CN111661313A - Quick separation mechanism for aircraft fairing and aircraft - Google Patents
Quick separation mechanism for aircraft fairing and aircraft Download PDFInfo
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- CN111661313A CN111661313A CN202010499534.9A CN202010499534A CN111661313A CN 111661313 A CN111661313 A CN 111661313A CN 202010499534 A CN202010499534 A CN 202010499534A CN 111661313 A CN111661313 A CN 111661313A
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- quick
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- plug socket
- aircraft
- disconnect mechanism
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C7/00—Structures or fairings not otherwise provided for
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- Aviation & Aerospace Engineering (AREA)
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Abstract
Embodiments of the invention provide a quick release mechanism for an aircraft fairing and an aircraft. Quick-release mechanism includes: the first fixing piece is used for fixing the lower head cover; the second fixing piece is used for fixing the upper head cover; the unlocking assembly comprises a plug connector, a first plug socket and a second plug socket, the first plug socket is connected with the first fixing piece, the second plug socket is connected with the second fixing piece, and the plug connector is movably inserted into the first plug socket and the second plug socket; and the at least one driving mechanism is in transmission connection with the corresponding plug connector so as to drive the plug connector to be inserted into or separated from the first plug socket, the second plug socket quick separation mechanism and the quick connection system. Utilize actuating mechanism drive plug connector to insert or break away from first plug socket and second plug socket to realize equipment or separation between lower head cover and the upper head cover, simple structure, the cost is lower, and stability improves greatly, and it can realize making the radome fairing separation that can be stable and quick in flight process.
Description
Technical Field
The invention relates to the technical field of aircraft fairing separation, in particular to a quick separation mechanism for an aircraft fairing and an aircraft.
Background
At present, the aircraft industry is developing rapidly, and the upgrading and updating of each component structure are imperative. The existing fairing separating mechanism is complex in structure, high in cost, poor in stability and relatively heavy. In order to improve the overall performance of the aircraft fairing, the fairing requires a separating mechanism of simple construction; the mechanism needs to be stable in performance; the required mechanism mass is light; the mechanism is required to be low in cost. The existing fairing separating mechanism is difficult to simultaneously have four directions of light weight, simple structure, stable performance and low cost. The quick separation mechanism for the small aircraft fairing has the advantages of light weight, simple structure, stable performance and low cost.
Disclosure of Invention
The invention aims to solve at least one technical problem in the prior art and provides a quick separation mechanism for an aircraft fairing and an aircraft.
In one aspect of the invention, there is provided a quick-disconnect mechanism for an aircraft fairing, the fairing including a lower nose cap and an upper nose cap, the quick-disconnect mechanism comprising:
the first fixing piece is used for fixing the lower head cover;
the second fixing piece is used for fixing the upper hood;
the unlocking assembly comprises a plug connector, a first plug socket and a second plug socket, the first plug socket is connected with the first fixing piece, the second plug socket is connected with the second fixing piece, and the plug connector is movably inserted into the first plug socket and the second plug socket;
and the driving mechanism is in transmission connection with the corresponding plug connector so as to drive the plug connector to be inserted into or separated from the first plug socket and the second plug socket.
Optionally, the drive mechanism comprises:
a drive source;
a rotating member rotatably connected to the driving source;
the first end of the transmission connecting rod is rotatably connected with the rotating piece, and the second end of the transmission connecting rod is rotatably connected with the plug connector.
Optionally, the drive source is a steering engine of the aircraft.
Optionally, the unlocking assembly further includes an elastic element located between the first fixing element and the second fixing element, two ends of the elastic element are respectively plugged with the first fixing element and the second fixing element, and when the plug-in unit is plugged into the first plug-in socket and the second plug-in socket, the elastic element is in a compressed state.
Optionally, the elastic member is a compression spring.
Optionally, the unlocking assembly further comprises a first positioning member, and the first positioning member passes through the first fixing member and is inserted into the elastic member.
