CN117550059B - Aircraft tail hatch door - Google Patents
Aircraft tail hatch door Download PDFInfo
- Publication number
- CN117550059B CN117550059B CN202311384298.6A CN202311384298A CN117550059B CN 117550059 B CN117550059 B CN 117550059B CN 202311384298 A CN202311384298 A CN 202311384298A CN 117550059 B CN117550059 B CN 117550059B
- Authority
- CN
- China
- Prior art keywords
- door body
- door
- tail
- lock
- cabin
- Prior art date
- 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.)
- Active
Links
- 230000007246 mechanism Effects 0.000 claims description 36
- 230000001939 inductive effect Effects 0.000 claims description 19
- 230000033001 locomotion Effects 0.000 claims description 18
- 230000009471 action Effects 0.000 claims description 8
- 230000005540 biological transmission Effects 0.000 claims description 8
- 230000006698 induction Effects 0.000 claims description 3
- 238000000034 method Methods 0.000 abstract description 10
- 230000009286 beneficial effect Effects 0.000 abstract description 3
- 230000008569 process Effects 0.000 description 8
- 239000000725 suspension Substances 0.000 description 5
- 238000012544 monitoring process Methods 0.000 description 4
- 230000000694 effects Effects 0.000 description 3
- 238000013519 translation Methods 0.000 description 3
- 230000008859 change Effects 0.000 description 2
- 238000012423 maintenance Methods 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- 238000007789 sealing Methods 0.000 description 2
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000002035 prolonged effect Effects 0.000 description 1
- 238000005096 rolling process Methods 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- 230000001360 synchronised effect Effects 0.000 description 1
Classifications
-
- 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
- B64C1/1415—Cargo doors, e.g. incorporating ramps
-
- 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
- B64C1/1461—Structures of doors or surrounding frames
-
- E—FIXED CONSTRUCTIONS
- E05—LOCKS; KEYS; WINDOW OR DOOR FITTINGS; SAFES
- E05B—LOCKS; ACCESSORIES THEREFOR; HANDCUFFS
- E05B15/00—Other details of locks; Parts for engagement by bolts of fastening devices
- E05B15/10—Bolts of locks or night latches
-
- E—FIXED CONSTRUCTIONS
- E05—LOCKS; KEYS; WINDOW OR DOOR FITTINGS; SAFES
- E05B—LOCKS; ACCESSORIES THEREFOR; HANDCUFFS
- E05B17/00—Accessories in connection with locks
- E05B17/22—Means for operating or controlling lock or fastening device accessories, i.e. other than the fastening members, e.g. switches, indicators
-
- E—FIXED CONSTRUCTIONS
- E05—LOCKS; KEYS; WINDOW OR DOOR FITTINGS; SAFES
- E05B—LOCKS; ACCESSORIES THEREFOR; HANDCUFFS
- E05B47/00—Operating or controlling locks or other fastening devices by electric or magnetic means
- E05B47/0001—Operating or controlling locks or other fastening devices by electric or magnetic means with electric actuators; Constructional features thereof
- E05B47/0012—Operating or controlling locks or other fastening devices by electric or magnetic means with electric actuators; Constructional features thereof with rotary electromotors
-
- E—FIXED CONSTRUCTIONS
- E05—LOCKS; KEYS; WINDOW OR DOOR FITTINGS; SAFES
- E05B—LOCKS; ACCESSORIES THEREFOR; HANDCUFFS
- E05B47/00—Operating or controlling locks or other fastening devices by electric or magnetic means
- E05B47/02—Movement of the bolt by electromagnetic means; Adaptation of locks, latches, or parts thereof, for movement of the bolt by electromagnetic means
- E05B47/023—Movement of the bolt by electromagnetic means; Adaptation of locks, latches, or parts thereof, for movement of the bolt by electromagnetic means the bolt moving pivotally or rotatively
-
- E—FIXED CONSTRUCTIONS
- E05—LOCKS; KEYS; WINDOW OR DOOR FITTINGS; SAFES
- E05B—LOCKS; ACCESSORIES THEREFOR; HANDCUFFS
- E05B63/00—Locks or fastenings with special structural characteristics
- E05B63/14—Arrangement of several locks or locks with several bolts, e.g. arranged one behind the other
- E05B63/146—Arrangement of several locks or locks with several bolts, e.g. arranged one behind the other locks with two or more bolts, each bolt itself being a tumbler
-
- E—FIXED CONSTRUCTIONS
- E05—LOCKS; KEYS; WINDOW OR DOOR FITTINGS; SAFES
- E05F—DEVICES FOR MOVING WINGS INTO OPEN OR CLOSED POSITION; CHECKS FOR WINGS; WING FITTINGS NOT OTHERWISE PROVIDED FOR, CONCERNED WITH THE FUNCTIONING OF THE WING
- E05F15/00—Power-operated mechanisms for wings
- E05F15/50—Power-operated mechanisms for wings using fluid-pressure actuators
- E05F15/53—Power-operated mechanisms for wings using fluid-pressure actuators for swinging wings
-
- E—FIXED CONSTRUCTIONS
- E05—LOCKS; KEYS; WINDOW OR DOOR FITTINGS; SAFES
- E05F—DEVICES FOR MOVING WINGS INTO OPEN OR CLOSED POSITION; CHECKS FOR WINGS; WING FITTINGS NOT OTHERWISE PROVIDED FOR, CONCERNED WITH THE FUNCTIONING OF THE WING
- E05F15/00—Power-operated mechanisms for wings
- E05F15/60—Power-operated mechanisms for wings using electrical actuators
- E05F15/603—Power-operated mechanisms for wings using electrical actuators using rotary electromotors
- E05F15/611—Power-operated mechanisms for wings using electrical actuators using rotary electromotors for swinging wings
-
- E—FIXED CONSTRUCTIONS
- E05—LOCKS; KEYS; WINDOW OR DOOR FITTINGS; SAFES
- E05B—LOCKS; ACCESSORIES THEREFOR; HANDCUFFS
- E05B47/00—Operating or controlling locks or other fastening devices by electric or magnetic means
- E05B47/0001—Operating or controlling locks or other fastening devices by electric or magnetic means with electric actuators; Constructional features thereof
- E05B2047/0014—Constructional features of actuators or power transmissions therefor
- E05B2047/0018—Details of actuator transmissions
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Structural Engineering (AREA)
- Physics & Mathematics (AREA)
- Electromagnetism (AREA)
- Power-Operated Mechanisms For Wings (AREA)
Abstract
The invention relates to the technical field of aircrafts, and provides an aircraft tail cabin door, which comprises: the door frame is arranged at the bottom of the tail cabin; the first door body and the second door body are detachably connected with the door frame, and the first door body is rotatably connected to the tail end of the tail cabin; the second door body is connected with the first door body in a foldable way; in the open state, the first door body rotates to the top of the tail cabin, and the second door body is folded to the inner side of the first door body; in the closed state, the first door body rotates to the bottom of the tail cabin, and the second door body is located at one end of the first door body, which is far away from the tail end of the tail cabin. According to the aircraft tail cabin door provided by the invention, the first door body and the second door body can avoid the cargo cabin, and compared with the situation that a part of cargo cabin space is occupied when the single tail door is internally used, the effective utilization of the cargo cabin space can be ensured; meanwhile, for the inward opening mode, under the air drop working condition, the method is more beneficial to reducing the interference starting during door opening so as to obtain better flight stability and safety.
Description
Technical Field
The invention relates to the technical field of aircrafts, in particular to an aircraft tail cabin door.
Background
Cargo doors are the necessary passage of cargo in and out of aircraft and are also important moving parts of the airframe that are directly related to the aerodynamic profile.
For small and medium-sized aircraft, a side opening cabin door is usually arranged on the side surface of the aircraft body and is called a side cabin door, the side cabin door is usually provided with an inner opening side door and an outer opening side door, and for the inner opening side door, a part of cargo space is occupied by a translation door or a revolving door; for an outward opening side door, if the side door is a revolving door, the side door cannot be used for aerial opening operation (such as air drop); although the sliding door can be used for opening and closing in the air, larger wind resistance is needed to resist when the sliding door is opened or closed, the operation difficulty is not small, and more power is consumed for balancing and controlling the flying gesture due to the asymmetric resistance characteristics formed on the two sides of the body. Accordingly, more and more small and medium aircraft have cargo doors provided on the aft.
However, as shown in fig. 1 and 2, the cargo space of the middle-small aircraft is relatively tight, and in the prior art, if the tail gate is directly stored in the tail cabin, the cargo space is occupied, which affects the capacity of the cargo space of the aircraft.
Disclosure of Invention
The invention provides an aircraft tail cabin door which is used for solving the defect that a cargo cabin of a medium-sized and small-sized aircraft is tense in the prior art, and the cargo cabin door occupies a cargo cabin space if the tail cabin door is directly stored in the tail cabin, so that effective utilization of the cargo cabin space can be ensured.
The invention provides an aircraft tail cabin door, which is arranged at the bottom of a tail cabin and comprises:
The door frame is arranged around the bottom door opening of the tail cabin;
The first door body and the second door body are detachably connected with the door frame, and the first door body is rotatably connected to the tail end of the tail cabin; the second door body is connected with the first door body in a foldable way;
in an open state, the first door body rotates to the top of the tail cabin, and the second door body is folded to the inner side of the first door body;
in a closed state, the first door body rotates to the bottom of the tail cabin, and the second door body is located at one end of the first door body, which is far away from the tail end of the tail cabin.
According to the invention, an aircraft tail gate is provided, which further comprises:
and one end of the first driving mechanism is connected with the top of the tail cabin, the other end of the first driving mechanism is connected with the first door body, and the first driving mechanism is used for driving the first door body to rotate relative to the tail of the tail cabin.
According to the invention, an aircraft tail gate is provided, which further comprises:
The second driving mechanism is arranged between the first door body and the second door body and is used for realizing the relative movement of the second door body and the first door body.
According to the present invention there is provided an aircraft tail gate, the second drive mechanism comprising:
The first sliding rail and the second sliding rail are arranged on the first door body, and the second sliding rail comprises a straight line section and an arc section;
The door body driving piece is arranged on the first door body;
the driven piece is connected with the door body driving piece and can move linearly along the first sliding rail;
One end of the connecting component is connected with the driven piece, and the other end of the connecting component is hinged with the second door body;
one end of the guide device is connected with one end of the second door body far away from the first door body, the other end of the guide device is connected with the second sliding rail in a sliding manner, and under the action of the door body driving piece, the guide device moves from the arc-shaped section to the straight-line section so as to drive the second door body to move to the top of the first door body.
According to the present invention there is provided an aircraft tail gate, the guide means comprising:
the first supporting block is arranged on the straight line section in a sliding manner;
The second supporting block is in sliding switching between the straight line section and the arc-shaped section;
the first support is arranged on one side, close to the first door body, of the second door body and is hinged with the second supporting block;
One end of the suspender is hinged with one side of the second door body far away from the first door body, and the other end of the suspender is connected with the first supporting block;
And along with the driving of the door body driving piece, the second supporting block moves from the arc section to the straight line section so as to drive the second door body to move between the first door body and the suspender.
According to the present invention there is provided an aircraft tail gate, the connection assembly comprising:
the connecting body is connected with the driven piece;
the second support is arranged at one end, close to the first door body, of the second door body and is hinged with the connecting body;
the hinge axis of the second support and the connecting body is a first axis;
the hinge axis of the first support and the hinge axis of the second support block are second axes;
The first axis is not coaxial with the second axis.
According to the aircraft tail cabin door provided by the invention, the second door body is provided with the locking plate, the door frame is provided with the clamping groove, and the locking plate is used for extending into or moving out of the clamping groove along with the movement of the second door body.
