CN103192993A - Aerial tanker taper sleeve with winglets - Google Patents
Aerial tanker taper sleeve with winglets Download PDFInfo
- Publication number
- CN103192993A CN103192993A CN2013101052047A CN201310105204A CN103192993A CN 103192993 A CN103192993 A CN 103192993A CN 2013101052047 A CN2013101052047 A CN 2013101052047A CN 201310105204 A CN201310105204 A CN 201310105204A CN 103192993 A CN103192993 A CN 103192993A
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- tapered sleeve
- winglet
- taper sleeve
- tanker
- helicopter
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Abstract
An aerial tanker taper sleeve with winglets comprises a fuel filling pipe, a connecting taper sleeve, an umbrella cover, two springs, two spindles and a pair of winglets. The pair of winglets is symmetrically installed on the lower side at the front end of the connecting taper sleeve through the spindles and capable of rotating with the spindles serving as axes. The distance between the axes of the spindles and the top of the connecting taper sleeve is 5% of the length of the connecting taper sleeve. The axes of the spindles are perpendicular to the surface of the connecting taper sleeve, and the included angle formed between the axes and the axial symmetrical surface of the connecting taper sleeve is phi=30 degrees. According to the aerial tanker taper sleeve, the taper sleeve is far away from a turbulent flow area of the tanker and can float in the air stably, so that butt joint of a fuel receiving helicopter and the tanker becomes easy, the fuel receiving helicopter approaches the tanker from above the tanker and cannot pass through disturbance flow fields generated by wings of the tanker, an engine and a refueling pod, the stability and the control ability of the helicopter cannot be disturbed, a driver can complete the refueling process easily, and the safety of the helicopter during aerial refueling is improved.
Description
Technical field
The present invention relates to the air refuelling field, specifically is a kind of oiling tapered sleeve that winglet is arranged for the helicopter inflight refueling pipe.
Background technology
Helicopter inflight refueling is a kind of emerging air refuelling technology, and helicopter inflight refueling generally adopts soft fuel loading system.During oiling, helicopter from fuel charger rear side below near fuel charger, the fuel charger elongated flexible hose of dishing out, hose end connects an oiling tapered sleeve, flexible pipe is under the combined action of the resistance of gravity and the generation of tapered sleeve rear end umbrella cover, fall in the back lower place of fuel charger, the inlet nozzle that is subjected to the oil pipe front end that stretched out by oily helicopter below inserts tapered sleeve, implements to refuel.
The fuel filler pipe tapered sleeve is formed by connecting tapered sleeve and umbrella cover usually.Connect the tapered sleeve front end and connect in oil pipe, the inlet nozzle that is subjected to the oil pipe front end of refueled aircraft is implemented to refuel before inserting and connecting tapered sleeve during oiling; Umbrella cover plays the increase resistance, oil pipe at the effect low suspension of self gravitation and umbrella cover resistance in the rear of fuel charger.Because fuel charger wing, driving engine and refuelling pod produce strong eddy current, being suspended in of making that tapered sleeve can not stable is aerial, makes relatively difficulty of butt joint, has increased the complexity of refueling process manipulation.In order to increase the stability of tapered sleeve, design the tapered sleeve of multiple anti-interference type both at home and abroad, around connecting tapered sleeve, four small fans are installed as the tapered sleeve of design in the patent [US2010/0282913A1], be used for adjusting the position of tapered sleeve, increase the stability of tapered sleeve; The tapered sleeve of design is connecting tapered sleeve arranged around air bag in the patent [US2010/0237196A1], control air-flow, the stability of increase tapered sleeve; Then be by around oil pipe, disposing variable fuel counterweight stabiliser, adjusting the position of tapered sleeve in the patent [CN101898642A]; In the patent of application number 200820053261.X, by above connecting tapered sleeve, settling winglet, produce negative lift by winglet, and below connecting tapered sleeve, add clump weight, the tapered sleeve height is descended, break away from the turbulent flow area of fuel charger, increase the stability of tapered sleeve.
Yet, for helicopter inflight refueling, because the helicopter structure is different from fixed wing aircraft, the oil pipe that is subjected to of helicopter generally is positioned at the below of helicopter fuselage, when adopting above tapered sleeve to refuel, helicopter mainly is the flow-disturbing that its rotor still is arranged in fuel charger, therefore fail to solve the problem that helicopter is subjected to fuel charger flow-disturbing effect rear stability and road-holding property variation, cause pilot guidance difficulty in the refueling process, the situation that lifting airscrew cuts off fuel filler pipe may occur, even cause aberdeen cutlet such as helicopter get out of hand.
