CN111232180A - Aircraft cabin door gust wind lock device - Google Patents
Aircraft cabin door gust wind lock device Download PDFInfo
- Publication number
- CN111232180A CN111232180A CN202010119372.1A CN202010119372A CN111232180A CN 111232180 A CN111232180 A CN 111232180A CN 202010119372 A CN202010119372 A CN 202010119372A CN 111232180 A CN111232180 A CN 111232180A
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- Prior art keywords
- locking
- door
- lock device
- aircraft
- locked
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- 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
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- 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
- B64C1/1407—Doors; surrounding frames
Abstract
The utility model provides an aircraft cabin door gust wind locking device, can fix a position the accuracy, can improve and lock, unblock the accuracy. The aircraft door gust locking device locks the door of the aircraft at a fixed position so as to lock the door at a maximum opening state, and comprises: a locked portion fixedly installed at a door jamb of the door and having a locked portion; and a locking part installed on the hinge arm of the door and having a locking member, a positioning member and a limiting member, wherein the locking member has a locking portion locked with the locked portion and has three catching portions at different positions, the positioning member is disposed adjacent to the locking member and has two protruding portions disposed opposite to the three catching portions, the limiting member is disposed between the locking member and the positioning member for limiting a movement range of a relative position of the limiting member and the positioning member, and at least two different relative positions of the locking member with respect to the positioning member are defined using the three catching portions of the locking member, the two protruding portions of the positioning member and the limiting member.
Description
Technical Field
The invention relates to the field of design of airplane cabin door mechanisms, in particular to an airplane cabin door gust lock device for preventing an airplane cabin door from shaking due to gust or other external forces.
Background
After the airplane cabin door is opened, the wind gust lock device can keep the airplane cabin door at a fixed position so as to prevent the airplane cabin door from shaking due to wind gust or other external forces. Such gust lock devices are generally suitable for use with an outward opening door and may be mounted adjacent to a fixed pivot shaft of an aircraft door to ensure that the aircraft door remains in an open position.
The conventional gust lock device is realized by using a boss-and-groove type limit structure and a stay-and-support type limit structure, and for example, refer to non-patent document 1 "gust lock of a gate for boarding a general-purpose aircraft (western aircraft design institute, china aviation industry group company) and non-patent document 2" a double-curved-section semi-plugged cargo door of a civil aircraft (central aviation sinking civil aircraft llc).
However, when the gust lock device is installed or removed or the parts of the gust lock device are replaced, other mechanisms of the aircraft door need to be removed, and the structure is complex and is difficult to process and install.
Therefore, how to design a novel airplane cabin door gust lock device which can accurately position and improve locking and unlocking accuracy becomes a technical problem to be solved urgently.
In addition, it is desirable to design an aircraft door gust lock device that reduces or even eliminates the impact on other mechanisms of the aircraft door when installing or removing the aircraft door gust lock device or replacing parts thereof, and that is simple in construction and easy to manufacture and install.
Disclosure of Invention
The invention aims to provide an aircraft cabin door gust wind lock device which can be accurately positioned and can improve the locking and unlocking accuracy.
In addition, another object of the present invention is to provide an aircraft door gust lock device, which can reduce or even eliminate the influence on other mechanisms of the aircraft door when the aircraft door gust lock device is installed or disassembled or the parts of the aircraft door gust lock device are replaced, and has the advantages of simple structure and easy processing and installation.
In order to solve the above technical problem, a first aspect of the present invention provides an aircraft door gust lock device for locking a door of an aircraft in a fixed position to lock the door in a maximum open state, the aircraft door gust lock device comprising: a locked portion fixedly mounted to a door jamb of the door and having a locked portion; and a locking part installed on the hinge arm of the hatch door and having a locking member, a positioning member and a limiting member, wherein the locking member has a locking portion locked with the locked portion and has three or more catching portions at different positions, the positioning member is disposed adjacent to the locking member and has two or more protruding portions disposed opposite to the three or more catching portions of the locking member, the limiting member is disposed between the locking member and the positioning member for limiting a movement range of a relative position of the limiting member and the positioning member, and at least two different relative positions of the locking member with respect to the positioning member are defined by the three or more catching portions of the locking member, the two or more protruding portions of the positioning member, and the limiting member.
