CN116692018A - A high-performance airfoil suitable for active stabilization of refueling drogues - Google Patents

Abstract

Translated fromChinese

本发明公开了一种适用于加油锥套主动增稳的高性能翼型，满足气动/几何约束条件下，设定翼型最大相对厚度为5.6％，最大相对厚度位置位于10％弦长；设定翼型最大相对弯度为4％，最大相对弯度位置位于31％弦长；设定翼型相对前缘半径为0.0081，翼型后缘相对厚度为1％。本发明所设计的翼型可实现在0.2‑0.3倍音速飞行速度，1千‑4千米飞行高度状态下，16°迎角范围内，升力随迎角保持线性变化，并为锥杯小翼提供较大升力，从而可为加/受油过程中抑制锥套飘摆提供有效支撑。

The invention discloses a high-performance airfoil suitable for the active stabilization of the refueling drogue sleeve. Under the aerodynamic/geometric constraints, the maximum relative thickness of the airfoil is set at 5.6%, and the position of the maximum relative thickness is located at 10% of the chord length; The maximum relative camber of the fixed airfoil is 4%, and the maximum relative camber position is located at 31% of the chord length; the relative leading edge radius of the airfoil is set to 0.0081, and the relative thickness of the airfoil trailing edge is 1%. The airfoil designed by the present invention can realize a flight speed of 0.2-0.3 times the speed of sound, a flight altitude of 1,000-4 kilometers, and within the range of 16° angle of attack, the lift force keeps linearly changing with the angle of attack, and is a cone cup winglet Provides greater lift, thereby providing effective support for suppressing drogue swing during refueling/receiving oil.

Description

Translated fromChinese

一种适用于加油锥套主动增稳的高性能翼型A high-performance airfoil suitable for active stabilization of refueling drogues

技术领域technical field

本发明属于翼型设计领域，具体为一种适用于加油锥套主动增稳的高性能翼型。The invention belongs to the field of airfoil design, in particular to a high-performance airfoil suitable for active stabilization of a refueling drogue sleeve.

背景技术Background technique

空中加油技术能够有效提升飞行器的航程和航时，使得飞行器拥有更大的飞行半径以及更长的留空时间，并且有效缓解了机场建设压力。软管式加油具有加油系统相对简单，平台改装方便，加油过程中无需加/受机保持相对位置不变，并且可同时给多个受油机加油等优点，因此，是一种适用于无人自主加油的加油方式。然而，由于加油软管以及锥套在高速飞行中易受大气紊流影响而出现摆动，并且当受油机靠近时，受到头波效应的影响，锥套将出现震荡，因而受油机与锥套对接过程中对准较难，从而导致软管式加油效率较低。因此，发展主动增稳锥套，抑制软管锥套飘摆幅度，是提升软管式加油效率的有效手段。加油锥套主动增稳的原理是通过增大加油锥套本身的阻尼，从而抑制锥套的摆动。在锥杯上安装小翼，并通过改变小翼相对位置产生不同的操纵力，是抑制锥套摆动的最有效方式之一。目前主动增稳锥套小翼所采取的翼型大多为平直翼型，这类翼型升力不足，且失速迎角较小，因而所产生的操纵力不足。翼型的气动特性主要取决于其几何形状。而翼型的气动特性决定了小翼抑制锥套摆动的能力，因此，设计一种适用于加油锥套主动增稳的高性能翼型是研制主动增稳锥套的基础。Aerial refueling technology can effectively improve the range and flight time of the aircraft, enabling the aircraft to have a larger flight radius and longer stay in the air, and effectively relieve the pressure on airport construction. Hose-type refueling has the advantages of relatively simple refueling system, easy platform modification, no need for refueling/receiving machines to keep the relative position unchanged during refueling, and multiple refueling machines can be refueled at the same time, so it is a suitable for unmanned Self-refueling refueling method. However, because the refueling hose and the drogue sleeve are susceptible to swing due to the influence of atmospheric turbulence during high-speed flight, and when the receiving aircraft approaches, affected by the head wave effect, the drogue sleeve will vibrate, so the receiving aircraft and the cone Difficult alignment during sleeve mating, resulting in inefficient hose refueling. Therefore, the development of active stabilizing drogues and restraining the swing range of hose drogues is an effective means to improve the efficiency of hose refueling. The principle of the active stabilization of the refueling drogue is to increase the damping of the refueling drogue itself, thereby inhibiting the swing of the drogue. Installing winglets on the cone cup and changing the relative position of the winglets to generate different control forces is one of the most effective ways to restrain the swing of the drogue sleeve. At present, most of the airfoils adopted by active stabilizing drogue winglets are straight airfoils. This type of airfoil has insufficient lift and a small stall angle of attack, so the resulting control force is insufficient. The aerodynamic properties of an airfoil mainly depend on its geometry. The aerodynamic characteristics of the airfoil determine the ability of the winglet to restrain the swing of the drogue. Therefore, designing a high-performance airfoil suitable for the active stabilization of the refueling drogue is the basis for the development of the active stabilization drogue.

综合上述分析，一种适用于加油锥套主动增稳的高性能翼型，其飞行速度与高度由加/受油机飞行状态决定；由于锥套摆动抑制主要依靠小翼产生的操纵力，因此，该翼型需具备高升力特征；由于锥套小翼相对位置变化较大，因此，该翼型需要具备较大的失速迎角，从而随着相对位置改变，升力变化线性度较好，有利于控制律设计；同时，为了小翼与锥杯在空间上能够协调，该翼型应在符合上述条件的基础上尽量薄。本专利针对以上设计需求，设计一种适用于加油锥套主动增稳的高性能翼型。Based on the above analysis, a high-performance airfoil suitable for the active stabilization of the refueling drogue, its flight speed and altitude are determined by the flight status of the refueling/refueling aircraft; since the drogue swing suppression mainly depends on the control force generated by the winglet, , the airfoil needs to have high-lift characteristics; since the relative position of the drogue winglet changes greatly, the airfoil needs to have a large stall angle of attack, so that the linearity of the lift change is better with the change of the relative position, and there is It is beneficial to the design of the control law; at the same time, in order to coordinate the winglet and the cone cup in space, the airfoil should be as thin as possible on the basis of meeting the above conditions. In response to the above design requirements, this patent designs a high-performance airfoil suitable for active stabilization of the refueling drogue.

发明内容Contents of the invention

本发明意在提供一种适用于加油锥套主动增稳的高性能翼型，有效增强锥套小翼的升力，从而提升加油锥套的主动增稳能力。The present invention intends to provide a high-performance airfoil applicable to the active stabilization of the refueling drogue, which can effectively enhance the lift force of the winglet of the refueling drogue, thereby improving the active stability enhancement capability of the refueling drogue.

为达到上述目的，本发明提供如下技术方案：To achieve the above object, the present invention provides the following technical solutions:

一种适用于加油锥套主动增稳的高性能翼型，满足气动/几何约束条件下，设定翼型最大相对厚度为5.6％，最大相对厚度位置位于10％弦长；设定翼型最大相对弯度为4％，最大相对弯度位置位于31％弦长；设定翼型相对前缘半径为0.0081，翼型后缘相对厚度为1％。A high-performance airfoil suitable for active stabilization of the refueling drogue. Under the aerodynamic/geometric constraints, the maximum relative thickness of the airfoil is set to 5.6%, and the maximum relative thickness is located at 10% of the chord length; the maximum relative thickness of the airfoil is set to The relative camber is 4%, and the maximum relative camber position is located at 31% of the chord length; the relative leading edge radius of the airfoil is set to 0.0081, and the relative thickness of the airfoil trailing edge is 1%.

进一步的，所述翼型具有较高的失速迎角，巡航马赫数为0.25时失速迎角为16°。Further, the airfoil has a relatively high stall angle of attack, and the stall angle of attack is 16° when the cruise Mach number is 0.25.

进一步的，所述翼型具有较大的最大升力系数，巡航马赫数为0.25时最大升力系数约为锥套小翼初始翼型的2倍。Further, the airfoil has a relatively large maximum lift coefficient, and when the cruising Mach number is 0.25, the maximum lift coefficient is about twice that of the initial airfoil of the drogue sleeve.

本发明的有益效果是：The beneficial effects of the present invention are:

一种适用于加油锥套主动增稳的高性能翼型，可实现在0.2-0.3倍音速飞行速度，1千-4千米飞行高度状态下，16°迎角范围内，升力随迎角保持线性变化，并为锥杯小翼提供较大升力，从而可为加/受油过程中抑制锥套飘摆提供有效支撑。A high-performance airfoil suitable for the active stabilization of the refueling drogue, which can realize the flight speed of 0.2-0.3 times the speed of sound, the flight altitude of 1000-4 kilometers, and within the range of 16° angle of attack, the lift force can be maintained with the angle of attack Linear change, and provide greater lift for the cone cup winglet, which can provide effective support for suppressing the drogue swing during refueling/refueling.

附图说明Description of drawings

图1为锥套小翼初始翼型几何形状图；Figure 1 is the initial airfoil geometry of the drogue winglet;

图2为本发明设计的翼型几何形状图；Fig. 2 is the airfoil geometry figure that the present invention designs;

图3为平板翼型和本发明设计的翼型的升力特性对比图。Fig. 3 is a comparison diagram of the lift characteristics of the flat airfoil and the airfoil designed in the present invention.

其中，附图标记为：1、前缘点；2、中弧线；3、弯度；4、上表面；5、后缘厚度；6、下表面；7、弦线；8、最大厚度；9、头部曲率圆。Wherein, reference signs are: 1, front edge point; 2, middle arc; 3, camber; 4, upper surface; 5, trailing edge thickness; 6, lower surface; 7, chord line; 8, maximum thickness; 9 , Head curvature circle.

具体实施方式Detailed ways

下面结合附图和实施方式对本发明作进一步的详细说明：Below in conjunction with accompanying drawing and embodiment the present invention is described in further detail:

由于加油机在巡航过程中，锥套需要缩回机腹内，并且由于锥杯内需要布置输油机构，导致小翼无法缩入锥杯，因此锥套小翼面积将受到约束，从而需要小翼翼型具备低速高升力特征。此外，由于加油锥套主动增稳原理主要依靠小翼改变相对位置，并且锥套增稳过程中其位置、姿态也将发生变化，以上原因导致小翼迎角变化范围较大，因此需要小翼翼型具备较大的失速迎角，从而保证小翼操纵力具有较好的线性度。Because the drogue sleeve needs to be retracted into the belly of the tanker during cruise, and because the oil delivery mechanism needs to be arranged in the cone cup, the winglet cannot be retracted into the cone cup, so the area of the small winglet of the drogue sleeve will be restricted, thus requiring a small The airfoil has the characteristics of low speed and high lift. In addition, since the active stabilization principle of the refueling drogue mainly depends on the change of the relative position of the winglet, and its position and attitude will also change during the stabilization process of the drogue, the above reasons lead to a large range of variation in the angle of attack of the winglet, so it is necessary to The type has a larger stall angle of attack, so as to ensure that the control force of the winglet has a better linearity.

锥套小翼初始翼型如图1所示，为平直对称形状。这类外形通常所能产生的最大升力较小，且失速迎角较小，因此所产生的操纵力无法有效抑制锥套飘摆，因而，以初始翼型为初始状态，设计一种适用于加油锥套主动增稳的高性能翼型。The initial airfoil shape of the drogue winglet is shown in Figure 1, which is a straight and symmetrical shape. The maximum lift that can be generated by this type of shape is generally small, and the stall angle of attack is small, so the control force generated cannot effectively restrain the drogue from fluttering. Therefore, with the initial airfoil as the initial state, design a High-performance airfoil with active stabilization by drogue sleeves.

翼型设计主要参数如图2所示，包括前缘点1、中弧线2、弯度3、上表面4、后缘厚度5、下表面6、弦线7、最大厚度8、头部曲率圆9。The main parameters of airfoil design are shown in Figure 2, including leading edge point 1, mid-arc line 2, camber 3, upper surface 4, trailing edge thickness 5, lower surface 6, chord line 7, maximum thickness 8, and head curvature circle 9.

