CN110937100B - Invisible connecting mechanism for aircraft flap - Google Patents
Invisible connecting mechanism for aircraft flap Download PDFInfo
- Publication number
- CN110937100B CN110937100B CN201911290269.7A CN201911290269A CN110937100B CN 110937100 B CN110937100 B CN 110937100B CN 201911290269 A CN201911290269 A CN 201911290269A CN 110937100 B CN110937100 B CN 110937100B
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- China
- Prior art keywords
- lock
- seat
- sliding support
- hexagonal
- flap
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- 230000007246 mechanism Effects 0.000 title claims abstract description 40
- 230000009471 action Effects 0.000 claims description 2
- 230000006978 adaptation Effects 0.000 description 2
- 230000001788 irregular Effects 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 230000008569 process Effects 0.000 description 2
- 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
- 238000012544 monitoring process Methods 0.000 description 1
- 238000007789 sealing Methods 0.000 description 1
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 concealed 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 slidably connected with the sliding support; the other end of the sliding support is movably connected with the connecting seat; the eccentric lock wheel passes 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 elastic piece is hung on the hexagonal lock cylinder, 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; and the limiting rod is fixedly connected with the hexagonal lock cylinder. The scheme of the invention can realize unlocking and locking of the opening cover, and is convenient for operation of the opening cover.
Description
Technical Field
The invention relates to the technical field of connection structures of aviation and aerospace aircrafts, in particular to a stealth connection mechanism for a flap of an aircraft.
Background
At present, aviation and spacecrafts such as airplanes are all provided with a large number of covers for maintenance, monitoring and other purposes. For ease of operation, the flap requires a quick connection.
The existing connecting lock applied to the aviation operation flap has the defects of large volume, heavy weight, incapability of free-hand operation, opening of the hole cover and the mouth frame, incapability of rain-proof sealing and the like, and can not meet the use requirements of higher and higher speed military products; in particular to the stealth aircraft, the existing connecting lock can not meet the low reflection requirement of radar waves at present, and is extremely inconvenient to lock and unlock.
Disclosure of Invention
The invention provides a concealed attachment mechanism for a flap of an aircraft. The opening and locking of the opening cover can be realized, and the operation of the opening cover is convenient.
In order to solve the technical problems, the embodiment of the invention provides the following scheme:
a concealed 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 slidably connected with the sliding support;
the other end of the sliding support is movably connected with the connecting seat;
the eccentric lock wheel passes through the interior 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 elastic piece is hung on the hexagonal lock cylinder, 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;
And 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 with the sliding support through a first screw.
Optionally, the eccentric lock wheel is provided with 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 in limit locking with the lock seat in a matched mode through the rivet.
Optionally, the rivet is a round head rivet.
Optionally, the connecting seat is fixedly connected with a flap of a cabin of the aircraft.
Optionally, the connecting seat is fixedly connected with a flap of the cabin of the aircraft through a self-locking nut by a second screw.
The scheme of the invention at least comprises the following beneficial effects:
According to the scheme, the invisible connecting mechanism for the aircraft flap comprises the following components: 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 slidably connected with the sliding support; the other end of the sliding support is movably connected with the connecting seat; the eccentric lock wheel passes through the interior 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 elastic piece is hung on the hexagonal lock cylinder, 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; and the limiting rod is fixedly connected with the hexagonal lock cylinder. Therefore, the locking and unlocking of the flap are realized, and the operation is convenient. The structure is simple, the size is small, the weight is light, the device is suitable for stealth aircraft, can realize multi-product linkage, is convenient and reliable to operate, and can adapt to regular-shape openings and irregular openings.
Drawings
FIG. 1 is a top view of the invisible connecting mechanism of the present invention;
FIG. 2 is a cross-sectional view of the invisible connecting mechanism of the present invention;
FIG. 3 is a cross-sectional view of the invisible connecting mechanism of the present invention;
FIG. 4 is a schematic view of the invisible connecting mechanism of the present invention in an exploded state;
FIG. 5 is a top view of the invisible connecting mechanism of the present invention in an unlocked state;
FIG. 6 is a cross-sectional view of the invisible connecting mechanism of the present invention in an unlocked state;
FIG. 7 is a side view of the invisible connecting mechanism of the present invention in an unlocked state;
FIG. 8 is a top view of the lock base of the invisible connecting mechanism of the present invention;
FIG. 9 is a cross-sectional view of the lock base of the invisible connecting mechanism of the present invention;
FIG. 10 is a side view of the lock base of the invisible connecting mechanism of the present invention;
FIG. 11 is a schematic view of the eccentric lock of the invisible connecting mechanism of the present invention;
FIG. 12 is a schematic view of the structure of the sliding support of the invisible connecting mechanism of the present invention;
FIG. 13 is a schematic view of the structure of the stop lever of the invisible connecting mechanism of the present invention;
fig. 14 is a schematic structural view of a connecting seat of the invisible connecting mechanism of the invention.
