CN109229331A - A kind of light-duty lid for aircaft configuration - Google Patents
A kind of light-duty lid for aircaft configuration Download PDFInfo
- Publication number
- CN109229331A CN109229331A CN201811008941.4A CN201811008941A CN109229331A CN 109229331 A CN109229331 A CN 109229331A CN 201811008941 A CN201811008941 A CN 201811008941A CN 109229331 A CN109229331 A CN 109229331A
- Authority
- CN
- China
- Prior art keywords
- light
- lid
- duty
- covering
- reinforcement structure
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Underground Structures, Protecting, Testing And Restoring Foundations (AREA)
Abstract
The invention belongs to airplane structural design technologies, are related to a kind of light-duty lid for aircaft configuration.The present invention includes covering (1) and reinforcement structure (4), and the reinforcement structure (4) is closed-loop frame made of the riveting of Z-shaped angle section；The Z-shaped angle section and covering are aluminum alloy materials；It is splicing between the reinforcement structure (4) and covering (1).Good rigidity of the present invention, it is light-weight, it is at low cost.
Description
Technical field
The invention belongs to airplane structural design technologies, are related to a kind of light-duty lid for aircaft configuration.
Background technique
Aircraft is since the needs installing, safeguard are provided with many lids, wherein have much using single-layer skins lid,
There are also reinforcement structures such as pressure stalk, angle sections inside the lid of part, this port cover structure is simple, light weight and cost is low, but structure is rigid
It is poor to spend, and is generally not suitable for in large-scale lid.Many large size lids use the composite material lid with honeycomb interlayer, this
It is kind of lid good rigidity, light-weight, it is at high cost but structure is complicated.
It is required according to the maintainability of model, needs large-scale maintenance lid in engine compartment two sides, size 835mm ×
430mm, lid are required to bear 204 DEG C of high temperature.
Single-layer skins formula lid poor rigidity is easily-deformable, and lid cost made of high temperature resistant composite is too high, needs again
Design a kind of light, high temperature resistant, maintenance lid at low cost.
Summary of the invention
The object of the present invention is to provide a kind of high temperature resistant for aircaft configuration and light-duty lids at low cost.
The technical scheme is that a kind of light-duty lid for aircaft configuration, including covering 1 and reinforcement structure 4, institute
Stating reinforcement structure 4 is closed-loop frame made of the riveting of Z-shaped angle section；The Z-shaped angle section and covering are aluminum alloy materials；It is described to add
It is splicing between strong structure 4 and covering 1.
Further, the light-duty lid further includes N item in the middle part of the reinforcement structure perpendicular to reinforcement structure length side
To Z-shaped reinforcer 5, covering is separated into the individual regions N+1 by the Z-shaped reinforcer 5.Wherein, N is natural number.The Z
Shape reinforcer is Z-shaped angle section.
Further, the shape of the light-duty lid is rectangle.
Further, further, the Z-shaped reinforcer 5 is two.
Further, the light-duty lid further includes hinge 2.
Further, the light-duty lid further includes strut 3.
The invention has the advantages that one, good rigidity, the moment of inertia of covering arbitrary section is noticeably greater than various forms of reinforcements and covers
The ability of skin lid, resistance to deformation is stronger.Two, light-weight.Due to using more reasonable strengthening form, the illiteracy selected
Skin, reinforcer are very thin, and angle stiffener exists only in part critical positions, therefore the weight of lid has obtained effective control
System.Three, at low cost.What lid was selected is general aviation aluminium alloy, does not select the high low cost materials such as high temperature resistant composite, is made
Making method has mature processing technology, and expense is low.
Detailed description of the invention
Fig. 1 is the light-duty port cover structure schematic diagram of the present invention；
Fig. 2 is the sectional view of the light-duty lid of the present invention along its length；
Wherein, wherein 1- covering, 2- hinge, 3- strut, 4- reinforcement structure, 5-Z shape reinforcer.
Specific embodiment
A specific embodiment of the invention is described further below with reference to specific attached drawing.
Referring to Fig. 1, Fig. 2, the reinforcement structure 4 inside lid covering is the closed-loop frame being made of Z-shaped angle section, and ring frame is deposited
The raising of matter is obtained in the arbitrary section the moment of inertia for making entire lid, therefore can be using the aluminum alloy thin of only 0.635mm thickness
Plate is as the aluminium alloy angle section of covering 1 and same 0.635mm as reinforcement structure 4.By taking the section in bead cover length direction as an example,
The sectional area for the lid reinforced through Z bar, it is smaller by 31% than the plate lid sectional area using 1.27mm, and the moment of inertia increases
49 times.Since reinforcement structure 4 is very close to 1 edge of lid covering, the rigidity at lid edge can be effectively improved.To sum up,
Lid has the characteristics that light-weight good rigidity.
In addition to the Z-shaped angle section of border, there are also two Z-shaped reinforcers 5 at middle part, and lid covering is divided into 3 individual regions,
The part that entire lid removes strut is similar to the Chinese character " mesh " being rotated by 90 °, and covering caused by aerodynamic loading can be greatly reduced
The arm of force of shearing flow.
