CN110725627A - Folding hinge mechanism of airplane cabin door - Google Patents
Folding hinge mechanism of airplane cabin door Download PDFInfo
- Publication number
- CN110725627A CN110725627A CN201910931071.6A CN201910931071A CN110725627A CN 110725627 A CN110725627 A CN 110725627A CN 201910931071 A CN201910931071 A CN 201910931071A CN 110725627 A CN110725627 A CN 110725627A
- Authority
- CN
- China
- Prior art keywords
- hinge
- cabin door
- folding hinge
- folding
- door
- 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.)
- Granted
Links
- 230000007246 mechanism Effects 0.000 title claims abstract description 43
- 238000007789 sealing Methods 0.000 claims abstract description 10
- 230000000694 effects Effects 0.000 claims description 7
- 230000001681 protective effect Effects 0.000 claims description 3
- 239000000428 dust Substances 0.000 abstract description 2
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 abstract description 2
- 238000010008 shearing Methods 0.000 abstract 1
- 238000009966 trimming Methods 0.000 abstract 1
- 238000009434 installation Methods 0.000 description 6
- 230000005540 biological transmission Effects 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 238000001125 extrusion Methods 0.000 description 1
- 230000001771 impaired effect Effects 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
Images
Classifications
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- E—FIXED CONSTRUCTIONS
- E05—LOCKS; KEYS; WINDOW OR DOOR FITTINGS; SAFES
- E05D—HINGES OR SUSPENSION DEVICES FOR DOORS, WINDOWS OR WINGS
- E05D3/00—Hinges with pins
- E05D3/06—Hinges with pins with two or more pins
-
- 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
-
- E—FIXED CONSTRUCTIONS
- E05—LOCKS; KEYS; WINDOW OR DOOR FITTINGS; SAFES
- E05D—HINGES OR SUSPENSION DEVICES FOR DOORS, WINDOWS OR WINGS
- E05D11/00—Additional features or accessories of hinges
- E05D11/10—Devices for preventing movement between relatively-movable hinge parts
-
- E—FIXED CONSTRUCTIONS
- E05—LOCKS; KEYS; WINDOW OR DOOR FITTINGS; SAFES
- E05D—HINGES OR SUSPENSION DEVICES FOR DOORS, WINDOWS OR WINGS
- E05D7/00—Hinges or pivots of special construction
-
- E—FIXED CONSTRUCTIONS
- E05—LOCKS; KEYS; WINDOW OR DOOR FITTINGS; SAFES
- E05Y—INDEXING SCHEME ASSOCIATED WITH SUBCLASSES E05D AND E05F, RELATING TO CONSTRUCTION ELEMENTS, ELECTRIC CONTROL, POWER SUPPLY, POWER SIGNAL OR TRANSMISSION, USER INTERFACES, MOUNTING OR COUPLING, DETAILS, ACCESSORIES, AUXILIARY OPERATIONS NOT OTHERWISE PROVIDED FOR, APPLICATION THEREOF
- E05Y2900/00—Application of doors, windows, wings or fittings thereof
- E05Y2900/50—Application of doors, windows, wings or fittings thereof for vehicles
- E05Y2900/502—Application of doors, windows, wings or fittings thereof for vehicles for aircraft or spacecraft
-
- E—FIXED CONSTRUCTIONS
- E05—LOCKS; KEYS; WINDOW OR DOOR FITTINGS; SAFES
- E05Y—INDEXING SCHEME ASSOCIATED WITH SUBCLASSES E05D AND E05F, RELATING TO CONSTRUCTION ELEMENTS, ELECTRIC CONTROL, POWER SUPPLY, POWER SIGNAL OR TRANSMISSION, USER INTERFACES, MOUNTING OR COUPLING, DETAILS, ACCESSORIES, AUXILIARY OPERATIONS NOT OTHERWISE PROVIDED FOR, APPLICATION THEREOF
- E05Y2900/00—Application of doors, windows, wings or fittings thereof
- E05Y2900/50—Application of doors, windows, wings or fittings thereof for vehicles
- E05Y2900/53—Type of wing
- E05Y2900/531—Doors
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Hinges (AREA)
Abstract
The invention discloses a folding hinge mechanism of an airplane cabin door. The mechanism comprises: the two fixed hinges are used for connecting the cabin door and the fuselage structure together and are used as rotating shafts when the cabin door is opened and closed; the folding hinges are arranged between the two hinges and used for transmitting the load of the cabin door when the cabin door is closed, and the mechanism is folded to avoid clamping stagnation when the cabin door is opened; the adjustable limiting mechanism is positioned on the cabin door body and used for limiting the folding hinge, helping the hinge to be tensioned when the cabin door is closed and assisting the hinge to transfer load; the movable skin is used for avoiding the interference between the cabin door and a fuselage structure when the cabin door is opened and closed; the sealing strip prevents water and dust from entering the cabin; and the pull rod pushes the movable skin to move. By adopting the invention, when the bearing cabin door is arranged at the hyperboloid position of the fuselage, cabin door hinge mechanisms can be arranged without trimming the outline of the fuselage into straight line segments, and when the cabin door is closed, the hinge mechanisms can transmit annular and shearing loads.
