CN110937100A - Invisible connecting mechanism for aircraft opening cover - Google Patents
Invisible connecting mechanism for aircraft opening cover Download PDFInfo
- Publication number
- CN110937100A CN110937100A CN201911290269.7A CN201911290269A CN110937100A CN 110937100 A CN110937100 A CN 110937100A CN 201911290269 A CN201911290269 A CN 201911290269A CN 110937100 A CN110937100 A CN 110937100A
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- CN
- China
- Prior art keywords
- lock
- flap
- hexagonal
- seat
- invisible
- 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.)
- Granted
Links
- 230000007246 mechanism Effects 0.000 title claims abstract description 31
- 230000008878 coupling Effects 0.000 description 4
- 238000010168 coupling process Methods 0.000 description 4
- 238000005859 coupling reaction Methods 0.000 description 4
- 230000001788 irregular Effects 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 230000008569 process Effects 0.000 description 2
- 230000009471 action Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000001125 extrusion Methods 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012544 monitoring process Methods 0.000 description 1
- 238000007789 sealing Methods 0.000 description 1
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/14—Windows; Doors; Hatch covers or access panels; Surrounding frame structures; Canopies; Windscreens accessories therefor, e.g. pressure sensors, water deflectors, hinges, seals, handles, latches, windscreen wipers
-
- E—FIXED CONSTRUCTIONS
- E05—LOCKS; KEYS; WINDOW OR DOOR FITTINGS; SAFES
- E05B—LOCKS; ACCESSORIES THEREFOR; HANDCUFFS
- E05B65/00—Locks or fastenings for special use
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Connection Of Plates (AREA)
Abstract
Embodiments of the present invention provide a stealth attachment mechanism for a flap of an aircraft, comprising: the lock comprises a lock seat, an elastic clamping ring, a sliding support, an eccentric lock wheel, an elastic piece, a connecting seat, a hexagonal lock cylinder and a limiting rod; one end of the lock seat is movably connected with the connecting seat, and the other end of the lock seat is connected with the sliding support in a sliding manner; the other end of the sliding support is movably connected with the connecting seat; the eccentric lock wheel penetrates through the sliding support to be matched with the lock seat and is fixedly connected with the hexagonal lock cylinder through the elastic clamping ring; the hexagonal lock cylinder is hung with the elastic piece, the first end of the elastic piece is lapped on the lock seat, and the other end of the elastic piece is hung on the limiting rod; the limiting rod is fixedly connected with the hexagonal lock cylinder. The scheme of the invention can realize the unlocking and locking of the opening cover, and is convenient for the operation of the opening cover.
Description
Technical Field
The invention relates to the technical field of connecting structures of aviation and aerospace aircrafts, in particular to an invisible connecting mechanism for a cover of an aircraft.
Background
At present, a large number of covers for the purposes of maintenance, monitoring and the like are installed on aviation and spacecrafts such as airplanes and the like. For ease of operation, the flap needs to be quickly attached.
The existing connecting lock applied to the aerospace operation opening cover has the defects of large volume, heavy weight, incapability of operating by hands, opening of the hole cover and the opening frame, incapability of sealing in a rainproof manner and the like, and cannot meet the use requirements of higher and higher military products; particularly, for stealth airplanes, the existing connecting locks cannot meet the requirement of low reflection of radar waves at present, and the locking and the unlocking are extremely inconvenient.
Disclosure of Invention
The invention provides a invisible attachment mechanism for a flap of an aircraft. The unlocking and locking of the opening cover can be realized, and the operation of the opening cover is convenient.
To solve the above technical problem, an embodiment of the present invention provides the following solutions:
a invisible attachment mechanism for a flap of an aircraft, comprising: the lock comprises a lock seat, an elastic clamping ring, a sliding support, an eccentric lock wheel, an elastic piece, a connecting seat, a hexagonal lock cylinder and a limiting rod;
one end of the lock seat is movably connected with the connecting seat, and the other end of the lock seat is connected with the sliding support in a sliding manner;
the other end of the sliding support is movably connected with the connecting seat;
the eccentric lock wheel penetrates through the inside of the sliding support to be matched with the lock seat and is fixedly connected with the hexagonal lock cylinder through the elastic clamping ring;
the hexagonal lock cylinder is hung with the elastic piece, the first end of the elastic piece is lapped on the lock seat, and the other end of the elastic piece is hung on the limiting rod;
the limiting rod is fixedly connected with the hexagonal lock cylinder.
Optionally, one end of the lock seat is movably connected with the connecting seat through a first pin shaft.
Optionally, the other end of the lock seat is slidably connected to the sliding support through a first screw.
Optionally, the eccentric lock wheel has a hexagonal hole, and the hexagonal lock cylinder is in sliding fit with the hexagonal hole of the eccentric lock wheel.
Optionally, the other end of the sliding support is movably connected with the connecting seat through a second pin shaft.
Optionally, the limiting rod is fixedly connected with the hexagonal lock cylinder through a third pin shaft.
Optionally, a rivet is fixed at the other end of the limiting rod, and the limiting rod is matched with the lock base through the rivet for limiting and locking.
Optionally, the rivet is a round head rivet.
Optionally, the connecting seat is fixedly connected with a cover of a cabin of the aircraft.
Optionally, the connecting seat passes through the self-locking nut through a second screw and is fixedly connected with a cover of the cabin of the aircraft.
The scheme of the invention at least comprises the following beneficial effects:
according to the above aspect of the present invention, the invisible connecting mechanism for a flap of an aircraft comprises: the lock comprises a lock seat, an elastic clamping ring, a sliding support, an eccentric lock wheel, an elastic piece, a connecting seat, a hexagonal lock cylinder and a limiting rod; one end of the lock seat is movably connected with the connecting seat, and the other end of the lock seat is connected with the sliding support in a sliding manner; the other end of the sliding support is movably connected with the connecting seat; the eccentric lock wheel penetrates through the inside of the sliding support to be matched with the lock seat and is fixedly connected with the hexagonal lock cylinder through the elastic clamping ring; the hexagonal lock cylinder is hung with the elastic piece, the first end of the elastic piece is lapped on the lock seat, and the other end of the elastic piece is hung on the limiting rod; the limiting rod is fixedly connected with the hexagonal lock cylinder. Thereby realize the locking and the unblock of flap, convenient operation. The hidden type aircraft has the advantages of simple structure, small volume, light weight, suitability for hidden airplanes, capability of linkage of multiple products, convenience and reliability in operation, and suitability for regular-shaped openings and irregular openings.
Drawings
FIG. 1 is a top view of the invisible attachment mechanism of the present invention;
FIG. 2 is a cross-sectional view of the invisible attachment mechanism of the present invention;
FIG. 3 is a cross-sectional view of the invisible attachment mechanism of the present invention;
FIG. 4 is a schematic exploded view of the invisible coupling mechanism of the present invention;
FIG. 5 is a top view of the invisible coupling mechanism of the present invention in an unlocked state;
FIG. 6 is a cross-sectional view of the invisible attachment mechanism of the present invention in an unlocked state;
FIG. 7 is a side view of the invisible attachment mechanism of the present invention in an unlocked state;
FIG. 8 is a top view of the lock housing of the invisible attachment mechanism of the present invention;
FIG. 9 is a cross-sectional view of the lock housing of the invisible attachment mechanism of the present invention;
FIG. 10 is a side view of the lock housing of the invisible attachment mechanism of the present invention;
FIG. 11 is a schematic view of the eccentric locking wheel of the invisible connecting mechanism of the present invention;
FIG. 12 is a schematic view of the structure of the shoe of the invisible coupling mechanism of the present invention;
FIG. 13 is a schematic structural view of a stop lever of the invisible connecting mechanism of the present invention;
fig. 14 is a schematic structural view of the connecting seat of the invisible connecting mechanism of the invention.
Description of reference numerals:
1-a lock seat; 2-a first screw; 3-an elastic collar; 4-a sliding support; 40-a support body; 41-a first hole; 42-a connecting portion; 43-a second well; 5-eccentric locking wheel; 51-hexagonal holes; 6-an elastic member; 7-a second pin shaft; 8-self-locking nut; 9-a connecting seat; 91-fifth hole; 92-sixth hole; 93-seventh hole; 10-a second screw; 11-a first pin; 12-a rivet; 13-a third pin; 14-a hexagonal lock cylinder; 15-a limiting rod; 151-third aperture; 152-fourth hole.
