CN108100237B - Novel aircraft backplate allies oneself with disconnected mechanism - Google Patents
Novel aircraft backplate allies oneself with disconnected mechanism Download PDFInfo
- Publication number
- CN108100237B CN108100237B CN201711231688.4A CN201711231688A CN108100237B CN 108100237 B CN108100237 B CN 108100237B CN 201711231688 A CN201711231688 A CN 201711231688A CN 108100237 B CN108100237 B CN 108100237B
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- CN
- China
- Prior art keywords
- guard plate
- rocker arm
- shell
- joint
- clamping part
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- 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.)
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/02—Undercarriages
- B64C25/08—Undercarriages non-fixed, e.g. jettisonable
- B64C25/10—Undercarriages non-fixed, e.g. jettisonable retractable, foldable, or the like
- B64C25/16—Fairings movable in conjunction with undercarriage elements
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/02—Undercarriages
- B64C25/08—Undercarriages non-fixed, e.g. jettisonable
- B64C25/10—Undercarriages non-fixed, e.g. jettisonable retractable, foldable, or the like
- B64C25/18—Operating mechanisms
- B64C25/20—Operating mechanisms mechanical
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/02—Undercarriages
- B64C25/08—Undercarriages non-fixed, e.g. jettisonable
- B64C25/10—Undercarriages non-fixed, e.g. jettisonable retractable, foldable, or the like
- B64C25/18—Operating mechanisms
- B64C25/26—Control or locking systems therefor
Abstract
The invention relates to a connecting and disconnecting mechanism between an aircraft guard plate and a guard plate retractable actuating cylinder, belonging to the field of aircraft structure design. A novel aircraft guard plate connection and disconnection mechanism is used for connection and disconnection between a guard plate and a guard plate retraction actuator cylinder, and mainly comprises a joint, a rocker arm with a latch hook, a shell, a rocker arm with a press key, a spring I and a spring II; one end of the joint is rotatably connected with the rotating shaft line of the guard plate, and the other end of the joint is connected with a piston rod of the guard plate retractable actuating cylinder; the rocker arm with the latch hook is provided with a connecting part I rotationally connected with the shell, a clamping part I clamped with the joint and a clamping part II clamped with the rocker arm with the press key, and the clamping part I and the clamping part II are arranged on two sides of the connecting part I; the shell is fixedly connected with a guard plate skin, and the guard plate skin covers the outer surface of the guard plate; the rocker arm with the press key is provided with a connecting part II rotationally connected with the shell, a limiting groove clamped with the clamping part II, and the press key which penetrates through the through hole in the guard plate skin and is flush with the outer surface of the guard plate skin. The invention has the following advantages: the structure is simple and reliable, the protective plate of the airplane wheel can be opened and closed quickly, and the maintainability of the airplane is improved.
Description
Technical Field
The invention relates to a connecting and disconnecting mechanism between an aircraft guard plate and a guard plate retractable actuating cylinder, belonging to the field of aircraft structure design.
Background
In an aircraft landing gear system, landing gear guard plates mainly comprise strut guard plates, wheel guard plates and the like, and the main function is to ensure the aerodynamic shape of an aircraft. The opening mode of the guard plate is generally two, and one mode is that the opening or closing of the guard plate is controlled directly by the retraction of the actuating cylinder. The other type is a follow-up type, namely the guard plate is connected with the undercarriage or the undercarriage retracting actuator cylinder through a pull rod and is opened or closed along with the retraction of the undercarriage. At present, most airplane wheel guard plates are controlled to be opened or closed through retraction and extension of a ram, and meanwhile, due to the overall requirement of an airplane, when a landing gear is put down, the airplane wheel guard plates driven by the ram need to be closed.
When the ground is maintained, when the accessories in the wheel cabins of the airplane are overhauled and maintained, the protective plate needs to be opened, under the normal condition, the protective plate is opened without a hydraulic source and an air source when the airplane is parked on the ground, and at the moment, a ground crew is usually required to manually disconnect the bolt connection of the hydraulic actuating cylinder and the protective plate. Because undercarriage wheel cabin space is narrower and small, lead to the bolt dismouting in-process like this, the home range of hand receives very big restriction, therefore dismouting maintenance process is very arduous.
Disclosure of Invention
The invention aims to provide a novel aircraft protective plate connecting and disconnecting mechanism which can quickly and conveniently open and close a protective plate under the condition without a hydraulic source and an air source.