According to the aircraft tail cabin door provided by the invention, the door lock driving piece is arranged on the first door body, the door lock executing device is arranged in the area, close to the second door body, of the first door body, the door lock driving device is arranged between the door lock driving piece and the door lock executing device, and the door lock executing device can lock or unlock the first door body and the door frame and the first door body and the second door body under the action of the door lock driving piece.
According to the invention, the aircraft tail cabin door is provided, and the door lock transmission device comprises:
At least two stay wires, and each side is provided with at least one stay wire; one end of the stay wire is connected with the door lock driving piece, and the other end of the stay wire is connected with the door lock executing device;
The door lock actuator includes:
the lock bolts are connected with the stay wires in one-to-one correspondence; in the locking state, one end of the lock tongue is limited by the lock tongue baffle plate, and the other end of the lock tongue is limited by the upper angle stop block of the second door body; the locking plate baffle is arranged on the door frame, and the upper corner stop block of the second door body is arranged on the second door body.
According to the invention, the aircraft tail cabin door, the door lock executing device further comprises:
one end of the locking torsion spring is connected with the second door body, the other end of the locking torsion spring is connected with the lock tongue, and the locking torsion spring is used for automatically resetting the lock tongue;
The locking inductive switch and the unlocking inductive switch are arranged on the first door body, and in the locking state, the lock tongue is in contact with the locking inductive switch; in the unlocking state, the lock tongue is in contact with the unlocking induction switch.
According to the aircraft tail cabin door, the first door body and the second door body are detachably connected with the door frame, the first door body is rotatably connected to the tail end of the tail cabin, the second door body is connected with the first door body in a folding manner, the first door body rotates to the top of the tail cabin in an opening state, the second door body is folded to the top of the first door body, the first door body and the second door body can avoid the cargo cabin, and compared with the situation that part of cargo cabin space is occupied when the first door body and the second door body are in a single tail door, the effective utilization of the cargo cabin space can be ensured; meanwhile, for the inward opening mode, under the air drop working condition, the method is more beneficial to reducing the interference starting during door opening so as to obtain better flight stability and safety.
Drawings
In order to more clearly illustrate the invention or the technical solutions of the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described, and it is obvious that the drawings in the description below are some embodiments of the invention, and other drawings can be obtained according to these drawings without inventive effort for a person skilled in the art.
FIG. 1 is a prior art partially out-opening partially in-opening tail gate;
FIG. 2 is a prior art tail gate of an inwardly opening door;
FIG. 3 is a schematic view of an aircraft tail gate mounting structure provided by the present invention;
fig. 4 is a schematic structural view of an aircraft tail door provided by the invention;
FIG. 5 is a schematic view of a connection structure of a first door, a second door and a second driving mechanism provided by the present invention;
FIG. 6 is a schematic view of a connection structure of a second slide rail and a guide device according to the present invention;
FIG. 7 is a schematic view of a connection structure of a connection assembly and a driven member according to the present invention;
FIG. 8 is a schematic view of a locked state of a first door and a second door provided by the present invention;
FIG. 9 is a schematic diagram of a locking process of a second door body and a door frame according to the present invention;
FIG. 10 is a schematic view of a door lock actuator according to the present invention;
FIG. 11 is a schematic structural view of a connection structure of a door lock transmission device and a door lock actuator provided by the invention;
Reference numerals:
100. a tail cabin; 101. a first hinge support; 102. a second hinge support;
1. a door frame; 2. a first door body; 3. a second door body; 4. a first driving mechanism; 5. a second driving mechanism;
11. A clamping groove; 12. a locking plate baffle; 13. a guide structure; 14. a lock point induction switch;
21. a door lock driving member; 211. a motor support; 212. a motor; 213. a rocker arm; 22. a door lock transmission; 23. a door lock actuator; 231. a bolt; 232. a locking torsion spring; 233. locking the inductive switch; 234. unlocking the inductive switch; 235. locking the limit column; 236. locking the contact block; 24. an arm hinge; 25. a third hinge support;
31. A locking plate; 32. a second door upper corner stop block;
51. A first slide rail; 52. a second slide rail; 53. a door body driving member; 54. a follower; 55. a connection assembly;
541. A ball screw; 542. a ball nut;
551. A connection body; 552. a second support; 56. a guide device; 561. a first support block; 562. a second support block; 563. a first support; 564. a boom; 565. and a roller.
Detailed Description
For the purpose of making the objects, technical solutions and advantages of the present invention more apparent, the technical solutions of the present invention will be clearly and completely described below with reference to the accompanying drawings, and it is apparent that the described embodiments are some embodiments of the present invention, not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
In the description of the embodiments of the present invention, it should be noted that the terms "center", "longitudinal", "lateral", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc. indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, are merely for convenience in describing the embodiments of the present invention and simplifying the description, and do not indicate or imply that the apparatus or elements referred to must have a specific orientation, be configured and operated in a specific orientation, and thus should not be construed as limiting the embodiments of the present invention. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.
The aircraft tail gate of the present invention is described below with reference to fig. 3 to 11, and is mainly suitable for small and medium-sized cargo aircraft, and aims at the situation that the cargo hold is relatively tight in the prior art, and if the tail gate is directly stored in the tail gate, the cargo hold space is occupied, and the cargo hold capacity of the aircraft is affected.
As shown in fig. 3 and 4, the present invention provides an aircraft tail gate, which is disposed at the bottom of a tail cabin 100 and includes a door frame 1, a first gate 2 and a second gate 3.
As shown in fig. 4, the door frame 1 is disposed around the door opening of the tail cabin 100; the first door body 2 and the second door body 3 are detachably connected with the door frame 1, and the first door body 2 is rotatably connected to the tail end of the tail cabin 100; the second door body 3 is connected with the first door body 2 in a foldable way; in the open state, the first door body 2 rotates to the top of the tail cabin 100, and the second door body 3 is folded to the top of the first door body 2, and the first door body 2 and the second door body 3 can avoid the cargo hold, and compared with the situation that a part of cargo hold space is occupied when a single tail door is used, the effective utilization of the cargo hold space can be ensured. In the closed state, the first door 2 is rotated to the bottom of the tail cabin 100, and the second door 3 is located at an end of the first door 2 away from the tail end of the tail cabin 100.
