CN106672200A - Airplane cabin door negative pressure device for water landing - Google Patents
Airplane cabin door negative pressure device for water landing Download PDFInfo
- Publication number
- CN106672200A CN106672200A CN201710008962.5A CN201710008962A CN106672200A CN 106672200 A CN106672200 A CN 106672200A CN 201710008962 A CN201710008962 A CN 201710008962A CN 106672200 A CN106672200 A CN 106672200A
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- CN
- China
- Prior art keywords
- negative pressure
- pressure device
- directive wheel
- bearing
- main part
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- 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
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Special Wing (AREA)
Abstract
The invention relates to an airplane cabin door negative pressure device for water landing. The airplane cabin door negative pressure device comprises a guiding wheel, a support and a guiding groove, wherein the guiding wheel is formed by a main body part and a polished rod part; the main body part and the polished rod part are both of hollow cylinder structures; the support is of a long-rod structure with a hole formed in the center; the polished rod part of the guiding wheel is inserted into one end of the support, penetrates through the guiding wheel from the main body part through a bolt and continuously penetrates into the support for being fixed; a fixing seat is arranged at the outer side of the support; the other end of the support penetrates through a frame of a cabin door and is connected with a longitudinal beam adjacent to the frame, and the support is fixed on the frame of the cabin door through the fixing seat; the guiding groove is formed in the frame of the cabin door and is used for guiding by matching with the main body part of the guiding wheel. According to the airplane cabin door negative pressure device for the water landing, disclosed by the invention, a guiding wheel lifting mechanism for half blocking the cabin door is designed into a device capable of bearing negative pressure load, so that not only can be structure weight be reduced, but also the manufacturing cost can be reduced.
Description
Technical field
It relates to vehicle technology field, and in particular to a kind of ditching aircraft door negative pressure device.
Background technology
When aircraft force-lands on the water, in order to slow down water intake velocity in cabin, hatch door of the airframe below horizontal plane
Or lid needs to bear the negative pressure load that water surface impact brings, and now needs a kind of structure to bear this load.And existing machine
Type, into hook locking type, this load is born by hatch door sealing typically by the door design below the water surface, and this door will also
Fuselage pressurization load is born, the weight of door can be than larger.And half blocking type hatch door is directed to, currently without good structure side
Case is solving problems.
The content of the invention
The purpose of the disclosure is to provide a kind of ditching aircraft door negative pressure device, can bear the negative of water surface impact
Compressive load.
A kind of to achieve these goals, ditching aircraft door negative pressure device of disclosure offer, including directive wheel,
Bearing, gathering sill；The directive wheel is made up of main part and smooth bar part, and the main part and smooth bar part are hollow
Cylindrical structure；The long rod structure of perforate centered on the bearing, the smooth bar part of the directive wheel inserts the bearing
One end, and by the way that bolt is from the main part end through the directive wheel and continues to penetrate bearing and is fixed；The bearing
Outside be provided with fixed seat, the other end of the bearing through hatch door frame and the longeron connection adjacent with frame, and by institute
State fixed seat the bearing is fixed on hatch door frame；The gathering sill on the hatch door mouth frame, and by with the guiding
The main part of wheel coordinates guiding.
Preferably, the diameter of the directive wheel main part is determined by the magnitude of load that the directive wheel is born.
Preferably, the length of the directive wheel smooth bar part is more than given threshold.
Preferably, the outside between the directive wheel main part and smooth bar part is provided with back-up ring, and the main part is led to
Cross the back-up ring and be fastened on the carrier exterior.
Preferably, the directive wheel also includes sleeve, and the sleeve is set in the main part and coordinates with its gap,
The sleeve is fastened in the main part by the back-up ring.
Preferably, between the sleeve and the back-up ring, it is additionally provided with bushing.
Preferably, centered on the bearing perforate cylinder long rod structure.
Preferably, the cell body outside of the gathering sill is provided with reinforcement.
The disclosure also provides a kind of aircraft, and negative pressure device as above is included on the hatch door of the aircraft.
Preferably, the upper left of the aircraft door, lower-left, upper right, lower right-most portion are respectively equipped with negative pressure device.
Other feature and advantage of the disclosure will be described in detail in subsequent specific embodiment part.
Description of the drawings
Accompanying drawing is, for providing further understanding of the disclosure, and to constitute the part of description, with following tool
Body embodiment is used to explain the disclosure together, but does not constitute restriction of this disclosure.In the accompanying drawings：
Fig. 1 is a kind of structural representation of the negative pressure device of the embodiment according to the disclosure；
Fig. 2 is the generalized section of Fig. 1；
Fig. 3 is a kind of scheme of installation of the negative pressure device of the embodiment according to the disclosure；
Fig. 4 is the schematic diagram that the negative pressure device of Fig. 3 bears hydraulic pressure load；
Fig. 5 is a kind of scheme of installation of the aircraft door of the embodiment according to the disclosure.
Description of reference numerals
The gathering sill of 1 negative pressure device, 2 directive wheel, 3 bearing 4
The bolt of 5 sleeve, 6 back-up ring, 7 fixed seat 8
Specific embodiment
It is described in detail below in conjunction with accompanying drawing specific embodiment of this disclosure.It should be appreciated that this place is retouched
The specific embodiment stated is merely to illustrate and explains the disclosure, is not limited to the disclosure.
As shown in Figure 1-2, according to an aspect of this disclosure, there is provided a kind of ditching aircraft door negative pressure device,
The negative pressure device 1 includes directive wheel 2, bearing 3, gathering sill 4；The directive wheel 2 is made up of main part and smooth bar part, described
Main part and smooth bar part are hollow cylindrical structure；The long rod structure of perforate centered on the bearing 3, the guiding
The smooth bar part of wheel 2 inserts one end of the bearing 3, and passes through the directive wheel 2 simultaneously from the main part end by bolt 8
Continue to penetrate bearing 3 and be fixed；The outside of the bearing 3 is provided with fixed seat 7, and the other end of the bearing 3 passes through hatch door side
Frame and the longeron connection adjacent with frame, and the bearing 3 is fixed on hatch door frame by the fixed seat 7；It is described to lead
To groove 4 on hatch door mouth frame, and guiding is coordinated by the main part with the directive wheel 2.
Wherein, the diameter of the main part of the directive wheel 2 is determined by the magnitude of load that the directive wheel 2 is born
Fixed, the load needs in addition to the load born, also including hydraulic pressure load when as guiding mechanism.
Outside between the main part and smooth bar part of the directive wheel 2 of the disclosure is additionally provided with back-up ring 6, and main part can be with
The outside of the bearing 3 is fastened on by the back-up ring 6；
It should be noted that in order to strengthen the load support that hydraulic pressure brings, the length of the smooth bar part of directive wheel 2 can be with
Tested by negative pressure load or calculated and obtain minimum threshold, and taking in practical application makes the length of smooth bar part be more than this
Threshold value.
The bearing 3 of the disclosure is specifically as follows the cylinder long rod structure of center drilling；
Wherein, centre bore can be through hole, after smooth bar part of the bolt 8 through directive wheel 2, by the center of bearing 3
Hole nuts and bolt 8 coordinates, and is fixed with bearing 3 so as to be directed to wheel 2；The centre bore of bearing 3 is designed as into through hole
This mode, connection is difficult to loosen, and fixed effect is more preferable.
In an embodiment of the present embodiment, the directive wheel 2 also includes sleeve 5, and the sleeve 5 is set in described
Main part simultaneously coordinates with its gap, so as to sleeve 5 can be rolled on the body portion, be led coordinating with the gathering sill 4
Xiang Shi, can be reduced and the friction between gathering sill 4.
Certainly, when directive wheel 2 is provided with sleeve 5, sleeve 5 is also it is fastened in main part by back-up ring 6；
Meanwhile, between sleeve 5 and back-up ring 6, the bushing that cross-section structure is L shape is also provided with, to reduce sleeve 5 and directive wheel 2
Between friction
In the present embodiment another embodiment, to undertake ditching load, the cell body outside of the gathering sill 4 is also
Reinforcement can be provided with；
It should be noted that because gathering sill 4 needs to accommodate directive wheel 2, the cell body of gathering sill 4 is the sky with certain depth
Cavity configuration, when cell body 4 is when laterally bearing hydraulic pressure load, in order to increase intensity, spreads hydraulic pressure load, can be in the outside of cell body
Main Impact direction on multiple reinforcements are set；It is the track lifted by hatch door as the shape configurations of the cell body of gathering sill 4
Determine, and it is the characteristics of the design phase is according to hatch door, the factor design such as configuration, lifting scheme to lift track, that is to say, that
The lifting track of different hatch doors is different, therefore the shape configurations of the cell body of gathering sill 4 are also what is be not quite similar, and the disclosure is simultaneously
Specifically do not limit.