Description
Technical Field
The invention relates to the structural design of an airplane cabin door, in particular to a foldable cabin door hinge mechanism.
Background
Aircraft often have fuselages that are streamlined to reduce aerodynamic drag. Some doors on the fuselage, such as cargo doors or luggage compartment doors, are often arranged in the rear and lower non-equal straight sections, where the fuselage has a hyperbolic profile, which makes the design of the doors difficult. For smaller doors, two hinges may be arranged, but for larger doors, the design is generally load-bearing to transfer fuselage hoop and shear loads, reducing structural weight.
The load-bearing cabin door is usually installed on the machine body by using a key hinge, and the installation and use functions require that hinge rotating shafts are arranged on the same straight line so as to avoid being blocked. This requires that the body contour at the hinge location must be straight or partially cushioned so that the hinge is straight. However, the integral cushioned version typically causes the hinge to bulge out of the fuselage contour, affecting the aerodynamic performance and appearance of the aircraft. When the XX type machine is used for designing the luggage compartment door, in order to meet the installation and use requirements of the hinge, the position of the hinge installation of the compartment door is repaired into a straight line, so that the local appearance of the luggage compartment door is changed violently, and certain influence is caused on the pneumatic performance and the appearance.
Disclosure of Invention
The purpose of the invention is: the foldable cabin door hinge mechanism can avoid linear installation of cabin door hinges, and is simple in structure, stable and reliable.
The technical scheme of the invention is as follows: the utility model provides an aircraft hatch door folding hinge mechanism, its includes a set of fixed hinge, a set of folding hinge subassembly and activity covering, wherein, fixed hinge arranges in the outside, and it connects fuselage and hatch door linkage segment respectively, folding hinge subassembly arranges between fixed hinge, and every folding hinge includes two hinge fixing support, folding hinge, stop gear, pull rod, and wherein, two hinge fixing support set up respectively at fuselage and hatch door body tip, and respectively through connecting rod and folding hinged joint, folding hinge or connecting rod pass through the pull rod and connect the activity covering, the articulated setting of activity covering one end is in hatch door body tip outside, stop gear sets up on the hatch door linkage segment for folding hinge position when the restriction hatch door is closed.
And a sealing pressing strip is arranged on the outer side of the machine body where the hinge fixing support is arranged.
The limiting mechanism is of a screw structure and is arranged on the outer side of the cabin door connecting section.
And the screw adjusting part of the limiting mechanism penetrates through the cabin door connecting section and extends into the cabin.
The connecting rod is connected with the pull rod through an independent hinge.
And a protective structure is arranged on one side of the folding hinge, which is in contact with the limiting mechanism.
The axes of rotation of all the fixed hinges and of the folding hinges are parallel to each other.
The included angle of the two connecting rods of the folding hinge is an obtuse angle facing the cabin when the cabin door is closed, so that the hinge can be smoothly folded when the cabin door is opened.
When the cabin door is opened, the folding hinge is folded, the included angle of the hinge connecting rod is reduced, and the folding hinge drives the pull rod to open the movable skin, so that the cabin door is opened; when the cabin door is closed, the folding hinge extends, the movable skin is pulled back through the pull rod, and when the cabin door reaches a closed position, the folding hinge protection structure is extruded and limited by the limiting mechanism, so that the folding hinge keeps tension.