If the inward turning type tail gate is only designed into a single whole long plate, part of cargo space is inevitably occupied in the opening process, and the aircraft cabin door disclosed by the invention has the advantages that the first gate body 2 and the second gate body 3 are arranged, the first gate body 2 and the second gate body 3 are completely retracted, and the cabin door movement can be effectively prevented from invading into the cargo space on the premise of ensuring the opening size of the tail gate, so that the top of the tail gate is higher than the ceiling of the cargo space, a horizontal in-out channel space can be formed right behind the aircraft body, the effective utilization space in the aircraft body is improved, and the economy of a freight aircraft is improved; the inner opening mode is adopted, so that the air-drop type air-drop device can be opened in the air, interference starting during door opening is reduced, the effect of small pneumatic influence is achieved, and better flight stability and safety are obtained.
As shown in fig. 4, in one possible embodiment of the present invention, the device further includes a first driving mechanism 4, where one end of the first driving mechanism 4 is connected to the top of the tail cabin 100, and the other end of the first driving mechanism 4 is connected to the first door body 2, and the first driving mechanism 4 is used to drive the first door body 2 to rotate relative to the tail of the tail cabin 100, where the first driving mechanism 4 may be a cylinder, a hydraulic cylinder, or other structures, as long as linear motion can be implemented.
As shown in fig. 4, specifically, a first hinge seat 101 may be disposed on the body at the tail of the tail cabin 100, and the first door body 2 may be connected with an hinge arm 24, where the hinge arm 24 is hinged with the first hinge seat 101. A second hinge seat 102 may be provided on the body at the top of the tail cabin 100, one end of the first driving mechanism 4 is hinged to the second hinge seat 102, a third hinge seat 25 is provided at the top of the first door body 2, and the other end of the first driving mechanism 4 is hinged to the third hinge seat 25. The first driving mechanism 4 drives the first door body 2 to rotate around the hinge point of the hinge arm 24 and the first hinge seat 101 through telescopic movement, so that the first door body 2 is opened and closed.
The first hinge support 101 and the second hinge support 102 are usually welded and fixed with the body of the tail cabin 100, so that the structure is stable and the process is simple.
Moreover, when part or all of the tail gate is used as a cargo bridge, the tail gate tends to mean larger mechanism weight and higher running cost, the heavier tail weight can cause the configuration of the center of the airplane to be biased or the whole airplane to be heavier, the applicability of the airplane is lost, and the tail gate only needs to meet the structural stability and reliability of the tail gate, so that the structural weight can be greatly reduced, and the tail gate has higher practicability and economic value.
In a possible embodiment of the invention, the folding door further comprises a second driving mechanism 5, wherein the second driving mechanism 5 is arranged between the first door 2 and the second door 3, and the second driving mechanism 5 is used for realizing the relative movement of the second door 3 and the first door 2 so that the second door 3 can be folded to the top side of the first door 2.
As shown in fig. 5, 6 and 7, in one possible embodiment of the present invention, the second driving mechanism 5 includes a first slide rail 51, a second slide rail 52, a door body driving member 53, a driven member 54, a connection assembly 55 and a guiding device 56, the first slide rail 51 and the second slide rail 52 are disposed on the first door body 2, and the second slide rail 52 includes a straight line section and an arc section; the door driving piece 53 is arranged on the first door body 2; the follower 54 is connected with the door body driving member 53, and the follower 54 can move linearly along the first slide rail 51; one end of the connecting component 55 is connected with the driven piece 54, and the other end is hinged with the second door body 3; one end of the guiding device 56 is connected with one end of the second door 3 far away from the first door 2, the other end is connected with the second sliding rail 52 in a sliding way, and under the action of the door driving piece 53, the guiding device 56 moves from the arc section to the straight section so as to drive the second door 3 to move to the top of the first door 2.
The door driving piece 53 is configured to provide a relative motion of the second door 3 with respect to the first door 2, where the second door 3 is disposed on the first door 2; the follower 54 is connected with the door body driving member 53, and the follower 54 can move linearly along the first slide rail 51; one end of the connecting component 55 is connected with the driven piece 54, and the other end is hinged with the second door body 3; one end of the guiding device 56 is connected with one end of the second door 3 far away from the first door 2, the other end is slidably connected with the second sliding rail 52, and under the action of the door driving piece 53, the guiding device 56 moves from the arc section to the straight section so as to drive the second door 3 to move to the inner side of the first door 2.
As shown in fig. 5, two guide devices 56 may be provided, and the two guide devices 56 are respectively located at two sides of the first sliding rail 51, so that the two guide devices 56 are provided, and the second door body 3 can be ensured to be stable in the running process along the second sliding rail 52, and prevent the deviation.
In one possible embodiment of the present invention, the guide 56 includes a first support block 561, a second support block 562, a first support 563, and a boom 564, the first support block 561 being slidably disposed in a straight line segment; the second support block 562 is slidingly switched between the straight segment and the arc segment; the first support 563 is arranged on one side of the second door body 3 close to the first door body 2, and the first support 563 is hinged with the second supporting block 562; one end of the suspension rod 564 is hinged with one side of the second door body 3 far away from the first door body 2, and the other end is connected with the first supporting block 561; and the second supporting block 562 moves from the arc section to the straight section along with the driving of the door driving piece 53, so as to drive the second door 3 to move between the first door 2 and the hanging rod 564. The second supporting block 562 moves from the arc section to the straight section along with the driving of the door driving piece 53, so as to drive the second door 3 to move between the first door 2 and the suspension rod 564. By providing the guide 56 in the structure of the first supporting block 561, the second supporting block 562, the first supporter 563, and the hanger rod 564, the second door 3 can be guided to move relatively to the first door 2 along the second slide rail 52, and the operation is smooth.
Wherein, two first supporting blocks 561 are arranged on each suspension rod 564, and the two first supporting blocks 561 can better support the suspension rods 564, so that the suspension rods 564 can stably drive the second door body 3 to move.
As shown in fig. 6, the bottom of the first supporting block 561 may be provided with a roller 565, where the roller 565 rolls in a straight line segment, and rolling friction is formed between the first supporting block 561 and the second sliding rail 52, so that friction force can be reduced, so that the second door 3 moves smoothly along the second sliding rail 52.
As shown in fig. 7, in one possible embodiment of the present invention, the connection assembly 55 includes a connection body 551 and a second support 552, the connection body 551 being connected with the follower 54; the second support 552 is arranged at one end of the second door body 3 close to the first door body 2, and the second support 552 is hinged with the connecting body 551; and, the hinge axis of the second support 552 and the connection body 551 is a first axis; the hinge axis of the first support 563 and the second support block 562 is a second axis; the first axis is not coaxial with the second axis. The first axis is not coaxial with the second axis, and one degree of freedom is constrained so that the second door 3 has only one door driving piece 53 and one degree of freedom, whereby a certain relative movement can be obtained.
Wherein, first support 563 and second support 552 are all with second door 3 fixed connection, can ensure that the connection of second door 3 and first door 2 is firm.
In addition, the door driving piece 53 may include a motor; as shown in fig. 7, the follower 54 may include a ball screw 541 and a ball nut 542, the ball screw 541 may be located in a groove of the first door body 2, and the ball screw 541 is connected to an output end of a motor, and the motor operates to drive the ball screw 541; the ball nut 542 is sleeved on the ball screw 541, and the ball nut 542 is connected to the connection assembly 55. Of course, the door driving member 53 may also adopt other driving modes, such as a driving rack-and-pinion mechanism, and may also be a sprocket-and-chain mechanism, so long as linear motion is achieved.
The second driving mechanism 5 works on the principle that: the ball screw 541 is fixed in a groove in the middle of the first door body 2, the ball screw 541 drives the ball nut 542 to do linear motion along the axis of the ball screw 541 through motor driving, the ball nut 542 is connected with the connecting component 55, when the ball nut 542 moves, the connecting component 55 follows the motion and also has one degree of freedom rotating around the cylindrical step axis of the ball nut 542, the lower end of the connecting component 55 is hinged to the second support 552, the second support 552 is fixedly connected to the middle of the side of the second door body 3, which is close to the first door body 2, the first support 563 is fixedly connected to the two sides of the second door body 3, which is close to the first door body 2, and the hinge axis of the first support 563 is not coaxial with the hinge axis of the second support 552, so that the motion mechanism can obtain definite relative motion.
The second door body 3 gradually gets into the inner side of the first door body 2 in a nearly translation mode, in the opening process, the aerodynamic change of the tail part of the aircraft body is more uniform, the attitude adjustment of the aircraft is easier to control, and for the first driving mechanism 4 and the second driving mechanism 5, the change of the load is more stable, the abrupt peak value is lower, the service lives of the first driving mechanism 4 and the second driving mechanism 5 are prolonged, the maintenance frequency of related devices is reduced, and the maintenance cost is reduced.
As shown in fig. 8-11, in a possible embodiment of the present invention, a locking plate 31 is provided on the second door body 3, a clamping groove 11 is provided on the door frame 1, and the locking plate 31 is used to extend into or move out of the clamping groove 11 along with the movement of the second door body 3, so that the second door body 3 can be locked by using its own movement, and the structure is simple. In the locked state, the first door body 2 and the second door body 3 are flush and both locked with the door frame 1, and in the unlocked state, the second door body 3 is located inside the first door body 2.
As shown in fig. 9, more specifically, a guiding structure 13 may be further disposed on the clamping groove 11, the guiding structure 13 is rotatably connected with the clamping groove 11, and the guiding structure 13 is used for limiting the moving track of the locking plate 31. When the guiding structure 13 is set as a guiding wheel, the extension line of the contact point of the locking plate 31 and the guiding wheel needs to be lower than the axis of the guiding wheel, so that the locking plate 31 can be inserted into the clamping groove 11 along the bottom of the guiding wheel, and the locking of the second door body 3 is realized.
In addition, the guiding structure 13 may be provided in other structures, for example, may be an L-shaped crank arm, where the L-shaped crank arm includes a long arm and a short arm, and a connection point of the long arm and the short arm is rotatably connected with the clamping groove 11. When the second door 3 is moved, the locking piece 31 is inserted into the locking groove 11 to lock the second door 3 and the door frame 1. The L-shaped crank arm needs to be provided with a reset structure, so that the second door body 3 can smoothly enter the clamping groove 11 when being locked again after being unlocked from the door frame 1. The reset structure may employ a torsion spring.
In addition, as shown in fig. 9, a lock point sensing switch 14 may be further disposed on the door frame 1, and in the locked state, one of the guide structure 13 and the locking piece 31 is in contact with the lock point sensing switch 14, so as to be able to signal whether the monitoring system is locked in place.
As shown in fig. 10, in one possible embodiment of the present invention, a door lock driving member 21 is provided on the first door body 2, a door lock actuator 23 is provided on a region of the first door body 2 close to the second door body 3, and a door lock transmission device 22 is provided between the door lock driving member 21 and the door lock actuator 23. The door lock transmission device 22 is used for transmitting power, and the door lock transmission device 22 can lock or unlock the first door body 2 and the door frame 1, the first door body 2 and the second door body 3 under the action of the door lock driving piece 21.
As shown in fig. 10, the door lock driving member 21 may include a motor support 211, a motor 212, and a swing arm 213, wherein the motor support 211 is disposed on the first door body 2, and the motor support 211 is used for providing a platform for installation of the motor 212; the motor 212 is arranged on the motor support 211 and is used for providing power; the rocker arm 213 is sleeved at the output end of the motor 212 and can rotate along with the operation of the motor 212; and the swing arm 213 is connected to the door lock gear 22, and the swing arm 213 can convert the power of the motor 212 into a pulling force on the door lock gear 22.
In one possible embodiment of the invention, the door lock actuator 22 comprises at least two wires, and at least one wire is provided on each side; one end of the stay wire is connected with the door lock driving piece 21, and the other end of the stay wire is connected with the door lock executing device 23; the door lock executing device 23 comprises at least two lock bolts 231, and the lock bolts 231 are connected with the stay wires in a one-to-one correspondence manner; in the locked state, one end of the lock tongue 231 is limited by the lock tongue baffle 12, and the other end is limited by the second door upper corner stop 32; wherein, the locking plate baffle 12 is arranged on the door frame 1, and the second door upper angle stop block 32 is arranged on the second door 3.
As shown in fig. 11, in one possible embodiment of the present invention, the door lock actuator 23 further includes a latching torsion spring 232, one end of the latching torsion spring 232 is connected to the second door body 3, the other end is connected to the latch tongue 231, and the latching torsion spring 232 is used for automatic reset of the latch tongue 231; the locking inductive switch 233 and the unlocking inductive switch 234 are both arranged on the first door body 2, and in the locking state, the lock tongue 231 is in contact with the locking inductive switch 233; in the unlocked state, the latch tongue 231 is in contact with the unlocking inductive switch 234.
In addition, in order to monitor whether the first door body 2 or the second door body 3 is locked in place, a locking limit column 235 may be further disposed on the second door body 3, and a locking contact block 236 is disposed on the locking bolt 231, when one end of the locking bolt 231 contacts the locking limit column 235 during locking rotation, the locking contact block 236 at the other end contacts the locking inductive switch 233, which indicates that the locking inductive switch 233 is locked in place, and the locking inductive switch 233 may send a locking in place signal to the door lock monitoring system. When the lock tongue 231 is unlocked and rotated anticlockwise, the lock tongue 231 is far away from the locking limit column 235 and the locking inductive switch 233 until the lock tongue 231 rotates to touch the unlocking inductive switch 234, and the unlocking inductive switch 234 can send an unlocking in-place signal to the door lock monitoring system.
As shown in fig. 8-11, in the unlocking process of the aircraft door lock mechanism provided by the invention, the motor 212 rotates anticlockwise, and synchronously drives the stay wires at two sides, so as to drive the lock tongue 231 to rotate anticlockwise, so that the lock tongue 231 rotates from a transverse state to a longitudinal state, and the lock tongue 231 rotates from the lock tongue baffle and the upper corner stop block of the first door body respectively, thereby realizing unlocking.
The locking process is that the motor 212 rotates clockwise, the stay wire is released, the lock tongue 231 rotates from a vertical state to a horizontal state under the action of the locking torsion spring 232, the upper corner stop block and the lock sheet baffle of the first door body are clamped at the same time, the lock tongue 231 touches the locking limit column 235 to stop, and simultaneously the locking contact block 236 touches the locking inductive switch 233 to send a locking in-place signal to the door lock monitoring system.
The transverse state may be understood as that the extending direction of the bolt 231 is consistent with the extending direction of the pull wire, that is, the bolt is in a locked state at this time; the longitudinally-placed state is understood to mean that the extending direction of the latch 231 is perpendicular to the extending direction of the pull wire, i.e., in the unlocked state at this time.
In addition, as shown in fig. 11, the first door body 2 and the second door body 3 are provided with integral inward-turning type overlapping edges, the overlapping edge steps are arranged at the edge of the door frame 1, and the door frame 1 is used for covering the first door body 2 and the second door body 3 from the outside, so that the sealing of the whole tail cabin door is facilitated. In particular, when the aircraft is a supercharger cabin, the cabin air pressure just presses the first door body 2 and the second door body 3 against the door frame, and even if an additional power-assisted compression structure is not needed, a good and uniform sealing effect can be achieved.
In summary, the aircraft tail cabin door provided by the invention adopts the fully-adduction cabin door design, and the second door body 3 is opened in a pre-or synchronous translation mode in the whole door opening process, so that compared with an outward opening mode, the aircraft tail cabin door is more beneficial to reducing the interference starting appearance during door opening under the air drop working condition, and better flight stability and safety are obtained; compared with the mode that part of cargo space is occupied when the single tail gate is internally used, the opening mode of the tail gate can ensure effective utilization of the cargo space.
When the ground loading and unloading is carried out, the whole door opening time is shorter, the second door body 3 and the first door body 2 can be synchronously driven, as long as the condition that the bottom edge movement track of the second door body 3 does not incline to the cargo hold side is met, the door opening speed can reach the fastest speed, and the door opening device can be arranged in a mode of firstly opening the second door body 3 and then integrally opening the first door body 2 when in air drop, so that the effect of least influencing the flight stability is achieved.
In describing embodiments of the present invention, it should be noted that, unless explicitly stated and limited otherwise, the terms "coupled," "coupled," and "connected" should be construed broadly, and may be either a fixed connection, a removable connection, or an integral connection, for example; can be mechanically or electrically connected; can be directly connected or indirectly connected through an intermediate medium. The specific meaning of the above terms in the embodiments of the present invention will be understood by those of ordinary skill in the art according to specific circumstances.
In the description of the present specification, reference to the terms "one embodiment," "some embodiments," "manner," "particular modes," or "some modes," etc., means that a particular feature, structure, material, or characteristic described in connection with the embodiment or mode is included in at least one embodiment or mode of the embodiments of the present invention. In this specification, the schematic representations of the above terms are not necessarily directed to the same embodiment or manner. Furthermore, the particular features, structures, materials, or characteristics may be combined in any suitable manner in any one or more embodiments or ways. Furthermore, various embodiments or modes and features of various embodiments or modes described in this specification can be combined and combined by those skilled in the art without mutual conflict.
Finally, it should be noted that: the above embodiments are only for illustrating the technical solution of the present invention, and are not limiting; although the invention has been described in detail with reference to the foregoing embodiments, it will be understood by those of ordinary skill in the art that: the technical scheme described in the foregoing embodiments can be modified or some technical features thereof can be replaced by equivalents; such modifications and substitutions do not depart from the spirit and scope of the technical solutions of the embodiments of the present invention.
Claims (6)
1. An aircraft tail gate, characterized by being disposed at the bottom of a tail cabin (100), comprising:
The door frame (1) is arranged around the bottom door opening of the tail cabin (100);
The first door body (2) and the second door body (3) are detachably connected with the door frame (1), and the first door body (2) is rotatably connected to the tail end of the tail cabin (100); the second door body (3) is connected with the first door body (2) in a foldable way;
In an open state, the first door body (2) rotates to the top of the tail cabin (100), and the second door body (3) is folded to the inner side of the first door body (2);
In a closed state, the first door body (2) rotates to the bottom of the tail cabin (100), and the second door body (3) is positioned at one end of the first door body (2) away from the tail end of the tail cabin (100);
One end of the first driving mechanism (4) is connected with the top of the tail cabin (100), the other end of the first driving mechanism is connected with the first door body (2), and the first driving mechanism (4) is used for driving the first door body (2) to rotate relative to the tail of the tail cabin (100);
the second driving mechanism (5) is arranged between the first door body (2) and the second door body (3), and the second driving mechanism (5) is used for realizing the relative movement of the second door body (3) and the first door body (2);
The second driving mechanism (5) includes:
the first sliding rail (51) and the second sliding rail (52) are arranged on the first door body (2), and the second sliding rail (52) comprises a straight line section and an arc section;
A door body driving member (53) disposed on the first door body (2);
the driven piece (54) is connected with the door body driving piece (53), and the driven piece (54) can move linearly along the first sliding rail (51);
a connecting component (55), one end of which is connected with the driven piece (54) and the other end of which is hinged with the second door body (3);
one end of the guide device (56) is connected with one end of the second door body (3) far away from the first door body (2), the other end of the guide device is connected with the second sliding rail (52) in a sliding way, and under the action of the door body driving piece (53), the guide device (56) moves from the arc section to the straight line section so as to drive the second door body (3) to move to the top of the first door body (2);
the guide (56) comprises:
a first supporting block (561) slidably disposed on the straight line section;
a second support block (562) slidingly switching between the straight segment and the arcuate segment;
The first support (563) is arranged on one side, close to the first door body (2), of the second door body (3), and the first support (563) is hinged with the second supporting block (562);
One end of the suspender (564) is hinged with one side of the second door body (3) far away from the first door body (2), and the other end of the suspender is connected with the first supporting block (561);
and along with the driving of the door body driving piece (53), the second supporting block (562) moves from the arc section to the straight line section so as to drive the second door body (3) to move between the first door body (2) and the suspender (564).
2. The aircraft tail door according to claim 1, wherein the connection assembly (55) comprises:
A connection body (551) connected to the follower (54);
The second support (552) is arranged at one end, close to the first door body (2), of the second door body (3), and the second support (552) is hinged with the connecting body (551);
and, the hinge axis of the second support (552) and the connecting body (551) is a first axis;
The hinge axis of the first support (563) and the second support block (562) is a second axis;
The first axis is not coaxial with the second axis.
3. The aircraft tail gate according to claim 2, characterized in that a locking piece (31) is arranged on the second gate body (3), a clamping groove (11) is arranged on the door frame (1), and the locking piece (31) is used for extending into or moving out of the clamping groove (11) along with the movement of the second gate body (3).
4. An aircraft tail gate according to claim 3, characterized in that a door lock driving member (21) is arranged on the first door body (2), a door lock executing device (23) is arranged in a region of the first door body (2) close to the second door body (3), a door lock transmission device (22) is arranged between the door lock driving member (21) and the door lock executing device (23), and the door lock executing device (23) can lock or unlock the first door body (2) and the door frame (1), the first door body (2) and the second door body (3) under the action of the door lock driving member (21).
5. The aircraft tail gate according to claim 4, wherein the door lock transmission (22) comprises:
at least two stay wires, and each side is provided with at least one stay wire; one end of the stay wire is connected with the door lock driving piece (21), and the other end of the stay wire is connected with the door lock executing device (23);
The door lock actuator (23) includes:
the locking bolts (231) are connected with the stay wires in a one-to-one correspondence manner; in the locking state, one end of the lock tongue (231) is limited by the lock sheet baffle (12), and the other end of the lock tongue is limited by the upper angle stop block (32) of the second door body; the locking plate baffle (12) is arranged on the door frame (1), and the second door upper corner stop block (32) is arranged on the second door body (3).
6. The aircraft tail gate according to claim 5, wherein the door lock actuation device (23) further comprises:
A locking torsion spring (232), one end of which is connected with the second door body (3), the other end of which is connected with the lock tongue (231), and the locking torsion spring (232) is used for automatic resetting of the lock tongue (231);
The locking inductive switch (233) and the unlocking inductive switch (234) are arranged on the first door body (2), and in the locking state, the lock tongue (231) is in contact with the locking inductive switch (233); in the unlocked state, the lock tongue (231) is in contact with the unlocking induction switch (234).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311384298.6A CN117550059B (en) | 2023-10-24 | 2023-10-24 | Aircraft tail hatch door |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311384298.6A CN117550059B (en) | 2023-10-24 | 2023-10-24 | Aircraft tail hatch door |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN117550059A CN117550059A (en) | 2024-02-13 |
| CN117550059B true CN117550059B (en) | 2024-06-11 |
Family
ID=89822351
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202311384298.6A Active CN117550059B (en) | 2023-10-24 | 2023-10-24 | Aircraft tail hatch door |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN117550059B (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117739088B (en) * | 2024-02-18 | 2024-04-30 | 四川腾盾科技有限公司 | Unmanned aerial vehicle tail cabin door transmission system and unmanned aerial vehicle tail cabin door structure |
Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE3831963A1 (en) * | 1988-09-21 | 1990-03-29 | Hettich Paul Gmbh & Co | Folding door having a plurality of leaf pairs |
| JPH06340256A (en) * | 1993-06-01 | 1994-12-13 | Nabco Ltd | Plug door device |
| DE102008005595A1 (en) * | 2008-01-22 | 2009-07-30 | Airbus Deutschland Gmbh | Cargo compartment door for use in fuselage of aircraft, has opening in fuselage closed by cargo compartment door and reinforced with door frame, and two door wings are provided for reducing space required for cargo compartment door |
| CN101522519A (en) * | 2006-10-04 | 2009-09-02 | 空中客车英国有限公司 | A door for opening and closing a door aperture in an aircraft |
| CN105818959A (en) * | 2015-01-28 | 2016-08-03 | 空客直升机德国有限公司 | Aircraft with inwardly foldable rear door |
| CN106184699A (en) * | 2015-05-12 | 2016-12-07 | 空中客车运营简化股份公司 | Be provided with folding door allows to carry out between at least two region surrounding shell the lane device that safety connects |
| CN110844043A (en) * | 2019-10-25 | 2020-02-28 | 中航西飞民用飞机有限责任公司 | Retraction mechanism of aircraft maintenance cabin door |
| CN112478128A (en) * | 2020-12-02 | 2021-03-12 | 中国航空工业集团公司沈阳飞机设计研究所 | Retraction mechanism and cabin door structure thereof |
| CN218907591U (en) * | 2022-12-26 | 2023-04-25 | 江西洪都航空工业集团有限责任公司 | Folding cabin door driven by actuating cylinder to open and close |
Family Cites Families (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6823927B2 (en) * | 2003-03-05 | 2004-11-30 | Charles F. Steel | Pocket door with pivoting panel |
| EP4029771A1 (en) * | 2021-01-15 | 2022-07-20 | Goodrich Actuation Systems Limited | Door arrangement for use on an aircraft |
| US20230122760A1 (en) * | 2021-10-19 | 2023-04-20 | Textron Aviation Inc. | Track door for aircraft |
-
2023
- 2023-10-24 CN CN202311384298.6A patent/CN117550059B/en active Active
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE3831963A1 (en) * | 1988-09-21 | 1990-03-29 | Hettich Paul Gmbh & Co | Folding door having a plurality of leaf pairs |
| JPH06340256A (en) * | 1993-06-01 | 1994-12-13 | Nabco Ltd | Plug door device |
| CN101522519A (en) * | 2006-10-04 | 2009-09-02 | 空中客车英国有限公司 | A door for opening and closing a door aperture in an aircraft |
| DE102008005595A1 (en) * | 2008-01-22 | 2009-07-30 | Airbus Deutschland Gmbh | Cargo compartment door for use in fuselage of aircraft, has opening in fuselage closed by cargo compartment door and reinforced with door frame, and two door wings are provided for reducing space required for cargo compartment door |
| CN105818959A (en) * | 2015-01-28 | 2016-08-03 | 空客直升机德国有限公司 | Aircraft with inwardly foldable rear door |
| CN106184699A (en) * | 2015-05-12 | 2016-12-07 | 空中客车运营简化股份公司 | Be provided with folding door allows to carry out between at least two region surrounding shell the lane device that safety connects |
| CN110844043A (en) * | 2019-10-25 | 2020-02-28 | 中航西飞民用飞机有限责任公司 | Retraction mechanism of aircraft maintenance cabin door |
| CN112478128A (en) * | 2020-12-02 | 2021-03-12 | 中国航空工业集团公司沈阳飞机设计研究所 | Retraction mechanism and cabin door structure thereof |
| CN218907591U (en) * | 2022-12-26 | 2023-04-25 | 江西洪都航空工业集团有限责任公司 | Folding cabin door driven by actuating cylinder to open and close |
Also Published As
| Publication number | Publication date |
|---|---|
| CN117550059A (en) | 2024-02-13 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN117550059B (en) | Aircraft tail hatch door | |
| CN108082441B (en) | Actuatable emergency exit door and associated aircraft or spacecraft with a pressurized cabin | |
| EP1881928B1 (en) | Helicopter one-piece door | |
| US5931415A (en) | Plug-type overwing emergency exit door assembly | |
| US5064147A (en) | Upwardly opening plug-type door for use as an over-wing emergency hatch | |
| US6345786B1 (en) | Linked multi-segment landing gear door for aircraft | |
| US10480232B2 (en) | Sliding door structure | |
| CN108118999B (en) | A kind of cargo door opening mechanism of integrated motor pressurized strut | |
| CN106740925B (en) | A kind of sliding plug door system for shipping EMU | |
| CN215244823U (en) | Hidden control console, cab and railway vehicle | |
| CN103917765A (en) | Thrust reverser having twin doors | |
| CN112141150B (en) | Carriage and vehicle with same | |
| CN107719644A (en) | Flap retracting device | |
| US8047141B2 (en) | Step actuator | |
| CN104816611B (en) | A kind of cabin door device and the car using the cabin door device | |
| CN208534283U (en) | A kind of automobile-used built-in sliding plug door system of high speed | |
| CN112145011B (en) | Control system, carriage and vehicle of top cap | |
| CN112249061B (en) | Carriage and vehicle with same | |
| CN212249599U (en) | Rail vehicle hood opening and closing mechanism | |
| CN205297107U (en) | Butterfly formula door hinge | |
| EP2921329B1 (en) | Convertible car with a hard-top and corresponding control method | |
| CN210554815U (en) | To opening door equipment and car | |
| RU2099240C1 (en) | Cargo compartment of flying vehicle | |
| CN209620983U (en) | Sliding door for manual plug mechanism | |
| CN114809844B (en) | Apron board pushes away side and draws switching device |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |