CN110588950A - One-way door opening device, door equipped with an opening device and aircraft equipped with a door - Google Patents
One-way door opening device, door equipped with an opening device and aircraft equipped with a door Download PDFInfo
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- CN110588950A CN110588950A CN201910968048.4A CN201910968048A CN110588950A CN 110588950 A CN110588950 A CN 110588950A CN 201910968048 A CN201910968048 A CN 201910968048A CN 110588950 A CN110588950 A CN 110588950A
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- Prior art keywords
- opening device
- door
- actuator
- lock
- door opening
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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
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Power-Operated Mechanisms For Wings (AREA)
Abstract
The invention relates to a one-way hatch opening device, comprising: the locking plate sleeve (7), the locking plate sleeve (7) is connected with the cabin door locking shaft (8) along the axial direction of the cabin door locking shaft (8); at least one drive (3, 4) for powering the hatch opening device; an actuator connection (1), one end of the actuator connection (1) being engaged with the drive means (3, 4); a lock cylinder (6), the lock cylinder (6) being connected to the other end of the actuator connection piece (1) and having the form of a tab projecting radially outwards of the door lock shaft (8). The lock cylinder (6) further comprises an abutment projection (6a) projecting axially towards the lock plate sleeve (7) at or near the tip of its tab, the abutment projection (6a) being capable of abutting against the lock plate sleeve (7) during rotation of the actuator connection piece (1). The hatch opening device has simple structure and quick response and can effectively ensure the safety and reliability of the use of the hatch.
Description
Technical Field
The invention relates to a one-way cabin door opening device. More specifically, the one-way door opening device is a multi-action door opening device. Furthermore, the invention relates to a door equipped with such a door opening device and to an aircraft equipped with such a door.
Background
If the aircraft meets an emergency situation in the process of flight test, the emergency cabin door needs to be unlocked immediately, the cabin door is thrown, and the escape passage is opened to ensure that related personnel can escape in time. At this point, a door opening device is generally used to ensure that the emergency door remains continuously open and to prevent any possibility of reclosing the door due to various accidental factors.
According to the fifteenth (fourth) provision of civil aviation products and component qualification rules, the applicant should demonstrate that sufficient measures are taken in each flight test, in addition to the glider or manned balloon, to enable the flight crew to leave and use the parachute … … in an emergency. Therefore, during the test flight of civil aircraft, emergency departure doors must be provided. For example, C919 aircraft employ jettisoning emergency exit doors. After the cabin door is unlocked by the cabin door opening device, the cabin door can be removed under the action of gravity and the pressure difference between the inside and the outside of the airplane, and two functions of emergency pressure relief and escape passage opening are realized.
The hatch opening device should meet two basic requirements:
1) under normal working conditions, the cabin door opening device should reduce the influence on the cabin door of the emergency machine to the greatest extent and ensure the connection performance of the cabin door and the machine body;
2) under the emergency working condition, the cabin door opening device has higher reliability so as to achieve the purpose of timely and effectively opening the cabin door of the emergency cabin.
Currently, door opening devices used in civil aircraft mainly include the following categories:
a) manual switch integral type: the cabin door opening device manually locks and unlocks the cabin door through a series of transmission mechanisms. For such a cabin door opening device, manual operation is the only actuation method, so specially trained personnel must be provided to operate the cabin door opening device, and in an air flight state, in order to prevent the cabin door from being opened by mistake, an additional set of flight lock mechanism needs to be configured.
2) Actuator assistance type: the cabin door opening device takes an actuator as power input, directly unlocks a cabin door lock shaft under an emergency condition, and then manually opens the cabin door. Alternatively, the door is unlocked manually and opened by an actuator. For such door opening devices, a high reliability of the actuator is required. If a plurality of actuators are arranged, there is a high demand for installation space. The response time is further extended if a two-step door opening device is used.
3) Blasting type: such hatch opening devices are mainly blasting devices arranged in the vicinity of the doors of emergency hatches, which can blast the doors open in emergency situations by detonating explosives. For the hatch opening device, high dangerous factors exist in the explosive during explosion, and the controllability of the opening of the escape passage after explosion is poor.
The various cabin door opening devices have the problems of slow response speed, insufficient functional reliability, poor controllability and the like, and cannot meet the requirements of the fields of aviation, aerospace and the like on the reliability and controllability of the cabin door opening device for the emergency cabin door.
For this reason, some related solutions have been proposed in the art.
A pop-up door for an aircraft is disclosed, for example, in canadian patent application CA2417559, and more particularly, as belonging to a parachuting door for a military aircraft. Such hatches are also unlocked by means of a connecting rod, which provides the guide with a stop that ensures the hatch is closed. During opening of the door, it is necessary to unlatch the connecting rod so that the door and the stopper block are misaligned with each other. Such a design is relatively complex on the one hand and requires a high degree of positional accuracy for the stop.
For another example, european patent application EP2170698 discloses an aircraft cargo compartment door opening and closing device with a latch mechanism. However, the switching device is provided with the latch hook at one side of the hatch door and the hinge at the other side of the hatch door, so that the hatch door cannot realize the throwing function, and therefore, the switching device is inconvenient to use in emergency and has insufficient safety and reliability.
Therefore, there is a need for a hatch opening device that has a simple structure, is fast in response, and can effectively ensure the safety and reliability of the use of the hatch.
Disclosure of Invention
The invention aims to provide a cabin door opening device which is simple in structure, quick in response and capable of effectively ensuring the use safety and reliability of a cabin door.
A first aspect of the present invention relates to a one-way hatch opening device comprising: the locking plate sleeve is connected with the cabin door locking shaft along the axial direction of the cabin door locking shaft; at least one drive for powering the hatch opening device; an actuator connector, one end of the actuator connector engaging the drive device; a lock cylinder connected to the other end of the actuator link and having a tab form protruding outward in a radial direction of the door lock shaft; and wherein the lock cylinder further comprises an abutment projection projecting axially towards the lock plate sleeve at or near the top end of the tab thereof, the abutment projection being abuttable with the lock plate sleeve during rotation of the actuator connector.
In a preferred embodiment, the latch sleeve may also have the form of a radially outwardly projecting tab, the abutment projection being capable of abutting the tab of the latch sleeve during rotation of the actuator attachment member.
In both embodiments, the actuator connector cooperates with the door lock shaft without regard to the coaxiality requirement.
In a preferred embodiment, the drive means may be at least one automatically controlled actuator.
More preferably, the actuator may be coupled to one end of the actuator connector via an actuator connector.
In another preferred embodiment, the drive means may be a manually controlled sling element.
More preferably, the sling component may be joined to one end of the actuator attachment member via a cable connector.
In a further preferred embodiment, the drive means may be constituted by at least one actuator and a sling element.
A second aspect of the invention relates to a door for an aircraft, wherein a one-way door opening device according to the first aspect of the invention is provided, which opens the door by rotating a door lock shaft of the door.
A third aspect of the invention relates to an aircraft, wherein a door according to the second aspect of the invention is provided.
The cabin door opening device can obtain the following technical effects:
(1) the device can ensure that one actuating system is used when any one actuating system fails or cannot be used by adopting two or more mutually independent actuating systems, thereby greatly improving the safety and reliability of the cabin door opening device.
(2) The device operates on the contact principle, i.e. the lock cylinder and the locking plate sleeve are independent parts. Therefore, the whole device only has the locking plate sleeve fixedly connected with the cabin door, so that the device is more flexible in arrangement and position selection, and the occupied space is smaller.
(3) The device can conveniently set the idle stroke of the cabin door opening device by adjusting the distance between the abutting projection part of the lock column and the locking plate sleeve, and can prevent the misoperation of the cabin door opening device to a certain extent. Meanwhile, due to the existence of the distance, the device can not cause extra load to the emergency cabin door due to overload, vibration and the like, the load of the cabin door and the load of the airplane body are only transmitted through the lock hook and the brake nail, and the requirement for strengthening the opening of the airplane body is low.
Drawings
To further illustrate the structure and the working process of the hatch opening device according to the invention, the invention will be described in detail below with reference to the accompanying drawings and specific embodiments, wherein:
fig. 1 is a schematic perspective view of a hatch opening device according to the present invention.
Reference numerals
1 actuator connector
2 actuator joint
3 actuator
4 sling component
5 stay cable joint
6 lock cylinder
6a contact projection
7 locking plate sleeve
8 hatch door lock shaft
Detailed Description
The structure of the hatch opening device of the invention and its working will be described below with reference to the accompanying drawings, in which like parts are designated by like reference numerals.
Fig. 1 shows a schematic view of an operation state of a one-way hatch opening device according to the present invention.
As shown in fig. 1, the one-way door opening device is composed of a locking plate sleeve 7, a driving device 3 and/or 4, an actuator attachment 1 and a locking cylinder 6.
The locking plate sleeve 7 is connected to the door lock shaft 8 in the axial direction of the door lock shaft 8 (which is part of the door). In other words, the latch sleeve 7 is fixed to one end of the door latch shaft 8. It should be noted that the term "connected" in the present invention covers not only the fastening means of welding, riveting, screwing, etc. for joining the two parts together, but also the forming means of the two parts as a single piece, and these variations are intended to fall within the scope of the present invention.
The actuator connector 1 has an elongate rod-like body which is coupled at one end to at least one drive means 3, 4 for powering the door opening device and at the other end to a lock cylinder 6. As shown in fig. 1, the lock cylinder 6 has the form of a tab projecting radially outward of the actuator connection member 1, at or near the tip of which an abutment projection 6a projecting axially toward the cleat sleeve is provided, which abutment projection 6a can abut the cleat sleeve 7 during rotation of the actuator connection member 1.
In this embodiment, the actuator attachment member 1 does not need to be arranged exactly on the same central axis as the door lock shaft 8 by means of the plate/cylinder contact, since the abutment protrusion 6a and the plate sleeve 7 are dimensioned. That is, the actuator connector 1 and the door lock shaft 8 can be fitted to each other with low coaxiality, and even the coaxiality requirement during fitting can be ignored. Thus, the matching requirement of the actuator connecting piece 1 and the cabin door locking shaft 8 is obviously reduced, and the manufacturing cost can be saved.
In another embodiment, the lock cylinder 6 may also be designed to have a tab form protruding radially outward of the door lock shaft 8, with the same technical effect as the previously described embodiment.
It should be noted that the term "axial direction" refers to a direction parallel to the central axis of the door lock shaft 8, and the term "radial direction" refers to a direction starting from a certain point on the central axis of the door lock shaft 8 and perpendicular to the central axis of the door lock shaft 8. The above directions can be clearly understood from fig. 1 and should be well known to those skilled in the art.
In the present embodiment, the so-called "tabs" have various forms including radially protruding overhanging short arms, blade-like projections, fingers, etc., as long as they have a certain rigidity and can rotate synchronously and unimpededly with the door lock shaft 8 around the center axis of the door lock shaft 8. Such variations are intended to fall within the scope of the present invention.
In a modified example of this embodiment, the locking plate sleeve 7 is also made in the form of a tab similar to that of the locking cylinder 6, i.e. with a tab projecting radially outwards. In this case, the abutment projection 6a can abut against the tab of the latch sleeve 7 during rotation of the actuator attachment 1. In this example, the cleat sleeve 7 and the lock cylinder 6 may be made in the same tab pattern (e.g., both the cleat sleeve 7 and the lock cylinder 6 are made as fingers), or the cleat sleeve 7 and the lock cylinder 6 may be made in different tab patterns (e.g., the cleat sleeve 7 is made as a finger and the lock cylinder 6 is made as a depending short arm), such variations being apparent to those of ordinary skill in the art.
In another modified example of this embodiment, the driving means may be an actuator 3 known in the art, the actuator 3 being an automatic control device which outputs kinetic energy by means of an internal piston-cylinder arrangement to power the door opening device.
The actuator 3 may be mounted directly to one end of the actuator connector 1 or may be coupled to one end of the actuator connector 1 via an actuator connector 2. As shown in fig. 1, the actuator joint 2 has a hinge-like function, one end of which is coupled to an output shaft of the actuator 3 and the other end of which is engaged with the actuator attachment 1, thereby transmitting the power output from the actuator 3 to the actuator attachment 1, causing it to rotate counterclockwise and the lock cylinder 6 to also rotate counterclockwise.
It should be noted that the term "joined" in the present invention covers the way of joining two members together by means of an intermediate member, both ends of which may be joined to the two members respectively, or one end may be joined to one of the members and the other end may be made integral with the other member, and these modifications are intended to fall within the scope of the present invention. It is therefore technically possible if the other end of the actuator connector 2 is made integral with the actuator connector 1.
Although the drive arrangement shown in fig. 1 comprises only one actuator 3, it will be appreciated by a person skilled in the art that more than one, for example two or more, actuators 3 may be provided. In this case, one end of the actuator connecting element 1 is connected to each of the actuators 3 via the same more than one actuator connection 2. It is clear that in this case the number of actuator joints 2 is equal to the number of actuators 3.
In a further modified example of this embodiment, the drive means may be a sling element 4 as known in the art, the sling element 4 being a manual control device. The operator can power the hatch opening device by manually pulling the sling element 4 to deliver kinetic energy in the event that the aircraft loses all power, including emergency power.
The suspension cable member 4 may be directly attached to one end of the actuator attachment 1, or may be joined to one end of the actuator attachment 1 via a cable joint 5. As shown in fig. 1, the cable joint 5 also has a hinge-like function, the suspension cable member 4 surrounds one end of the cable joint 5, and the other end of the cable joint is coupled to the actuator link 1, so that the power output from the suspension cable member 4 is transmitted to the actuator link 1, and the actuator link 1 rotates counterclockwise and drives the lock cylinder 6 to rotate counterclockwise as well.
In general, only one manually dedicated sling element 4 is required to meet the need for emergency hatch opening.
Of course, it will be readily understood by those skilled in the art that in another modified example of this embodiment, the drive means is constituted by at least one actuator 3 and one sling element 4, as shown in fig. 1. Since the automatically controlled actuator and the manually controlled sling member are operated independently of each other, such an arrangement maximizes the safety and reliability of the hatch opening device.
The operation of the hatch opening device of the present invention will be described in detail below.
In the event that unlocking of the door is required, the actuator 3 or sling element 4 may be activated as required. When the actuator 3 is activated, it outputs kinetic energy by means of an internal piston-cylinder arrangement and, via the actuator connector 2, transmits the power output by the actuator 3 to the actuator attachment 1 and rotates it in the counterclockwise direction. At this time, the rope of the sling member 4 is compressed and does not generate a tensile force. Thus, the deployment actuator 3 does not cause damage to the sling element 4.
When the sling element 4 is activated, the cable of the sling element 4 is tensioned by the generated vertical upward force, generating a tensile force and transmitting the power output by the sling element 4 via the cable joint 5 to the actuator attachment 1 and rotating it in a counterclockwise direction. At this time, the piston rod of the actuator 3 moves outward, and the actuator 3 is not damaged.
As the actuator linkage 1 rotates in a counter-clockwise direction, the lock cylinder 6 connected to the actuator linkage 1 also rotates in a counter-clockwise direction. At this time, since the hatch is still in the closed state, the hatch lock shaft 8 is also stationary at its closed angle. As the lock cylinder 6 continues to rotate in the counterclockwise direction, the distance between the abutment projection 6a projecting axially from at or near the top end of its tab toward the cleat sleeve 7 and the tab of the cleat sleeve 7 is reduced until completely eliminated. At this time, the abutment protrusion 6a and the latch sleeve 7 abut against each other. With the lock cylinder 6 continuing to rotate along the counterclockwise direction, the abutting protrusions 6a abutting against each other move together with the locking plate sleeve 7, so that the locking plate sleeve 7 also rotates counterclockwise along with the lock cylinder 6, and finally drives the cabin door lock shaft 8 to rotate from the closing angle to the opening angle, thereby completely opening the cabin door.
The cabin door opening device provided by the invention can be used for opening the cabin door to obtain the following technical effects:
the cabin door opening device is a multi-actuation type opening device, and can ensure that one actuation system is used when any one actuation system fails or cannot be used by adopting two or more independent actuation systems, so that the safety and the reliability of the cabin door opening device are greatly improved.
The hatch opening device of the invention operates on the contact principle, i.e. the lock cylinder and the lock plate sleeve are independent parts. Therefore, the whole device only has the locking plate sleeve fixedly connected with the cabin door (namely, the cabin door locking shaft), so that the device is more flexible in arrangement and position selection and occupies smaller space.
The hatch opening device is a one-way opening device, and the idle stroke of the hatch opening device can be conveniently set by adjusting the distance between the abutting projection part of the lock column and the locking plate sleeve, so that the incorrect operation of the hatch opening device can be prevented to a certain extent. Meanwhile, due to the existence of the distance, the cabin door opening device cannot cause extra load to the emergency cabin door due to overload, vibration and the like, the load of the cabin door and the load of the airplane body are only transmitted through the lock hook and the brake nail, and the requirement for strengthening the opening of the airplane body is low.
Although the construction of the hatch opening device of the present invention and its operation have been described above in connection with preferred embodiments, it will be appreciated by those skilled in the art that the above examples are intended to be illustrative only and are not intended to be limiting. Therefore, modifications and variations of the present invention may be made within the true spirit and scope of the claims, and these modifications and variations are intended to fall within the scope of the claims of the present invention.
Claims (10)
1. A one-way hatch opening device comprising:
the locking plate sleeve (7) is connected with the cabin door locking shaft (8) along the axial direction of the cabin door locking shaft (8);
at least one drive (3, 4) for powering the hatch opening device;
an actuator connection (1), one end of the actuator connection (1) being engaged with the drive means (3, 4);
a lock cylinder (6), the lock cylinder (6) being connected to the other end of the actuator connection piece (1) and having the form of a tab projecting radially outwards of the door lock shaft (8);
wherein the lock cylinder (6) further comprises an abutment protrusion (6a) protruding in the axial direction towards the lock plate sleeve (7) at or near the top end of its tab, the abutment protrusion (6a) being abuttable against the lock plate sleeve (7) during rotation of the actuator connection piece (1).
2. One-way door opening device according to claim 1, characterized in that said latch sleeve (7) also has the form of a tab projecting radially outwards, said abutment projection (6a) being able to abut against the tab of said latch sleeve (7) during rotation of said actuator connection member (1).
3. One-way door opening device according to claim 1, characterized in that the actuator connection (1) cooperates with the door lock shaft (8) without regard to the coaxiality requirement.
4. One-way door opening device according to claim 2, characterized in that said driving means (3, 4) is at least one automatically controlled actuator (3).
5. A one-way door opening device according to claim 4, characterized in that the actuator (3) is coupled to one end of the actuator attachment (1) via an actuator joint (2).
6. One-way door opening device according to claim 2, characterized in that said driving means (3, 4) is a manually controlled sling element (4).
7. A one-way door opening device according to claim 6, characterized in that the sling element (4) is joined to one end of the actuator attachment (1) via a cable joint (5).
8. One-way door opening device according to claim 1, characterized in that said drive means (3, 4) are constituted by at least one actuator (3) and a sling element (4).
9. A door for an aircraft, wherein a one-way door opening device according to claim 1 is provided, which opens the door by rotating a door lock shaft (8) of the door.
10. An aircraft, wherein a door according to claim 9 is provided.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910968048.4A CN110588950B (en) | 2019-10-12 | 2019-10-12 | One-way door opening device, door equipped with an opening device and aircraft equipped with a door |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910968048.4A CN110588950B (en) | 2019-10-12 | 2019-10-12 | One-way door opening device, door equipped with an opening device and aircraft equipped with a door |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN110588950A true CN110588950A (en) | 2019-12-20 |
| CN110588950B CN110588950B (en) | 2023-03-21 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910968048.4A Active CN110588950B (en) | 2019-10-12 | 2019-10-12 | One-way door opening device, door equipped with an opening device and aircraft equipped with a door |
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| Country | Link |
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| CN (1) | CN110588950B (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114876305A (en) * | 2022-04-27 | 2022-08-09 | 上海工程技术大学 | Side-opening aircraft cabin door constant-torque electric lifting mechanism driven by non-circular gear |
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| DE10020825A1 (en) * | 2000-04-28 | 2001-11-08 | Eurocopter Deutschland | Method and device for closing an aircraft door |
| US20100001136A1 (en) * | 2007-07-31 | 2010-01-07 | B/E Aerospace, Inc. | Aircraft door and method for using the same |
| CN102030101A (en) * | 2010-11-24 | 2011-04-27 | 西安飞机工业（集团）有限责任公司 | Aircraft hatch flexible pressure release mechanism |
| US9296464B1 (en) * | 2014-11-12 | 2016-03-29 | The Boeing Company | Aircraft and associated door member biasing assembly and method |
| CN107724841A (en) * | 2017-09-30 | 2018-02-23 | 中国航空工业集团公司西安飞机设计研究所 | A kind of door ladder unification landing gate sequence control mechanism |
| CN109606618A (en) * | 2018-12-14 | 2019-04-12 | 中航沈飞民用飞机有限责任公司 | A kind of hatch door timesharing driving mechanism and its application |
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2019
- 2019-10-12 CN CN201910968048.4A patent/CN110588950B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE10020825A1 (en) * | 2000-04-28 | 2001-11-08 | Eurocopter Deutschland | Method and device for closing an aircraft door |
| US20100001136A1 (en) * | 2007-07-31 | 2010-01-07 | B/E Aerospace, Inc. | Aircraft door and method for using the same |
| CN102030101A (en) * | 2010-11-24 | 2011-04-27 | 西安飞机工业（集团）有限责任公司 | Aircraft hatch flexible pressure release mechanism |
| US9296464B1 (en) * | 2014-11-12 | 2016-03-29 | The Boeing Company | Aircraft and associated door member biasing assembly and method |
| CN107724841A (en) * | 2017-09-30 | 2018-02-23 | 中国航空工业集团公司西安飞机设计研究所 | A kind of door ladder unification landing gate sequence control mechanism |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN114876305A (en) * | 2022-04-27 | 2022-08-09 | 上海工程技术大学 | Side-opening aircraft cabin door constant-torque electric lifting mechanism driven by non-circular gear |
Also Published As
| Publication number | Publication date |
|---|---|
| CN110588950B (en) | 2023-03-21 |
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