CN106477021A - Aircraft cellular-type cabin balanced controls - Google Patents
Aircraft cellular-type cabin balanced controls Download PDFInfo
- Publication number
- CN106477021A CN106477021A CN201611026126.1A CN201611026126A CN106477021A CN 106477021 A CN106477021 A CN 106477021A CN 201611026126 A CN201611026126 A CN 201611026126A CN 106477021 A CN106477021 A CN 106477021A
- Authority
- CN
- China
- Prior art keywords
- housing
- nacelle
- rolling element
- balanced controls
- type 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.)
- Pending
Links
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
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Wind Motors (AREA)
- Rolling Contact Bearings (AREA)
Abstract
The invention discloses a kind of aircraft cellular-type cabin balanced controls, include housing, it is provided with nacelle in described housing, several rolling elements are distributed between the end of the end of described nacelle and described housing, the end outer wall of the described rolling element described nacelle of laminating, described rolling element is also fitted the inner wall of end of described housing, and described rolling element can carry out rotation；By arranging several rolling elements between housing and nacelle, principle using divergence type bearing, make housing in the case of run-off the straight, upset, nacelle does not rotate with housing, reaches the purpose avoiding passenger to be affected in craft inclination, switching process, avoid article to drop and ensure personal security.
Description
Technical field
The present invention relates to aircraft application field is and in particular to aircraft cellular-type cabin balanced controls.
Background technology
Present aircraft is integral type substantially entirely, and that is, housing and cabin are connected as a single entity, in aircraft flight pose adjustment
Or when being disturbed, cabin is also interfered, and adjust therewith.Now the personnel in cabin with suffered by article gravity with
Holding power is not often in same direction, and run-off the straight, the personnel in cabin and article are it may happen that move or even dangerous.
Content of the invention
For solving above-mentioned technical problem, the present invention proposes aircraft cellular-type cabin balanced controls, avoids taking advantage of to reach
The purpose that visitor is affected in craft inclination, switching process, avoids article to drop and ensure personal security.
For reaching above-mentioned purpose, technical scheme is as follows：
A kind of aircraft cellular-type cabin balanced controls, include housing, are provided with nacelle in described housing, described nacelle
Several rolling elements, the outer wall of described rolling element laminating described nacelle, described rolling are distributed between the end of end and described housing
Kinetoplast is also fitted the inner wall of end of described housing, and described rolling element can carry out rotation.
The present invention passes through to arrange several rolling elements between housing and nacelle, using the principle of divergence type bearing, makes housing
In the case of run-off the straight, upset, nacelle does not rotate with housing, reaches and avoids passenger in craft inclination, switching process
In the purpose that is affected, avoids article to drop and ensure personal security.
Separated using retainer as between preferred, adjacent rolling element.Adjacent rolling element is made to divide using retainer
Open so that rolling element can only carry out rotation, it is to avoid rolling element generation is crooked, also avoids adjacent rolling element mutually to collide, enters one
Step ensures the safety of flight.
As preferred, between described retainer and described rolling element, scribble grease.
As preferred, described housing is made using superhard aluminium.
As preferred, described rolling element is made using high-strength structure Steel material.
As preferred, described retainer is made using brass material.
As preferred, described nacelle is made using superhard aluminium.
The invention has the advantages that：
1. the present invention passes through to arrange several rolling elements between housing and nacelle, using the principle of divergence type bearing, makes shell
In the case of run-off the straight, upset, nacelle does not rotate body with housing, reaches and avoids passenger in craft inclination, is turned over
The purpose being affected in journey, avoiding article to drop and ensure personal security.
2. the present invention makes adjacent rolling element separately so that rolling element can only carry out rotation using retainer, it is to avoid roll
Body generation is crooked, also avoids adjacent rolling element mutually to collide, is further ensured that the safety of flight.
Brief description
In order to be illustrated more clearly that the embodiment of the present invention or technical scheme of the prior art, below will be to embodiment or existing
The accompanying drawing having required use in technology description is briefly described.
Fig. 1 is the cross-sectional schematic of aircraft cellular-type cabin balanced controls disclosed in the embodiment of the present invention；
Fig. 2 is the schematic side view of aircraft cellular-type cabin balanced controls disclosed in the embodiment of the present invention；
Fig. 3 is the horizontality schematic diagram of aircraft cellular-type cabin balanced controls disclosed in the embodiment of the present invention；
Fig. 4 is the heeling condition schematic diagram of aircraft cellular-type cabin balanced controls disclosed in the embodiment of the present invention；
Corresponding component title represented by figure numeral and letter：
1. housing 2. nacelle 3. rolling element.
Specific embodiment
Below in conjunction with the accompanying drawing in the embodiment of the present invention, the technical scheme in the embodiment of the present invention is carried out clear, complete
Site preparation describes.
The invention provides aircraft cellular-type cabin balanced controls, its operation principle is by between housing and nacelle
Several rolling elements are set, using the principle of divergence type bearing, make housing in the case of run-off the straight, upset, nacelle is not with shell
Body rotates together, reaches and avoids passenger to be affected in craft inclination, switching process, avoids article to drop and guarantee personnel peace
Full purpose.
