CN105501431B - Safeguard the folding structure of hatch door in a kind of aircraft bottom - Google Patents
Safeguard the folding structure of hatch door in a kind of aircraft bottom Download PDFInfo
- Publication number
- CN105501431B CN105501431B CN201510866517.3A CN201510866517A CN105501431B CN 105501431 B CN105501431 B CN 105501431B CN 201510866517 A CN201510866517 A CN 201510866517A CN 105501431 B CN105501431 B CN 105501431B
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- CN
- China
- Prior art keywords
- hatch door
- aircraft
- door
- door frame
- hinged
- 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.)
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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
- B64C1/1446—Inspection hatches
-
- 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
- B64C1/24—Steps mounted on, and retractable within, fuselages
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Closing And Opening Devices For Wings, And Checks For Wings (AREA)
- Specific Sealing Or Ventilating Devices For Doors And Windows (AREA)
Abstract
Safeguard the folding structure of hatch door in a kind of aircraft bottom, contain aircraft door and hatch door frame, the hatch door frame is a horizontal mount structure being fixed on airframe, the aircraft door is the overhead door of an inner band airstair, two parallel suspension arms for having inclination angle are stretched out at the inside suspension end of described aircraft door, the outer end of two suspension arms is hinged on one end of doorframe by connecting seat respectively, there are two parallel gas springs to be respectively hinged the other end of the inner and doorframe of two suspension arms, a suspended axle is respectively fixed with the nearly suspended end in both sides of doorframe, it is hinged with the bearing rod of a groove profile respectively at the remote suspended end in both sides of hatch door, the other end of the bearing rod is connected with the suspended axle of the doorframe both sides.
Description
Technical field
The present invention relates to airplane design technology, the folding structure of hatch door is safeguarded in specifically a kind of aircraft bottom.
Background technology
Aircraft maintenance hatch door is the important feature part on aircraft maintenance maintenance facility access way, and the quality that it is designed is straight
Connect and have influence on the current of the daily maintaining of aircraft and instrument and equipment, to ensureing that military secret wartime rapid-maintenance and civil aircraft are persistently fitted
Boat is particularly important, and existing safeguard more than hatch door carries out folding and unfolding using four-bar mechanism, and is carried out using its dead point after hatch door opening completely
Stop, but dead point can bring adverse effect (direction even uncertain mechanism dieback) to packing up action, therefore need to often install additional
A set of finished product positions latch mechanism, to ensure that folding structure also can be by hatch door positive lock, but so when being in non-dead-centre position
Since, it can not only make cost increase, it is complex that structure also becomes, need to be while complete unlocking motion when hatch door is packed up, operability
It is poor；In addition, the principal layout of four-bar mechanism, which also results in, influences the current of personnel and equipment when folding structure is put down, and pack up
Space in more cabin is taken afterwards.
The content of the invention
The purpose of the application is to provide a kind of simple in construction, easy to operate, and favourable personnel and equipment are passed through and taken empty
Between less aircraft bottom safeguard the folding structure of hatch door.
The folding structure of hatch door is safeguarded in a kind of aircraft bottom, containing aircraft door and hatch door frame, and the hatch door frame is one solid
The horizontal mount structure on airframe is scheduled on, the aircraft door is the overhead door of an inner band airstair, it is characterised in that
Two parallel suspension arms for having inclination angle are stretched out at described aircraft door inside suspension end, and the outer end of each suspension arm passes through connection
Seat is hinged on one end of hatch door frame, and is hinged with a gas spring between suspension arm the inner and the other end of hatch door frame, in hatch door
A suspended axle is respectively fixed with the nearly suspended end in both sides of frame, a groove is hinged with respectively at the remote suspended end in both sides of hatch door
The bearing rod of type, the other end of the bearing rod is connected with the suspended axle of the hatch door frame both sides.
The beneficial effect of the application is：1) the folding and unfolding action of hatch door is realized using leverage principle as few as possible, is subtracted
Lack the use of auxiliary finished parts, saved the development cost of hatch door, improve the reliability of hatch door folding and unfolding action.2) suspension arm
It is the extension of boarding side of the ladder wall positioned at the both sides of airstair, with the space-saving advantage of compact conformation., it is simple compact
Structure lightened design, not only makes maintenance hatch door have enough passage spaces, and with stronger loading allowance, to ensureing
Rapid-maintenance and civil aircraft continuing airworthiness are significant.3) gas spring is conducive to the folding and unfolding of hatch door to buffer, and can prevent outdoor fitful wind
Disturbance.4) hatch door opened is suspended on hatch door frame respectively by bearing rod and suspension arm, and suspended axle is limited by the chute of suspension arm
It is fixed, it is rational in infrastructure.
