CN102642613B - Low-resistance fairing of corrugate sheath - Google Patents
Low-resistance fairing of corrugate sheath Download PDFInfo
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- CN102642613B CN102642613B CN201210146223.XA CN201210146223A CN102642613B CN 102642613 B CN102642613 B CN 102642613B CN 201210146223 A CN201210146223 A CN 201210146223A CN 102642613 B CN102642613 B CN 102642613B
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- radiation fins
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Abstract
The invention belongs to the technical field of airplane design, and relates to a low-resistance fairing of a corrugate sheath, which is improved on a plane fairing part. The fairing consists of a fairing head part, a fairing back part, a fairing corrugate sheath, a resilient surface rubber, a plane body surface and a through hole, wherein the fairing head part is fixedly riveted or bonded on the plane body surface, the through hole is arranged at the most front end of the fairing head part, i.e. near an airflow stationary point, the through hole is communicated with an inner cavity of the fairing, the fairing corrugate sheath is arranged in the position with the biggest cross section area of the fairing, the fairing corrugate sheath is bonded between the fairing head part and the fairing back part, and the resilient surface rubber is bonded on the outer surface of a wave crest position of the corrugate sheath. The low-resistance fairing of the corrugate sheath disclosed by the invention can be balanced between pressure drag and frictional drag, the shape of the fairing is self-adaptively changed according to flight speed, flow separation on the fairing under a high-speed condition is restrained, and the vortex intensity at the tail part of the fairing is improved, so that the differential pressure between the front and the back of the fairing is reduced and the plane flight resistance is reduced.
Description
Technical field:
The invention belongs to airplane design technical field, relate to a kind of to the improved radiation fins low-resistance of aircraft radome parts fairing.
Background technology
Existing subsonic aircraft extensively adopts the fairing profile shown in Fig. 1, Fig. 2, to reduce the flight resistance of aircraft.Fairing generally according to following current to layout, adopt the head of raindrop type, the afterbody of wedge shape, the Diffusion of gas stream angle of afterbody is generally in 10 degree left and right, this fairing can well reduce pressure drag in certain particular speed range, but, when the increase along with flying speed, after certain speed, fairing overdraught can separate, form the turbulent region of afterbody, be whirlpool, the pressure in whirlpool district is less than the pressure in anterior incoming flow district, thus difference of pressure before and after forming, pressure direction backward, is pressure drag backward.The slenderness ratio of this fixed fairing is invariable, and drag reduction advantage is only defined in certain speed range.According to the aerodynamic force feature on fairing, a good fairing wishes that slenderness ratio can regulate according to aircraft flight speed, and to avoid the appearance in afterbody whirlpool district, and the fairing of existing aircraft does not possess this feature.
Summary of the invention
The object of the invention is to propose the radiation fins low-resistance fairing that a kind of slenderness ratio of aircraft radome can regulate according to aircraft flight speed.Technical solution of the present invention is, described fairing is by fairing head, fairing rear portion, fairing radiation fins, surface elasticity rubber, body surface, through hole composition, fairing head is fixing rivets or is bonded on airframe surface, at fairing head is to stay a through hole near air-flow stationary point foremost, through hole and fairing inner chamber connect, at area place, the maximum cross section of fairing, a fairing radiation fins is set, fairing radiation fins front end is bonded on the aft end face of fairing head, the rear end of fairing radiation fins is connected to fairing rear portion, the rear end of fairing radiation fins is connected to the front end at fairing rear portion, the gap of 1-5mm is left at the position that fairing rear portion and body surface suit mutually, slided along body surface in fairing rear portion under the drive of fairing radiation fins, surface elasticity rubber is bonded in the outside face of radiation fins crest location.
The described fairing radiation fins arranging at area place, the maximum cross section of fairing, its length is the 8-15% of whole fairing total length.
The advantage that the present invention has and beneficial effect,
The present invention increases elastic corrugated shape god contracting cover at existing fairing the maximum cross-section area place, the outside face of radiation fins crest location is bonded with elasticity rubber [4] that can guarantor's type, can automatically change fairing slenderness ratio according to differential pressure conditions before and after fairing, thereby while taking into account aircraft low-speed operations, there is little area and the little friction drag of soaking, when high-speed flight, there are suitable slenderness ratio and little pressure drag, thereby improve the aircraft drag characteristic of each flying speed.
Radiation fins low-resistance fairing of the present invention, can between pressure drag, friction drag, weigh, according to the shape of flying speed adaptively changing fairing, suppress the burbling on fairing under large speed conditions, improve the vortex strength degree of fairing afterbody, thereby pressure reduction reduces before and after making fairing, reduce the flight resistance of aircraft.
On aircraft, have a lot of fairings, all fairings all adopt this technology, will play considerable drag-reduction effect, of great advantage for the 1ift-drag ratio, the increase voyage that promote aircraft.
The present invention, by traditional fairing segmentation, increases the unitized construction of a set of flexible radiation fins, plasticity rubber, simple in structure, operability is very strong.
Brief description of the drawings
Fig. 1 is existing Typical Aircraft fairing front view;
Fig. 2 is existing aircraft radome generalized section;
Fig. 3 is that fairing master of the present invention looks schematic diagram;
Fig. 4 is fairing of the present invention elevation profile connection diagram;
Fig. 5 is the elevation profile connection diagram of fairing radiation fins extended state of the present invention.
Detailed description of the invention
Below in conjunction with accompanying drawing, the present invention is elaborated.
Described fairing is by fairing head 1, fairing rear portion 2, and fairing radiation fins 3, surface elasticity rubber 4, body surface 5, through hole 6 forms.The fixing riveted joint of fairing head 1 or be bonded on airframe surface 5, at fairing head 1 is to stay a through hole 6, through hole and the perforation of fairing inner chamber near air-flow stationary point foremost.Fairing radiation fins 3 front ends are bonded on the aft end face of fairing head 1, and the rear end of fairing radiation fins [3] is connected with fairing rear portion 2, and fairing radiation fins 3 longitudinally has good retractility, has good support rigidity in other directions.Surface elasticity rubber 4 is bonded in radiation fins outside, the crest location that bonding position is radiation fins.
Its principle of work of described fairing is: in the time that air speed is 0, fairing radiation fins 3 is in free state, it is minimum that the slenderness ratio of whole fairing keeps, length minimum, soak area minimum, in the time of aircraft flight, through hole [6] can ensure that the pressure in chamber is consistent with near pressure stationary point, for maximum pressure, the pressure of fairing rear end can be smaller, in chamber with the difference of pressure effect of fairing rear end under, can pull scalable fairing radiation fins [3], the slenderness ratio that changes fairing, reaches new force balance.In the time that air speed is very high, the pressure drag that the burbling on fairing is brought is the principal element of resistance, and external and internal pressure is now poor larger, can drive radiation fins to have larger amount of tension, thereby largely change the slenderness ratio of fairing, suppress burbling, reduce pressure drag.
Fairing taking existing total length as 800mm is example, makes improvements, and fairing adopts raindrop type head, wedge shape afterbody, being maximum cross section apart from fairing front end 300mm place, fairing is divided into two parts, i.e. fairing head 1, fairing rear portion 2.Fairing head 1 is fixedly riveted on airframe surface 5, fairing head 1 be to stay a through hole 6 near air-flow stationary point foremost, through-hole diameter is 2mm.Fairing radiation fins 3 front ends are bonded on the aft end face of fairing head 1, and the rear end of fairing radiation fins 3 is connected with fairing rear portion 2, and fairing radiation fins 3 longitudinally has good retractility, has good support rigidity in other directions.Surface elasticity rubber 4 is bonded in radiation fins 3 outsides, and bonding position is the crest location of radiation fins 3, to ensure the outside face fairing of fairing.
Radiation fins low-resistance fairing principle of work is: in the time that air speed is 0, fairing radiation fins is in free state, it is minimum that the slenderness ratio of whole fairing keeps, length minimum, soak area minimum, pressure in cavity is consistent with local outside pressure, in the time that aircraft flight arrives 350km/h, fairing local air flow separates, afterbody forms eddy zone, now the pressure at stationary point place is the external atmosphere pressure of 1.26 times, in chamber, pressure is also the external atmosphere pressure of 1.26 times, eddy zone, fairing rear portion pressure is the external atmosphere pressure of 0.73 times, under inside and outside differential pressure effect, radiation fins has extended 76mm, effectively slow down the burbling of fairing, suppress trailing vortex intensity, simultaneously, elasticity rubber is along with radiation fins stretches together, play the effect of good guarantor's type, ensure fairing outside face fairing streamline, reduce pressure drag.