Detailed Description
Exemplary embodiments of the present disclosure will be described in more detail below with reference to the accompanying drawings. While exemplary embodiments of the present disclosure are shown in the drawings, it should be understood that the present disclosure may be embodied in various forms and should not be limited to the embodiments set forth herein. Rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the scope of the disclosure to those skilled in the art.
As shown in fig. 1 to 4, an embodiment of the present invention provides a concealed coupling mechanism for a flap of an aircraft, including: the lock comprises a lock seat 1, an elastic collar 3, a sliding support 4, an eccentric lock wheel 5, an elastic piece 6, a connecting seat 9, a hexagonal lock cylinder 14 and a limiting rod 15;
one end of the lock seat 1 is movably connected with the connecting seat 9, and the other end of the lock seat 1 is slidably connected with the sliding support 4;
the other end of the sliding support 4 is movably connected with the connecting seat 9;
the eccentric lock wheel 5 penetrates through the inside of the sliding support 4 to be matched with the lock seat 1, and is fixedly connected with the hexagonal lock cylinder 14 through the elastic clamping ring 3;
the hexagonal lock cylinder 14 is provided with the elastic part 6 in a hanging manner, the elastic part 6 can be a spring, a first end of the elastic part 6 is lapped on the lock seat 1, and the other end of the elastic part 6 is provided with the limiting rod 15 in a hanging manner;
the limiting rod 15 is fixedly connected with the hexagonal lock cylinder 14. Thereby realize quick locking and the unblock of flap, convenient operation.
In an alternative embodiment of the present invention, as shown in fig. 8 to 10, the lock seat 1 has a first connecting portion and a second connecting portion, the first connecting portion has a hole for the first pin 11 to pass through, the second connecting portion has a hole for the first screw 2 to insert into, and one end of the lock seat 1 is movably connected to the connecting seat 9 through the first pin 11. The other end of the lock seat 1 is connected with the sliding support 4 in a sliding mode through a first screw 2.
In an alternative embodiment of the present invention, as shown in fig. 11, the cam wheel 5 has a hexagonal hole 51, and the hexagonal key cylinder 14 is slidably fitted in the hexagonal hole 51 of the cam wheel 5.
In an alternative embodiment of the present invention, as shown in fig. 12, the sliding support 4 has a support body 40, the support body 40 has a first hole 41 for the eccentric locking wheel 5 to pass through and a connecting portion 42 connected to the connecting seat 9, the connecting portion 42 has a second hole 43 for the second pin 7 to pass through, and the other end of the sliding support 4 is movably connected to the connecting seat 9 through the second pin 7.
In an alternative embodiment of the present invention, as shown in fig. 13, the limiting rod 15 has a third hole 151 through which the third pin 13 passes and a fourth hole 152 through which the rivet 12 passes, and the limiting rod 15 is fixedly connected to the hexagonal lock cylinder 14 through the third pin 13. The rivet 12 is fixed at the other end of the limiting rod 15, and the limiting rod 15 is matched with the lock base 1 for limiting and locking through the rivet 12. Optionally, the rivet 12 is a round head rivet 12.
In an alternative embodiment of the present invention, as shown in fig. 14, the connecting base 9 has a fifth hole 91 for the first pin 11 to pass through, a sixth hole 92 for the second pin 7 to pass through, and a seventh hole 93 for the second screw 10 to pass through, and the connecting base 9 is connected to the door of the cabin of the aircraft. Optionally, the connecting base 9 is connected to the door of the cabin of the aircraft by a second screw 10 passing through the sixth hole 92 and the self-locking nut 8.
As shown in fig. 1 to 4, the locking working principle and process of the stealth connection mechanism are as follows: during locking, the hexagonal lock cylinder 14 is rotated anticlockwise to drive the eccentric lock wheel 5 to rotate, and the lock cylinder structure (mainly comprising an elastic collar 3, the eccentric lock wheel 5, an elastic part 6, a round-head rivet 12 and the hexagonal lock cylinder 14) rotates, so that the sliding support 4 moves linearly relative to the lock base 1; when the sliding support 4 moves to a limit position, at this time, the head of the round-head rivet 12 of the limit mechanism (the limit mechanism is composed of the round-head rivet 12 and the limit rod 15) just sinks into the hole of the lock base 1, and under the extrusion action provided by the elastic part 6, the limit rod 15 has enough holding force and is in a locking state.
