Quick separation mechanism for aircraft fairing and aircraft
阅读说明:本技术 一种用于飞行器整流罩的快速分离机构和飞行器 (Quick separation mechanism for aircraft fairing and aircraft ) 是由 邹云翔 季宝锋 王志勇 尚博 刘发杰 刘含洋 韩宇 于 2020-06-04 设计创作,主要内容包括:本发明的实施例提供一种用于飞行器整流罩的快速分离机构和飞行器。快速分离机构包括:第一固定件,用于固定下头罩;第二固定件,用于固定上头罩;至少一个解锁组件,包括插接件、第一插接座以及第二插接座,第一插接座与第一固定件相连,第二插接座与第二固定件相连,插接件可移动地插设在第一插接座和第二插接座中;至少一个驱动机构,与对应的插接件传动相连,以驱动插接件插入或脱离第一插接座和第二插接座快速分离机构和快速连接系统。利用驱动机构驱动插接件插入或脱离第一插接座和第二插接座,从而实现下头罩和上头罩之间的组装或分离,结构简单,成本较低,稳定性大大提高,其可以实现在飞行过程中可以稳定且快速的使整流罩分离。(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.)
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.
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
Illustratively, as shown in fig. 1, the lower head cover 1 and the
As shown in fig. 1, the
Illustratively, as shown in fig. 1, the unlocking assembly includes a
Illustratively, as shown in fig. 1, the driving mechanism is in transmission connection with the
Specifically, referring to fig. 2 together, the
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
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
Combine fig. 5 in the lump, when lower hood 1 and
Illustratively, as shown in fig. 1, the unlocking assembly further comprises a
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.
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