Since the frame of lid needs and fixed structure sealing or connect, and lid thickness is very thin unsuitable plays countersunk head riveting
Nail, so to be glued between the angle stiffener and covering of lid, and still using riveting between angle stiffener.
Strut 3 is installed in lid, strut 3 is supported into designated position when lid is opened, lid is in always and beats
Open state.One end of strut is fixed in reinforcement structure 4, it can be achieved that the rotation of two freedom degrees, the other end are mounted on Z-shaped reinforcement
It is openable on the spring clip of part.
The light-duty lid told about herein is applied to the on both sides of the middle of Y12F type machine enging cabin.Lid fixing end passes through hinge
It is connect with enging cabin fixed structure, movable end is connect by latch mechanism with fixed structure when lid is closed, when lid is opened
When strut is taken out and supports to enging cabin designated position.The size of lid is big, good rigidity is unlikely to deform, switchs and consolidates
It is fixed convenient, model has been fully met to the needs in terms of maintainability.
Claims (6)
1. a kind of light-duty lid for aircaft configuration, it is characterized in that: the light-duty lid includes covering (1) and reinforcement structure
(4), the reinforcement structure (4) is closed-loop frame made of the riveting of Z-shaped angle section；The Z-shaped angle section and covering are aluminium alloy material
Material；It is splicing between the reinforcement structure (4) and covering (1).
2. light-duty lid according to claim 1, it is characterized in that: the light-duty lid further includes being located in the middle part of reinforcement structure
N item perpendicular to reinforcement structure length direction Z-shaped reinforcer (5), the Z-shaped reinforcer (5) by covering be separated into N+1 it is single
Only region；Wherein, N is natural number；The Z-shaped reinforcer is Z-shaped angle section.
3. light-duty lid according to claim 1, it is characterized in that: the shape of the light-duty lid is rectangle.
4. light-duty lid according to claim 2, it is characterized in that: the Z-shaped reinforcer (5) is two.
5. light-duty lid according to claim 1, it is characterized in that: the light-duty lid further includes hinge (2).
6. light-duty lid according to claim 1, it is characterized in that: the light-duty lid further includes strut (3).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811008941.4A CN109229331A (en) | 2018-08-30 | 2018-08-30 | A kind of light-duty lid for aircaft configuration |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811008941.4A CN109229331A (en) | 2018-08-30 | 2018-08-30 | A kind of light-duty lid for aircaft configuration |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN109229331A true CN109229331A (en) | 2019-01-18 |
Family
ID=65069500
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811008941.4A Withdrawn CN109229331A (en) | 2018-08-30 | 2018-08-30 | A kind of light-duty lid for aircaft configuration |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109229331A (en) |
Cited By (1)
| 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 |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN203547321U (en) * | 2013-08-23 | 2014-04-16 | 中国航空工业集团公司西安飞机设计研究所 | Bracing rod |
| CN204775983U (en) * | 2015-06-19 | 2015-11-18 | 中国航空工业集团公司西安飞机设计研究所 | Light aerocraft covering opening reinforcing plate |
| CN205203405U (en) * | 2015-12-09 | 2016-05-04 | 中国航空工业集团公司沈阳飞机设计研究所 | Airborne gravity oiling flap subassembly and have its aircraft tank |
| CN205203354U (en) * | 2015-12-01 | 2016-05-04 | 中国航空工业集团公司沈阳飞机设计研究所 | High temperature resistant combined material flap |
| CN108238262A (en) * | 2017-12-08 | 2018-07-03 | 西安飞机工业（集团）有限责任公司 | A kind of sealing structure of nacelle of airplane lid |
-
2018
- 2018-08-30 CN CN201811008941.4A patent/CN109229331A/en not_active Withdrawn
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN203547321U (en) * | 2013-08-23 | 2014-04-16 | 中国航空工业集团公司西安飞机设计研究所 | Bracing rod |
| CN204775983U (en) * | 2015-06-19 | 2015-11-18 | 中国航空工业集团公司西安飞机设计研究所 | Light aerocraft covering opening reinforcing plate |
| CN205203354U (en) * | 2015-12-01 | 2016-05-04 | 中国航空工业集团公司沈阳飞机设计研究所 | High temperature resistant combined material flap |
| CN205203405U (en) * | 2015-12-09 | 2016-05-04 | 中国航空工业集团公司沈阳飞机设计研究所 | Airborne gravity oiling flap subassembly and have its aircraft tank |
| CN108238262A (en) * | 2017-12-08 | 2018-07-03 | 西安飞机工业（集团）有限责任公司 | A kind of sealing structure of nacelle of airplane lid |
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 |
| 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 |
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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 | ||
| WW01 | Invention patent application withdrawn after publication | ||
| WW01 | Invention patent application withdrawn after publication |
Application publication date: 20190118 |