The invention has the technical effects that: the folding hinge mechanism of the airplane cabin door can be installed and used at the position of the appearance of a non-linear section of the airplane body through the special structural design of the fixed hinge and the folding hinge, avoids the modification and compromise of the appearance of the airplane body for the installation of the cabin door, realizes the reliable opening and closing of the cabin door of the airplane body, and effectively solves the installation and use problems of the lower cabin door hinge with a curved surface appearance. Meanwhile, the structure is simple, the weight is light, the opening and closing operation is convenient, and compared with the traditional cabin door structure, the cabin door structure has greater technical progress and practical application value.
Drawings
FIG. 1 is a schematic side view of an embodiment of the folding hinge mechanism of the present invention, showing the hinge mechanism in a closed position;
FIG. 2 illustrates the state of the hinge mechanism with the hatch open, in one embodiment;
fig. 3 shows an arrangement of folding and fixed hinges on the fuselage.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
Referring to fig. 1, the present invention provides a structural schematic view of an embodiment of the folding hinge for aircraft doors.
In the embodiment, the folding hinge of the airplane cabin door comprises a hinge fixing support 1 positioned on a fuselage 11, a sealing strip 2, a connecting rod 3, a folding hinge 4, a movable skin 5, a pull rod 6, a fixing support 7 positioned on a cabin door 8, a limiting mechanism 9 positioned on the cabin door and a fixing hinge 10. Wherein the fixed hinge 10 is arranged on the outside and the folding hinge fixing support 1 is arranged on the inside, see fig. 3, and is arranged along the curved surface of the fuselage. Wherein, the fixed hinge 10 is fixed on the fuselage and connected with the cabin door connecting section. The two hinge fixing supports are respectively arranged at the end parts of the machine body and the cabin door body and are respectively connected with the folding hinges through connecting rods.
The folding hinges or the connecting rods are connected with the movable skin through pull rods, wherein the pull rods are adjustable in length, and the position of the movable skin can be adjusted conveniently.
The movable end of the movable skin is butted with the machine body when being closed, the sealing batten is pressed tightly, the other end of the movable skin is hinged and arranged at the outer side of the end part of the cabin door body,
the limiting mechanism is in a screw structure and is arranged on the cabin door connecting section and used for limiting the position of the folding hinge when the cabin door is closed. In addition, the screw adjusting part passes through the cabin door connecting section according to the requirement and extends to the interior of the cabin so as to facilitate adjustment.
And a sealing pressing strip is arranged on the outer side of the machine body where the hinge fixing support is arranged.
When the pull rod is arranged on the connecting rod, the pull rod and the connecting rod are connected through an independent hinge, so that the linkage between the pull rod and the skin is convenient to realize.
Folding hinge is provided with protective structure with stop gear contact one side, avoids receiving stop gear extrusion impaired.
The axes of rotation of all the fixed hinges and of the folding hinges are parallel to each other to ensure an efficient operation of the folding mechanism.
In addition, as a modified version of the pull rod 6, it can be designed as a connecting rod with adjustable length to facilitate the adjustment of the gap with the sealing strip.
As a modification of the folding hinge 4, the hinge can be designed not only as a single-double-lug structure but also as a multi-lug hinge structure according to the magnitude of the load.
The invention relates to a working process of an airplane cabin door folding hinge mechanism, which comprises the following steps:
when the cabin door 8 is closed, the folding hinge 4 is extended, the connecting rod 3 and the pull rod 6 form an obtuse angle, the limiting mechanism 9 compresses the folding hinge 4 by adjusting the threads of the limiting mechanism 9, the folding hinge 4 is in a tensioning state, and force transmission of a cabin door structure is facilitated. The limiting mechanism 9 is provided with a locking nut, so that the limiting mechanism 9 is prevented from loosening. At the moment, the movable skin 5 is restrained by the pull rod 6 and is tightly attached to the sealing strip 2 to provide sealing for a cabin door gap and prevent water and dust from entering the cabin. As shown in fig. 1.
When the cabin door 8 is opened, the folding hinge 4 starts to be folded, the included angle of the connecting rod 3 is reduced, and the movable skin 5 is pushed by the pull rod 6 to be opened outwards, so that the interference with the fuselage 11 is avoided.
The folding hinge mechanism of the airplane cabin door comprises two fixed hinges 10 and a plurality of folding hinges 4 arranged between the two hinges; the limiting mechanism 9 is positioned on the cabin door body and used for limiting the folding hinge; a movable skin 5, a sealing strip 2, a pull rod 6 and the like.