Reference numerals illustrate:
1-a lock base; 2-a first screw; 3-an elastic collar; 4-sliding support; 40-a support body; 41-a first hole; 42-connecting part; 43-a second hole; 5-eccentric lock wheels; 51-hexagonal holes; 6-elastic members; 7-a second pin shaft; 8-self-locking nuts; 9-connecting seats; 91-fifth hole; 92-sixth hole; 93-seventh well; 10-a second screw; 11-a first pin; 12-rivets; 13-a third pin; 14-hexagonal lock core; 15-a limiting rod; 151-a third hole; 152-fourth well.
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 attachment mechanism for a flap of an aircraft, comprising: the lock comprises a lock seat 1, an elastic clamping 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 passes through the interior 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 elastic piece 6 is hung on the hexagonal lock cylinder 14, the elastic piece 6 can be a spring, the first end of the elastic piece 6 is lapped on the lock seat 1, and the other end is hung on the limit rod 15;
the limiting rod 15 is fixedly connected with the hexagonal lock cylinder 14. Thereby realizing the quick locking and unlocking of the flap and facilitating the operation.
In an alternative embodiment of the present invention, as shown in fig. 8 to 10, the lock base 1 has a first connection portion and a second connection portion, the first connection portion has a hole for passing the first pin 11, the second connection portion has a hole for inserting the first screw 2, and one end of the lock base 1 is movably connected with the connection base 9 through the first pin 11. The other end of the lock seat 1 is in sliding connection with the sliding support 4 through a first screw 2.
In an alternative embodiment of the invention, as shown in fig. 11, the eccentric lock 5 has a hexagonal hole 51, and the hexagonal lock cylinder 14 is slidably engaged with the hexagonal hole 51 of the eccentric lock 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 through which the eccentric lock 5 passes, and a connection portion 42 connected to the connection seat 9, the connection portion 42 has a second hole 43 through which the second pin 7 passes, and the other end of the sliding support 4 is movably connected to the connection seat 9 through the second pin 7.
In an alternative embodiment of the present invention, as shown in fig. 13, the stop lever 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 stop lever 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 seat 1 to limit and lock through the rivet 12. Alternatively, the rivet 12 is a round head rivet 12.
In an alternative embodiment of the invention, as shown in fig. 14, the connection seat 9 has a fifth hole 91 through which the first pin 11 passes, a sixth hole 92 through which the second pin 7 passes, and a seventh hole 93 through which the second screw 10 passes, and the connection seat 9 is connected to the flap of the cabin of the aircraft. Alternatively, the connection seat 9 is connected to the flap of the cabin of the aircraft by means of a second screw 10, which passes through a sixth hole 92 and a self-locking nut 8.
As shown in fig. 1 to 4, the locking working principle and process of the stealth connecting mechanism are as follows: when in locking, the hexagonal lock cylinder 14 is rotated anticlockwise to drive the eccentric lock wheel 5 to rotate, and the lock cylinder structure (the lock cylinder structure mainly comprises an elastic clamping ring 3, the eccentric lock wheel 5, an elastic piece 6, a round head rivet 12 and the hexagonal lock cylinder 14) performs rotary motion, so that the sliding support 4 performs linear motion relative to the lock seat 1; when the sliding support 4 moves to a limit position, at this time, the round head rivet 12 head 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 seat 1, and under the extrusion action provided by the elastic piece 6, the limit rod 15 has enough holding force and is in a locking state.
As shown in fig. 5 to 7, the operation principle and the 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 round head rivet 12 can be separated from the top surface of the hole of the lock seat 1, the hexagonal lock cylinder 14 rotates 90 degrees clockwise to drive the eccentric lock wheel 5 to rotate, so that the sliding support 4 moves linearly relative to the lock seat 1, the sliding support 4 is positioned at the other limit position by limiting the position of the sliding support 4 through the first screw 2 arranged on the lock seat 1, the stealth connecting mechanism is unlocked, and the connected flap can be opened.
