unlocking state is shown in figure 1; when the handle 4 is pushed, the handle 4 is engaged with the spindle 5 to drive the spindle 5 to rotate anticlockwise around the axis of the spindle, the spindle 5 rotates to drive the rocker arm 9 engaged with the spindle to rotate, the rocker arm 9 slides into the spring clamp 8 to complete the locking action, and the locking state is shown in fig. 4.
Finally, it should be noted that: the above embodiments are only used to illustrate the technical solution of the present invention, and not to limit the same; while the invention has been described in detail and with reference to the foregoing embodiments, it will be understood by those skilled in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some or all of the technical features may be equivalently replaced; and the modifications or the substitutions do not make the essence of the corresponding technical solutions depart from the scope of the technical solutions of the embodiments of the present invention.
Furthermore, those skilled in the art will appreciate that while some embodiments herein include some features included in other embodiments, rather than other features, combinations of features of different embodiments are meant to be within the scope of the invention and form different embodiments. For example, in the claims above, any of the claimed embodiments may be used in any combination. The information disclosed in this background section is only for enhancement of understanding of the general background of the invention and should not be taken as an acknowledgement or any form of suggestion that this information forms the prior art already known to a person skilled in the art.
Claims (9)
1. An aircraft cabin locking device, characterized by: comprises a screw (1), a handle (4), a main shaft (5), a handle seat (7), a spring clamp (8), a rocker arm (9), a switching rocker arm (11), a nut (12), a split pin (13) and a lock pull rod (14), wherein the handle seat (7) is provided with a main shaft mounting hole, the handle seat (7) is arranged on a frame of a machine body opening, the main shaft (5) is a stepped shaft with three sections of gradually-reduced outer diameters, the main shaft is provided with a boss A (15) and a boss B (16), the boss A (15) is positioned on the left side of a first section of outer diameter shaft, the boss B (16) is positioned on the right side of a second section of outer diameter shaft, a third section of outer thread matched with the nut (12) is arranged on the third section of shaft, a through hole is arranged on the outer wall of the right side of the section of outer shaft, the main shaft (5) passes through the main shaft mounting hole on the handle seat (7) and is arranged on the handle seat (7) and is sleeved on the exposed end of the third section of the main shaft (5) through the nut (12) and fixed on the handle seat (7), spring card (8) are installed to handle seat (7) bottom, spring card (8) are located rocking arm (9) rear side and are used for fixed rocking arm (9) when locking, avoid taking place the mistake and unblank when maneuvering, handle (4) one end is cup jointed on boss A (15) of main shaft (5), and be fixed in on boss A (15) of main shaft (5) through screw (1), the handle (4) other end is the end of gripping, rocking arm (9) one end is cup jointed on boss B (16) of main shaft (5), rocking arm (9) other end is rotated with switching rocking arm (11) one end and is connected, the switching rocking arm (11) other end is connected with lock pull rod (14), split pin (13) pass the through-hole on main shaft (5) and screw up, in order to prevent droing of nut (12).
2. The aircraft cabin lock arrangement of claim 1, wherein: one end of the handle (4) is sleeved on a boss A (15) of the main shaft (5), the handle (4) is fixed on the boss A (15) of the main shaft (5) by sequentially penetrating through the elastic pad (2) and the gasket (3) through the screw (1), the other end of the rocker arm (9) is rotatably connected with one end of the switching rocker arm (11) through the cylindrical pin (10), and the main shaft (5) penetrates through a main shaft mounting hole in the handle seat (7) and is fixed on the handle seat (7) through an exposed end of a third section shaft of the main shaft (5) sleeved with the nut (12) and the gasket (3).
3. The aircraft cabin lock arrangement of claim 1, wherein: the handle seat (7) is an L-shaped support, two lug plates (20) are vertically and upwards protruded at the right end of the transverse support at the bottom of the L-shaped support, a gap is arranged between the two lug plates (20), the lower end of a vertical support on the left side of the L-shaped support is provided with a main shaft mounting hole A (17), two lug plates are respectively provided with a main shaft mounting hole B (18) and a main shaft mounting hole C (21), the main shaft mounting hole B (18) is positioned between the main shaft mounting hole A (17) and the main shaft mounting hole C (21), the bottom of a handle seat (7) is also provided with 4 bolt mounting holes, the handle seat (7) is arranged on a frame of a machine body opening through the bolt mounting holes, a main shaft (5) sequentially penetrates through the main shaft mounting hole A (17), the main shaft mounting hole B (18) and the main shaft mounting hole C (21) on the handle seat (7) through a third section shaft of the main shaft (5) and is arranged on the handle seat (7), and the boss B (16) on the main shaft (5) is positioned in the gap between the two lugs (20).
4. The aircraft cabin lock arrangement of claim 3, wherein: the main shaft mounting hole A (17), the main shaft mounting hole B (18) and the main shaft mounting hole C (21) are located on the same horizontal height, the aperture of the main shaft mounting hole A (17) and the aperture of the main shaft mounting hole B (18) are matched with the outer diameter of a second section shaft of the main shaft (5), and the aperture of the main shaft mounting hole C (21) is matched with the outer diameter of a third section shaft of the main shaft (5).
5. The aircraft cabin lock arrangement of claim 3, wherein: bushings (6) are arranged in the main shaft mounting hole A (17), the main shaft mounting hole B (18) and the main shaft mounting hole C (21), and the main shaft (5) is prevented from rotating to wear the handle seat (7).
6. The aircraft cabin lock arrangement of claim 3, wherein: the handle seat (7) is of an integrally formed structure, and a lightening hole (19) is further formed in the upper end of the vertical support in the left side of the handle seat (7).
7. The aircraft cabin lock arrangement of claim 3, wherein: the spring clip (8) is of a U-shaped structure and is narrowed at the U-shaped opening, the bottom of the spring clip (8) is riveted on a transverse support at the bottom between the two lugs (20) on the handle seat (7), the U-shaped opening of the spring clip (8) is positioned at the rear side of the rocker arm (9), and the rocker arm (9) can be clipped in the U-shaped opening after being locked.
8. The aircraft cabin lock arrangement of claim 7, wherein: the opening width of the U-shaped opening narrowing part of the spring clamp (8) is smaller than the outer diameter of the rocker arm (9).
9. The aircraft cabin lock arrangement of claim 7, wherein: the bottom of the spring clamp (8) is fixed on the handle seat (7) through two rivets.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111545466.6A CN114348233B (en) | 2021-12-17 | 2021-12-17 | Aircraft cabin lock device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111545466.6A CN114348233B (en) | 2021-12-17 | 2021-12-17 | Aircraft cabin lock device |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN114348233A true CN114348233A (en) | 2022-04-15 |
| CN114348233B CN114348233B (en) | 2023-08-11 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202111545466.6A Active CN114348233B (en) | 2021-12-17 | 2021-12-17 | Aircraft cabin lock device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN114348233B (en) |
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| CN213144141U (en) * | 2020-07-29 | 2021-05-07 | 浙江星洲航空科技有限公司 | Helicopter cockpit door locking mechanism |
| CN112158324A (en) * | 2020-09-25 | 2021-01-01 | 中国直升机设计研究所 | Connecting rod throwing device |
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| Publication number | Publication date |
|---|---|
| CN114348233B (en) | 2023-08-11 |
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