According to the structure, the locked part (namely, the latch part) of the airplane door gust lock device is fixedly arranged on the door frame of the door, and the locked part (namely, the latch hook part) of the airplane door gust lock device is arranged on the hinge arm of the door, so that when the airplane door gust lock device is installed or disassembled or replaced, other mechanisms of the door cannot be influenced, and the disassembly operation of other mechanisms of the door DC is not needed.
In addition, according to the above configuration, since the at least two different relative positions of the locking member with respect to the positioning member are defined by the at least three locking portions of the locking member, the at least two protrusions of the positioning member, and the stopper, the positioning can be performed accurately, and the accuracy of locking and unlocking can be improved.
The aircraft door gust lock device according to a second aspect of the present invention is the aircraft door gust lock device according to the first aspect of the present invention, and is characterized in that one of the two or more protrusions, i.e., the first protrusion, is capable of engaging with two of the three or more locking portions, i.e., the first locking portion or the second locking portion, so that the locking member and the positioning member are located at the first relative position or the second relative position.
An aircraft door gust lock device according to a third aspect of the present invention is the aircraft door gust lock device according to the second aspect of the present invention, and is characterized in that, in the first relative position, the first protrusion of the positioning member abuts against the first catch portion of the locking member, the stopper abuts against a second protrusion of one of the two or more protrusions of the positioning member, and the locking portion of the locking member is completely disengaged from the locked portion, in the second relative position, the first protrusion of the positioning member abuts against the second catch portion of the locking member, the stopper abuts against a third catch portion of the other of the three or more catch portions of the locking member, and the locking portion of the locking member is locked to the locked portion, in which the locking member and the positioning member are provided so as to be able to rotate between the first relative position and the second relative position And (6) moving.
According to the above configuration, when the cabin door of the aircraft is fully locked (the second relative position), since the first protrusion of the positioning member (i.e., the second ratchet wheel) abuts against the second catch portion of the locking member (i.e., the first ratchet wheel) and the limiting member (i.e., the limiting pin) abuts against the third catch portion of the locking member (i.e., the first ratchet wheel), the locked of the locked portion (i.e., the latch portion) and the locking portion (i.e., the latch portion) can be maintained by the positioning member (i.e., the second ratchet wheel) and the limiting member (i.e., the limiting pin).
The aircraft door gust lock device according to a fourth aspect of the present invention is the aircraft door gust lock device according to the third aspect of the present invention, and is characterized in that the lock portion further includes a telescopic rod, a fixed end of the telescopic rod is provided on one of the locking member and the positioning member, and a telescopic end is provided on the other of the locking member and the positioning member, and the telescopic rod is in an extended state at the first relative position and in a retracted state at the second relative position.
The aircraft door gust lock device according to a fifth aspect of the present invention is the aircraft door gust lock device according to the fourth aspect of the present invention, and is characterized in that the locking portion further includes a compression spring which is fitted over the telescopic rod and exerts an urging force in an extension direction when the telescopic rod is retracted.
According to the above configuration, when the cabin door of the aircraft is completely locked (the second relative position), since the telescopic rod is pressed to contract while the compression spring fitted over the telescopic rod applies an urging force in the extending direction, the first protrusion of the positioning member (i.e., the second ratchet wheel) can be more securely brought into abutment against the second catch of the locking member (i.e., the first ratchet wheel), thereby more securely locking the locked portion (i.e., the latch portion) and the locking portion (i.e., the latch portion).
The aircraft door gust lock device according to a sixth aspect of the present invention is the aircraft door gust lock device according to any one of the first to fifth aspects of the present invention, characterized in that the aircraft door gust lock device further comprises an operating portion coupled to the locking portion via a transmission lever.