Optionally, the unlocking assembly further includes a second positioning element, and the second positioning element passes through the second fixing element and is inserted into the elastic element.
Optionally, the first positioning element and/or the second positioning element employ positioning bolts.
Optionally, the quick separation mechanism includes two unlocking assemblies and two driving mechanisms, the two unlocking assemblies are symmetrically arranged, and each unlocking assembly corresponds to one driving mechanism.
In another aspect of the present invention, an aircraft is provided, where the aircraft includes a fairing including a lower hood and an upper hood, and a quick-release mechanism as described above, where the quick-release mechanism is provided, the first fixing member is connected to the lower hood, and the second fixing member is connected to the upper hood.
The scheme of the invention at least comprises the following beneficial effects:
according to the scheme, the driving mechanism is used for driving the plug connector to be inserted into or separated from the first plug socket and the second plug socket, so that the lower hood and the upper hood are assembled or separated, the structure is simple, the cost is low, the stability is greatly improved, and the fairing can be stably and quickly separated in the flying process.
Drawings
FIG. 1 is a schematic structural view of a quick-disconnect mechanism according to an embodiment of the present invention;
FIG. 2 is a locking state diagram of a quick release mechanism according to another embodiment of the present invention;
FIG. 3 is a view of the quick release mechanism of another embodiment of the present invention shown in an open position from a perspective;
FIG. 4 is a view of the quick release mechanism of another embodiment of the present invention shown in an open position from another perspective;
fig. 5 is a view of a quick disconnect mechanism in a fully open state in accordance with another embodiment of the present invention.
Description of reference numerals:
1-lower head cover; 2-upper head cover; 3-a hinge; 4-an elastic member; 5-a second fixing piece; 6-a second positioning element; 7 a second socket; 8-plug connector; 9-a transmission link; 10-a rotating member; 11-a drive source; 12-a first fixture; 13-a first socket; 14-first positioning element.
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, an embodiment of the present invention is directed to a quick-disconnect mechanism for an aircraft fairing including a lower cowl 1 and an upper cowl 2, the quick-disconnect mechanism including a first mount 12, a second mount 5, at least one unlocking assembly, and at least one drive mechanism.
Illustratively, as shown in fig. 1, the lower head cover 1 and the upper head cover 2 may be in the shape of a cylindrical structure, in an aircraft, the lower head cover 1 and the upper head cover 2 are two independent parts, and the lower head cover 1 and the upper head cover 2 are respectively rotatably connected to a column segment of the aircraft, illustratively, as shown in fig. 1, hinges 3 may be respectively disposed on the lower head cover 1 and the upper head cover 2, so that when the lower head cover 1 and the upper head cover 2 are separated, the lower head cover 1 and the upper head cover 2 can be completely separated around the respective hinge rotation axes, and of course, besides, a person skilled in the art can design some other rotatable connection structures of the lower head cover 1 and the upper head cover 2 and the column segment of the aircraft according to actual needs, which the embodiment is not limited.
As shown in fig. 1, the first fixing member 12 is connected to the lower head cover 1, for example, the first fixing member 12 may be screwed with the lower head cover 1 (using a threaded fastener such as a bolt or a screw), the second fixing member 5 is connected to the upper head cover 2, and the second fixing member 5 may also be screwed with the upper head cover 2, and besides, the first fixing member 12 and the second fixing member 5 may also be fixedly connected to the lower head cover 1 and the upper head cover 2 in other ways, which is not limited in this embodiment.
Illustratively, as shown in fig. 1, the unlocking assembly includes a plug 8, a first socket 13 and a second socket 7. The first inserting seat 13 is connected with the first fixing part 12, the second inserting seat 7 is connected with the second fixing part 5, and the inserting piece 8 is movably inserted in the first inserting seat 13 and the second inserting seat 7. For example, the first inserting seat 13 may be screwed with the first fixing element 12, and the second inserting seat 7 may also be screwed with the second fixing element 5, and of course, other ways may also be adopted to implement the connection therebetween, which is not limited in this embodiment. Furthermore, the plug 8 is movably inserted into the first socket 13 and the second socket 7, for example, a jack or a slot matching with the plug 8 may be provided in each of the first socket 13 and the second socket 7 so that the plug 8 is inserted therein.