As shown in fig. 5 to 7, the working principle and process of opening the stealth connection mechanism are as follows: the hexagonal lock cylinder 14 is pressed firstly, the elastic piece 6 is in a highly contracted state, when the bottom surface of the head of the round-head rivet 12 can be separated from the top surface of a hole of the lock base 1, the hexagonal lock cylinder 14 rotates 90 degrees clockwise, the eccentric lock wheel 5 is driven to rotate, so that the sliding support 4 moves linearly relative to the lock base 1, the position of the sliding support 4 is limited by the first screw 2 arranged on the lock base 1, the sliding support 4 is located at the other limit position, the invisible connecting mechanism completes unlocking, and the connected cover cap can be opened.
According to the embodiment of the invention, when the invisible connecting mechanism is connected with the cover cap of the aircraft, the cover cap can be conveniently locked and unlocked. The invisible connecting mechanism is simple in structure, small in size, light in weight, suitable for invisible airplanes, capable of achieving linkage of multiple products, convenient and reliable to operate and capable of adapting to openings with regular shapes and irregular openings.
While the foregoing is directed to the preferred embodiment of the present invention, it will be understood by those skilled in the art that various changes and modifications may be made without departing from the spirit and scope of the invention as defined in the appended claims.
Claims (10)
1. A invisible attachment mechanism for a flap of an aircraft, comprising: the lock comprises a lock seat (1), an elastic retainer ring (3), a sliding support (4), an eccentric lock wheel (5), an elastic piece (6), a connecting seat (9), a hexagonal lock cylinder (14) and a limiting rod (15);
one end of the lock seat (1) is movably connected with the connecting seat (9), and the other end of the lock seat (1) is slidably connected with the sliding support (4);
the other end of the sliding support (4) is movably connected with the connecting seat (9);
the eccentric lock wheel (5) penetrates through the sliding support (4) to be matched with the lock seat (1) and is fixedly connected with the hexagonal lock cylinder (14) through the elastic clamping ring (3);
the elastic piece (6) is hung on the hexagonal lock cylinder (14), the first end of the elastic piece (6) is lapped on the lock seat (1), and the other end of the elastic piece is hung on the limiting rod (15);
the limiting rod (15) is fixedly connected with the hexagonal lock cylinder (14).
2. Invisible connection for a flap of an aircraft according to claim 1, characterized in that one end of the lock holder (1) is movably connected to the connection holder (9) by a first pin (11).
3. Invisible connection of a flap for an aircraft according to claim 1, characterized in that the other end of the lock holder (1) is slidingly connected to the sliding support (4) by means of a first screw (2).
4. Invisible connection of a flap for an aircraft according to claim 1, characterized in that the cam wheel (5) has a hexagonal hole, the hexagonal cylinder (14) being a sliding fit with the hexagonal hole of the cam wheel (5).
5. Invisible connection for a flap of an aircraft according to claim 1, characterized in that the other end of the sliding support (4) is movably connected to the connecting seat (9) by a second pin (7).
6. Invisible connection for a flap of an aircraft according to claim 1, characterized in that the limit lever (15) is fixedly connected to the hexagonal key cylinder (14) by a third pin (13).
7. The invisible connecting mechanism for a flap of an aircraft according to claim 1, characterized in that a rivet (12) is fixed to the other end of the limiting rod (15), and the limiting rod (15) is matched with the lock base (1) through the rivet (12) for limiting and locking.
8. Invisible attachment means for a flap of an aircraft according to claim 7, characterized in that the rivet (12) is a round rivet (12).
9. Invisible connection for a flap of an aircraft according to claim 1, characterized in that the connection socket (9) is fixedly connected with a flap of a cabin of an aircraft.