The aircraft door of the disclosure, as shown in figure 3, due to the effect of hydraulic pressure, gathering sill has one to directive wheel laterally
Pressure, the disclosure increases the length of smooth bar part and bearing by changing the structure of original type leading wheel framework, by it
It is designed to be able to bear the device of negative pressure load, hence it is evident that increase the ability that directive wheel bears lateral pressure, while can also rise
To guide function, manufacturing cost is saved；Meanwhile, the safety of hatch door is higher during half blocking, is door design conventional at present
Mode, but weightening design is had proved to be, how loss of weight is following needs is further excavated, and the technical scheme of the disclosure,
Cabin door structure is simplified, the effect for mitigating construction weight has been reached.
According to another aspect of the present disclosure, there is provided a kind of aircraft, the hatch door of the aircraft is provided with ditching negative pressure
Device 1.As shown in figure 5, being respectively equipped with negative pressure device 1 in the upper left of the aircraft door, lower-left, upper right, lower right-most portion.
The preferred implementation of the disclosure is described in detail above in association with accompanying drawing, but, the disclosure is not limited to above-mentioned reality
The detail in mode is applied, in the range of the technology design of the disclosure, various letters can be carried out with technical scheme of this disclosure
Monotropic type, these simple variants belong to the protection domain of the disclosure.
It is further to note that each particular technique feature described in above-mentioned specific embodiment, in not lance
In the case of shield, can be combined by any suitable means.In order to avoid unnecessary repetition, the disclosure to it is various can
The compound mode of energy is no longer separately illustrated.
Additionally, combination in any can also be carried out between a variety of embodiments of the disclosure, as long as it is without prejudice to this
Disclosed thought, it should equally be considered as disclosure disclosure of that.
Claims (10)
1. a kind of ditching aircraft door negative pressure device, it is characterised in that the negative pressure device (1) including directive wheel (2),
Bearing (3), gathering sill (4)；The directive wheel (2) is made up of main part and smooth bar part, the main part and light bar portion
Divide and be hollow cylindrical structure；The long rod structure of perforate centered on the bearing (3), the light bar portion of the directive wheel (2)
Divide one end of the insertion bearing (3), and by bolt (8) from the main part end is through the directive wheel (2) and continues
Penetrate bearing (3) to be fixed；Fixed seat (7) is provided with the outside of the bearing (3), the other end of the bearing (3) passes through cabin
Doorjamb and the longeron connection adjacent with frame, and the bearing (3) is fixed on by hatch door frame by the fixed seat (7)
On；The gathering sill (4) coordinates guiding on hatch door mouth frame by the main part with the directive wheel (2).
2. negative pressure device according to claim 1, it is characterised in that the diameter of directive wheel (2) main part
The magnitude of load born by the directive wheel (2) is determined.
3. negative pressure device according to claim 1 and 2, it is characterised in that the length of directive wheel (2) smooth bar part is big
In given threshold.
4. negative pressure device according to claim 1 and 2, it is characterised in that directive wheel (2) main part and light bar portion
/ outside be provided with back-up ring (6), it is outside that the main part is fastened on the bearing (3) by the back-up ring (6).
5. negative pressure device according to claim 4, it is characterised in that the directive wheel (2) also includes sleeve (5), described
Sleeve (5) is set in the main part and coordinates with its gap, and the sleeve (5) is fastened on described by the back-up ring (6)
In main part.
6. negative pressure device according to claim 5, it is characterised in that between the sleeve (5) and the back-up ring (6),
It is additionally provided with bushing.
7. negative pressure device according to claim 1, it is characterised in that the cylinder of perforate is long centered on the bearing (3)
Bar structure.
8. negative pressure device according to claim 1, it is characterised in that the cell body outside of the gathering sill (4) is provided with reinforcement
Muscle.
9. a kind of aircraft, it is characterised in that include the negative pressure dress described in any one of claim 1-8 on the aircraft door
Put (1).
10. aircraft according to claim 9, it is characterised in that the upper left of the aircraft door, lower-left, upper right, the right side
Lower part is respectively equipped with negative pressure device (1).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710008962.5A CN106672200A (en) | 2017-01-06 | 2017-01-06 | Airplane cabin door negative pressure device for water landing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710008962.5A CN106672200A (en) | 2017-01-06 | 2017-01-06 | Airplane cabin door negative pressure device for water landing |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN106672200A true CN106672200A (en) | 2017-05-17 |
Family
ID=58849165
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710008962.5A Withdrawn CN106672200A (en) | 2017-01-06 | 2017-01-06 | Airplane cabin door negative pressure device for water landing |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106672200A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2020178283A1 (en) * | 2019-03-06 | 2020-09-10 | Latecoere | Aircraft pressurised cabin door with internal force-absorbing frame |
| CN113859545A (en) * | 2021-10-18 | 2021-12-31 | 中航通飞华南飞机工业有限公司 | Fire-extinguishing type airplane water-feeding cabin door |
| EP4296157A1 (en) * | 2022-06-21 | 2023-12-27 | Airbus Operations | Aircraft comprising a fuselage and a panel removably secured to the fuselage using attachment means |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4473201A (en) * | 1982-10-29 | 1984-09-25 | The Boeing Company | Canopy-type aircraft cargo door and actuating mechanisms |
| CN204998747U (en) * | 2015-07-30 | 2016-01-27 | 中航沈飞民用飞机有限责任公司 | Partly block up formula passenger plane hatch door guiding axle with door bolt function |
| CN204998746U (en) * | 2015-07-30 | 2016-01-27 | 中航沈飞民用飞机有限责任公司 | Civil aircraft partly blocks up formula hatch door guide way |
| CN105667757A (en) * | 2016-04-05 | 2016-06-15 | 中航沈飞民用飞机有限责任公司 | Double-bent-section and semi-blocking type cargo space door of civil airplane |
| CN206954487U (en) * | 2017-01-06 | 2018-02-02 | 江苏美龙振华科技有限公司 | A kind of ditching aircraft door negative pressure device and aircraft |
-
2017
- 2017-01-06 CN CN201710008962.5A patent/CN106672200A/en not_active Withdrawn
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4473201A (en) * | 1982-10-29 | 1984-09-25 | The Boeing Company | Canopy-type aircraft cargo door and actuating mechanisms |
| CN204998747U (en) * | 2015-07-30 | 2016-01-27 | 中航沈飞民用飞机有限责任公司 | Partly block up formula passenger plane hatch door guiding axle with door bolt function |
| CN204998746U (en) * | 2015-07-30 | 2016-01-27 | 中航沈飞民用飞机有限责任公司 | Civil aircraft partly blocks up formula hatch door guide way |
| CN105667757A (en) * | 2016-04-05 | 2016-06-15 | 中航沈飞民用飞机有限责任公司 | Double-bent-section and semi-blocking type cargo space door of civil airplane |
| CN206954487U (en) * | 2017-01-06 | 2018-02-02 | 江苏美龙振华科技有限公司 | A kind of ditching aircraft door negative pressure device and aircraft |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2020178283A1 (en) * | 2019-03-06 | 2020-09-10 | Latecoere | Aircraft pressurised cabin door with internal force-absorbing frame |
| FR3093500A1 (en) * | 2019-03-06 | 2020-09-11 | Latecoere | PRESSURIZED AIRCRAFT CAR DOOR WITH INTERIOR REBUILDING FRAME |
| US11753139B2 (en) | 2019-03-06 | 2023-09-12 | Latecoere | Aircraft pressurised cabin door with internal force-absorbing frame |
| CN113859545A (en) * | 2021-10-18 | 2021-12-31 | 中航通飞华南飞机工业有限公司 | Fire-extinguishing type airplane water-feeding cabin door |
| EP4296157A1 (en) * | 2022-06-21 | 2023-12-27 | Airbus Operations | Aircraft comprising a fuselage and a panel removably secured to the fuselage using attachment means |
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| 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 | ||
| WW01 | Invention patent application withdrawn after publication |
Application publication date: 20170517 |
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| WW01 | Invention patent application withdrawn after publication |