CN211568284U - Invisible connecting mechanism for aircraft opening cover - Google Patents
Invisible connecting mechanism for aircraft opening cover Download PDFInfo
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- CN211568284U CN211568284U CN201922246697.1U CN201922246697U CN211568284U CN 211568284 U CN211568284 U CN 211568284U CN 201922246697 U CN201922246697 U CN 201922246697U CN 211568284 U CN211568284 U CN 211568284U
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- lock
- flap
- seat
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- invisible
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Abstract
An embodiment of the utility model provides an invisible coupling mechanism for flap of aircraft, include: 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 utility model discloses a scheme can realize unblanking and locking of flap, makes things convenient for the operation of flap.
Description
Technical Field
The utility model relates to an aviation, aerospace vehicle's connection structure technical field especially indicates a stealthy coupling mechanism of flap for 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; especially for stealthy aircraft use, present connecting lock all can not satisfy radar wave low reflection demand at present, and present connecting lock, locking and open are extremely inconvenient.
SUMMERY OF THE UTILITY MODEL
The utility model provides a stealthy coupling mechanism of flap for aircraft. The unlocking and locking of the opening cover can be realized, and the operation of the opening cover is convenient.
In order 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 above technical scheme of the utility model at least include following beneficial effect: above-mentioned scheme of the utility model, an stealthy coupling mechanism for flap of aircraft includes: 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 connecting 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 view of the invisible connecting mechanism according to the present invention in an exploded state;
FIG. 5 is a plan view of the invisible connecting mechanism of the present invention in an unlocking state;
FIG. 6 is a 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 housing of the invisible connecting 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 structural view of an eccentric lock wheel of the invisible connecting mechanism of the present invention;
fig. 12 is a schematic structural view of a sliding support of the invisible connecting 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 connection seat of the invisible connection mechanism of the present 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. 1-4, embodiments of the present invention provide a stealth attachment mechanism for a flap of an aircraft, comprising: 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 optional 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, 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 eccentric lock wheel 5 has a hexagonal hole 51, and the hexagonal lock cylinder 14 is slidably fitted in the hexagonal hole 51 of the eccentric lock wheel 5.
In an optional 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 optional 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 seat 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 seat 9 is connected to the cover 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.
The above embodiment of the utility model, when stealthy coupling mechanism is connected with the flap of aircraft, can conveniently realize locking and opening the flap. 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.
The foregoing is a preferred embodiment of the present invention, and it should be noted that, for those skilled in the art, a plurality of improvements and decorations can be made without departing from the principle of the present invention, and these improvements and decorations should also be regarded as the protection scope of the present invention.
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 |
|---|---|---|---|
| CN201922246697.1U CN211568284U (en) | 2019-12-16 | 2019-12-16 | Invisible connecting mechanism for aircraft opening cover |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201922246697.1U CN211568284U (en) | 2019-12-16 | 2019-12-16 | Invisible connecting mechanism for aircraft opening cover |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN211568284U true CN211568284U (en) | 2020-09-25 |
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ID=72548292
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201922246697.1U Active CN211568284U (en) | 2019-12-16 | 2019-12-16 | Invisible connecting mechanism for aircraft opening cover |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN211568284U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110937100A (en) * | 2019-12-16 | 2020-03-31 | 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 CN201922246697.1U patent/CN211568284U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110937100A (en) * | 2019-12-16 | 2020-03-31 | 天津爱思达航天科技有限公司 | Invisible connecting mechanism for aircraft opening cover |
| CN110937100B (en) * | 2019-12-16 | 2024-05-24 | 天津爱思达航天科技有限公司 | Invisible connecting mechanism for aircraft flap |
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| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
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| CP01 | Change in the name or title of a patent holder |
Address after: No.2 workshop of high power bulldozer, No.18, Yingchun Road, Huaming hi tech Industrial Zone, Dongli District, Tianjin Patentee after: Tianjin istar-space Technology Co.,Ltd. Address before: No.2 workshop of high power bulldozer, No.18, Yingchun Road, Huaming hi tech Industrial Zone, Dongli District, Tianjin Patentee before: SUZHOU ISTAR AVIATION TECHNOLOGY Co.,Ltd. |