CN104890872B - A kind of fan wing aircraft fairing and the aircraft with it - Google Patents
A kind of fan wing aircraft fairing and the aircraft with it Download PDFInfo
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- CN104890872B CN104890872B CN201510346260.9A CN201510346260A CN104890872B CN 104890872 B CN104890872 B CN 104890872B CN 201510346260 A CN201510346260 A CN 201510346260A CN 104890872 B CN104890872 B CN 104890872B
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- wing
- roller
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- fairing
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Abstract
Wing aircraft fairing and aircraft with it are fanned the invention discloses a kind of.The fan wing aircraft fairing is arranged on air inlet (5) place of first wing (2) and second wing (3), when the aircraft runs, air-flow by the roller (41) passes through the fairing first, the fairing is used to decay the pulsation of the shunting in air-flow therethrough with the normal orientation relative to the roller (41), so that passing through the roller (41) through the air-flow after overdamping.In fan wing aircraft fairing in the present invention, there is the pulsation of the shunting relative to the roller normal orientation in fairing decay air-flow therethrough, so that passing through roller through the air-flow after overdamping.So as to reduce the influence of the flow-disturbing pair roller in air-flow, the stability of fan wing class aircraft is increased.
Description
Technical field
It is more particularly to a kind of to fan wing aircraft fairing and with it the present invention relates to fan wing aircraft technical field
Aircraft.
Background technology
In the prior art, its power source of fan wing class aircraft is fan wing roller, in flight course, is held at the roller air inlet
It is vulnerable to the influence of outer gas stream disturbance, so as to cause the unstable of whirlpool in roller, easily induces loss of lift.
Thus, it is desirable to have a kind of technical scheme come overcome or at least mitigate prior art at least one drawbacks described above.
The content of the invention
Prior art is overcome or at least mitigated with fairing it is an object of the invention to provide a kind of wing aircraft of fanning
At least one drawbacks described above.
To achieve the above object, the present invention provides a kind of fan wing aircraft fairing.The fan wing aircraft has mutual
With fuselage symmetrical the first wing and the second wing, fan wing rolling is provided with first wing and second wing
Wheel, the roller in aircraft running status, the fan wing roller bears the air-flow relative with the aircraft traffic direction, described
The air inlet of the first wing and second wing is respectively arranged with fairing, when the aircraft runs, by described
, first by the fairing, the fairing in air-flow therethrough of decaying for having relative to institute for the air-flow of roller
The pulsation of the shunting of the normal orientation of roller is stated, so that passing through the roller through the air-flow after overdamping.
The fan wing aircraft is included with fairing：Punished in the air inlet of first wing and second wing
Fairing is not provided with, it is described whole by the air-flow of the roller first by the fairing when aircraft runs
Device is flowed for the pulsation of the shunting in air-flow therethrough of decaying with the normal orientation relative to the roller, so that through
Air-flow after overdamping passes through the roller.
Preferably, the fairing is guide-ring, and parallel to the direction of motion setting of the air-flow.
Preferably, the position of the guide-ring is：The extension that the guide-ring extends to the fan wing roller direction
Central axis of the line through the roller in the fan wing roller.
Preferably, the guide-ring is shaped as plate body.
Preferably, radius of the width dimensions of the guide-ring no more than the roller.
Preferably, described guide-ring one end is arranged on fuselage, and the other end is connected with roller axial wall.
Preferably, the guide-ring is welded to each other with the fuselage and the roller axial wall.
Preferably, first wing and the second wing air inlet are provided with support, and the guide-ring leads to
Cross support and be arranged on first wing and the second wing air inlet.
Present invention also offers one kind fan wing class aircraft, the fan wing class aircraft is filled including rectification as described above
Put.
In fan wing aircraft fairing in the present invention, fairing decay in air-flow therethrough have relative to
The pulsation of the shunting of the roller normal orientation, so that passing through roller through the air-flow after overdamping.So as in reducing air-flow
Flow-disturbing pair roller influence, increased fan wing class aircraft stability.
Brief description of the drawings
Fig. 1 is the structural representation of fan wing aircraft fairing according to an embodiment of the invention.
