CN103192993A - Aerial tanker taper sleeve with winglets - Google Patents

Abstract

Translated fromChinese

一种有小翼的空中加油机锥套，包括加油管、连接锥套、伞套、两根弹簧、两个转轴和一对小翼。一对小翼通过转轴对称的安装在连接锥套前端下侧，并能够以转轴为轴心旋转。转轴轴心距连接锥套顶端的距离为该连接锥套长度的5％。转轴的轴线垂直于所在位置的连接锥套的表面，并且该轴线与连接锥套轴向对称面之间的夹角为Φ，Φ=30°。本发明中，锥套远离加油机的扰流区，能更稳定的浮于空中，使受油直升机与加油机的对接变得容易，并且受油直升机从加油机上方接近加油机，从而不会穿过加油机机翼、发动机以及加油吊舱产生的扰动流场，直升机稳定性和操纵性不会受到干扰，驾驶员完成加油过程变得容易，提高了直升机空中加油时的直升机的安全性。

The utility model relates to an air tanker drogue with winglets, which comprises a refueling pipe, a connecting drogue, an umbrella cover, two springs, two rotating shafts and a pair of winglets. A pair of winglets are symmetrically installed on the lower side of the front end of the connecting taper sleeve through the rotating shaft, and can rotate around the rotating shaft. The distance between the shaft center and the top end of the connecting taper sleeve is 5% of the length of the connecting taper sleeve. The axis of the rotating shaft is perpendicular to the surface of the connecting taper sleeve at the location, and the included angle between the axis and the axial symmetry plane of the connecting taper sleeve is Φ, Φ=30°. In the present invention, the drogue sleeve is far away from the turbulence area of the tanker, and can float in the air more stably, so that the docking of the oil receiving helicopter and the tanker becomes easy, and the oil receiving helicopter approaches the tanker from above the tanker, so that it will not Passing through the turbulent flow field generated by the tanker's wing, engine and refueling pod, the stability and maneuverability of the helicopter will not be disturbed, and the driver can easily complete the refueling process, which improves the safety of the helicopter during aerial refueling.

Description

Translated fromChinese

一种有小翼的空中加油机锥套A Drogue Bushing for Air Tanker with Small Wings

技术领域technical field

本发明涉及空中加油领域，具体是一种用于直升机空中加油管的有小翼的加油锥套。The invention relates to the field of aerial refueling, in particular to a refueling drogue with winglets for a helicopter aerial refueling pipe.

背景技术Background technique

直升机空中加油是一种新兴的空中加油技术，直升机空中加油一般采用软式加油系统。加油时，直升机从加油机后侧下方接近加油机，加油机抛出细长的柔性软管，软管端部连接一个加油锥套，软管在重力和锥套后端伞套产生的阻力的共同作用下，垂于加油机的后下方，受油直升机下方伸出的受油管前端的进油嘴插入锥套，实施加油。Helicopter aerial refueling is an emerging aerial refueling technology, and helicopter aerial refueling generally adopts a soft refueling system. When refueling, the helicopter approaches the tanker from the bottom of the rear side of the tanker. The tanker throws out a slender flexible hose, and the end of the hose is connected to a refueling drogue. Under the combined action, the oil inlet nozzle at the front end of the oil receiving pipe extending below the oil receiving helicopter is inserted into the drogue sleeve to implement refueling.

加油管锥套通常由连接锥套和伞套组成。连接锥套前端于油管连接，加油时受油机的受油管前端的进油嘴插入连接锥套前实施加油；伞套起增加阻力，油管在自身重力和伞套阻力的作用下悬浮于加油机的后方。由于加油机机翼、发动机以及加油吊舱产生强烈的涡流，使锥套不可能稳定的悬浮于空中，使对接比较困难，增加了加油过程操纵的复杂性。为了增加锥套的稳定性，国内外设计出多种抗干扰型的锥套，如专利【US2010/0282913A1】中设计的锥套在连接锥套四周安装四个小风扇，用于调整锥套的位置，增加锥套的稳定性；专利【US2010/0237196A1】中设计的锥套在连接锥套周围布置气囊，控制气流，增加锥套的稳定性；专利【CN101898642A】中则是通过在油管周围配置可变燃油配重稳定器，调整锥套的位置；申请号200820053261.X的专利中，通过在连接锥套上方安置小翼，通过小翼产生负升力，并在连接锥套下方添加配重块，使锥套高度下降，脱离加油机的扰流区，增加锥套的稳定性。The drogue sleeve of the oil filling pipe is usually composed of a connecting drogue sleeve and an umbrella sleeve. The front end of the connecting drogue sleeve is connected to the oil pipe. When refueling, the oil inlet nozzle at the front end of the oil receiving pipe of the refueling machine is inserted into the connecting drogue sleeve to carry out refueling; the umbrella cover increases the resistance, and the oil pipe is suspended in the tanker under the action of its own gravity and the resistance of the umbrella cover. rear. Due to the strong vortex generated by the wings, engine and refueling pod of the tanker, it is impossible for the drogue to be suspended in the air stably, which makes the docking more difficult and increases the complexity of the refueling process. In order to increase the stability of the taper sleeve, a variety of anti-interference type taper sleeves have been designed at home and abroad, such as the taper sleeve designed in the patent [US2010/0282913A1], four small fans are installed around the connecting taper sleeve to adjust the taper sleeve. Position, increase the stability of the taper sleeve; the taper sleeve designed in the patent [US2010/0237196A1] arranges airbags around the connecting taper sleeve to control the air flow and increase the stability of the taper sleeve; in the patent [CN101898642A], it is arranged around the oil pipe Variable fuel counterweight stabilizer to adjust the position of the drogue sleeve; in the patent application number 200820053261.X, a small wing is placed above the connecting drogue sleeve to generate negative lift through the small wing, and a counterweight is added below the connecting drogue sleeve , so that the height of the taper sleeve is lowered, away from the turbulence area of the fuel dispenser, and the stability of the taper sleeve is increased.

然而，对于直升机空中加油，由于直升机构造有别于固定翼飞机，直升机的受油管一般位于直升机机身的下方，采用以上锥套进行加油时，直升机主要是其旋翼仍位于加油机的扰流中，因此未能解决直升机受到加油机扰流作用后稳定性和操纵性变差的问题，造成加油过程中飞行员操纵困难，可能会出现直升机旋翼切断加油管的情况，甚至造成直升机失去控制等严重飞行事故。However, for helicopter aerial refueling, because the structure of helicopters is different from that of fixed-wing aircraft, the oil receiving pipe of helicopters is generally located below the helicopter fuselage. Therefore, the problem of poor stability and maneuverability of the helicopter after being affected by the turbulence of the tanker has not been solved, resulting in difficulties for the pilot to control during the refueling process, and the situation that the helicopter rotor may cut off the refueling pipe may even cause serious flight such as loss of control of the helicopter. ACCIDENT.

发明内容Contents of the invention

为克服现有技术中存在的加油过程中飞行员操纵困难，安全性差的不足，本发明提出了一种有小翼的空中加油机锥套。In order to overcome the deficiencies in the prior art, such as the pilot's difficulty in maneuvering and poor safety during the refueling process, the present invention proposes a drogue sleeve for an air tanker with winglets.

本发明包括加油管、连接锥套、伞套、两根弹簧、两个转轴和一对小翼。所述的一对小翼通过转轴对称的安装在连接锥套前端下侧，并能够以所述转轴为轴心旋转。所述转轴轴心距连接锥套顶端的距离为该连接锥套长度的5％。所述转轴的轴线垂直于所在位置的连接锥套的表面，并且该轴线与连接锥套轴向对称面之间的夹角为Φ，Φ=30°。The invention comprises a refueling pipe, a connecting taper sleeve, an umbrella sleeve, two springs, two rotating shafts and a pair of winglets. The pair of winglets are symmetrically installed on the lower side of the front end of the connecting taper sleeve through the rotating shaft, and can rotate around the rotating shaft. The distance between the shaft center and the top end of the connecting taper sleeve is 5% of the length of the connecting taper sleeve. The axis of the rotating shaft is perpendicular to the surface of the connecting taper sleeve at the position, and the included angle between the axis and the axial symmetry plane of the connecting taper sleeve is Φ, Φ=30°.

所述的连接锥套轴向对称面过该连接锥套的轴线，并与水平面垂直。The axial symmetry plane of the connecting taper sleeve passes through the axis of the connecting taper sleeve and is perpendicular to the horizontal plane.

在所述转轴与连接锥套顶端之间固定有定位销，并且该定位销的表面与转轴之间的距离与小翼的半弦长相同。A positioning pin is fixed between the rotating shaft and the top end of the connecting taper sleeve, and the distance between the surface of the positioning pin and the rotating shaft is the same as the half chord length of the winglet.

所述小翼的展弦比为8。The aspect ratio of the winglet is 8.

所述弹簧位于连接锥套的表面，该弹簧的一端固定在所述小翼的根部，另一端固定在连接锥套的表面。The spring is located on the surface of the connecting taper sleeve, one end of the spring is fixed on the root of the winglet, and the other end is fixed on the surface of the connecting taper sleeve.

本发明在小翼的作用下，锥套悬浮于加油机的上方，位于加油机扰流区之外，不会受到加油机扰流的干扰。同时，直升机从加油机上方接近加油机，并完成对接，因此将不会受到加油机流场的干扰，使加油机与受油直升机对接变得容易，大大降低直升机旋翼切断加油管的风险。In the present invention, under the action of the winglets, the drogue sleeve is suspended above the tanker, and is located outside the turbulence area of the tanker, and will not be disturbed by the turbulence of the tanker. At the same time, the helicopter approaches the tanker from above the tanker and completes the docking, so it will not be disturbed by the flow field of the tanker, making the docking of the tanker and the receiving helicopter easier, and greatly reducing the risk of the helicopter rotor cutting off the fueling pipe.

本发明中，在加油锥套的下侧安装一对可展开收起的小翼。锥套收于加油吊舱内时，小翼折叠收起；当锥套由加油吊舱伸出后，小翼在弹簧的作用下，小翼展开。小翼受到空气的作用，产生向上的升力（F_y），Fy=5000N±500N，该升力作用在锥套上，使其悬浮于加油机上方3～5m处，进行加油。加油完成后，锥套收起，在加油舱油管口的阻挡下小翼收起，油管和锥套收入加油吊舱。In the present invention, a pair of expandable and retractable winglets are installed on the underside of the refueling drogue. When the drogue is stored in the refueling pod, the winglets are folded; when the drogue is stretched out from the refueling pod, the winglets are unfolded under the action of the spring. The winglet is affected by the air to generate an upward lift (F_y ), Fy=5000N±500N, the lift acts on the drogue, making it suspend at 3-5m above the tanker for refueling. After the refueling is completed, the drogue is retracted, and the winglets are retracted under the obstruction of the oil pipe port of the refueling cabin, and the oil pipe and the drogue are received into the refueling pod.

由于所采取的上述技术方案，本发明取得了以下效果：Due to the above technical scheme adopted, the present invention has achieved the following effects:

第一，锥套远离加油机的扰流区，能更稳定的浮于空中，使受油直升机与加油机的对接变得容易。First, the drogue is far away from the turbulence area of the tanker, and can float more stably in the air, which makes it easier for the docking helicopter and the tanker to be connected.

第二，受油直升机从加油机上方接近加油机，从而不会穿过加油机机翼、发动机以及加油吊舱产生的扰动流场，直升机稳定性和操纵性不会受到干扰，驾驶员完成加油过程变得容易，提高了直升机空中加油时的直升机的安全性。Second, the refueling helicopter approaches the tanker from above the tanker, so that it will not pass through the turbulent flow field generated by the tanker's wings, engines, and refueling pods, the stability and maneuverability of the helicopter will not be disturbed, and the driver completes the refueling The process becomes easier and the safety of the helicopter during aerial refueling of the helicopter is improved.

附图说明：Description of drawings:

图1是本发明的三维示意图。Fig. 1 is a three-dimensional schematic diagram of the present invention.

图2是本发明的结构示意图。Fig. 2 is a structural schematic diagram of the present invention.

图3是本发明的右视图。Fig. 3 is a right side view of the present invention.

图4是小翼的示意图，其中，图4a是主视图，图4b是图4a的A-A视图。Fig. 4 is a schematic diagram of a winglet, wherein Fig. 4a is a front view, and Fig. 4b is an A-A view of Fig. 4a.

图中：1.加油管，2.连接锥套，3.小翼，4.定位销，5.弹簧，6.转轴，7.伞套。In the figure: 1. Refueling pipe, 2. Connecting taper sleeve, 3. Small wing, 4. Locating pin, 5. Spring, 6. Rotating shaft, 7. Umbrella cover.

具体实施方式Detailed ways

本实施例是一种有小翼的空中加油机锥套，包括加油管1、连接锥套2、伞套7、两根弹簧5、两个转轴6和一对小翼3。所述加油管1、连接锥套2和伞套7均为现有技术。The present embodiment is a drogue sleeve for an aerial refueling machine with winglets, including a refuelingpipe 1, a connectingdrogue sleeve 2, anumbrella sleeve 7, two springs 5, two rotating shafts 6 and a pair ofwinglets 3. The refuelingpipe 1, the connectingtaper sleeve 2 and theumbrella sleeve 7 are all prior art.

所述的空中加油机锥套为对称结构，本实施例仅对一侧的结构特征加以描述。The air tanker drogue has a symmetrical structure, and this embodiment only describes the structural features of one side.

所述的一对小翼3通过转轴6对称的安装在连接锥套2前端下侧，并能够以所述转轴为轴心旋转。所述转轴轴心距连接锥套2顶端的距离为该连接锥套2长度的5％。所述转轴的轴线垂直于所在位置的连接锥套2的表面，并且该轴线与连接锥套2轴向对称面之间的夹角为Φ，Φ=30°。所述的连接锥套2轴向对称面过该连接锥套2的轴线，并与水平面垂直。在所述转轴6与连接锥套2顶端之间固定有定位销4，并且该定位销4的表面与转轴6之间的距离与小翼3的半弦长相同。The pair ofwinglets 3 are symmetrically installed on the lower side of the front end of the connectingtaper sleeve 2 through the rotating shaft 6, and can rotate around the rotating shaft. The distance between the shaft center and the top end of the connectingtaper sleeve 2 is 5% of the length of the connectingtaper sleeve 2 . The axis of the rotating shaft is perpendicular to the surface of the connectingtaper sleeve 2 where it is located, and the included angle between the axis and the axial symmetry plane of the connectingtaper sleeve 2 is Φ, Φ=30°. The axial symmetry plane of the connectingtaper sleeve 2 passes through the axis of the connectingtaper sleeve 2 and is perpendicular to the horizontal plane. A positioning pin 4 is fixed between the rotating shaft 6 and the top end of the connectingtaper sleeve 2 , and the distance between the surface of the positioning pin 4 and the rotating shaft 6 is the same as the half chord length of thewinglet 3 .

所述小翼3的展弦比为8，采用EPPLER858高升力翼型的平直翼。The aspect ratio of describedwinglet 3 is 8, adopts the straight wing of EPPLER858 high-lift airfoil.

当锥套收于加油吊舱内时，在加油吊舱的作用下，小翼折叠收起；当锥套由加油吊舱伸出后，小翼在弹簧5的作用下，小翼绕转轴旋转，旋转至定位销处，通过所述定位销定位。When the drogue is stored in the refueling pod, under the action of the refueling pod, the winglets are folded and retracted; when the drogue is stretched out from the refueling pod, the winglets rotate around the shaft under the action of the spring 5 , rotate to the positioning pin, and locate through the positioning pin.

所述弹簧5位于连接锥套2的表面，该弹簧的一端固定在所述小翼的根部，另一端固定在连接锥套2的表面。The spring 5 is located on the surface of the connectingtaper sleeve 2 , one end of the spring is fixed on the root of the winglet, and the other end is fixed on the surface of the connectingtaper sleeve 2 .

小翼在弹簧和定位销的共同作用下固定于与连接锥套轴线垂直位置。小翼受到空气的作用，产生向上的升力（Fy），该升力作用在锥套上，使其悬浮于加油机上方3～5m处，进行加油。加油完成后，锥套收起，在加油舱油管口的阻挡下小翼收起，油管和锥套收入加油吊舱。The winglet is fixed at a position perpendicular to the axis of the connecting taper sleeve under the joint action of the spring and the positioning pin. The winglet is affected by the air to generate an upward lift (Fy), which acts on the drogue to suspend it at 3-5m above the tanker for refueling. After the refueling is completed, the drogue is retracted, and the winglets are retracted under the obstruction of the oil pipe port of the refueling cabin, and the oil pipe and the drogue are received into the refueling pod.

Claims (5)

Translated fromChinese

1.一种有小翼的空中加油机锥套，其特征在于，包括加油管、连接锥套、伞套、两根弹簧、两个转轴和一对小翼；所述的一对小翼通过转轴对称的安装在连接锥套前端下侧，并能够以所述转轴为轴心旋转；所述转轴轴心距连接锥套顶端的距离为该连接锥套长度的5％；所述转轴的轴线垂直于所在位置的连接锥套的表面，并且该轴线与连接锥套轴向对称面之间的夹角为Φ，Φ=30°。1. A drogue sleeve for air tanker with winglets is characterized in that it comprises a refueling pipe, a connecting awl sleeve, an umbrella cover, two springs, two rotating shafts and a pair of winglets; the pair of winglets pass through The rotating shaft is symmetrically installed on the lower side of the front end of the connecting taper sleeve, and can rotate with the rotating shaft as the axis; the distance between the axis center of the rotating shaft and the top end of the connecting taper sleeve is 5% of the length of the connecting taper sleeve; the axis of the rotating shaft It is perpendicular to the surface of the connecting taper sleeve at the position, and the angle between the axis and the axial symmetry plane of the connecting taper sleeve is Φ, Φ=30°.2.如权利要求1所述一种有小翼的空中加油机锥套，其特征在于，所述的连接锥套轴向对称面过该连接锥套的轴线，并与水平面垂直。2. A drogue sleeve for air tanker with winglets as claimed in claim 1, wherein the axial symmetry plane of the connecting drogue sleeve passes through the axis of the connecting drogue sleeve and is perpendicular to the horizontal plane.3.如权利要求1所述一种有小翼的空中加油机锥套，其特征在于，在所述转轴与连接锥套顶端之间固定有定位销，并且该定位销的表面与转轴之间的距离与小翼的半弦长相同。3. A kind of air tanker drogue with winglets as claimed in claim 1, characterized in that, a locating pin is fixed between the rotating shaft and the top end of the connecting drogue, and the surface of the locating pin and the rotating shaft The distance is the same as the half-chord length of the winglet.4.如权利要求1所述一种有小翼的空中加油机锥套，其特征在于，所述小翼的展弦比为8。4 . A kind of air tanker drogue with winglets as claimed in claim 1 , wherein the aspect ratio of the winglets is 8. 5 .5.如权利要求1所述一种有小翼的空中加油机锥套，其特征在于，所述弹簧位于连接锥套的表面，该弹簧的一端固定在所述小翼的根部，另一端固定在连接锥套的表面。5. A kind of air tanker drogue with winglet as claimed in claim 1, is characterized in that, described spring is positioned at the surface that connects drogue, and one end of this spring is fixed on the root of described winglet, and the other end is fixed on On the surface of the connecting taper sleeve.

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