Summary of the invention
For overcoming pilot guidance difficulty in the refueling process that exists in the prior art, the deficiency of poor stability the present invention proposes a kind of tanker aircraft tapered sleeve that winglet is arranged.
The present invention includes fuel filler pipe, connect tapered sleeve, umbrella cover, two springs, two rotating shafts and a pair of winglet.Described a pair of winglet connects tapered sleeve front end downside by being installed in of rotating shaft symmetry, and can be the axle center rotation with described rotating shaft.Described rotating shaft core connects 5% of tapered sleeve length apart from the distance that connects the tapered sleeve top for this.The axis normal of described rotating shaft is in the surface of the connection tapered sleeve of position, and this axis is Φ with the angle that is connected between the axial plane of symmetry of tapered sleeve, Φ=30 °.
The axial plane of symmetry of described connection tapered sleeve is crossed the axis of this connection tapered sleeve, and vertical with horizontal surface.
Locating dowel pin is fixedly arranged in described rotating shaft with being connected between the tapered sleeve top, and the semifocal chord appearance of the surface of this locating dowel pin and the distance between the rotating shaft and winglet with.
The aspect ratio of described winglet is 8.
Described spring is positioned at the surface that connects tapered sleeve, and an end of this spring is fixed on the root of described winglet, and the other end is fixed on the surface that connects tapered sleeve.
The present invention is under the effect of winglet, and tapered sleeve is suspended in the top of fuel charger, is positioned at outside the fuel charger turbulent flow area, can not be subjected to the interference of fuel charger flow-disturbing.Simultaneously, helicopter near fuel charger, and is finished butt joint from fuel charger top, therefore will can not be subjected to the interference in fuel charger flow field, makes fuel charger and dock by oily helicopter to become easy, reduce the risk of lifting airscrew cut-out fuel filler pipe greatly.
Among the present invention, at the downside of oiling tapered sleeve a pair of deployable winglet of packing up is installed.When tapered sleeve closed in the refuelling pod, little wingfold was packed up; After tapered sleeve was stretched out by refuelling pod, winglet was under the effect of spring, and winglet launches.Winglet is subjected to the effect of air, produces lift (F upwards
y), Fy=5000N ± 500N, this lift acts on the tapered sleeve, makes it be suspended in 3～5m place, fuel charger top, refuels.After oiling was finished, tapered sleeve was packed up, and winglet is packed up under the stopping that adds cargo tank oil pipe mouth, oil pipe and tapered sleeve income refuelling pod.
Because the technique scheme of taking, the present invention has obtained following effect:
The first, tapered sleeve is away from the turbulent flow area of fuel charger, and can be more stable float on is aerial, makes to be subjected to oily helicopter and docking of fuel charger to become easy.
Second, be subjected to oily helicopter from fuel charger top near fuel charger, thereby can not pass the disturbance flow field that fuel charger wing, driving engine and refuelling pod produce, helicopter stability and road-holding property can not be interfered, chaufeur is finished refueling process and is become easily, the safety of the helicopter when having improved helicopter inflight refueling.
Description of drawings:
Fig. 1 is schematic three dimensional views of the present invention.
Fig. 2 is structural representation of the present invention.
Fig. 3 is right elevation of the present invention.
Fig. 4 is the scheme drawing of winglet, and wherein, Fig. 4 a is front view, and Fig. 4 b is the A-A view of Fig. 4 a.
Among the figure: 1. fuel filler pipe 2. connects tapered sleeve, 3. winglet, 4. locating dowel pin, 5. spring, 6. rotating shaft, 7. umbrella cover.
The specific embodiment
Present embodiment is a kind of tanker aircraft tapered sleeve that winglet is arranged, and comprises fuel filler pipe 1, connects tapered sleeve 2, umbrella cover 7, two springs 5, two rotating shafts 6 and a pair of winglet 3.Described fuel filler pipe 1, connection tapered sleeve 2 and umbrella cover 7 are prior art.
Described tanker aircraft tapered sleeve is symmetrical structure, and present embodiment is only described the architectural feature of a side.
Described a pair of winglet 3 connects tapered sleeve 2 front end downsides by being installed in of rotating shaft 6 symmetries, and can be the axle center rotation with described rotating shaft.Described rotating shaft core connects 5% of tapered sleeve 2 length apart from the distance that connects tapered sleeve 2 tops for this.The axis normal of described rotating shaft is in the surface of the connection tapered sleeve 2 of position, and this axis is Φ with the angle that is connected between the tapered sleeve 2 axial planes of symmetry, Φ=30 °.The described connection tapered sleeve 2 axial planes of symmetry are crossed the axis of this connection tapered sleeve 2, and vertical with horizontal surface.Locating dowel pin 4 is fixedly arranged in described rotating shaft 6 with being connected between tapered sleeve 2 tops, and the semifocal chord appearance of the distance between the surface of this locating dowel pin 4 and the rotating shaft 6 and winglet 3 with.
The aspect ratio of described winglet 3 is 8, adopts the straight wing of EPPLER858 high lift aerofoil profile.
In the time of in tapered sleeve closes at refuelling pod, under the effect of refuelling pod, little wingfold is packed up; After tapered sleeve was stretched out by refuelling pod, winglet was under the effect of spring 5, and winglet rotates around the shaft, rotated to the locating dowel pin place, by described locating dowel pin location.
Described spring 5 is positioned at the surface that connects tapered sleeve 2, and an end of this spring is fixed on the root of described winglet, and the other end is fixed on the surface that connects tapered sleeve 2.
Winglet is fixed under the combined action of spring and locating dowel pin and is connected tapered sleeve axis normal position.Winglet is subjected to the effect of air, produces lift (Fy) upwards, and this lift acts on the tapered sleeve, makes it be suspended in 3～5m place, fuel charger top, refuels.After oiling was finished, tapered sleeve was packed up, and winglet is packed up under the stopping that adds cargo tank oil pipe mouth, oil pipe and tapered sleeve income refuelling pod.
Claims (5)
1. the tanker aircraft tapered sleeve that winglet is arranged is characterized in that, comprises fuel filler pipe, connects tapered sleeve, umbrella cover, two springs, two rotating shafts and a pair of winglet; Described a pair of winglet connects tapered sleeve front end downside by being installed in of rotating shaft symmetry, and can be the axle center rotation with described rotating shaft; Described rotating shaft core connects 5% of tapered sleeve length apart from the distance that connects the tapered sleeve top for this; The axis normal of described rotating shaft is in the surface of the connection tapered sleeve of position, and this axis is Φ with the angle that is connected between the axial plane of symmetry of tapered sleeve, Φ=30 °.
2. a kind of tanker aircraft tapered sleeve that winglet is arranged according to claim 1 is characterized in that the axial plane of symmetry of described connection tapered sleeve is crossed the axis of this connection tapered sleeve, and vertical with horizontal surface.
3. a kind of tanker aircraft tapered sleeve that winglet is arranged according to claim 1 is characterized in that, locating dowel pin is fixedly arranged in described rotating shaft with being connected between the tapered sleeve top, and the semifocal chord appearance of the surface of this locating dowel pin and the distance between the rotating shaft and winglet with.
4. a kind of tanker aircraft tapered sleeve that winglet is arranged according to claim 1 is characterized in that the aspect ratio of described winglet is 8.
5. a kind of tanker aircraft tapered sleeve that winglet is arranged according to claim 1 is characterized in that, described spring is positioned at the surface that connects tapered sleeve, and an end of this spring is fixed on the root of described winglet, and the other end is fixed on the surface that connects tapered sleeve.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2013101052047A CN103192993A (en) | 2013-03-28 | 2013-03-28 | Aerial tanker taper sleeve with winglets |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2013101052047A CN103192993A (en) | 2013-03-28 | 2013-03-28 | Aerial tanker taper sleeve with winglets |
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| CN103192993A true CN103192993A (en) | 2013-07-10 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN2013101052047A Pending CN103192993A (en) | 2013-03-28 | 2013-03-28 | Aerial tanker taper sleeve with winglets |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110304262A (en) * | 2019-06-21 | 2019-10-08 | 西北工业大学 | A kind of autonomous motor-driven tapered sleeve and control method of unmanned plane air refuelling |
| CN110356574A (en) * | 2018-04-11 | 2019-10-22 | 闵杰 | A kind of device improving hose type in-flight refueling rate |
| CN112591117A (en) * | 2020-12-30 | 2021-04-02 | 航宇救生装备有限公司 | Full speed variable resistance characteristic refueling hose joint stabilizing umbrella |
| CN114577431A (en) * | 2022-02-28 | 2022-06-03 | 西北工业大学 | Autonomous aerial refueling test taper sleeve based on control surface |
| CN115416858A (en) * | 2022-08-25 | 2022-12-02 | 中国空气动力研究与发展中心空天技术研究所 | Stability augmentation ring for taper sleeve for air refueling |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2859002A (en) * | 1954-03-05 | 1958-11-04 | Boeing Co | Airfoil aircraft interconnecting boom |
| GB2418186A (en) * | 2003-08-29 | 2006-03-22 | Smiths Aerospace Inc | Active control and stabilization of a refuelling drogue |
| EP1754660A2 (en) * | 2005-08-19 | 2007-02-21 | The Boeing Company | Flexible air refueling boom extendable tube |
| US20080308679A1 (en) * | 2007-06-15 | 2008-12-18 | Eads Construcciones Aeronauticas, S.A. | Device to reduce the lateral force generated by aerial refueling boom cross-section |
| CN201254296Y (en) * | 2008-05-26 | 2009-06-10 | 廖志明 | Airfoil fuel filling taper sleeve of aerial tanker |
| US20090184205A1 (en) * | 2008-01-22 | 2009-07-23 | William Francis Matheny | Method and apparatus for aerial fuel transfer |
| US20100237196A1 (en) * | 2003-08-29 | 2010-09-23 | Smiths Aerospace, Llc | Active stabilization of a refueling drogue |
-
2013
- 2013-03-28 CN CN2013101052047A patent/CN103192993A/en active Pending
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2859002A (en) * | 1954-03-05 | 1958-11-04 | Boeing Co | Airfoil aircraft interconnecting boom |
| GB2418186A (en) * | 2003-08-29 | 2006-03-22 | Smiths Aerospace Inc | Active control and stabilization of a refuelling drogue |
| US20100237196A1 (en) * | 2003-08-29 | 2010-09-23 | Smiths Aerospace, Llc | Active stabilization of a refueling drogue |
| EP1754660A2 (en) * | 2005-08-19 | 2007-02-21 | The Boeing Company | Flexible air refueling boom extendable tube |
| US20070040065A1 (en) * | 2005-08-19 | 2007-02-22 | Von Thal German | Flexible refueling boom extendable tube |
| US20080308679A1 (en) * | 2007-06-15 | 2008-12-18 | Eads Construcciones Aeronauticas, S.A. | Device to reduce the lateral force generated by aerial refueling boom cross-section |
| US20090184205A1 (en) * | 2008-01-22 | 2009-07-23 | William Francis Matheny | Method and apparatus for aerial fuel transfer |
| CN201254296Y (en) * | 2008-05-26 | 2009-06-10 | 廖志明 | Airfoil fuel filling taper sleeve of aerial tanker |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110356574A (en) * | 2018-04-11 | 2019-10-22 | 闵杰 | A kind of device improving hose type in-flight refueling rate |
| CN110304262A (en) * | 2019-06-21 | 2019-10-08 | 西北工业大学 | A kind of autonomous motor-driven tapered sleeve and control method of unmanned plane air refuelling |
| CN112591117A (en) * | 2020-12-30 | 2021-04-02 | 航宇救生装备有限公司 | Full speed variable resistance characteristic refueling hose joint stabilizing umbrella |
| CN112591117B (en) * | 2020-12-30 | 2023-10-27 | 航宇救生装备有限公司 | Full speed variable resistance characteristic refuelling hose connector stability umbrella |
| CN114577431A (en) * | 2022-02-28 | 2022-06-03 | 西北工业大学 | Autonomous aerial refueling test taper sleeve based on control surface |
| CN114577431B (en) * | 2022-02-28 | 2022-12-30 | 西北工业大学 | Autonomous aerial refueling test taper sleeve based on control surface |
| CN115416858A (en) * | 2022-08-25 | 2022-12-02 | 中国空气动力研究与发展中心空天技术研究所 | Stability augmentation ring for taper sleeve for air refueling |
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Application publication date: 20130710 |