10. Invisible connection for a flap of an aircraft according to claim 1, characterized in that the connection socket (9) is fixedly connected to the flap of the cabin of the aircraft by means of a second screw (10) passing through a self-locking nut (8).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911290269.7A CN110937100B (en) | 2019-12-16 | 2019-12-16 | Invisible connecting mechanism for aircraft flap |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911290269.7A CN110937100B (en) | 2019-12-16 | 2019-12-16 | Invisible connecting mechanism for aircraft flap |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN110937100A true CN110937100A (en) | 2020-03-31 |
| CN110937100B CN110937100B (en) | 2024-05-24 |
Family
ID=69910710
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201911290269.7A Active CN110937100B (en) | 2019-12-16 | 2019-12-16 | Invisible connecting mechanism for aircraft flap |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN110937100B (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115126363A (en) * | 2021-03-29 | 2022-09-30 | 空客直升机德国有限公司 | Opening system for a door |
| US12031367B2 (en) | 2021-03-29 | 2024-07-09 | Airbus Helicopters Deutschland GmbH | Opening system for a door |
Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4341407A (en) * | 1980-05-09 | 1982-07-27 | Rexnord Inc. | Adjustable retention latch assembly |
| US6866442B1 (en) * | 2004-05-20 | 2005-03-15 | Dabico, Inc. | Aircraft service pit T-handle latch |
| CN202279229U (en) * | 2011-10-28 | 2012-06-20 | 北京机电工程研究所 | Automatic locking mechanism for movable cover |
| US20140035296A1 (en) * | 2011-01-10 | 2014-02-06 | Hartwell Corporation | Pressure relief latch mechanism |
| CN105672781A (en) * | 2014-11-19 | 2016-06-15 | 中国航空工业集团公司西安飞机设计研究所 | Quickly-disassembled rotary opening cover lock |
| CN108756517A (en) * | 2018-04-16 | 2018-11-06 | 西安飞机工业（集团）有限责任公司 | A kind of quick-detachable lock of airplane hatch cover |
| CN108843161A (en) * | 2018-07-19 | 2018-11-20 | 今创集团股份有限公司 | Stopping sliding door link-type auxiliary lock |
| US20190127041A1 (en) * | 2017-10-27 | 2019-05-02 | Airbus Operations Sl | Access cover |
| CN211568284U (en) * | 2019-12-16 | 2020-09-25 | 天津爱思达航天科技有限公司 | Invisible connecting mechanism for aircraft opening cover |
-
2019
- 2019-12-16 CN CN201911290269.7A patent/CN110937100B/en active Active
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4341407A (en) * | 1980-05-09 | 1982-07-27 | Rexnord Inc. | Adjustable retention latch assembly |
| US6866442B1 (en) * | 2004-05-20 | 2005-03-15 | Dabico, Inc. | Aircraft service pit T-handle latch |
| US20140035296A1 (en) * | 2011-01-10 | 2014-02-06 | Hartwell Corporation | Pressure relief latch mechanism |
| CN202279229U (en) * | 2011-10-28 | 2012-06-20 | 北京机电工程研究所 | Automatic locking mechanism for movable cover |
| CN105672781A (en) * | 2014-11-19 | 2016-06-15 | 中国航空工业集团公司西安飞机设计研究所 | Quickly-disassembled rotary opening cover lock |
| US20190127041A1 (en) * | 2017-10-27 | 2019-05-02 | Airbus Operations Sl | Access cover |
| CN108756517A (en) * | 2018-04-16 | 2018-11-06 | 西安飞机工业（集团）有限责任公司 | A kind of quick-detachable lock of airplane hatch cover |
| CN108843161A (en) * | 2018-07-19 | 2018-11-20 | 今创集团股份有限公司 | Stopping sliding door link-type auxiliary lock |
| CN211568284U (en) * | 2019-12-16 | 2020-09-25 | 天津爱思达航天科技有限公司 | Invisible connecting mechanism for aircraft opening cover |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115126363A (en) * | 2021-03-29 | 2022-09-30 | 空客直升机德国有限公司 | Opening system for a door |
| CN115126363B (en) * | 2021-03-29 | 2024-01-30 | 空客直升机德国有限公司 | Opening system for a door |
| US12031367B2 (en) | 2021-03-29 | 2024-07-09 | Airbus Helicopters Deutschland GmbH | Opening system for a door |
Also Published As
| Publication number | Publication date |
|---|---|
| CN110937100B (en) | 2024-05-24 |
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