The fixed hinge and the folding hinge are arranged as close to the fuselage skin as possible, so that load transfer is facilitated. As shown in fig. 3, the two fixed hinges 10 are coaxial, and the folding hinge 1 is not coaxial with the fixed hinges, but the axes of all the hinges are parallel, so that the hatch can be opened without interference and jamming.
When the cabin door is closed, the folding hinge is unfolded, and the stretching angle is adjusted through the limiting mechanism 9, so that the cabin door hinge can be tensioned, and the force transmission of the structure is facilitated. When the hatch door is opened, the folding hinge 4 is folded inwards, the movable skin 5 is opened outwards, the structural interference is avoided, and the hatch door can be opened to a required angle. When the folding hinge connecting rod 3 is in the closed position, a certain obtuse angle needs to be ensured, otherwise the cabin door cannot be folded when being opened.
The foregoing is merely a detailed description of the embodiments of the present invention, and is not intended to represent the conventional art. The scope of the present invention is not limited thereto, and any changes or substitutions that can be easily made by those skilled in the art within the technical scope of the present invention will be covered by the scope of the present invention. The protection scope of the present invention shall be subject to the protection scope of the claims.
Claims (9)
1. The utility model provides an aircraft hatch door folding hinge mechanism which characterized by: including a set of fixed hinge, a set of folding hinge subassembly and activity covering, wherein, fixed hinge arranges in the outside, and it connects fuselage and hatch door linkage segment respectively, folding hinge subassembly arranges between fixed hinge, and every folding hinge includes two hinge fixing support, folding hinge, stop gear, pull rod, and wherein, two hinge fixing support set up respectively at fuselage and hatch door body tip, and respectively through connecting rod and folding hinged joint, folding hinge or connecting rod pass through the pull rod and connect the activity covering, the articulated setting of activity covering one end is in the hatch door body tip outside, stop gear sets up on the hatch door linkage segment for folding hinge position when restriction hatch door is closed.
2. The aircraft door folding hinge mechanism according to claim 1, characterized in that: and a sealing pressing strip is arranged on the outer side of the machine body where the hinge fixing support is arranged.
3. The aircraft door folding hinge mechanism according to claim 1, characterized in that: the limiting mechanism is of a screw structure and is arranged on the outer side of the cabin door connecting section.
4. The aircraft door folding hinge mechanism according to claim 1, characterized in that: and the screw adjusting part of the limiting mechanism penetrates through the cabin door connecting section and extends into the cabin.
5. The aircraft door folding hinge mechanism according to claim 1, characterized in that: the connecting rod is connected with the pull rod through an independent hinge.
6. The aircraft door folding hinge mechanism according to claim 1, characterized in that: and a protective structure is arranged on one side of the folding hinge, which is in contact with the limiting mechanism.
7. The aircraft door folding hinge mechanism according to claim 1, characterized in that: the axes of rotation of all the fixed hinges and of the folding hinges are parallel to each other.
8. The aircraft door folding hinge mechanism according to claim 1, characterized in that: the included angle of the two connecting rods of the folding hinge is an obtuse angle facing the cabin when the cabin door is closed, so that the hinge can be smoothly folded when the cabin door is opened.
9. The aircraft door folding hinge mechanism according to claim 1, characterized in that: when the cabin door is opened, the folding hinge is folded, the included angle of the hinge connecting rod is reduced, and the folding hinge drives the pull rod to open the movable skin, so that the cabin door is opened; when the cabin door is closed, the folding hinge extends, the movable skin is pulled back through the pull rod, and when the cabin door reaches a closed position, the folding hinge protection structure is extruded and limited by the limiting mechanism, so that the folding hinge keeps tension.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910931071.6A CN110725627B (en) | 2019-09-29 | 2019-09-29 | Folding hinge mechanism of airplane cabin door |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910931071.6A CN110725627B (en) | 2019-09-29 | 2019-09-29 | Folding hinge mechanism of airplane cabin door |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN110725627A true CN110725627A (en) | 2020-01-24 |
| CN110725627B CN110725627B (en) | 2022-09-20 |
Family
ID=69219586
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910931071.6A Active CN110725627B (en) | 2019-09-29 | 2019-09-29 | Folding hinge mechanism of airplane cabin door |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN110725627B (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112145000A (en) * | 2020-11-02 | 2020-12-29 | 赵一霖 | Automobile door hinge with installation screw holes |
| CN112613117A (en) * | 2020-12-11 | 2021-04-06 | 成都飞机工业（集团）有限责任公司 | Rapid construction and design method for aviation flap from unfolding size to 3D |
| CN113753219A (en) * | 2021-09-24 | 2021-12-07 | 中国航空工业集团公司西安飞机设计研究所 | Hinge support for airplane cabin door |
| CN113879538A (en) * | 2021-10-13 | 2022-01-04 | 北京机电工程研究所 | Bury formula folding lug mechanism and aircraft |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4854010A (en) * | 1987-11-20 | 1989-08-08 | The Boeing Company | Hinge mechanism for aircraft door |
| CN203476099U (en) * | 2013-10-15 | 2014-03-12 | 霍志文 | Suspended folding door |
| CN203666350U (en) * | 2013-12-06 | 2014-06-25 | 马可波罗（常州）客车零部件有限公司 | Coach four-bar linkage hinge cabin door |
| CN104213807A (en) * | 2014-08-29 | 2014-12-17 | 厦门威迪思汽车设计服务有限公司 | Slippage four-rod hinge coach cabin door opening mechanism |
| CN104816611A (en) * | 2015-04-17 | 2015-08-05 | 郑州宇通客车股份有限公司 | Door device and passenger car employing door device |
-
2019
- 2019-09-29 CN CN201910931071.6A patent/CN110725627B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4854010A (en) * | 1987-11-20 | 1989-08-08 | The Boeing Company | Hinge mechanism for aircraft door |
| CN203476099U (en) * | 2013-10-15 | 2014-03-12 | 霍志文 | Suspended folding door |
| CN203666350U (en) * | 2013-12-06 | 2014-06-25 | 马可波罗（常州）客车零部件有限公司 | Coach four-bar linkage hinge cabin door |
| CN104213807A (en) * | 2014-08-29 | 2014-12-17 | 厦门威迪思汽车设计服务有限公司 | Slippage four-rod hinge coach cabin door opening mechanism |
| CN104816611A (en) * | 2015-04-17 | 2015-08-05 | 郑州宇通客车股份有限公司 | Door device and passenger car employing door device |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112145000A (en) * | 2020-11-02 | 2020-12-29 | 赵一霖 | Automobile door hinge with installation screw holes |
| CN112145000B (en) * | 2020-11-02 | 2022-03-08 | 宁波乾方汽车配件有限公司 | Automobile door hinge with installation screw holes |
| CN112613117A (en) * | 2020-12-11 | 2021-04-06 | 成都飞机工业（集团）有限责任公司 | Rapid construction and design method for aviation flap from unfolding size to 3D |
| CN113753219A (en) * | 2021-09-24 | 2021-12-07 | 中国航空工业集团公司西安飞机设计研究所 | Hinge support for airplane cabin door |
| CN113753219B (en) * | 2021-09-24 | 2023-08-18 | 中国航空工业集团公司西安飞机设计研究所 | Hinge support for cabin door of aircraft |
| CN113879538A (en) * | 2021-10-13 | 2022-01-04 | 北京机电工程研究所 | Bury formula folding lug mechanism and aircraft |
| CN113879538B (en) * | 2021-10-13 | 2023-07-14 | 北京机电工程研究所 | Buried folding lifting lug mechanism and aircraft |
Also Published As
| Publication number | Publication date |
|---|---|
| CN110725627B (en) | 2022-09-20 |
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| TA01 | Transfer of patent application right |
Effective date of registration: 20220819 Address after: 519040 building 201, 999 Jinhai Middle Road, Jinwan District, Zhuhai City, Guangdong Province Applicant after: SOUTH CHINA AIRCRAFT INDUSTRY CO., LTD. OF CHINA AVIATION INDUSTRY GENERAL AIRCRAFT Co.,Ltd. Address before: 519040 AVIC Tongfei industrial base, aviation industrial park, Jinwan District, Zhuhai City, Guangdong Province Applicant before: R&D INSTITUTE OF CHINA AVIATION INDUSTRY GENERAL AIRCRAFT Co.,Ltd. |
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