CN203780795U - Aft body blowing type rectifying device of airplane with double engines and single vertical fin - Google Patents
Aft body blowing type rectifying device of airplane with double engines and single vertical fin Download PDFInfo
- Publication number
- CN203780795U CN203780795U CN201420190016.9U CN201420190016U CN203780795U CN 203780795 U CN203780795 U CN 203780795U CN 201420190016 U CN201420190016 U CN 201420190016U CN 203780795 U CN203780795 U CN 203780795U
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- China
- Prior art keywords
- vertical fin
- airplane
- aircraft
- rectifying device
- blowing type
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- 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.)
- Expired - Lifetime
Links
- 238000007664 blowing Methods 0.000 title claims abstract description 13
- 238000005452 bending Methods 0.000 claims description 3
- 230000010349 pulsation Effects 0.000 abstract description 5
- 238000000034 method Methods 0.000 abstract description 2
- 230000002411 adverse Effects 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 239000007921 spray Substances 0.000 description 2
- 238000012795 verification Methods 0.000 description 2
- 238000004458 analytical method Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
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- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The utility model relates to the technical field of aerodynamic configuration structure design of airplanes, in particular to an aft body blowing type rectifying device of an airplane with double engines and a single vertical fin. The aft body blowing type rectifying device comprises a guide pipe, wherein the guide pipe comprises a left branch pipe and a right branch pipe; the two branch pipes are respectively positioned between tail fairings of the airplane on the two sides and a vertical fin seat of the airplane; two air inlets of the two branch pipes are positioned above the tail fairings of the airplane; the two branch pipes extend between the tail fairings of the airplane on the two sides and the side wall of the vertical fin seat of the airplane; the two branch pipes at the back of the vertical fin seat of the airplane are merged into one exhaust port, so that the whole guide pipe is of a V-shaped structure. According to the aft body blowing type rectifying device, the guide pipe of the V-shaped structure introduces air flows from the two sides of the vertical fin seat, the air flows are sprayed out through the exhaust port after being merged between the two tail fairings at the aft body of the airplane, so that the flow field of the aft body is improved, the pressure pulsation is reduced, negative influences are reduced, the structure is simple, and the device is easy to produce and process.
Description
Technical field
The utility model relates to Aerodynamic Configuration of Aireraft structure-design technique field, specifically, relates to body air blowing type rectifying device after a kind of two bill vertical fin formula aircrafts.
Background technology
Two bill vertical fin formula aircrafts, have referred to two driving engines, the aircraft of single vertical fin, for general two bill vertical fin formulas, after aircraft, between two tail fairings of body, gap is little, air turbulence, be easy to produce burbling, after aircraft, on body, produce pressure pulsation, aircraft is had a negative impact.Therefore, be necessary to design a kind of novel structure, be intended to improve aircraft afterbody flowfield stalling characteristic, reduce pressure pulsation.
Utility model content
The purpose of this utility model is to overcome the deficiencies in the prior art, adapts to reality needs, and body air blowing type rectifying device after a kind of pair of bill vertical fin formula aircrafts is provided.
In order to realize the purpose of this utility model, the technical solution adopted in the utility model is:
Body air blowing type rectifying device after a kind of two bill vertical fin formula aircraft, comprise a mozzle, described mozzle comprises left arm, right arm, two arms lay respectively between both sides aircraft tail fairing and aircraft vertical fin seat, two admission ports of two arms are positioned at aircraft tail fairing top, two arms extend between both sides aircraft tail fairing and aircraft vertical fin seat sidewall, and at the rear of aircraft vertical fin seat, two arms are merged into an exhausr port, make the V-shaped structure of whole mozzle.
The cross-sectional area sum of two admission ports of described left and right arm is 1.2～1.3 times of exhausr port cross-sectional area.
Outside and the inside of described left arm, right arm are all smooth curve bending, and the radius of curvature of described left arm, right arm line of centers admission port and exhaust ports is all greater than the radius of curvature of interlude.
The beneficial effects of the utility model are:
The mozzle of 1.V type structure is introduced air-flow from vertical fin seat both sides, after mozzle merges, after aircraft, between body two tail fairings, spray by exhausr port, improves aircraft afterbody flowfield, reduces pressure pulsation, reduces adverse effect;
2. simple in structure, be easy to production and processing.
Brief description of the drawings
Fig. 1 is structural representation of the present utility model.
In figure, 1 is aircraft tail fairing, and 2 is mozzle, and 21 is left arm, and 22 is right arm, and 23 is the first admission port, and 24 is the second admission port, and 3 is rear body back, and 4 is aircraft vertical fin seat, and 5 is exhausr port.
Detailed description of the invention
Below in conjunction with drawings and Examples, the utility model is further illustrated:
Embodiment: referring to Fig. 1.
The utility model discloses body air blowing type rectifying device after a kind of two bill vertical fin formula aircrafts, comprise a mozzle 2, described mozzle 2 comprises a left side, right two, be defined as left arm 21, right arm 22, left arm 21, right arm 22 lays respectively between both sides aircraft tail fairing 1 and aircraft vertical fin seat 4, described left arm 21, two admission ports of right arm 22 are defined as first, the second admission port 23, 24, two admission ports are positioned at aircraft tail fairing 1 top, left arm 21, right arm 22 extends between both sides aircraft tail fairing 1 and aircraft vertical fin seat 4 sidewalls, at the rear of aircraft vertical fin seat 4, two arms are merged into an exhausr port 5, make the V-shaped structure of whole mozzle 2.The mozzle 2 of V-structure is introduced air-flow from vertical fin seat both sides by left and right arm 21,22, after mozzle merges, after aircraft, between body two tail fairings, sprays by exhausr port 5, improves aircraft afterbody flowfield, reduces pressure pulsation, reduces adverse effect.
The cross-sectional area sum of two admission ports of described left and right arm 21,22 is 1.2～1.3 times of exhausr port cross-sectional area.
Outside and the inside of described left arm 21, right arm 22 are all smooth curve bending, and the radius of curvature of described left arm 21, right arm 22 line of centers admission ports and exhaust ports is all greater than the radius of curvature of interlude.
In order to ensure that mozzle has enough charge airs, for blowing down low energy stall spot air-flow, also should notice that its size should not be too large, otherwise affect the full machine lifting resistance characteristic of aircraft simultaneously.By repeatedly parameter comparison analysis and verification experimental verification, the cross-sectional area sum of two admission ports is designed to 1.2～1.3 times of exhausr port cross-sectional area the most at last.Meanwhile, in order to ensure that the flow field entering in mozzle pipeline does not separate, in case reduce flowed energy, therefore need to distribute by rational pipeline area, the air of pipeline is accelerated, improve the speed of blowning installation exit flow.Therefore, by the radius of curvature that is all greater than interlude of the line of centers radius of curvature design of admission port and exhaust ports, and meet 1.2～1.3 times that admission port area sum is exhaust port area, can meet above-mentioned requirements.
Claims (3)
1. body air blowing type rectifying device after two bill vertical fin formula aircrafts, it is characterized in that: comprise a mozzle, described mozzle comprises left arm, right arm, two arms lay respectively between both sides aircraft tail fairing and aircraft vertical fin seat, two admission ports of two arms are positioned at aircraft tail fairing top, two arms extend between both sides aircraft tail fairing and aircraft vertical fin seat sidewall, and at the rear of aircraft vertical fin seat, two arms are merged into an exhausr port, make the V-shaped structure of whole mozzle.
2. body air blowing type rectifying device after according to claim 1 pair of bill vertical fin formula aircraft, is characterized in that: the cross-sectional area sum of two admission ports of described left and right arm is 1.2～1.3 times of exhausr port cross-sectional area.
3. according to body air blowing type rectifying device after claim 1 or claimed in claim 2 pair of bill vertical fin formula aircraft, it is characterized in that: outside and the inside of described left arm, right arm are all smooth curve bending, the radius of curvature of described left arm, right arm line of centers admission port and exhaust ports is all greater than the radius of curvature of interlude.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420190016.9U CN203780795U (en) | 2014-04-18 | 2014-04-18 | Aft body blowing type rectifying device of airplane with double engines and single vertical fin |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420190016.9U CN203780795U (en) | 2014-04-18 | 2014-04-18 | Aft body blowing type rectifying device of airplane with double engines and single vertical fin |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203780795U true CN203780795U (en) | 2014-08-20 |
Family
ID=51317006
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201420190016.9U Expired - Lifetime CN203780795U (en) | 2014-04-18 | 2014-04-18 | Aft body blowing type rectifying device of airplane with double engines and single vertical fin |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN203780795U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105181289A (en) * | 2015-09-14 | 2015-12-23 | 江西洪都航空工业集团有限责任公司 | Fairing for empennage wind tunnel testing |
| CN107187608A (en) * | 2017-05-24 | 2017-09-22 | 江西洪都航空工业集团有限责任公司 | A kind of air blowing type afterbody flowfield fairing |
-
2014
- 2014-04-18 CN CN201420190016.9U patent/CN203780795U/en not_active Expired - Lifetime
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105181289A (en) * | 2015-09-14 | 2015-12-23 | 江西洪都航空工业集团有限责任公司 | Fairing for empennage wind tunnel testing |
| CN107187608A (en) * | 2017-05-24 | 2017-09-22 | 江西洪都航空工业集团有限责任公司 | A kind of air blowing type afterbody flowfield fairing |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CX01 | Expiry of patent term | ||
| CX01 | Expiry of patent term |
Granted publication date: 20140820 |