CN102501966B - Spoiler for aircraft cabin door and aircraft cabin door provided with same - Google Patents
Spoiler for aircraft cabin door and aircraft cabin door provided with same Download PDFInfo
- Publication number
- CN102501966B CN102501966B CN201110348772.0A CN201110348772A CN102501966B CN 102501966 B CN102501966 B CN 102501966B CN 201110348772 A CN201110348772 A CN 201110348772A CN 102501966 B CN102501966 B CN 102501966B
- Authority
- CN
- China
- Prior art keywords
- spoiler
- door
- hatch door
- aircraft
- inside panel
- 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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Links
- 238000012423 maintenance Methods 0.000 claims abstract description 20
- 238000004026 adhesive bonding Methods 0.000 claims description 4
- 238000009434 installation Methods 0.000 abstract description 9
- 230000007246 mechanism Effects 0.000 abstract description 5
- 230000008859 change Effects 0.000 abstract description 3
- 238000000034 method Methods 0.000 description 4
- 230000008569 process Effects 0.000 description 4
- 230000006872 improvement Effects 0.000 description 2
- 230000003068 static effect Effects 0.000 description 2
- 238000010586 diagram Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000005484 gravity Effects 0.000 description 1
- 230000003993 interaction Effects 0.000 description 1
- 238000000465 moulding Methods 0.000 description 1
- 230000002093 peripheral effect Effects 0.000 description 1
- 230000009467 reduction Effects 0.000 description 1
- 238000004088 simulation Methods 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C7/00—Structures or fairings not otherwise provided for
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/02—Undercarriages
- B64C25/08—Undercarriages non-fixed, e.g. jettisonable
- B64C25/10—Undercarriages non-fixed, e.g. jettisonable retractable, foldable, or the like
- B64C25/16—Fairings movable in conjunction with undercarriage elements
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Specific Sealing Or Ventilating Devices For Doors And Windows (AREA)
Abstract
The invention provides a spoiler for an aircraft door, which is arranged on an inner skin of the door on the inner side of the windward front edge of a left front door and a right front door of a front undercarriage of an aircraft, is tightly attached to the inner skin of the door and is used for reducing the door opening force of the door. The invention also provides an aircraft door, and the spoiler for the aircraft door is arranged on the inner skin of the aircraft door. According to the spoiler disclosed by the invention, the door opening force of the cabin door can be effectively reduced; and the change to the original mechanism is small, and the installation and the maintenance are convenient.
Description
Technical field
The present invention relates to a kind of part on aircraft door, particularly relate to a kind of spoiler for aircraft door and the aircraft door of this spoiler is housed.
Background technology
In the design of aircraft nose landing gear extension and retraction system, its frontal resistance and gravity are obvious load factors, stop in receipts because it often helps to put down, the emphasis of analysis and designation work is always concentrated on and receives upper but not put down process, some type nose-gear can be caused to occur unexpected situation putting down in process.The node configuration that before this kind of alighting gear is mainly, a hatch door and column link, does not have front independent hatch door actuating device, and this configuration is complicated, but controls simple, does not need independent front door control system.Owing to being interaction relation, during mechanism design, interfere putting down in process for avoiding hatch door and front wheel, hatch door must be opened fast, quick closedown after nose-gear puts down and puts in place, cause start to put down and finally put down lock time, the load on hatch door has very large sensivity to front folding and unfolding performance.
In flight course, as long as hatch door is not closely closed, conventional hatch door moulding is by generation enabling aerodynamic force, put down the initial stage, this aerodynamic force helps to put down, but is putting down the stage of locking, rise before this load stops and lock, the folding and unfolding performance risen before having a strong impact on, rise to put down before even making and lock.For this kind of situation, there is following several design plan: 1. improve Landing Gear System folding and unfolding connecting rod mechanism; 2. change hatch door size and 3. increase the schemes such as hydraulic booster.By simulation analysis, such scheme is changed comparatively large to original mechanism, realize complicated; And by hatch door space constraint, all there is certain difficulty in installation, maintenance, assembling.
Summary of the invention
The present invention devises a kind of spoiler reducing hatch door enabling power, and this kind of spoiler can reduce the enabling power of hatch door effectively; And change less to original mechanism, convenient installation and maintenance.
According to an aspect of the present invention, each increase a slice spoiler inside the leading edge windward of front front door both sides, be arranged on hatch door inside panel, fit tightly with hatch door inside panel, reduction enabling aerodynamic force that just can be larger, that rises before improving puts down performance of locking.
Advantageously, the width of spoiler is identical with thickness with the width of hatch door inside panel with thickness, spoiler has the recess adapted with maintenance lid shape in the side of the maintenance lid on hatch door inside panel, to reserve the installing space of hatch door maintenance lid and to ensure enough installation strength, hatch door inside panel is extended at the opposite side away from maintenance lid, such as, about 10mm is extended.
Advantageously, spoiler adopts the material identical with hatch door inside panel.Advantageously, according to the speed of aircraft, by the mode of glueing joint or rivet, it is connected with hatch door inside panel, and ensures that spoiler and hatch door inside panel fit tightly.In addition, should be understood that, spoiler installation site otherwise affect the function of other annexes of hatch door.The size of spoiler need adjust according to the size of hatch door.
According to another aspect of the present invention, provide a kind of aircraft door, the inside panel of described aircraft door inside the leading edge windward of nose-gear left and right front door is separately installed with spoiler of the present invention.
If gear down had problems, adopt aircraft door spoiler of the present invention, can improve and normally put down more than speed 10 joint, successful.The present invention can be applied to the aircraft of all similar configuration, solve aircraft front normally put down, even emergency extension is locked time speed restriction, have simple, the feature of successful.
Accompanying drawing explanation
Fig. 1 is the schematic diagram of the spoiler according to one embodiment of the present invention;
The installation site figure that Fig. 2 is the spoiler shown in Fig. 1.
Detailed description of the invention
The description of the preferred embodiments of the invention is provided below herein with reference to the accompanying drawings in detail.
Fig. 1 shows the structural representation of the spoiler in one embodiment of the present invention.Spoiler 1 adopts the material (as 7075-O) identical with hatch door inside panel 4.The width of spoiler 1 is substantially identical with thickness with the width of hatch door inside panel 4 with thickness.For ensureing Joint strenght, spoiler 1 has the recess adapted with maintenance lid 2 shape in the side of the maintenance lid 2 on hatch door inside panel 4, to reserve the installing space of maintenance lid, in the present embodiment, recess, for opening wide opening shape, is looped around on the part peripheral of maintenance lid 2.Be understandable that, in other embodiment, recess can be also closed opening form, makes it be looped around the whole outer of maintenance lid 2 and places.Spoiler 1 extends hatch door inside panel 4 slightly at the opposite side away from maintenance lid 2, and such as, in the present embodiment, spoiler 1 extends hatch door inside panel 4 about 10mm.In addition, should be understood that, the installation site of spoiler 1 on hatch door inside panel 4 otherwise affect the function of other annexes of hatch door, as in switch gate process, and the gap etc. between body doorframe, its concrete installation site is relevant with arranging of the attaching partss such as rivet.For the determination of the size of spoiler 1, need adjust according to the size of hatch door.
Fig. 2 further illustrates the scheme of installation of spoiler 1 on aircraft door.Spoiler 1 is arranged on hatch door inside panel 4, by glueing joint or riveting or other connection mode, fits tightly with hatch door inside panel 4.
The present invention increases spoiler 1 pair of hatch door local air flow and carries out disturbance on hatch door, under the prerequisite not eliminating hatch door exterior skin 3 local static pressure (enabling power), produce new local static pressure (door closing force), by the counteracting of two power, effectively reduce total enabling power, improve the ability that nose-gear puts down, eliminate the important measures that speed that is normal and emergency extension limits, all aircraft with comparable conformation can be effectively applied to, because this achievement is implemented simple, successful, large configuration amendment can not be brought, the long lead time, high development cost.
Be described in further detail invention has been by specific embodiment above, but be not limited only to these embodiments, without departing from the inventive concept of the premise, other embodiments of more evolutions or improvement can also be had, and these changes and improvements all belong to scope of the present invention.
Claims (7)
1. the spoiler for aircraft door, it is characterized in that, described spoiler (1) is arranged on hatch door inside panel (4) inside the leading edge windward of aircraft nose landing gear left and right front door, fit tightly with described hatch door inside panel (4), for reducing hatch door enabling power, the width of described spoiler (1) is identical with described hatch door inside panel (4) with thickness, described spoiler (1) has in the side of the maintenance lid (2) on described hatch door inside panel (4) recess adapted with described maintenance lid (2) shape, described hatch door inside panel (4) is extended at the opposite side away from described maintenance lid (2).
2. the spoiler for aircraft door according to claim 1, is characterized in that, described spoiler (1) extends described hatch door inside panel (4) 10mm at the opposite side away from described maintenance lid (2).
3. the spoiler for aircraft door according to claim 1 and 2, is characterized in that, described spoiler (1) adopts the material identical with described hatch door inside panel (4).