Reference：
| 1 | Fuselage | 5 | Air inlet |
| 2 | First wing | 6 | Guide-ring |
| 3 | Second wing | 7 | Roller axial wall |
| 4 | Fan wing roller | ||
| 41 | Roller |
Specific embodiment
To make the purpose, technical scheme and advantage of present invention implementation clearer, below in conjunction with the embodiment of the present invention
Accompanying drawing, the technical scheme in the embodiment of the present invention is further described in more detail.In the accompanying drawings, identical from start to finish or class
As label represent same or similar element or the element with same or like function.Described embodiment is the present invention
A part of embodiment, rather than whole embodiments.Embodiment below with reference to Description of Drawings is exemplary, it is intended to used
It is of the invention in explaining, and be not considered as limiting the invention.Based on the embodiment in the present invention, ordinary skill people
The every other embodiment that member is obtained under the premise of creative work is not made, belongs to the scope of protection of the invention.Under
Face is described in detail with reference to accompanying drawing to embodiments of the invention.
In the description of the invention, it is to be understood that term " " center ", " longitudinal direction ", " transverse direction ", "front", "rear",
The orientation or position relationship of the instruction such as "left", "right", " vertical ", " level ", " top ", " bottom " " interior ", " outward " are based on accompanying drawing institute
The orientation or position relationship for showing, are for only for ease of the description present invention and simplify description, rather than the dress for indicating or implying meaning
Put or element with specific orientation, with specific azimuth configuration and operation, therefore it is not intended that must be protected to the present invention
The limitation of scope.
Fan wing aircraft fairing of the invention is used to fan wing class aircraft, wherein, fan wing aircraft has mutually with fuselage
Symmetrical the first wing and the second wing, is provided with fan wing roller on the first wing and the second wing, shape is run in aircraft
State, the roller in fan wing roller bears the air-flow relative with aircraft traffic direction, in the first wing and the air intake of the second wing
Fairing is respectively arranged with mouthful, i.e., fairing of the invention is arranged on the air inlet of the first wing and the second wing
Place.When wing aircraft operation is fanned, by the air-flow of roller first by fairing, fairing is used for gas therethrough of decaying
The pulsation of the shunting with the normal orientation relative to roller in stream, so that passing through roller through the air-flow after overdamping.
In fan wing aircraft fairing in the present invention, fairing decay in air-flow therethrough have relative to
The pulsation of the shunting of the roller normal orientation, so that passing through roller through the air-flow after overdamping.So as in reducing air-flow
Flow-disturbing pair roller influence, increased fan wing class aircraft stability.
Fig. 1 is the structural representation of fan wing aircraft fairing according to an embodiment of the invention.
Aircraft has mutually with fuselage 1 symmetrical the first wing 2 and the second wing 3, the first wing 2 and the second wing
Fan wing roller 4 is provided with 3, the roller 41 in aircraft running status, fan wing roller 4 bears relative with aircraft traffic direction
Air-flow.
In fan wing aircraft fairing shown in Fig. 1, distinguish at the air inlet 5 of the first wing 2 and the second wing 3
Fairing is provided with, when aircraft runs, by the air-flow of roller 41 first by fairing, fairing is used to decay and passes through
The pulsation of the shunting with the normal orientation relative to roller 41 is crossed in its air-flow, so that passing through through the air-flow after overdamping
Roller 41.
Specifically, fairing is guide-ring 6, and parallel to the direction of motion setting of air-flow.
Advantageously, the position of guide-ring 6 is：Guide-ring 6 passes through fan to the extended line that the direction of fan wing roller 4 extends
The central axis of the roller 41 in wing roller 4.It is understood that the extended line is in virtual extended line, i.e. guide-ring 6
Center line between two ends is with the central axis for fanning the roller in wing roller 4 in a plane.I.e. from the front of guide-ring 6
(left side in figure) is looked squarely, and should see the central axis of fan wing roller 4
Referring to Fig. 1, in this embodiment, the one end of guide-ring 6 is set on the fuselage 1, and the other end is connected with roller axial wall 7.
Specifically, in the present embodiment, guide-ring 6 is welded to each other with fuselage 1 and roller axial wall 7.
It is understood that mode can also be detachably connected by bolt etc. being attached, it is advantageous that, should be tight
It is solidly connected.
It is understood that in an alternative embodiment, the first wing and the second wing air inlet are provided with branch
Frame, guide-ring is arranged on the first wing and the second wing air inlet by support.
It is understood that in this alternative embodiment, the set location and setting shape of support should be to entering
Air-flow at air port is interfered.
Advantageously, the support follows air motion direction to move for servo support, the i.e. support are shaped to, so that
Farthest reduce the contact area with air-flow.
It is understood that above-mentioned guide-ring is shaped as tabular, i.e., its thickness the distance between (two faces) is remote
Less than its length (the distance between two ends) and width (distance of nearly roller to remote roller direction).
It is understood that radius of the width dimensions of above-mentioned guide-ring no more than the roller.So, that is, ensure
Guide-ring effect in the present invention, again will not be wide because of guide-ring, and causes to be bowed in fan wing aircraft flight
When facing upward flight, the performance of fan wing aircraft is influenceed because guide-ring is wide.
Present invention also offers one kind fan wing class aircraft, the fan wing class aircraft is filled including rectification as described above
Put.
It is last it is to be noted that：The above embodiments are merely illustrative of the technical solutions of the present invention, rather than its limitations.To the greatest extent
Pipe has been described in detail to the present invention with reference to the foregoing embodiments, it will be understood by those within the art that：It is still
Technical scheme described in foregoing embodiments can be modified, or which part technical characteristic is equally replaced
Change；And these modifications or replacement, do not make the essence of the essence disengaging various embodiments of the present invention technical scheme of appropriate technical solution
God and scope.
Claims (8)
1. a kind of fan wing aircraft fairing, the fan wing aircraft have mutually with symmetrical the first wing (2) of fuselage (1) with
And second wing (3), fan wing roller (4) is provided with first wing (2) and second wing (3), in aircraft fortune
Row state, the roller (41) in the fan wing roller (4) bears the air-flow relative with the aircraft traffic direction, and its feature exists
In, fairing is respectively arranged with air inlet (5) place of first wing (2) and second wing (3), it is described whole
Stream device is guide-ring (6), and parallel to the direction of motion setting of the air-flow, when the aircraft runs, by the rolling
The air-flow of (41) is taken turns first by the fairing, the fairing be used to decaying in air-flow therethrough have relative to
The pulsation of the shunting of the normal orientation of the roller (41), so that passing through the roller (41) through the air-flow after overdamping.
It is 2. as claimed in claim 1 to fan wing aircraft fairing, it is characterised in that
The position of the guide-ring (6) is：The extended line that the guide-ring (6) extends to the described fan wing roller (4) direction
Through the central axis of the roller (41) in fan wing roller (4).
3. fan wing aircraft fairing as claimed in claim 2, it is characterised in that the guide-ring is shaped as tabular
Body.
4. it is as claimed in claim 3 to fan wing aircraft fairing, it is characterised in that the width dimensions of the guide-ring are not
More than the radius of the roller.
5. it is as claimed in claim 2 to fan wing aircraft fairing, it is characterised in that described guide-ring (6) one end is set
On fuselage (1), the other end is connected with roller axial wall (7).
6. it is as claimed in claim 5 to fan wing aircraft fairing, it is characterised in that the guide-ring (6) and the machine
Body (1) and the roller axial wall (7) are welded to each other.
7. it is as claimed in claim 2 to fan wing aircraft fairing, it is characterised in that first wing and described second
Wing air inlet is provided with support, and the guide-ring is arranged on first wing and second wing by support
Air inlet.
8. it is a kind of to fan wing class aircraft, it is characterised in that the fan wing class aircraft is including any one in such as claim 1 to 7
Fairing described in.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510346260.9A CN104890872B (en) | 2015-06-23 | 2015-06-23 | A kind of fan wing aircraft fairing and the aircraft with it |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510346260.9A CN104890872B (en) | 2015-06-23 | 2015-06-23 | A kind of fan wing aircraft fairing and the aircraft with it |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN104890872A CN104890872A (en) | 2015-09-09 |
| CN104890872B true CN104890872B (en) | 2017-06-16 |
Family
ID=54023946
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510346260.9A Active CN104890872B (en) | 2015-06-23 | 2015-06-23 | A kind of fan wing aircraft fairing and the aircraft with it |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN104890872B (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110466758B (en) * | 2019-04-29 | 2022-07-15 | 南京工程学院 | Emergency fan wing rotating speed control method for fan wing aircraft |
Family Cites Families (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB9902653D0 (en) * | 1999-02-05 | 1999-03-31 | Peebles Patrick | Aerodynamic lift generating device |
| US7607606B2 (en) * | 2002-09-11 | 2009-10-27 | Milde Jr Karl F | VTOL personal aircraft |
| GB0606518D0 (en) * | 2006-03-31 | 2006-05-10 | Fanwing Ltd | Aircraft with aerodynamic lift generating device |
| CN203544372U (en) * | 2013-11-15 | 2014-04-16 | 浙江师范大学 | Fixed-wing aircraft additionally provided with cross-flow fan |
| CN203767062U (en) * | 2014-04-22 | 2014-08-13 | 刘新广 | High-speed fan wing aircraft |
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2015
- 2015-06-23 CN CN201510346260.9A patent/CN104890872B/en active Active
Also Published As
| Publication number | Publication date |
|---|---|
| CN104890872A (en) | 2015-09-09 |
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