In order to achieve the purpose, the invention adopts the following technical scheme: a novel aircraft guard plate connection and disconnection mechanism is used for connection and disconnection between a guard plate and a guard plate retraction actuator cylinder, and mainly comprises a joint, a rocker arm with a latch hook, a shell, a rocker arm with a press key, a spring I and a spring II; one end of the joint is rotatably connected with the rotating shaft line of the guard plate, and the other end of the joint is connected with a piston rod of the guard plate retractable actuating cylinder; the rocker arm with the latch hook is provided with a connecting part I rotationally connected with the shell, a clamping part I clamped with the joint and a clamping part II clamped with the rocker arm with the press key, and the clamping part I and the clamping part II are arranged on two sides of the connecting part I; the shell is fixedly connected with a guard plate skin, and the guard plate skin covers the outer surface of the guard plate; the rocker arm with the press key is provided with a connecting part II rotationally connected with the shell, a limiting groove clamped with the clamping part II, and the press key which penetrates through the through hole in the guard plate skin and is flush with the outer surface of the guard plate skin; one end of the spring I is connected with a rocker arm with a pressing key, the other end of the spring I is connected with an angle sheet, and the angle sheet is connected with the shell; one end of the spring II is connected with the rocker arm with the lock hook, the other end of the spring II is connected with the corner piece, and the corner piece is connected with the shell.
Preferably, a limiting bush is mounted on the joint through a bolt, and the clamping portion I is clamped with the limiting bush when the guard plate and the guard plate retracting actuator cylinder are in a connected state.
Preferably, the rocker arm with the latch hook is connected with the shell through a bolt, a gasket and a gasket, a nut is in threaded connection with the bolt, and a through hole for allowing the opening pin to pass through is formed in the end part where the bolt and the nut are fixed.
Preferably, a nine-stage precision bushing is installed between the rocker arm with the latch hook and the bolt.
After the guard plate connection and disconnection mechanism is adopted, a pressing key of the connection and disconnection mechanism can be pressed outside the guard plate, the rocker arm is driven by pressing the pressing key, the connection between the guard plate and the guard plate retractable actuating cylinder can be quickly disconnected, and the guard plate is opened. After the work is finished, the guard plate is pushed to the closing position by hand, the rocker arm with the locking hook is locked, and the guard plate can be automatically and reliably connected with the guard plate retracting actuator cylinder. After the guard plate is connected with the guard plate retractable actuating cylinder, the retractable movement of the guard plate is restored to be controlled by the actuating cylinder, and the guard plate is closed.
Compared with the prior art, the invention has the following advantages: the structure is simple and reliable, the protective plate of the airplane wheel can be opened and closed quickly, and the maintainability of the airplane is improved.
Drawings
FIG. 1 is a schematic illustration of an aircraft fender configuration according to an embodiment of the invention;
FIG. 2 is a top view of the hidden frame guard retracting actuator cylinder of FIG. 1;
FIG. 3 is a schematic structural view of a guard plate coupling and disconnecting mechanism in a locked state according to an embodiment of the present invention;
FIG. 4 is a schematic structural view of a guard plate linking mechanism in an unlocked state according to an embodiment of the present invention;
FIG. 5 is a schematic view of FIG. 3A;
FIG. 6 is a cross-sectional view of FIG. 5B-B;
FIG. 7 is a cross-sectional view of FIGS. 5C-C;
FIG. 8 is a schematic structural view of a fender panel coupling mechanism according to an embodiment of the invention;
FIG. 9 is a schematic view of the shield linking mechanism of FIG. 8 with the housing removed and in a locked position;
FIG. 10 is a schematic view of the shield linking mechanism in the unlocked state with the outer case removed;
in the figure, 1, a guard plate folding and unfolding actuating cylinder, 2, a guard plate, 3, a joint, 4, a joint, 5, a guard plate connecting and disconnecting mechanism, 6, a joint, 7, a rocker arm with a lock hook, 8, a shell, 9, a spring, 10, a guard plate skin, 11, a rocker arm with a press key, 12, a spring, 13, a connecting joint, 14, a limiting bush, 15, a bolt, 16, a gasket, 17, a bolt, 18, a gasket, 19, a nine-stage precision bush, 20, a cotter pin, 21, a nut, 22, a corner piece, 23 and a skin connecting piece.
Detailed Description
The invention is described in further detail below with reference to the accompanying figures 1-10: the guard plate linkage breaking mechanism 5 consists of a joint 6, a rocker arm 7 with a latch hook, a rocker arm 11 with a press key, a spring 9, a spring 12 and a shell 8; as shown in fig. 3 and 5, one end of the joint 6 is installed on the rotation axis of the guard plate 2, and the other end is connected with the piston rod of the guard plate retracting actuator cylinder 1 through a connecting joint 13, as shown in fig. 6, a limit bushing 14 is installed in the joint 6 through a bolt 15; as shown in fig. 3-4 and 6, the middle part of the rocker arm 7 with the latch hook is rotatably connected with the housing 8, one end of the rocker arm is clamped with the limiting bush 14 of the joint 6, and the other end of the rocker arm is clamped with the limiting groove of the rocker arm with the press key; the middle part of a rocker arm 11 with a press key is rotatably connected with a shell 8, one end of the rocker arm is a limiting groove clamped with the rocker arm 7 with a lock hook, and the other end of the rocker arm is the press key which penetrates through a through hole on a guard plate skin 10 and is flush with the outer surface of the rocker arm; the shell 8 is fixedly connected with a guard plate skin 10, and the guard plate skin covers the outer surface of the guard plate 2; as shown in fig. 1 and 2, during the extension of the piston rod, the joint 3, the joint 4, the joint 6 and all points on the joints rotate around the axis of the guard plate 2.
As shown in fig. 3, when the guard plate linking and disconnecting mechanism 5 is in a locked state, the guard plate 2 and the guard plate retracting and releasing actuator cylinder 1 are connected together by the rocker arm 7 with the latch hook, the guard plate 2 retracts and releases under the action of the guard plate retracting and releasing actuator cylinder 1, and due to the action of the rocker arm 7 with the latch hook, the retracting and releasing motion track of the guard plate retracting and releasing actuator cylinder 1 is determined; as shown in fig. 4 and 6, when the guard plate 2 needs to be opened, the pressing key of the rocker arm 11 with the pressing key is pressed outside the guard plate 2, the restriction of the rocker arm 7 with the latch hook by the limiting groove on the rocker arm 11 with the pressing key is released, the rocker arm 7 with the latch hook automatically separates from the limiting bush 14 under the action of the spring 12, and the connection between the rocker arm 7 with the latch hook and the joint 6 is disconnected, namely the connection between the guard plate 2 and the guard plate retraction jack 1 is disconnected.
As shown in fig. 4, when the protector plate link mechanism 5 is in the unlocked state, the protector plate 2 can rotate freely; the method for connecting the guard plate 2 and the guard plate retractable actuating cylinder 1 is simple, the guard plate 2 is pushed to the closing position by only slightly impacting with hands, the locking hook on the rocker arm 7 with the locking hook is rotated under the action of the limiting bush 14 after being contacted with the limiting bush 14 on the joint 6, and meanwhile, the spring 9 drives the rocker arm 11 with the press key to rotate until the rocker arm 7 with the locking hook is locked by the limiting groove on the rocker arm 11 with the press key. Therefore, the guard plate 2 is connected with the guard plate retractable actuating cylinder 1, and the guard plate 2 can be retracted and retracted under the action of the guard plate retractable actuating cylinder 1.
As shown in fig. 7, the rocker arm 7 with the latch hook is connected with the housing 8 through a bolt 17, a gasket 16 and a gasket 18, a nut 21 is screwed with the bolt to fasten the rocker arm 7 with the latch hook with the housing 8, in order to prevent looseness, a through hole for a cotter pin 20 to pass through is arranged at the end part where the bolt 17 and the nut 21 are fixed, and the cotter pin is inserted into the through hole; in order to make the rocker arm 7 with the latch hook rotate flexibly, a nine-stage precision bushing 19 is arranged between the rocker arm 7 with the latch hook and the bolt 17.
As shown in fig. 8, 9 and 10, one end of the spring 12 is connected with the rocker arm 7 with the locking hook, the other end is connected with the corner piece 22, one end of the spring 9 is connected with the rocker arm 11 with the press key, the other end is connected with the corner piece 22, and the corner piece 22 is connected with the shell through a rivet. When the guard plate disconnecting mechanism is in a connection locking state, the press key on the rocker arm 11 with the press key is positioned in the through hole between the skin connecting sheet 23 and the guard plate skin 10, the end of the press key is flush with the outer surface of the guard plate skin 10, and the skin connecting sheet 23 is riveted with the guard plate skin 10.
The above examples are merely preferred embodiments of the present invention and are not intended to limit the present invention. Any extension or modification made on the basis of the present invention is within the protection scope of the present invention.
Claims (4)
1. The utility model provides a novel aircraft backplate allies oneself with disconnected mechanism for be connected and break off between backplate (2) and backplate receive and release pressurized cylinder (1), its characterized in that: the guard plate linkage and disconnection mechanism (5) mainly comprises a joint (6), a rocker arm (7) with a locking hook, a shell (8), a rocker arm (11) with a pressing key, a spring I (9) and a spring II (12);
one end of the joint (6) is rotatably connected with the rotating shaft line of the guard plate (2), and the other end of the joint is connected with a piston rod of the guard plate retractable actuating cylinder (1);
the rocker arm (7) with the latch hook is provided with a connecting part I rotationally connected with the shell (8), a clamping part I clamped with the joint (6) and a clamping part II clamped with the rocker arm (11) with the press key, wherein the clamping part I and the clamping part II are arranged on two sides of the connecting part I;
the shell (8) is fixedly connected with a guard plate skin (10), and the guard plate skin (10) covers the outer surface of the guard plate (2);
the rocker arm (11) with the press key is provided with a connecting part II rotationally connected with the shell (8), a limiting groove clamped with the clamping part II, and the press key which penetrates through the through hole on the guard plate skin (10) and is flush with the outer surface of the guard plate skin;
one end of a spring I (9) is connected with a rocker arm (11) with a press key, the other end of the spring I is connected with an angle sheet (22), and the angle sheet (22) is connected with the shell (8);
one end of a spring II (12) is connected with the rocker arm (7) with the latch hook, the other end of the spring II is connected with the corner piece (22), and the corner piece (22) is connected with the shell (8).
2. The novel aircraft fender linkage mechanism of claim 1, wherein: and a limiting bush (14) is arranged on the joint (6) through a bolt (15), and the clamping part I is clamped with the limiting bush (14) when the guard plate (2) and the guard plate retractable actuating cylinder (1) are in a connecting state.
3. The novel aircraft fender linkage mechanism according to claim 1 or 2, characterized in that: the rocker arm (7) with the latch hook is connected with the shell (8) through a bolt (17), a gasket (16) and a gasket (18), a nut (21) is in threaded connection with the bolt (17), and a through hole for allowing a split pin (20) to penetrate is formed in the end part where the bolt and the nut are fixed.
4. The novel aircraft fender linkage mechanism of claim 3, wherein: and a nine-grade precision bushing (19) is arranged between the rocker arm (7) with the latch hook and the bolt (17).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711231688.4A CN108100237B (en) | 2017-11-30 | 2017-11-30 | Novel aircraft backplate allies oneself with disconnected mechanism |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711231688.4A CN108100237B (en) | 2017-11-30 | 2017-11-30 | Novel aircraft backplate allies oneself with disconnected mechanism |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN108100237A CN108100237A (en) | 2018-06-01 |
| CN108100237B true CN108100237B (en) | 2021-01-05 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201711231688.4A Active CN108100237B (en) | 2017-11-30 | 2017-11-30 | Novel aircraft backplate allies oneself with disconnected mechanism |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108100237B (en) |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7188804B1 (en) * | 2004-06-25 | 2007-03-13 | Boetto Steven C | Float retractable landing gear |
| CN104176244A (en) * | 2014-09-17 | 2014-12-03 | 江西洪都航空工业集团有限责任公司 | Linked landing gear cabin door folding and unfolding device |
| CN204210730U (en) * | 2014-09-18 | 2015-03-18 | 中国商用飞机有限责任公司 | Landing gear uplock mechanism |
| CN105584628A (en) * | 2015-10-27 | 2016-05-18 | 成都飞机工业（集团）有限责任公司 | Guard plate and landing gear linkage retracting device |
| CN106218866A (en) * | 2016-08-19 | 2016-12-14 | 中航飞机起落架有限责任公司 | A kind of backplate follower of undercarriage |
-
2017
- 2017-11-30 CN CN201711231688.4A patent/CN108100237B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7188804B1 (en) * | 2004-06-25 | 2007-03-13 | Boetto Steven C | Float retractable landing gear |
| CN104176244A (en) * | 2014-09-17 | 2014-12-03 | 江西洪都航空工业集团有限责任公司 | Linked landing gear cabin door folding and unfolding device |
| CN204210730U (en) * | 2014-09-18 | 2015-03-18 | 中国商用飞机有限责任公司 | Landing gear uplock mechanism |
| CN105584628A (en) * | 2015-10-27 | 2016-05-18 | 成都飞机工业（集团）有限责任公司 | Guard plate and landing gear linkage retracting device |
| CN106218866A (en) * | 2016-08-19 | 2016-12-14 | 中航飞机起落架有限责任公司 | A kind of backplate follower of undercarriage |
Also Published As
| Publication number | Publication date |
|---|---|
| CN108100237A (en) | 2018-06-01 |
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