翼型按照0.25倍音速飞行速度，2千米飞行高度进行设计。满足气动/几何约束条件下，设定翼型最大相对厚度为5.6％，最大相对厚度位置位于10％弦长，设定翼型前缘半径为0.0081，翼型后缘相对厚度为1％，使翼型头部半径较大，并且最大半径后部曲率缓慢变化，具备较好的失速特性。设定翼型最大相对弯度为4％，最大相对弯度位置位于31％弦长，增大翼型升力。The airfoil is designed according to the flying speed of 0.25 times the speed of sound and the flying height of 2 kilometers. Under the aerodynamic/geometric constraints, the maximum relative thickness of the airfoil is set to 5.6%, the maximum relative thickness is located at 10% of the chord length, the leading edge radius of the airfoil is set to 0.0081, and the relative thickness of the airfoil trailing edge is 1%, so that The radius of the airfoil head is large, and the curvature of the rear part of the maximum radius changes slowly, which has better stall characteristics. The maximum relative camber of the airfoil is set to 4%, and the position of the maximum relative camber is located at 31% of the chord length to increase the lift of the airfoil.

为进一步说明一种适用于加油锥套主动增稳的高性能翼型的优点，图3给出了设计状态下该翼型和初始翼型升力系数随迎角变化的规律。由图3可见，本发明翼型失速迎角为16°，远大于初始翼型的失速迎角，并且本发明翼型最大升力系数约为初始翼型的两倍。In order to further illustrate the advantages of a high-performance airfoil suitable for active stabilization of the refueling drogue, Fig. 3 shows the law of the lift coefficient of the airfoil and the initial airfoil changing with the angle of attack under the design state. As can be seen from Fig. 3, the stall angle of attack of the airfoil of the present invention is 16°, which is far greater than that of the initial airfoil, and the maximum lift coefficient of the airfoil of the present invention is about twice that of the initial airfoil.

以上所述的仅是本发明的实施例，方案中公知的具体技术方案和/或特性等常识在此未作过多描述。应当指出，对于本领域的技术人员来说，在不脱离本发明技术方案的前提下，还可以做出若干变形和改进，这些也应该视为本发明的保护范围，这些都不会影响本发明实施的效果和专利的实用性。本申请要求的保护范围应当以其权利要求的内容为准，说明书中的具体实施方式等记载可以用于解释权利要求的内容。What is described above is only an embodiment of the present invention, and common knowledge such as specific technical solutions and/or characteristics known in the solutions will not be described here too much. It should be pointed out that for those skilled in the art, without departing from the technical solutions of the present invention, some modifications and improvements can also be made, which should also be regarded as the protection scope of the present invention, and these will not affect the present invention The effect of the implementation and the utility of the patent. The scope of protection required by this application shall be based on the content of the claims, and the specific implementation methods and other records in the specification may be used to interpret the content of the claims.

Claims (3)

1. The utility model provides a high performance wing section suitable for refueling taper sleeve initiative stability augmentation which characterized in that: under the condition of meeting aerodynamic/geometric constraint conditions, setting the maximum relative thickness of the airfoil to be 5.6%, wherein the position of the maximum relative thickness is positioned at 10% chord length; setting the maximum relative camber of the airfoil to be 4%, wherein the maximum relative camber position is positioned at 31% chord length; the airfoil was set to a relative leading edge radius of 0.0081 and airfoil trailing edge relative thickness of 1%.

2. The high performance airfoil adapted for active stability augmentation of a refueling drogue according to claim 1 wherein: the airfoil has a high stall angle of attack, which is 16 ° at a cruise mach number of 0.25.

3. The high performance airfoil adapted for active stability augmentation of a refueling drogue according to claim 1 wherein: the airfoil profile has a relatively large maximum lift coefficient, and the maximum lift coefficient is about 2 times that of the initial airfoil profile of the cone sleeve winglet at a cruise Mach number of 0.25.