Accompanying drawing is described in further detail to the application with reference to embodiments.
Brief description of the drawings
Fig. 1 is the folding structure signal that hatch door is safeguarded in aircraft bottom
Fig. 2 is cabin door structure signal
Fig. 3 is the open mode signal that hatch door is safeguarded in aircraft bottom
Fig. 4 is the closed mode signal that hatch door is safeguarded in aircraft bottom
Explanation is numbered in figure：1 airframe, 2 hatch door frames, 3 hatch doors, 4 suspension arms, 5 connecting seats, 6 gas springs, 7 suspended axles,
8 bearing rods, 9 rotating shafts, 10 back-moving springs
Embodiment
Referring to accompanying drawing, the folding structure of hatch door is safeguarded in aircraft bottom, contains aircraft door 3 and hatch door frame 2, the hatch door frame 2
It is a horizontal mount structure being fixed on airframe 1, the aircraft door 3 is the overhead door of an inner band airstair,
The inside suspension end of aircraft door is stretched out in two parallel suspension arms 4 for having inclination angle, the present embodiment, and the suspension arm is in hatch door
The extended structure of side boarding side of the ladder wall, in T-shape, as shown in Fig. 2 suspension arm is in about 60 degree of angles with the plane where hatch door,
The outer end of two suspension arms 4 is hinged on one end of hatch door frame 2 by connecting seat 5 respectively, rotates about hatch door and realizes that folding and unfolding is moved
Make, separately there are two parallel gas springs 6 to be respectively hinged the other end of the inner and hatch door frame of two suspension arms 4, constitute four bars
Mechanism, a suspended axle 7 is respectively fixed with the nearly suspended end in both sides of hatch door frame 2, in the remote suspended end punishment in the both sides of hatch door
The bearing rod 8 of a groove profile, the other end of the bearing rod 8 and the suspended axle 7 of the hatch door frame both sides are not hinged with by rotating shaft 9
Connection, suspended axle 7 is embedded in the groove of bearing rod 8.In order to prevent the interference of bearing rod 8 and hatch door frame 2, in bearing rod 8
Provided with a back-moving spring 10 between portion and hatch door 3.
When opening hatch door, after being unlocked by operating outdoor handle, hatch door 3 is opened under gravity, and gas spring 6 will continuous quilt
Compression is so as to play buffer damping, and hatch door 3 is during descending, when suspended axle 7 is encountered in the end of bearing rod 8, hatch door 3
Just hang on this and stop motion, meanwhile, the position of gas spring 6 also have been located in connecting seat 5 with below the pin joint of hatch door 3,
Therefore hatch door 3 can reliably rest on precalculated position under the stabilizing moment effect of gas spring 6, without beat or by fitful wind and
The disturbance of other factors, its full open position is as shown in Figure 3.When packing up hatch door, the effect of gravity and gas spring 6 is overcome first
Power, after hatch door 3 is rotated up smaller stroke, when the position of gas spring 6 is located at connecting seat 5 with more than the pin joint of hatch door 3,
The active force of gas spring 6 is just changed into power-assisted by resistance, and now, one end of bearing rod 8 is pulled patch by back-moving spring 10 all the time
Close in rotating shaft 9 to prevent from interfering with hatch door frame 2, after hatch door 3 is closed in place, then by operating outdoor handle, so as to realize
The locking of hatch door 3.
Claims (3)
1. the folding structure of hatch door is safeguarded in a kind of aircraft bottom, containing aircraft door and hatch door frame, the hatch door frame is a fixation
Horizontal mount structure on airframe, the aircraft door is the overhead door of an inner band airstair, it is characterised in that institute
Two parallel suspension arms for having inclination angle are stretched out at the inside suspension end for the aircraft door stated, and the outer end of two suspension arms passes through respectively
Connecting seat is hinged on one end of hatch door frame, has two parallel gas springs respectively by the another of the inner of two suspension arms and hatch door frame
One end is hinged, and is respectively fixed with a suspended axle at the nearly suspended end in both sides of hatch door frame, is far hung in the both sides of aircraft door
The bearing rod of a groove profile is hinged with end respectively, the other end of the bearing rod is connected with the suspended axle of the hatch door frame both sides.
2. the folding structure of hatch door is safeguarded in aircraft bottom as claimed in claim 1, it is characterised in that described bearing rod
There is a back-moving spring between middle part and aircraft door.