With reference to embodiment and specific embodiment, the present invention is further detailed explanation.
As Figure 1-Figure 4, a kind of aircraft cellular-type cabin balanced controls, include housing 1, are provided with described housing
Nacelle 2, is distributed with several rolling elements 3 between the end of the end of described nacelle and described housing, described rolling element laminating is described
The end outer wall of nacelle, described rolling element is also fitted the inner wall of end of described housing, and described rolling element can carry out rotation.
The present invention passes through to arrange several rolling elements between housing and nacelle, using the principle of divergence type bearing, makes housing
In the case of run-off the straight, upset, nacelle does not rotate with housing, reaches and avoids passenger in craft inclination, switching process
In the purpose that is affected, avoids article to drop and ensure personal security.
It should be noted that being separated using retainer between adjacent rolling element.Make adjacent rolling element using retainer
Separately so that rolling element can only carry out rotation, it is to avoid rolling element generation is crooked, also avoids adjacent rolling element mutually to collide, enters
One step ensures the safety of flight.
It should be noted that scribbling grease between described retainer and described rolling element.
It should be noted that described housing is made using superhard aluminium.
It should be noted that described rolling element is made using high-strength structure Steel material.
It should be noted that described retainer is made using brass material.
It should be noted that described nacelle is made using superhard aluminium.
The specifically used step of the present invention is as follows：Again as Figure 1-Figure 4, in actual application, rolling element is permissible
It is arranged on the end of nacelle 2 it is also possible to be arranged on middle part or the other positions of nacelle, the present embodiment is arranged on cabin with rolling element
As a example the end of body 2.In housing 1 run-off the straight, upset, rolling element 3 rotation, so that nacelle 2 and housing 1 is produced relative rotation,
Nacelle held stationary under the influence of by self gravitation, will not overturn with housing, it is to avoid body in personnel together simultaneously
Discomfort, also avoids article to drop.
By way of above, aircraft cellular-type cabin balanced controls provided by the present invention, by housing and cabin
Several rolling elements are set between body, using the principle of divergence type bearing, make housing in the case of run-off the straight, upset, nacelle
Do not rotate with housing, reach and avoid passenger to be affected in craft inclination, switching process, avoid article to drop, maintain
The steadily purpose with guarantee personal security of nacelle.
Above-described be only aircraft cellular-type cabin balanced controls disclosed in this invention preferred implementation, should
When pointing out, for the person of ordinary skill of the art, without departing from the concept of the premise of the invention, can also make
Some deformation and improvement, these broadly fall into protection scope of the present invention.
Claims (7)
1. a kind of aircraft cellular-type cabin balanced controls, it is characterised in that including housing, are provided with nacelle in described housing,
Several rolling elements are distributed with, outside the described rolling element described nacelle of laminating between the end of the end of described nacelle and described housing
Wall, described rolling element is also fitted the inner wall of end of described housing, and described rolling element can carry out rotation.
2. aircraft cellular-type cabin balanced controls according to claim 1 are it is characterised in that between adjacent rolling element
Separated using retainer.
3. aircraft cellular-type cabin balanced controls according to claim 2 it is characterised in that described retainer with described
Grease is scribbled between rolling element.
4. aircraft cellular-type cabin balanced controls according to claim 1 are it is characterised in that described housing is using superhard
Aluminium is made.
5. aircraft cellular-type cabin balanced controls according to claim 1 are it is characterised in that described rolling element is using high
Strength structure Steel material is made.
6. aircraft cellular-type cabin balanced controls according to claim 2 are it is characterised in that described retainer is using yellow
Copper product is made.
7. aircraft cellular-type cabin balanced controls according to claim 1 are it is characterised in that described nacelle is using superhard
Aluminium is made.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611026126.1A CN106477021A (en) | 2016-11-22 | 2016-11-22 | Aircraft cellular-type cabin balanced controls |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611026126.1A CN106477021A (en) | 2016-11-22 | 2016-11-22 | Aircraft cellular-type cabin balanced controls |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN106477021A true CN106477021A (en) | 2017-03-08 |
Family
ID=58272623
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201611026126.1A Pending CN106477021A (en) | 2016-11-22 | 2016-11-22 | Aircraft cellular-type cabin balanced controls |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106477021A (en) |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN201472668U (en) * | 2009-06-12 | 2010-05-19 | 段霄驰 | Flying saucer |
| CN203958617U (en) * | 2014-06-30 | 2014-11-26 | 张飞 | Butterfly list duct tiltrotor aircraft |
-
2016
- 2016-11-22 CN CN201611026126.1A patent/CN106477021A/en active Pending
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN201472668U (en) * | 2009-06-12 | 2010-05-19 | 段霄驰 | Flying saucer |
| CN203958617U (en) * | 2014-06-30 | 2014-11-26 | 张飞 | Butterfly list duct tiltrotor aircraft |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20170308 |