An aircraft door gust lock device according to a seventh aspect of the present invention is the aircraft door gust lock device according to the sixth aspect of the present invention, wherein the operating portion is attached to the hinge arm of the door, and has a handle, a handle rotation shaft, a connecting rod, and a handle crank shaft, the handle rotation shaft being connected to the handle, and being rotated to lock or unlock the locking portion connected to the connecting rod of the operating portion via the handle crank shaft and the transmission rod with respect to the locked portion fixedly attached to the door frame of the door.
An aircraft door gust lock device according to an eighth aspect of the present invention is the aircraft door gust lock device according to the seventh aspect of the present invention, and is characterized in that the operating portion further includes a stopper pin, a torsion spring, and a spring stopper seat, the torsion spring is restricted in its axial degree of freedom along the connecting rod by the spring stopper seat, and the torsion spring provides a circumferential torsion moment to prevent the handle from rotating in the unlocking direction when the locking portion is locked with respect to the locked portion.
According to the above configuration, when the cabin door of the aircraft is completely locked (the second relative position), the torsion spring provided in the operation portion is in a twisted state, and provides a torque to the handle crankshaft, and is transmitted to the second ratchet via the transmission rod, thereby preventing the second ratchet from rotating backward, and thus, the latch portion can be prevented from being disengaged from the latch hook portion 120, and safety can be improved.
Drawings
Fig. 1 is a schematic view showing the position of the aircraft door gust lock device of the present invention with the door in an open state.
Fig. 2 is a schematic view showing the overall structure of the aircraft door gust lock device of the present invention in the state of fig. 1.
Fig. 3 is a view showing a fully locked state of the aircraft door gust lock device according to the present invention, which is a schematic view showing positions of respective members in the fully locked state of the aircraft door gust lock device.
Fig. 4 is a diagram showing an unlocked state of the aircraft door gust lock device of the present invention, which is a schematic position diagram of each component in the unlocked state of the aircraft door gust lock device.
Fig. 5 is a view showing a fully locked state of the aircraft door gust lock device according to the present invention, which is a schematic view showing relative positions of the latch hook and the latch in the fully locked state of the aircraft door gust lock device.
Fig. 6 is a diagram showing an unlocked state of the aircraft door gust lock device of the present invention, which is a schematic diagram showing relative positions of the lock hook and the lock latch in the unlocked state of the aircraft door gust lock device.
Detailed Description
Hereinafter, the structure of the aircraft door gust lock device 100 according to the present invention will be described with reference to the accompanying drawings.
Fig. 1 is a schematic view showing the position of the aircraft door gust lock device 100 of the present invention with the door in an open state.
As shown in fig. 1, door jambs CD are provided on both sides of a door of an aircraftFL、DFRDoor jambs CD on both sidesFL、DFRCross member CD passing through cabin doorCBAre connected.
The aircraft door gust lock device 100 of the present invention locks the door of the aircraft in a fixed position to maintain the maximum open state of the door and prevent the door from shaking due to gusts of wind or other external forces.
In addition, when it is desired to close a door of an aircraft, the aircraft door gust lock device 100 needs to be released first.
Fig. 2 is a schematic view showing the overall structure of the aircraft door gust lock device 100 of the present invention in the state of fig. 1.
As shown in fig. 2, the aircraft door gust lock device 100 of the present invention includes a latch unit 110, a latch hook 120, an operating unit 130 and a transmission rod 140, wherein the latch unit 110 and the latch hook 120 are engaged in a fully locked state of the door and are disengaged in a fully unlocked state of the door, and the operating unit 130 is coupled to the latch hook 120 through the transmission rod 140 and is operated to lock or unlock the door of the aircraft.
The latch part 110 is fixedly installed at a door jamb CD of a door of an aircraftFLAnd includes a latch 111 and a latch holder 112, wherein the latch holder 112 supports the latch 111 and is provided with a pair of latch holes 112a, 112b through which the latch 111 passes.
The latch hook part 120 is installed on the hinge arm HA, and includes a first ratchet 121 formed with a latch hook 121a capable of being engaged with or disengaged from the latch 111 and having three catching parts 121b, 121c, 121d at a position different from the latch hook 121a, a second ratchet 122 disposed adjacent to the first ratchet 121 and having two protrusions 122a, 122b disposed opposite to the catching parts 121b, 121c, 121d of the first ratchet 121, a stopper pin 123 disposed between each catching part 121b, 121c, 121d of the first ratchet 121 and each protrusion 122a, 122b of the second ratchet 122 for limiting a moving range of a relative position of the first ratchet 121 and the second ratchet 122, a compression spring 125, and a fixed end of the expansion link 124 disposed at one of the first ratchet 121 and the second ratchet 122, the retractable end is provided on the other of the first ratchet wheel 121 and the second ratchet wheel 122, and the compression spring 125 is fitted around the retractable rod 124 and applies an urging force in the extending direction when the retractable rod 124 is retracted.
Of the two protrusions 122a, 122b of the second ratchet 122, the first protrusion 122a can engage with the first locking portion 121b or the second locking portion 121c of the three locking portions 121b, 121c, 121d, so that the first ratchet 121 and the second ratchet 122 are in the first relative position or the second relative position.
In addition, when the first ratchet wheel 121 and the second ratchet wheel 122 are in the first relative position (the unlocking position), the first protrusion 122a of the second ratchet wheel 122 abuts against the first blocking portion 121b of the first ratchet wheel 121, and the limit pin 123 abuts against the second protrusion 122b of the second ratchet wheel 122. When the first ratchet 121 and the second ratchet 122 are at the second relative position (the fully locked position), the first protrusion 122a of the second ratchet 122 abuts against the second catch 121c of the first ratchet 121, and the limit pin 123 abuts against the third catch 121d of the first ratchet 121. The first ratchet wheel 121 and the second ratchet wheel 122 are provided to be rotatable between a first relative position and a second relative position by the respective catching portions 121b, 121c, 121d, the respective protrusions 122a, and the stopper pin 123.
In the state where the hatch is unlocked, the first ratchet 121 and the second ratchet 122 are in a first relative position to each other, at this time, the latch hook 121a formed on the first ratchet 121 is completely disengaged from the latch 111, and the telescopic rod 124 is in an extended state (having a first length) such that the coupling end of the first ratchet 121 and the coupling end of the second ratchet 122 are away from each other.
On the other hand, in the state where the hatch door is completely locked, the first ratchet 121 and the second ratchet 122 are in a second relative position to each other, at this time, the locking hook 121a formed on the first ratchet 121 is hooked in the locking latch 111, and the telescopic rod 124 is in a contracted state (having a second length) such that the coupling end of the first ratchet 121 and the coupling end of the second ratchet 122 are close to each other.
The operating part 130 is also mounted on the hinge arm HA and comprises a handle 131, a handle spindle 132, a connecting rod 133 and a handle crankshaft 134, wherein the handle 131 is a gripping part for the operator to grip the operating part 130, the handle spindle 132 is connected to the handle 131, and the latch hook 120 connected to the connecting rod 133 of the operating part 130 via the handle crankshaft 134 and the transmission rod 140 is rotatable relative to a door jamb CD fixedly mounted on a door of an aircraftFLThe latch part 110 is hooked or unhooked.
The operating portion 130 further includes a limiting pin 135, a torsion spring 136 and a spring limiting seat 137, the torsion spring 136 is limited in its axial degree of freedom along the connecting rod 133 by the spring limiting seat 137, and under the action of the limiting pin 135, when locked, the torsion spring 136 provides a circumferential torsion moment to prevent the handle 131 from rotating in the unlocking direction.
The aircraft door gust lock device 100 according to the present invention has two modes of locking and unlocking, and the movement of the aircraft door gust lock device 100 in the two modes of locking and unlocking will be described below.
Lock
Fig. 3 and 5 are views showing a completely locked state of the aircraft door gust lock device 100 according to the present invention, in which fig. 3 is a schematic view showing positions of respective members in the completely locked state of the aircraft door gust lock device 100, and fig. 5 is a schematic view showing a relative position of the latch hook 121a and the latch bar 111 in the completely locked state of the aircraft door gust lock device 100.
As shown in fig. 3 and 5, when the operator opens the door DC of the aircraft, the latch hook 120 of the aircraft door gust lock device 100 rotates around the rotation shaft together with the hinge arm HA, and the latch hook 121a of the latch hook 120 formed on the first ratchet 121 comes into contact with the latch 111 of the latch part 110 near the end of the door DC opening process, and the extendable rod 124 is still at the first length. As the door DC is further opened, the telescopic rod 124 is compressed, so that the latch hook 121a formed on the first ratchet wheel 121 rotates until the latch hook 121a is completely hooked with the latch 111, and at this time, the door DC is opened to the maximum position, and the telescopic rod 124 is at the second length, and the first protrusion 122a of the second ratchet wheel 122 abuts against the second catch 121c of the first ratchet wheel 121, and the latch hook 121a is locked with the latch 111 under the combined action of the compression spring 125. In addition, as shown in fig. 2, since the torsion spring 136 is in a torsion state at this time, a torque is provided to the handle crankshaft 134 and is transmitted to the second ratchet 122 through the transmission rod 140, and the second ratchet 122 is prevented from rotating back, thereby further reliably abutting the second ratchet 122 against the first ratchet 121, so that the latch hook 121a is locked.
Unlocking of
Fig. 4 and 6 are diagrams showing an unlocked state of the aircraft door gust lock device 100 according to the present invention, wherein fig. 4 is a schematic diagram showing positions of respective members in the unlocked state of the aircraft door gust lock device 100, and fig. 6 is a schematic diagram showing a relative position of the latch hook 121a and the latch 111 in the unlocked state of the aircraft door gust lock device 100.
As shown in fig. 4 and 6, when the operator wants to close the door DC of the aircraft, the handle 131 is pushed first, the handle crank 134 rotates, and the second ratchet 122 is pushed to rotate around its axis by the transmission rod 140, and at this time, the first protrusion 122a of the second ratchet 122 is out of contact with the second catch 121c of the first ratchet 121. Subsequently, under the extending action of the telescopic rod 124, the latch hook 121a formed on the first ratchet 121 rotates clockwise around its axis and moves away from the latch 111 of the latch part 110 until completely disengaging from the latch 111, and becomes an unlocked state.
According to the above configuration, in the aircraft door gust lock device 100 of the present invention, when the door CB of the aircraft is completely locked, the first protrusion 122a of the second ratchet 122 abuts against the second stopper 121c of the first ratchet 121, and the stopper pin 123 abuts against the third stopper 121d of the first ratchet 121, so that the lock between the latch part 110 and the latch hook part 120 can be maintained by the second ratchet 122 and the stopper pin 123.
In the aircraft door gust lock apparatus 100 according to the present invention, when the door CB of the aircraft is completely locked, the extendable rod 124 is pushed and retracted, and the compression spring 125 fitted over the extendable rod 124 applies an urging force in the extension direction, so that the first protrusion 122a of the second ratchet 122 can be more securely brought into contact with the second stopper 121c of the first ratchet 121, thereby more securely locking the latch 110 and the latch hook 120.
In the aircraft door gust lock apparatus 100 according to the present invention, when the door CB of the aircraft is completely locked, the torsion spring 136 provided in the operating unit 130 is in a twisted state, and applies a torque to the handle crank 134, and the torque is transmitted to the second ratchet 122 through the transmission rod 140, thereby preventing the second ratchet 122 from rotating, and thus preventing the latch unit 110 from being disengaged from the latch unit 120, and improving the safety of locking.
In addition, according to the above-mentioned structure, in the aircraft door gust lock device 100 of the present invention, the latch part 110 is fixedly installed on the door jamb CD of the door of the aircraftFLThe locking hook 120 is mounted on the hinge arm HA, and the operation portion 130 is also mounted on the hinge arm HA, so that when the aircraft door gust lock device 100 is installed or disassembled or the aircraft door gust lock device 100 is replaced, other mechanisms of the door DC are not affected, and the disassembly operation of other mechanisms of the door DC is not required. In addition, the aircraft cabin door gust lock device 100 is simple in structure, accurate in positioning, convenient to process and install, capable of reducing assembly cost and improving locking and unlocking accuracy.
Additional advantages and modifications will readily occur to those skilled in the art. Therefore, the invention in its broader aspects is not limited to the specific details and representative embodiments shown and described herein. Accordingly, modifications may be made without departing from the spirit or scope of the general inventive concept as defined by the appended claims and their equivalents.
In the embodiment of the present invention, the latch part 110 (latch 111) is explained as an example of the locked part (locked portion), but the present invention is not limited to this, and may be any other suitable part or portion as long as it can lock the locking member thereto, and their shape, size, and the like are not limited.
In addition, in the embodiment of the present invention, the explanation has been made taking the example in which the locking hook portion 120 (the locking hook 121a of the first ratchet 121) is taken as the locking portion (the locking portion of the locking member), but the present invention is not limited to this, and may be any other suitable member or portion as long as it can be locked on the locked portion of the locked portion, and their shape, size, and the like are not limited.
In addition, in the embodiment of the present invention, the example in which the first ratchet 121 having three catching portions is used as the locking member, the example in which the second ratchet 122 having two protruding portions is used as the positioning portion, and the example in which the stopper pin 123 is used as the stopper portion has been described, but the present invention is not limited to this, and any other suitable member or portion may be used as long as the locking member has a function of being locked and unlocked with respect to the locked portion and has a function of being firmly fixed at the locked position and the unlocked position together with the stopper member, and their shape, size, and the like are not limited. The number of the engaging portions is not limited to three, and may be four or more, and the number of the protruding portions is not limited to two, and may be three or more.
Claims (9)
1. An aircraft door gust lock device (100) for locking a door of an aircraft in a fixed position to lock the door in a maximum open position, the aircraft door gust lock device (100) comprising:
a locked portion fixedly mounted to a door jamb (CD) of the doorFL) And has a locked portion; and
a locking part mounted on a Hinge Arm (HA) of the hatch and having a locking member, a positioning member and a limiting member, wherein,
the locking member has a locking portion locked with the to-be-locked portion and has three or more catching portions (121b, 121c, 121d) at different positions,
the positioning member is disposed adjacent to the locking member and has two or more protruding portions (122a, 122b) disposed opposite to the three or more catching portions (121b, 121c, 121d) of the locking member,
the limiting piece is arranged between the locking piece and the positioning piece and used for limiting the movement range of the relative position of the limiting piece and the positioning piece,
at least two different relative positions of the locking member with respect to the positioning member are defined by the three or more catching portions (121b, 121c, 121d) of the locking member, the two or more protrusions (122a, 122b) of the positioning member, and the limiting member.
2. The aircraft door gust lock device (100) according to claim 1,
one of the two or more protrusions (122a, 122b), i.e., the first protrusion (122a), can be engaged with two of the three or more engaging portions (121b, 121c, 121d), i.e., the first engaging portion (121b) or the second engaging portion (121c), so that the locking member and the positioning member are located at the first relative position or the second relative position.
3. The aircraft door gust lock device (100) according to claim 2,
in the first relative position, the first protrusion (122a) of the positioning member abuts against the first catching portion (121b) of the locking member, the stopper abuts against one of the two or more protrusions (122a, 122b) of the positioning member, that is, a second protrusion (122b), and the locking portion of the locking member is completely disengaged from the locked portion,
in the second relative position, the first protrusion (122a) of the positioning member abuts against the second catching portion (121c) of the locking member, the stopper abuts against the third catching portion (121d) which is another one of the three or more catching portions (121b, 121c, 121d) of the locking member, and the locking portion of the locking member is locked to the locked portion,
the locking member and the positioning member are arranged to be rotatable between the first relative position and the second relative position.
4. The aircraft door gust lock device (100) according to claim 3,
the locking part further comprises a telescopic rod (124), the fixed end of the telescopic rod (124) is arranged on one of the locking part and the positioning part, the telescopic end is arranged on the other of the locking part and the positioning part,
in the first relative position, the telescopic rod (124) is in an extended state,
in the second relative position, the telescoping rod (124) is in a retracted state.
5. The aircraft door gust lock device (100) according to claim 4,
the locking part also comprises a compression spring (125), the compression spring (125) is sleeved on the telescopic rod (124) and applies acting force towards the extension direction when the telescopic rod (124) contracts.
6. The aircraft door gust lock device (100) according to any one of claims 1 to 5,
the aircraft door gust lock device (100) further comprises an operating part (130), the operating part (130) being linked with the locking part by a transmission rod (140).
7. The aircraft door gust lock device (100) according to claim 6,
the operating part (130) is mounted on the Hinge Arm (HA) of the hatch door and HAs a handle (131), a handle spindle (132), a connecting rod (133) and a handle crankshaft (134),
the handle rotation shaft (132) is connected to the handle (131) and rotates the locking part connected to the connecting rod (133) of the operating part (130) via the handle crank shaft (134) and the transmission rod (140) with respect to the door jamb (CD) fixedly installed at the doorFL) Is locked or unlocked by the lock portion.
8. The aircraft door gust lock device (100) according to claim 7,
the operating part (130) also comprises a limiting pin (135), a torsion spring (136) and a spring limiting seat (137),
the torsion spring (136) is limited in its axial degree of freedom along the link (133) by the spring stopper (137), and the torsion spring (136) provides a circumferential torsion moment to prevent the handle (131) from rotating in an unlocking direction when the locking portion is locked with respect to the locked portion.
9. The aircraft door gust lock device (100) according to claim 8,
the locked portion is a latch portion (110),
the locked portion is a latch (111),
the locking portion is a lock hook portion (120),
the locking portion is a hook latch (121a),
the locking piece is a first ratchet wheel (121) with three blocking parts,
the positioning member is a second ratchet (122) having two protrusions,
the positioning piece is a positioning pin (123).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010119372.1A CN111232180B (en) | 2020-02-26 | 2020-02-26 | Aircraft cabin door gust wind lock device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010119372.1A CN111232180B (en) | 2020-02-26 | 2020-02-26 | Aircraft cabin door gust wind lock device |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN111232180A true CN111232180A (en) | 2020-06-05 |
| CN111232180B CN111232180B (en) | 2021-10-19 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202010119372.1A Active CN111232180B (en) | 2020-02-26 | 2020-02-26 | Aircraft cabin door gust wind lock device |
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| CN (1) | CN111232180B (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113719215A (en) * | 2021-09-10 | 2021-11-30 | 庆安集团有限公司 | Method and device for operating cabin door |
| CN115306218A (en) * | 2022-06-24 | 2022-11-08 | 上海工程技术大学 | High-bearing gust wind lock with cam link mechanism |
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| DE102018117696A1 (en) * | 2018-07-23 | 2020-01-23 | Kiekert Ag | Motor vehicle lock |
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| CN204433026U (en) * | 2014-12-19 | 2015-07-01 | 成都飞机设计研究所 | A kind of hatch door is received and is put in place and lock detection device |
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| EP3418478A1 (en) * | 2017-06-22 | 2018-12-26 | Brose Schließsysteme GbmH & Co. Kommanditgesellschaft | Motor vehicle lock |
| DE102018117696A1 (en) * | 2018-07-23 | 2020-01-23 | Kiekert Ag | Motor vehicle lock |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113719215A (en) * | 2021-09-10 | 2021-11-30 | 庆安集团有限公司 | Method and device for operating cabin door |
| CN115306218A (en) * | 2022-06-24 | 2022-11-08 | 上海工程技术大学 | High-bearing gust wind lock with cam link mechanism |
Also Published As
| Publication number | Publication date |
|---|---|
| CN111232180B (en) | 2021-10-19 |
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