Illustratively, as shown in fig. 1, the driving mechanism is in transmission connection with the corresponding plug 8 to drive the plug 8 to be inserted into or removed from the first socket 13 and the second socket 7, and the specific structure of the driving mechanism is not limited, for example, as shown in fig. 1, the driving mechanism may employ a crank and rocker mechanism, and besides, a person skilled in the art may design some other driving mechanisms according to actual needs, for example, a rack and pinion mechanism, and the like, which is not limited in this embodiment. In addition, each driving mechanism may correspond to one unlocking assembly, and of course, a person skilled in the art may also design some other corresponding manners of the driving mechanism and the unlocking assembly according to actual needs, for example, each driving mechanism may correspond to a plurality of unlocking assemblies, and the like, which is not limited in this embodiment.
Specifically, referring to fig. 2 together, the plug 8 is fully inserted into the first and second sockets 13 and 7, so that the lower head housing 1 and the upper head housing 2 are fixedly connected together. When it is necessary to separate the lower head housing 1 and the upper head housing 2, as shown in fig. 1, 3 and 4, the driving mechanism drives the plug-in unit 8 to move so that the plug-in unit 8 is separated from the first and second plug sockets 13 and 7, thereby separating the lower head housing 1 and the upper head housing 2.
The quick separation mechanism of this embodiment utilizes actuating mechanism drive plug connector to insert or break away from first plug socket and second plug socket to realize equipment or separation between lower hood and the upper hood, simple structure, the cost is lower, and stability improves greatly, and it can realize making the radome fairing separation that can be stable and quick in flight process.
Illustratively, as shown in fig. 1, the driving mechanism includes a driving source 11, a rotating member 10, and a transmission link 9. The drive links 9 here may be a plurality of drive links, not limited to three or four drive links. The driving source 11 may be a driving motor, and in order to further simplify the quick release mechanism, a steering engine of the aircraft may be reused as the driving source 11, which is not limited in this embodiment. The rotation member 10 is rotatably connected to the driving source 11. The first end of the transmission connecting rod 9 and the rotation component 10 can be rotationally connected, the second end of the transmission connecting rod 9 and the plug connector 8 can be rotationally connected, for example, the first end of the transmission connecting rod 9 can be rotationally connected with the rotation component 10 through a pin or a screw, the second end of the transmission connecting rod 9 can be rotationally connected with the plug connector 8 through a pin or a screw, and the embodiment is not limited thereto.
The quick release mechanism of the embodiment forms a crank rocker mechanism by utilizing the driving source, the rotating piece and the transmission connecting rod, has simple structure and higher stability, and is also favorable for quickly and stably realizing the installation and the separation of the lower head cover and the upper head cover.
Illustratively, as shown in fig. 1, the unlocking assembly further includes an elastic member 4 located between the first fixing member 12 and the second fixing member 5, two ends of the elastic member 4 are respectively inserted into the first fixing member 12 and the second fixing member 5, and when the plug member 8 is inserted into the first insertion seat 13 and the second insertion seat 7, the elastic member 4 is in a compressed state. Illustratively, the elastic member 4 may be a compression spring or other elastic structure.
Combine fig. 5 in the lump, when lower hood 1 and upper hood 2 need the separation, control driving source 11 (steering wheel) rotate, and rotation piece 10 on the steering wheel drives transmission connecting rod 9, and then drives the separation of plug connector 8 on the transmission connecting rod 9 from first plug socket 13 and second plug socket 7, and elastic component 4 loses the constraint this moment, because plug connector 8 inserts first plug socket 13 with during the second plug socket 7, elastic component 4 is in compression state, consequently after elastic component 4 loses the constraint, its length of recovering originally, and this elastic force promotes lower hood 1 and upper hood 2 separation, and then makes lower hood 1 and upper hood 2 separate completely around hinge 3 pivot separately with the aid of aerodynamic force.