According to the embodiment of the invention, when the invisible connecting mechanism is connected with the aircraft flap, the flap can be conveniently locked and unlocked. The invisible connecting mechanism has the advantages of simple structure, small volume, light weight, suitability for stealth aircraft, capability of realizing multi-product linkage, convenience and reliability in operation and suitability for regular-shape openings and irregular openings.
While the foregoing is directed to the preferred embodiments of the present invention, it will be appreciated by those skilled in the art that various modifications and adaptations can be made without departing from the principles of the present invention, and such modifications and adaptations are intended to be comprehended within the scope of the present invention.
Claims (8)
1. A concealed attachment mechanism for a flap of an aircraft, comprising: the lock comprises a lock seat (1), an elastic clamping 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) passes 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);
the connecting seat (9) is fixedly connected with a port cover of a cabin of the aircraft;
a rivet (12) is fixed at the other end of the limiting rod (15), and the limiting rod (15) is matched with the lock seat (1) to be limited and locked through the rivet (12);
When the invisible connecting mechanism is locked, the hexagonal lock cylinder (14) rotates anticlockwise and drives the eccentric lock wheel (5) to rotate, the lock cylinder structure rotates to enable the sliding support (4) to move linearly relative to the lock seat (1), when the sliding support (4) moves to a limit position, the head of the rivet (12) sinks into a hole of the lock seat (1), and under the action of the elastic piece (6), the limiting rod (15) is in a locking state;
when the invisible connecting mechanism is unlocked, the hexagonal lock cylinder (14) is pressed to enable the elastic piece (6) to be in a contracted state, when the bottom surface of the head of the rivet (12) is separated from the top surface of the hole of the lock seat (1), the hexagonal lock cylinder (14) rotates clockwise and drives the eccentric lock wheel (5) to rotate, the sliding support (4) moves linearly relative to the lock seat (1), and the position of the sliding support (4) is limited by the first screw (2) arranged on the lock seat (1), so that the sliding support (4) is located at the other limit position, and the invisible connecting mechanism is unlocked.
2. Invisible connection mechanism for a flap of an aircraft according to claim 1, characterized in that one end of the lock base (1) is movably connected with the connection base (9) by means of a first pin (11).
3. Invisible connection mechanism for a flap of an aircraft according to claim 1, characterized in that the other end of the lock base (1) is slidingly connected with the sliding support (4) by means of a first screw (2).
4. Invisible connection mechanism for a flap of an aircraft according to claim 1, characterized in that the eccentric lock (5) has a hexagonal hole, the hexagonal lock cylinder (14) being in sliding engagement with the hexagonal hole of the eccentric lock (5).
5. Invisible connection mechanism for a flap of an aircraft according to claim 1, characterized in that the other end of the sliding support (4) is movably connected with the connection seat (9) by means of a second pin (7).
6. Invisible connection mechanism for a flap of an aircraft according to claim 1, characterized in that the limit lever (15) is fixedly connected with the hexagonal lock cylinder (14) by means of a third pin (13).
7. Invisible connection mechanism for a flap of an aircraft according to claim 1, characterized in that the rivet (12) is a round head rivet (12).
8. Invisible connection mechanism for the flap of an aircraft according to claim 1, characterized in that the connection seat (9) is fixedly connected with the flap of the cabin of the aircraft by means of a second screw (10) 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 CN110937100A (en) | 2020-03-31 |
| CN110937100B true 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) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP4067235B1 (en) * | 2021-03-29 | 2024-02-28 | AIRBUS HELICOPTERS DEUTSCHLAND GmbH | An opening system for a door |
Citations (7)
| 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 |
| 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 |
| 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 |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CA2826868C (en) * | 2011-01-10 | 2019-12-03 | Hartwell Corporation | Pressure relief latch mechanism |
| ES2802546T3 (en) * | 2017-10-27 | 2021-01-20 | Airbus Operations Sl | Access cover |
-
2019
- 2019-12-16 CN CN201911290269.7A patent/CN110937100B/en active Active
Patent Citations (7)
| 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 |
| 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 |
| 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 |
Also Published As
| Publication number | Publication date |
|---|---|
| CN110937100A (en) | 2020-03-31 |
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