Described dome structure is simple, easy operating, and it can weigh between pressure drag, friction drag, according to the shape of flying speed adaptively changing fairing, has stronger practicality.
Claims (2)
1. a radiation fins low-resistance fairing, it is characterized in that: described fairing is by fairing head [1], fairing rear portion [2], fairing radiation fins [3], surface elasticity rubber [4], body surface [5], through hole [6] composition, fairing head [1] is fixing rivets or is bonded on airframe surface [5], at fairing head [1] is to stay a through hole [6] near air-flow stationary point foremost, through hole and fairing inner chamber connect, at the maximum cross-section area place of fairing, a fairing radiation fins [3] is set, fairing radiation fins [3] front end is bonded on the aft end face of fairing head [1], the rear end of fairing radiation fins [3] is connected to the front end of fairing rear portion [2], the gap of 1-5mm is left at the position that fairing rear portion [2] and body surface [5] suit mutually, slided along body surface in fairing rear portion [2] under the drive of fairing radiation fins [3], surface elasticity rubber [4] is bonded in the outside face of radiation fins crest location.
2. a kind of radiation fins low-resistance fairing according to claim 1, is characterized in that: the fairing radiation fins [3] that the described the maximum cross-section area place at fairing arranges, its length is 8-15% of whole fairing total length.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210146223.XA CN102642613B (en) | 2012-05-11 | 2012-05-11 | Low-resistance fairing of corrugate sheath |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210146223.XA CN102642613B (en) | 2012-05-11 | 2012-05-11 | Low-resistance fairing of corrugate sheath |
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| Publication Number | Publication Date |
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| CN102642613A CN102642613A (en) | 2012-08-22 |
| CN102642613B true CN102642613B (en) | 2014-12-10 |
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| CN201210146223.XA Active CN102642613B (en) | 2012-05-11 | 2012-05-11 | Low-resistance fairing of corrugate sheath |
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Families Citing this family (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103303461B (en) * | 2013-06-28 | 2016-02-10 | 江西洪都航空工业集团有限责任公司 | A kind of aircraft antenna fairing |
| FR3013677B1 (en) * | 2013-11-27 | 2015-12-04 | Eurocopter France | GIRAVION TOP SIDE COMPRISING A TRUNK WATER DROP PROFILE HAVING A SURFACE SURFACE MISFEED |
| CN107799895A (en) * | 2017-09-12 | 2018-03-13 | 陕西飞机工业（集团）有限公司 | A kind of balance beam profile and direction-finder antenna cover |
| CN109823516B (en) * | 2019-02-14 | 2022-05-10 | 成都飞机工业（集团）有限责任公司 | Airplane stealth steering engine bulge |
| CN117458140A (en) * | 2022-07-18 | 2024-01-26 | 华为技术有限公司 | Fairing cover |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1151373A (en) * | 1995-12-05 | 1997-06-11 | 冯金宝 | Unidirectional automatic rotary device |
| CN101708772A (en) * | 2009-11-24 | 2010-05-19 | 南京航空航天大学 | Skin of morphing wing and drive method thereof |
| CN202130570U (en) * | 2011-05-16 | 2012-02-01 | 湖北航天技术研究院总体设计所 | Aircraft cowling shell |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2892999B1 (en) * | 2005-11-08 | 2008-02-01 | Airbus France Sas | AIRCRAFT COMPRISING A CENTRAL CARRIAGE PRESSURE ADJUSTER VESSEL BY LOCAL GEOMETRIC DEFORMATIONS |
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2012
- 2012-05-11 CN CN201210146223.XA patent/CN102642613B/en active Active
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1151373A (en) * | 1995-12-05 | 1997-06-11 | 冯金宝 | Unidirectional automatic rotary device |
| CN101708772A (en) * | 2009-11-24 | 2010-05-19 | 南京航空航天大学 | Skin of morphing wing and drive method thereof |
| CN202130570U (en) * | 2011-05-16 | 2012-02-01 | 湖北航天技术研究院总体设计所 | Aircraft cowling shell |
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| CN102642613A (en) | 2012-08-22 |
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