3. the folding structure of hatch door is safeguarded in aircraft bottom as claimed in claim 1, it is characterised in that described suspension arm is
The extended structure of boarding side of the ladder wall on the inside of aircraft door.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510866517.3A CN105501431B (en) | 2015-11-30 | 2015-11-30 | Safeguard the folding structure of hatch door in a kind of aircraft bottom |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510866517.3A CN105501431B (en) | 2015-11-30 | 2015-11-30 | Safeguard the folding structure of hatch door in a kind of aircraft bottom |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN105501431A CN105501431A (en) | 2016-04-20 |
| CN105501431B true CN105501431B (en) | 2017-07-28 |
Family
ID=55709838
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510866517.3A Active CN105501431B (en) | 2015-11-30 | 2015-11-30 | Safeguard the folding structure of hatch door in a kind of aircraft bottom |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105501431B (en) |
Families Citing this family (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20170210459A1 (en) * | 2016-01-21 | 2017-07-27 | Gulfstream Aerospace Corporation | Aircraft air stair support |
| CN109502005B (en) * | 2018-11-07 | 2021-12-24 | 中国航空工业集团公司西安飞机设计研究所 | Aircraft door |
| CN110356541B (en) * | 2019-06-11 | 2023-07-28 | 江西昌河航空工业有限公司 | Light high strength helicopter tail-gate structure |
| 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 |
| WO2022016487A1 (en) * | 2020-07-24 | 2022-01-27 | 江苏凤凰智慧教育研究院有限公司 | Easy access aviation simulation cabin |
| CN112208770B (en) * | 2020-10-10 | 2022-08-26 | 江西洪都航空工业集团有限责任公司 | Cabin door linkage retracting and releasing device for exposed equipment of airplane |
| CN112265630A (en) * | 2020-10-27 | 2021-01-26 | 西安航空职业技术学院 | Retraction mechanism of aircraft maintenance cabin door |
| CN112455647B (en) * | 2020-11-13 | 2023-08-22 | 中国航空工业集团公司沈阳飞机设计研究所 | Aircraft landing gear cabin door hanging structure |
| CN114590383B (en) * | 2022-02-24 | 2023-02-03 | 中国人民解放军海军工程大学 | Shaftless propulsion system integrated on aircraft shell and control method thereof |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2739343A (en) * | 1951-07-03 | 1956-03-27 | Ole O Rahm | Hatch cover and self-adjusting hinge therefor |
| US4176812A (en) * | 1977-10-31 | 1979-12-04 | The Boeing Company | Midcabin door for blended wing aircraft |
| US4601446A (en) * | 1983-09-29 | 1986-07-22 | The Boeing Company | Aircraft door counterbalance system |
| RU2339539C1 (en) * | 2007-02-28 | 2008-11-27 | Общество с ограниченной ответственностью "Авиа СТЭП" (ООО "Авиа СТЭП") | Entrance stairs for transportation vehicle, for instance for aircraft plane |
| CN101341069A (en) * | 2005-12-19 | 2009-01-07 | 欧洲直升机德国有限责任公司 | Aircraft door assembly, and aircraft fuselage comprising such an aircraft door assembly |
-
2015
- 2015-11-30 CN CN201510866517.3A patent/CN105501431B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2739343A (en) * | 1951-07-03 | 1956-03-27 | Ole O Rahm | Hatch cover and self-adjusting hinge therefor |
| US4176812A (en) * | 1977-10-31 | 1979-12-04 | The Boeing Company | Midcabin door for blended wing aircraft |
| US4601446A (en) * | 1983-09-29 | 1986-07-22 | The Boeing Company | Aircraft door counterbalance system |
| CN101341069A (en) * | 2005-12-19 | 2009-01-07 | 欧洲直升机德国有限责任公司 | Aircraft door assembly, and aircraft fuselage comprising such an aircraft door assembly |
| RU2339539C1 (en) * | 2007-02-28 | 2008-11-27 | Общество с ограниченной ответственностью "Авиа СТЭП" (ООО "Авиа СТЭП") | Entrance stairs for transportation vehicle, for instance for aircraft plane |
Also Published As
| Publication number | Publication date |
|---|---|
| CN105501431A (en) | 2016-04-20 |
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| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CP03 | Change of name, title or address | ||
| CP03 | Change of name, title or address |
Address after: No. 710089 in Shaanxi province Xi'an city Yanliang District West Avenue Patentee after: AVIC Xi'an Aircraft Industry Group Co.,Ltd. Address before: 1 No. 710089 Shaanxi province Xi'an city Yanliang District West Avenue Patentee before: AVIC AIRCRAFT Corp. |
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| TR01 | Transfer of patent right | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20210616 Address after: 1 No. 710089 Shaanxi province Xi'an city Yanliang District West Avenue Patentee after: AVIC AIRCRAFT Corp. Address before: 1 No. 710089 Shaanxi province Xi'an city Yanliang District West Avenue Patentee before: XI'AN AIRCRAFT BRANCH OF XI'AN AIRCRAFT INTERNATIONAL Corp. |