Illustratively, as shown in fig. 1, the unlocking assembly further comprises a first fixing member 14 and a second fixing member 6, wherein the first fixing member 14 passes through the first fixing member 12 and is inserted into the elastic member 4. The second positioning element 6 passes through the second fixing element 5 and is inserted into the elastic element 4. For example, the first positioning element 14 and the second positioning element 6 may be positioning bolts, the first positioning element 14 may be screwed with the first fixing element 12, and the second positioning element 6 may also be screwed with the second fixing element 5, and besides, the first positioning element 14 and the second positioning element 6 may also adopt other positioning element structures and other connection manners, which is not limited in this embodiment. In addition, the first positioning element 14 and the second positioning element 6 preferably exist at the same time, and of course, in practical application, only the first positioning element 14 may be included, or only the second positioning element 6 may be included, which may be determined according to practical needs, and the present embodiment is not limited thereto.
The quick separation mechanism of this embodiment can effectively fix a position the elastic component and the mounting that corresponds through the first setting element and the second setting element that set up to can further effectively realize quick installation and rapid and stable separation.
Illustratively, as shown in fig. 1 and 2, the quick-release mechanism includes two unlocking assemblies and two driving mechanisms, the two unlocking assemblies are symmetrically arranged, and each unlocking assembly corresponds to one driving mechanism.
In another aspect of the present invention, an aircraft is provided, where the aircraft includes a fairing including a lower hood and an upper hood and a quick release mechanism, where the quick release mechanism is the quick release mechanism described in the foregoing, and reference may be made to the foregoing description, which is not repeated herein. The first fixing piece is connected with the lower head cover, and the second fixing piece is connected with the upper head cover.
The aircraft of this embodiment has the quick separation mechanism of the aforesaid record, utilizes actuating mechanism drive plug connector to insert or break away from first plug socket and second plug socket to realize the equipment or the separation between lower head cover and the upper head cover, simple structure, the cost is lower, and stability improves greatly, and it can realize can be stable and quick messenger's radome fairing separation in the flight process.
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 quick-disconnect mechanism for an aircraft fairing, the fairing including a lower cowl and an upper cowl, the quick-disconnect mechanism comprising:
the first fixing piece is used for fixing the lower head cover;
the second fixing piece is used for fixing the upper hood;
the unlocking assembly comprises a plug connector, a first plug socket and a second plug socket, the first plug socket is connected with the first fixing piece, the second plug socket is connected with the second fixing piece, and the plug connector is movably inserted into the first plug socket and the second plug socket;
and the driving mechanism is in transmission connection with the corresponding plug connector so as to drive the plug connector to be inserted into or separated from the first plug socket and the second plug socket.
2. The quick disconnect mechanism of claim 1, wherein the drive mechanism comprises:
a drive source;
a rotating member rotatably connected to the driving source;
the first end of the transmission connecting rod is rotatably connected with the rotating piece, and the second end of the transmission connecting rod is rotatably connected with the plug connector.
3. The quick disconnect mechanism of claim 2, wherein the drive source employs a steering engine of the aircraft.
4. The quick-disconnect mechanism of any one of claims 1-3, wherein the unlocking assembly further comprises a resilient member located between the first and second securing members, opposite ends of the resilient member being respectively engaged with the first and second securing members, and the resilient member being in a compressed state when the plug member is inserted into the first and second receptacles.
5. The quick release mechanism of claim 4, wherein the resilient member is a compression spring.
6. The quick disconnect mechanism of claim 4, wherein the unlocking assembly further comprises a first locator that passes through the first securing member and is inserted into the resilient member.
7. The quick disconnect mechanism of claim 6, wherein the unlocking assembly further comprises a second locating member that passes through the second securing member and is inserted into the resilient member.
8. The quick-disconnect mechanism of claim 7, wherein the first and/or second positioning members employ positioning bolts.
9. The quick-disconnect mechanism of any one of claims 1-3, comprising two unlocking assemblies and two drive mechanisms, the two unlocking assemblies being symmetrically arranged and one drive mechanism for each unlocking assembly.
10. An aircraft comprising a fairing comprising a lower hood and an upper hood and a quick-disconnect mechanism, wherein the quick-disconnect mechanism is as claimed in any one of claims 1 to 9, the first attachment means being connected to the lower hood and the second attachment means being connected to the upper hood.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010499534.9A CN111661313B (en) | 2020-06-04 | 2020-06-04 | Quick separation mechanism for aircraft fairing and aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010499534.9A CN111661313B (en) | 2020-06-04 | 2020-06-04 | Quick separation mechanism for aircraft fairing and aircraft |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN111661313A true CN111661313A (en) | 2020-09-15 |
| CN111661313B CN111661313B (en) | 2022-06-14 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202010499534.9A Active CN111661313B (en) | 2020-06-04 | 2020-06-04 | Quick separation mechanism for aircraft fairing and aircraft |
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| CN (1) | CN111661313B (en) |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20050230562A1 (en) * | 2003-06-11 | 2005-10-20 | Buehler David B | Payload fairing separation system |
| CN103129740A (en) * | 2013-02-07 | 2013-06-05 | 玉环县天润航空机械制造厂 | Locking mechanism of engine compartment fairing |
| CN103510783A (en) * | 2013-10-18 | 2014-01-15 | 青岛四方车辆研究所有限公司 | Opening-closing mechanism with self-locking devices |
| JP5417040B2 (en) * | 2009-05-25 | 2014-02-12 | 株式会社Ｉｈｉエアロスペース | Sliding fairing decapitation device and sliding fairing decapitation method |
| US8931738B2 (en) * | 2012-02-21 | 2015-01-13 | Raytheon Company | Releasable radome cover |
| CN107628042A (en) * | 2017-09-13 | 2018-01-26 | 中车青岛四方车辆研究所有限公司 | Rail vehicle kuppe, switching mechanism and self-locking locking mechanism |
| CN111006837A (en) * | 2019-11-22 | 2020-04-14 | 中国航天空气动力技术研究院 | Hood separation wind tunnel test device applied to large dynamic pressure continuous adjustment |
| CN111037501A (en) * | 2019-12-17 | 2020-04-21 | 湖北航天技术研究院总体设计所 | Spring separation device with cam limiting mechanism |
-
2020
- 2020-06-04 CN CN202010499534.9A patent/CN111661313B/en active Active
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20050230562A1 (en) * | 2003-06-11 | 2005-10-20 | Buehler David B | Payload fairing separation system |
| JP5417040B2 (en) * | 2009-05-25 | 2014-02-12 | 株式会社Ｉｈｉエアロスペース | Sliding fairing decapitation device and sliding fairing decapitation method |
| US8931738B2 (en) * | 2012-02-21 | 2015-01-13 | Raytheon Company | Releasable radome cover |
| CN103129740A (en) * | 2013-02-07 | 2013-06-05 | 玉环县天润航空机械制造厂 | Locking mechanism of engine compartment fairing |
| CN103510783A (en) * | 2013-10-18 | 2014-01-15 | 青岛四方车辆研究所有限公司 | Opening-closing mechanism with self-locking devices |
| CN107628042A (en) * | 2017-09-13 | 2018-01-26 | 中车青岛四方车辆研究所有限公司 | Rail vehicle kuppe, switching mechanism and self-locking locking mechanism |
| CN111006837A (en) * | 2019-11-22 | 2020-04-14 | 中国航天空气动力技术研究院 | Hood separation wind tunnel test device applied to large dynamic pressure continuous adjustment |
| CN111037501A (en) * | 2019-12-17 | 2020-04-21 | 湖北航天技术研究院总体设计所 | Spring separation device with cam limiting mechanism |
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| Publication number | Publication date |
|---|---|
| CN111661313B (en) | 2022-06-14 |
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