4. the spoiler for aircraft door according to claim 1 and 2, is characterized in that, described spoiler (1) is connected with described hatch door inside panel (4) by the mode of glueing joint or rivet.
5. an aircraft door, is characterized in that, the inside panel of described aircraft door inside the leading edge windward of nose-gear left and right front door is separately installed with the spoiler for aircraft door as described in one of claim 1-4.
6. aircraft door as claimed in claim 5, is characterized in that, described spoiler (1) is fitted tightly by the mode of glueing joint or rivet and described hatch door inside panel (4).
7. the aircraft door as described in claim 5 or 6, it is characterized in that, described spoiler (1) has in the side of the maintenance lid (2) on described hatch door inside panel (4) recess adapted with described maintenance lid (2) shape, extends described hatch door inside panel (4) at the opposite side away from described maintenance lid (2).
Priority Applications (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201110348772.0A CN102501966B (en) | 2011-11-07 | 2011-11-07 | Spoiler for aircraft cabin door and aircraft cabin door provided with same |
| PCT/CN2012/083355 WO2013067885A1 (en) | 2011-11-07 | 2012-10-23 | Spoiler for hatch door on aeroplane and hatch door on aeroplane having same |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201110348772.0A CN102501966B (en) | 2011-11-07 | 2011-11-07 | Spoiler for aircraft cabin door and aircraft cabin door provided with same |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN102501966A CN102501966A (en) | 2012-06-20 |
| CN102501966B true CN102501966B (en) | 2016-04-13 |
Family
ID=46214121
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201110348772.0A Active CN102501966B (en) | 2011-11-07 | 2011-11-07 | Spoiler for aircraft cabin door and aircraft cabin door provided with same |
Country Status (2)
| Country | Link |
|---|---|
| CN (1) | CN102501966B (en) |
| WO (1) | WO2013067885A1 (en) |
Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102501966B (en) * | 2011-11-07 | 2016-04-13 | 中国商用飞机有限责任公司 | Spoiler for aircraft cabin door and aircraft cabin door provided with same |
| CN112478129B (en) * | 2020-12-04 | 2023-02-28 | 中国航空工业集团公司沈阳飞机设计研究所 | Aircraft delivery cabin door |
| CN113511329B (en) * | 2021-05-12 | 2022-12-13 | 上海机电工程研究所 | Appearance gradual change formula horizontal whole separation radome fairing and aircraft |
| CN116147880B (en) * | 2023-04-23 | 2023-06-27 | 中国空气动力研究与发展中心高速空气动力研究所 | Cabin door and turbulence combined control mechanism for wind tunnel test |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6739554B1 (en) * | 2003-06-02 | 2004-05-25 | The United States Of America As Represented By The Secretary Of The Air Force | Aircraft weapons bay acoustic resonance suppression system |
| CN101018708A (en) * | 2004-08-03 | 2007-08-15 | 空中客车公司 | Door for closing an opening inside an aircraft |
Family Cites Families (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2880614B1 (en) * | 2005-01-07 | 2007-02-23 | Latecoere Sa | IMPROVEMENT AT THE DOORS OF AIRCRAFT CABINS |
| FR2927686B1 (en) * | 2008-02-20 | 2010-10-08 | Eads Socata | MONOLITHIC COMPOSITE PANEL SELF-RAIDI AND SWIVEL, IN PARTICULAR FOR A MOBILE AIRCRAFT PART. |
| GB0812542D0 (en) * | 2008-07-09 | 2008-08-13 | Airbus Uk Ltd | Landing gear noise reduction assembley |
| GB0814291D0 (en) * | 2008-08-05 | 2008-09-10 | Airbus Uk Ltd | Landing gear with noise reduction fairing |
| CN102501966B (en) * | 2011-11-07 | 2016-04-13 | 中国商用飞机有限责任公司 | Spoiler for aircraft cabin door and aircraft cabin door provided with same |
-
2011
- 2011-11-07 CN CN201110348772.0A patent/CN102501966B/en active Active
-
2012
- 2012-10-23 WO PCT/CN2012/083355 patent/WO2013067885A1/en active Application Filing
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6739554B1 (en) * | 2003-06-02 | 2004-05-25 | The United States Of America As Represented By The Secretary Of The Air Force | Aircraft weapons bay acoustic resonance suppression system |
| CN101018708A (en) * | 2004-08-03 | 2007-08-15 | 空中客车公司 | Door for closing an opening inside an aircraft |
Also Published As
| Publication number | Publication date |
|---|---|
| CN102501966A (en) | 2012-06-20 |
| WO2013067885A1 (en) | 2013-05-16 |
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| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant |