CN112478129B - Aircraft delivery cabin door - Google Patents
Aircraft delivery cabin door Download PDFInfo
- Publication number
- CN112478129B CN112478129B CN202011402266.0A CN202011402266A CN112478129B CN 112478129 B CN112478129 B CN 112478129B CN 202011402266 A CN202011402266 A CN 202011402266A CN 112478129 B CN112478129 B CN 112478129B
- Authority
- CN
- China
- Prior art keywords
- cabin door
- aircraft
- door
- front edge
- cabin
- 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.)
- Active
Links
Images
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
-
- 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
- B64C1/1415—Cargo doors, e.g. incorporating ramps
Abstract
The application belongs to the aircraft hatch door field, in particular to aircraft release hatch door. The cross section of the front edge of the aircraft launching cabin door is a curved surface. The aircraft launching cabin door changes the design of the straight edge right angle of the existing cabin door, and utilizes the curve and the curved surface to replace the design scheme of the inner side of the cabin door, thereby changing and optimizing the pressure distribution of the cabin door, and avoiding the phenomenon that the pressure change is overlarge when the curvature of the front edge part of the cabin door changes suddenly and the load of the front edge part of the cabin door is changed. The application can improve the overall stress state of the cabin door, can lighten the strength of devices such as the cabin door and the like, thereby reducing the weight of the airplane, and has the advantages of light weight, small occupied space and the like.
Description
Technical Field
The application belongs to the aircraft hatch door field, in particular to aircraft release hatch door.
Background
With the progress and development of passenger aircraft, the demand of society for aircrafts is increasing, and the demand for aircrafts is also increasing. The air drop capability of the aircraft is one of the capabilities, the opening of the cabin door is an important link, the design of the cabin door can directly affect the local stress state of the cabin door, and therefore the rigidity and strength design problems of the cabin door are affected, at present, the layout form of the cabin door in the prior art is shown in figures 1 to 2, the stress of the layout of the cabin door in the form is overlarge, the corresponding rigidity strength needs to be increased, and the weight of the aircraft can be increased.
Accordingly, a technical solution is desired to overcome or at least alleviate at least one of the above-mentioned drawbacks of the prior art.
Disclosure of Invention
It is an object of the present application to provide an aircraft launch door to solve at least one problem of the prior art.
The technical scheme of the application is as follows:
an aircraft launch door comprising:
the cross section of the front edge of the aircraft launching cabin door is a curved surface;
if the aircraft launching cabin door is a subsonic aircraft launching cabin door, the curved surface equation of the front edge cross section of the aircraft launching cabin door is as follows:
wherein d is the thickness of the cabin door, L is the length of the transition area of the front edge part of the cabin door, x is the transverse direction of the cabin door, y is the thickness direction of the cabin door, and the original points of x and y are positioned at the front edge point of the cabin door.
Optionally, the leading edge of the aircraft launch door is serrated.
Optionally, the leading edge of the aircraft launch door is rectangular.
Optionally, the aircraft launch door is arranged in the belly of the aircraft fuselage.
Optionally, the aircraft launch door comprises an alloy steel skeleton and a carbon fiber composite skin coated outside the alloy steel skeleton.
The invention has at least the following beneficial technical effects:
the aircraft launching cabin door improves the pressure distribution of the surface of the opened cabin door, optimizes the load of the cabin door, improves the overall stress state of the cabin door, and can reduce the strength of the devices such as the cabin door and the like, thereby reducing the weight of an aircraft.
Drawings
Figure 1 is a schematic view of an aircraft launch door according to one embodiment of the prior art;
figure 2 is a schematic view of another embodiment of an aircraft launch door according to the prior art;
figure 3 is a schematic view of an aircraft launch door of an embodiment of the present application;
fig. 4 isbase:Sub>A viewbase:Sub>A-base:Sub>A of fig. 3.
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the drawings in the embodiments of the present application. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are a subset of the embodiments in the present application and not all embodiments in the present application. The embodiments described below with reference to the drawings are exemplary and intended to be used for explaining the present application and should not be construed as limiting the present application. 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 application. Embodiments of the present application will be described in detail below with reference to the accompanying drawings.
In the description of the present application, it is to be understood that the terms "center", "longitudinal", "lateral", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like indicate orientations or positional relationships based on those shown in the drawings, and are used merely for convenience in describing the present application and for simplifying the description, and do not indicate or imply that the referenced device or element must have a particular orientation, be constructed in a particular orientation, and be operated, and therefore should not be construed as limiting the scope of the present application.
The present application is described in further detail below with reference to fig. 3-4.
The application provides an aircraft launch hatch door, the leading edge cross section of aircraft launch hatch door is the curved surface.
The aircraft launching hatch door changes the design of the straight arris right angle of the existing hatch door, and utilizes the curve and the curved surface to replace the design scheme of the inner side of the hatch door, thereby changing and optimizing the pressure distribution of the hatch door, and avoiding the phenomenon that the pressure changes too much when the curvature of the front edge part of the hatch door changes suddenly and the load of the front edge part of the hatch door changes.
In one embodiment of the present application, as shown in fig. 3, the shape of the leading edge of the aircraft launch door includes, but is not limited to, a sawtooth shape. In another embodiment the leading edge of the aircraft launch door is rectangular.
According to the aircraft release cabin door, the outer surface of the cabin door is matched with the design appearance of an aircraft, and the section between the outer surface and the inner surface is designed into a curved surface. In one embodiment of the application or the aircraft launch door is a subsonic aircraft launch door, the curved profile of the cross section of the leading edge is shown in fig. 4. In this embodiment, the curved surface equation of the cross section of the leading edge of the aircraft launch door is:
wherein d is the thickness of the cabin door, L is the length of the transition area of the front edge part of the cabin door, x is the transverse direction of the cabin door, y is the thickness direction of the cabin door, and the origin points of x and y are positioned at the front edge point of the cabin door. The formula is given based on the NACA five digit series airfoil thickness distribution formula, with the cutoff at the location of maximum thickness.
The aircraft launching cabin door can be arranged on the belly of an aircraft body. In this embodiment, the preferable aircraft launch cabin door includes the alloy steel skeleton and the carbon-fiber composite skin of cladding in the alloy steel skeleton outside, satisfies the strength requirement, and the quality is light.
The aircraft launching cabin door can improve the pressure distribution of the opened surface of the cabin door, optimize the load of the cabin door, improve the overall stress state of the cabin door, and reduce the strength of devices such as the cabin door and the like, thereby reducing the weight of an aircraft, and the aircraft launching cabin door has the advantages of light weight, small occupied space and the like.
The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (5)
1. An aircraft launch door, characterized in that it comprises:
the cross section of the front edge of the aircraft launching cabin door is a curved surface;
the aircraft launching cabin door is a subsonic aircraft launching cabin door, and then the curved surface equation of the front edge cross section of the aircraft launching cabin door is as follows:
wherein d is the thickness of the cabin door, L is the length of the transition area of the front edge part of the cabin door, x is the transverse direction of the cabin door, y is the thickness direction of the cabin door, and the origin points of x and y are positioned at the front edge point of the cabin door.
2. Aircraft launch door according to claim 1, characterized in that the leading edge of the aircraft launch door is serrated.
3. Aircraft launch door according to claim 1, characterized in that the front edge of the aircraft launch door is rectangular.
4. Aircraft launch door according to claim 1, characterized in that said aircraft launch door is arranged in the belly of an aircraft fuselage.
5. Aircraft launch door according to claim 1, characterized in that it comprises an alloy steel skeleton and a carbon fiber composite skin covering the outside of the alloy steel skeleton.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011402266.0A CN112478129B (en) | 2020-12-04 | 2020-12-04 | Aircraft delivery cabin door |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011402266.0A CN112478129B (en) | 2020-12-04 | 2020-12-04 | Aircraft delivery cabin door |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN112478129A CN112478129A (en) | 2021-03-12 |
| CN112478129B true CN112478129B (en) | 2023-02-28 |
Family
ID=74939349
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202011402266.0A Active CN112478129B (en) | 2020-12-04 | 2020-12-04 | Aircraft delivery cabin door |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN112478129B (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112627663A (en) * | 2020-12-03 | 2021-04-09 | 中国航空工业集团公司沈阳飞机设计研究所 | Aircraft valve opening mechanism |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4176812A (en) * | 1977-10-31 | 1979-12-04 | The Boeing Company | Midcabin door for blended wing aircraft |
| CN102501966A (en) * | 2011-11-07 | 2012-06-20 | 中国商用飞机有限责任公司 | Spoiler for aircraft cabin door and aircraft cabin door with spoiler |
| CN203889086U (en) * | 2014-06-24 | 2014-10-22 | 中国飞机强度研究所 | Bi-direction transmitted load loading device of arc-shaped structure |
| CN108706092A (en) * | 2018-05-31 | 2018-10-26 | 中国空气动力研究与发展中心高速空气动力研究所 | A kind of zigzag flight device noise suppression device for weapon bay |
| CN208647131U (en) * | 2018-03-16 | 2019-03-26 | 陕西飞机工业（集团）有限公司 | A kind of fixed aircraft door and floor transition structure |
| CN111332454A (en) * | 2020-03-19 | 2020-06-26 | 中国航空工业集团公司沈阳飞机设计研究所 | Variable-configuration cabin door for enhancing aircraft course stability and control method thereof |
Family Cites Families (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7198062B2 (en) * | 2002-11-21 | 2007-04-03 | The Boeing Company | Fluid control valve |
| DE102015113471A1 (en) * | 2015-08-14 | 2017-02-16 | Airbus Operations Gmbh | Aircraft door arrangement with a noise-reduced, coverable by an aircraft door cavity |
| US11338900B2 (en) * | 2017-04-21 | 2022-05-24 | James M. Curry | Aircraft plug door with in-plane load transfer capacity and methods of use |
-
2020
- 2020-12-04 CN CN202011402266.0A patent/CN112478129B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4176812A (en) * | 1977-10-31 | 1979-12-04 | The Boeing Company | Midcabin door for blended wing aircraft |
| CN102501966A (en) * | 2011-11-07 | 2012-06-20 | 中国商用飞机有限责任公司 | Spoiler for aircraft cabin door and aircraft cabin door with spoiler |
| CN203889086U (en) * | 2014-06-24 | 2014-10-22 | 中国飞机强度研究所 | Bi-direction transmitted load loading device of arc-shaped structure |
| CN208647131U (en) * | 2018-03-16 | 2019-03-26 | 陕西飞机工业（集团）有限公司 | A kind of fixed aircraft door and floor transition structure |
| CN108706092A (en) * | 2018-05-31 | 2018-10-26 | 中国空气动力研究与发展中心高速空气动力研究所 | A kind of zigzag flight device noise suppression device for weapon bay |
| CN111332454A (en) * | 2020-03-19 | 2020-06-26 | 中国航空工业集团公司沈阳飞机设计研究所 | Variable-configuration cabin door for enhancing aircraft course stability and control method thereof |
Also Published As
| Publication number | Publication date |
|---|---|
| CN112478129A (en) | 2021-03-12 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN101786499B (en) | Impact resistant aircraft leading edge structures and aircraft including the same | |
| CA2634307C (en) | Aircraft wing and fuselage contours | |
| CN106167085B (en) | For airframe pressure bulkhead and include the aircraft of this pressure bulkhead | |
| US20200407039A1 (en) | Wing-to-body trailing edge fairing and method of fabricating same | |
| CN112478129B (en) | Aircraft delivery cabin door | |
| US4067518A (en) | Drag reducer for lift surface of aircraft | |
| JP2020534214A (en) | Aircraft cupola fairing and its manufacturing method | |
| US11745849B2 (en) | Aircraft portion with reduced wave drag | |
| CN101568467B (en) | Aircraft fuselage | |
| US20120193473A1 (en) | Torsion box skin stiffened with non parallel stringers | |
| US8205824B2 (en) | Aircraft fuselage structure | |
| US20040069903A1 (en) | Integrated aircraft windshields and associated methods | |
| US11584506B2 (en) | Aircraft wing assemblies | |
| CN116255559A (en) | Aircraft tank for storing cryogenic H2 and aircraft comprising such an aircraft tank | |
| RU2400402C1 (en) | Multimode high maneuverability aircraft of integral aerodynamic configuration | |
| CN211519837U (en) | Low-noise supersonic speed official business machine | |
| US11511873B2 (en) | Propulsion assembly for an aircraft, comprising a nacelle load support fastened to a pylon | |
| EP3059156B1 (en) | Flat kinked rear pressure bulkhead | |
| CN107745796B (en) | Backpack type large-scale radome double-leg | |
| DE102015111032A1 (en) | Wing assembly in boxwing configuration | |
| CN206615385U (en) | A kind of fixed-wing unmanned plane | |
| CN218317276U (en) | Integral cabin mouth frame | |
| CN210634742U (en) | Unmanned aerial vehicle | |
| EP2612811A1 (en) | A combination comprising an aircraft wing trailing edge section and an adjustment body | |
| RU2403175C2 (en) | Fuselage nose compartment |
Legal Events
| 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 | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |