WO2012122925A1 - 飞机翼尖装置 - Google Patents

飞机翼尖装置 Download PDF

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Publication number
WO2012122925A1
WO2012122925A1 PCT/CN2012/072188 CN2012072188W WO2012122925A1 WO 2012122925 A1 WO2012122925 A1 WO 2012122925A1 CN 2012072188 W CN2012072188 W CN 2012072188W WO 2012122925 A1 WO2012122925 A1 WO 2012122925A1
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WO
WIPO (PCT)
Prior art keywords
wing tip
wing
aircraft
transition portion
chord length
Prior art date
Application number
PCT/CN2012/072188
Other languages
English (en)
French (fr)
Inventor
陈迎春
张淼
刘铁军
张美红
汪君红
马涂亮
于哲慧
周峰
张冬云
Original Assignee
中国商用飞机有限责任公司
中国商用飞机有限责任公司上海飞机设计研究院
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Priority claimed from CN201110059421.8A external-priority patent/CN102167152B/zh
Priority claimed from CN201110059438.3A external-priority patent/CN102167153B/zh
Priority claimed from CN201110059442.XA external-priority patent/CN102167154B/zh
Application filed by 中国商用飞机有限责任公司, 中国商用飞机有限责任公司上海飞机设计研究院 filed Critical 中国商用飞机有限责任公司
Priority to EP12757583.5A priority Critical patent/EP2684797B1/en
Publication of WO2012122925A1 publication Critical patent/WO2012122925A1/zh

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C23/00—Influencing air flow over aircraft surfaces, not otherwise provided for
    • B64C23/06—Influencing air flow over aircraft surfaces, not otherwise provided for by generating vortices
    • B64C23/065—Influencing air flow over aircraft surfaces, not otherwise provided for by generating vortices at the wing tips
    • B64C23/069—Influencing air flow over aircraft surfaces, not otherwise provided for by generating vortices at the wing tips using one or more wing tip airfoil devices, e.g. winglets, splines, wing tip fences or raked wingtips
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/10—Drag reduction

Definitions

  • the invention relates to a wing tip device for an aircraft wing. Background technique
  • the lift required to maintain normal flight is caused by the pressure difference between the upper and lower surfaces of the wing. Due to the pressure difference between the upper and lower surfaces, the air on the lower surface of the wing near the wing tip will flow to the upper surface, forming a wing tip vortex, resulting in a wing. The pressure difference between the upper and lower surfaces of the wing in the vicinity of the tip is reduced, resulting in a decrease in lift generated in this area.
  • a winglet is usually provided on the wing tip of the aircraft, and the main function of the winglet is to increase the effective aspect ratio without increasing the length of the wing.
  • the two-dimensional effect of the wing is enhanced, the induced resistance is reduced, the lift is increased, and the lift-to-drag ratio is increased.
  • the winglets also consume energy to dissipate the wing vortex, reducing the threat to small aircraft that follow the flight.
  • Wing Tips Wings increase the wing moment and shear load of the wing wing and result in an increase in the weight of the wing structure.
  • the wing tip wing is not well designed, and the separation characteristics and dither characteristics of the aircraft will also deteriorate.
  • wing tip sail According to the shape of the wing tip device, there are currently several types in the world: one is a wing tip sail, or an upper wing tip winglet.
  • This type of wingtip winglet generally has a three-stage structure, that is, a mounting section, a circular arc transition section, and a straight section.
  • This wingtip device has relatively obvious curved fins.
  • Boeing Company Boeing's 747-400 aircraft and Airbus' A330 and A340 series aircraft use such wingtip devices.
  • such wingtip devices are also installed when retrofitted on Boeing 727, Boeing 757 and Boeing 767 aircraft.
  • the other is a triangular wing-tip sail.
  • This form of wing-tip sail is used in the Airbus A320 series, A310 and A380.
  • This type of wing tip device is also a standard form of Airbus aircraft.
  • Boeing's newly designed passenger aircraft such as the Boeing 777, Boeing 787 and Boeing 747-8 replace the wingtip with a special shark fin winglet.
  • wingtips and wingtips have significant drag reduction effects, they are small in wingtips.
  • the wings are also wing-tip sails, and their wing roots have larger bending moments, which increases their own structural weight and has an impact on the flight characteristics of the aircraft.
  • the present invention provides an aircraft wing tip device, the aircraft wing tip device including a transition portion and a wing tip portion, the inner end portion of the transition portion being coupled to a distal end of the aircraft wing, the transition portion An outer end portion is coupled to the wing tip portion, wherein the wing tip portion includes a plurality of wing tip segments, each wing tip segment including a wing tip and a wing root, respectively, the wing of the first wing tip segment a root is coupled to an outer end of the transition portion, a wing root of the n+1th wing tip segment is located on a wing tip of the nth wing tip segment, and a root chord of the n+1th wing tip segment The length is less than or equal to the wing tip chord of the nth wing tip segment, where n>0.
  • each wing tip section of the aircraft is referred to as the "wing tip”
  • the bottom of each wing tip section of the aircraft is referred to as the "wing root”.
  • the wing tip section may be disposed at any position outside the transition portion, for example, may be aligned with the trailing edge of the outer end portion of the transition portion, or may be aligned with the leading edge of the outer end portion of the transition portion. Or disposed between the leading edge and the trailing edge of the outer end of the transition portion.
  • the n+1th wing tip segment has a thickness thinner than the nth wing tip segment.
  • chord length of the wing tip of each wing tip segment is less than the chord length of its wing root. More specifically, each of the wing tip segments is a wing tip segment that tapers in length.
  • chord length of the wing root of the first wing tip segment is less than or equal to the chord length of the outer end portion of the transition portion.
  • the inner end chord length of the transition portion is greater than the outer end chord length of the transition portion.
  • the transition portion is a transition portion in which the chord length is tapered.
  • the upper curved surface and the lower curved surface of the transition portion are smooth curved surfaces.
  • the transition is smoothly connected to the distal end of the aircraft wing.
  • the aircraft wing tip device is integrally formed with the aircraft wing.
  • the trailing edge line of the wing tip is aligned with the trailing edge line of the transition.
  • the starting end of the transition portion of the wing tip device is located at the extension of the wing along the span
  • chord length of the first segment of the wing tip is from 10% to 100% of the chord length of the outer end of the transition.
  • leading edge line of each wing tip section of the wing tip is a conic line segment, a spline, a straight line or a broken line segment. More particularly, the conic line segments are parabolic, hyperbolic or elliptical.
  • the present invention also provides an aircraft wing tip device, the aircraft wing tip device comprising a transition portion and a wing tip portion, the inner end portion of the transition portion being connected to the distal end of the aircraft wing, the outer side of the transition portion An end portion is coupled to the wing tip portion, wherein the wing tip portion includes a wing root and a wing tip, and a wing root of the wing tip portion is coupled to an outer end surface of the transition portion, the chord of the wing root The length is less than or equal to the chord length of the outer end surface of the transition portion.
  • the thickness of the wing tip is thinner than the transition.
  • the wing tip chord length of the wing tip is less than its wing root chord length. More specifically, the wing tip is a wing tip that tapers in length. More specifically, the transition portion is a transition portion in which the chord length is tapered.
  • the upper curved surface and the lower curved surface of the transition portion are smooth curved surfaces.
  • the transition is smoothly connected to the distal end of the aircraft wing.
  • the aircraft wing tip device is integrally formed with the aircraft wing.
  • the trailing edge line of the wing tip is aligned with the trailing edge line of the transition.
  • the starting end of the transition portion of the wing tip device is located at the extension of the wing along the span
  • chord length of the wing root of the wing tip is the chord length of the outer end of the transition portion
  • leading edge line of the wing tip is a conic line segment, a spline, a straight line or a broken line segment. More particularly, the conic line segments are parabolic, hyperbolic or elliptical.
  • the wing tip device of the present invention is arranged in a stepped manner, more than one cross section is added to the wing tip, so that the wing tip vortices induced by the wing tip mutually suppress each other, and the eddy current intensity is weakened, thereby achieving the drag reducing effect.
  • the wing root bending moment increment of the present invention is small, thereby reducing the structural weight of the aircraft and having less influence on the flutter characteristics.
  • Figure 1 is a front elevational view of an embodiment of a trailing edge aligned winglet of the present invention
  • Figure 2 is a schematic view of the winglet shown in Figure 1;
  • Figure 3 is a front elevational view of an embodiment of a leading edge aligned winglet of the present invention
  • Figure 4 is a schematic view of the winglet as shown in Figure 3;
  • Figure 5 is a front elevational view of another embodiment of the winglet of the present invention, in which the stepped wing tip portion is disposed in the middle;
  • Figure 6 is a schematic view of the winglet as shown in Figure 5;
  • Figure 7 shows an embodiment of another trailing edge alignment winglet of the present invention, in which the wing chord length of the n+1th wing tip segment and the wing tip chord length of the nth wing tip segment are equal .
  • the aircraft wing tip device has a multi-step shape including a transition portion 1 and a wing tip portion 2, the inner end portion of the transition portion 1 and the aircraft the distal end of the wing 6 is connected, is connected to the outer portion 1 of the tip end portion of the transition portion 2, wherein said tip portion comprises a plurality of tip sections 3 n, respectively, each segment comprising wingtip wingtip 4 "and n-blade root 5, a tip of the first section 3, the wing root 5, and the transition portion connected to an outer end portion, and the rear edge of the outer end portion of said transition portion Aligned, the n+1th wing tip segment 3 n+I wing ⁇ 5 n+I is located on the wing tip 4 n of the nth wing tip segment 3 n , and the n+1th wing tip segment 3
  • the wing root of the 11+1 is 5 n+1 chord length smaller than the wing tip 4 n chord of the nth wing
  • the wing tip portion 2 is rearward The edge line is aligned with the trailing edge line of the transition portion 1.
  • the n+1th wing tip 3 n The thickness of +1 is thinner than the nth wing tip portion 3 n .
  • the chord length of the wing tip 4 of each wing tip section 3 is smaller than the chord length of its wing root 5, and forms a wing tip section 3 whose chord length is tapered.
  • the chord length of the wing root 5 of the first wing tip segment 3 is less than or equal to the chord length of the outer end portion of the transition portion 1.
  • the chord length of the inner end portion of the transition portion 1 is larger than the chord length of the outer end portion of the transition portion 1, and forms a transition portion 1 in which the chord length is tapered.
  • the upper curved surface and the lower curved surface of the transition portion 1 are smooth curved surfaces.
  • the transition 1 is smoothly connected to the distal end of the aircraft wing.
  • the aircraft wing tip device is integrally formed with the aircraft wing.
  • the starting end of the transition portion 1 of the wing tip device is located at 85%-100% of the extension of the wing along the span, and the wing tip portion 2 a wing root 5,
  • the chord length is 10% to 100% of the chord length of the outer end portion of the transition portion 1.
  • the wing tip device may also be in a single step shape, including a transition portion 1 and a wing tip portion 2, the inner end portion of the transition portion 1 being connected to the distal end of the aircraft wing 6
  • the outer end of the transition portion 1 is connected to the wing tip portion, wherein the wing tip portion 2 includes a wing root 5 and a wing tip 4, and the wing root 5 of the wing tip portion 2 is
  • the outer end surface of the transition portion 1 is connected and aligned with the rear edge of the outer end portion of the transition portion 1, and the chord length of the wing root 5 is smaller than the chord length of the outer end surface of the transition portion 1.
  • leading edge line of each wing tip section 3 of the wing tip portion 2 is a conic line segment, a spline, a straight line or a broken line segment. More particularly, the conic line segments are parabolic, hyperbolic or elliptical. As shown in Fig. 1, in one embodiment of the invention, the leading edge of each wing tip section 3 of the wing tip portion 2 is a circular curve line segment.
  • the wing root 5t of the first wing tip segment 3t may also be aligned with the leading edge of the outer end portion of the transition portion 1. At this time, the leading edge line of the wing tip portion 2 is aligned with the leading edge line of the transition portion 1.
  • each wing tip section 3 of the wing tip portion 2 is a conic line segment, a spline, a straight line or a broken line segment. More particularly, the conic line segments are parabolic, curved or elliptical. As shown in Fig. 3, in one embodiment of the invention, the trailing edge line of each wing tip section 3 of the wing tip portion 2 is a straight line.
  • the wing tip portion 2 may be disposed in the middle of the outer end portion of the transition portion 1, that is, the first wing tip portion
  • the wing root 5 of 3! is neither aligned with the leading edge of the outer end portion of the transition portion 1, nor is it aligned with the trailing edge of the outer end portion of the transition portion 1.
  • the leading edge line and the trailing edge line of each wing tip section of the wing tip portion 2 may be a conic line segment, a spline line, a straight line or a broken line segment, respectively, and more particularly, the conic line segment is Parabolic, hyperbolic or elliptical.
  • the leading edge line and the trailing edge line may be of the same type of line segment, or different types of line segments may be used. 5 and 6, in one embodiment of the present invention, the trailing edge line of the wing tip section 3 of the wing tip portion 2 is a straight line, and the leading edge line is a conic section.
  • FIG. 3-6 can also be applied to a single stepped winglet, and the setting method thereof is similar to that of the above-described multi-stepped winglet, and details are not described herein again.
  • n-1 wing tip segment 3 n+1 has a wing root 5 n+1 chord length and the nth wing tip segment 3 n has a wing tip 4 n chord length equal, in this case, at each wing tip segment
  • the joint cuts the chord length, so it can still produce a stepped shape.

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Description

飞机翼尖装置
技术领域
本发明涉及一种飞机机翼的翼尖装置。 背景技术
飞机维持正常飞行时所需的升力是靠机翼上下表面的压力差产生的，由 于上下表面压差的存在， 翼尖附近机翼下表面空气会绕流到上表面， 形成翼 尖涡， 致使翼尖附近区域机翼上下表面的压差降低， 从而导致这一区域产生 的升力降低。
针对上述问题， 通常在飞机机翼翼尖上再设置翼尖小翼（winglet ) , 该 小翼的主要作用是在不增大机翼展长的前提下， 提高有效的展弦比。 这样机 翼的二维效应增强， 诱导阻力减小， 升力增加， 升阻比提高。 其次， 翼梢小 翼还能耗散翼尖涡， 减少对尾随飞行的小飞机的威胁。
然而， 飞机机翼一旦加装了翼尖小翼， 增加了翼尖小翼的重量。 机翼翼 端结构为了组装翼尖小翼会变得比较复杂， 也会增加一些额外的重量。 翼尖 小翼使机翼翼根弯矩和剪切载荷增大，还要导致机翼结构重量的增加。而且， 翼尖小翼设计得不好， 飞机的分离特性、 颤振特性也会随之变差。
近几十年来，世界各个航空工业发达国家都在为研制翼尖装置而不懈努 力， 并设计出了各种不同类型的翼尖装置。
根据翼尖装置的形状， 目前国际上有几类： 一种是翼尖帆， 或称上反式 翼尖小翼。 这种式样的翼尖小翼一般具有三段式的结构， 即具有安装段、 圆 弧过渡段和直板段， 这种翼尖装置有比较明显的弯曲翼片， 在实际应用中， 波音公司 ( Boeing )生产的 747-400型飞机和空中客车 ( Airbus )的 A330和 A340系列飞机都使用了这样的翼尖装置。 另外在如波音 727、 波音 757和波 音 767飞机进行改装时， 也会安装这种翼尖装置。
另一种是三角形翼尖帆，这种形式的翼尖帆在空中客车 A320系列、 A310 和 A380中运用， 这种类型的翼尖装置也可说是空中客车飞机的标准形式。
另外， 波音新设计的客机如波音 777、 波音 787、 波音 747-8都以特殊的 鲨鱼鰭式翼尖装置 （ raked winglet ) 来代替翼尖帆。
虽然上反式翼尖小翼和翼尖帆都有明显的减阻效果，但是无论是翼尖小 翼还是翼尖帆， 它们翼根的弯矩都较大， 这就增加了其自身的结构重量， 并 对飞机的颤振特性产生一定影响。
因此， 人们希望能在保持翼尖装置气动特性的同时， 减少翼尖装置的重 量， 降低因安装翼尖装置所带来的弯矩重量增加和对颤振特性的影响。 发明内容
本发明的目的在于提供一种翼尖装置，其能够在保持翼尖装置气动特性 的同时， 减少翼尖装置的重量。
为实现上述目的， 本发明提供一种飞机翼尖装置， 所述飞机翼尖装置包 括过渡部和翼尖部， 所述过渡部的内侧端部与飞机机翼的远端连接， 所述过 渡部的外侧端部与所述翼尖部连接， 其中， 所述翼尖部包括多个翼尖段， 每 个翼尖段都分别包括翼尖和翼根， 所述第一个翼尖段的翼根与所述过渡部的 外侧端部连接， 第 n+1个翼尖段的翼根位于第 n个翼尖段的翼尖上， 并且所 述第 n+1个翼尖段的翼根弦长小于等于第 n个翼尖段的翼尖弦长，其中 n>0。
在本发明中， 将飞机每个翼尖段中的顶部称作为 "翼尖" ， 将飞机每个 翼尖段的底部称作为 "翼根" 。 另外， 在本发明中， 所述翼尖段可以设置在 过渡部外侧的任何位置， 例如可以与所述过渡部外侧端部的后缘对齐， 或者 与所述过渡部外侧端部的前缘对齐， 或者设置在所述过渡部外侧端部的前缘 和后缘之间。
特别地， 所述第 n+1个翼尖段的厚度薄于所述第 n个翼尖段。
特別地，所述每个翼尖段的翼尖的弦长都小于其翼根的弦长。更特别地， 所述每个翼尖段都为弦长渐缩的翼尖段。
特别地， 所述第一个翼尖段的翼根的弦长小于等于所述过渡部的外侧端 部的弦长。
特别地， 所述过渡部的内侧端部弦长大于所述过渡部的外侧端部弦长。 特别地， 所述过渡部为弦长渐缩的过渡部。
特别地， 所述过渡部的上曲面和下曲面为光滑曲面。
特别地， 所述过渡部与所述飞机机翼的远端光滑连接。
特别地， 所述飞机翼尖装置与所述飞机机翼一体成型。
特别地， 所述翼尖部的后缘线和所述过渡部的后缘线对齐。 特别地， 所述翼尖装置的过渡部的起始端位于所述机翼沿展向的展长的
85%- 100%。
特别地， 所述翼尖部的第一段翼根的弦长为所述过渡部外侧端部弦长的 10%- 100%。
特别地， 所述翼尖部的每个翼尖段的前缘线是圓锥曲线线段、 样条线、 直线或折线段。 更特别地， 所述圆锥曲线线段是抛物线、 双曲线或椭圆。
另外， 本发明还提供一种飞机翼尖装置， 所述飞机翼尖装置包括过渡部 和翼尖部， 所述过渡部的内侧端部与飞机机翼的远端连接， 所述过渡部的外 侧端部与所述翼尖部连接， 其特征在于， 所述翼尖部包括翼根和翼尖， 所述 翼尖部的翼根与所述过渡部的外侧端面连接， 所述翼根的弦长小于等于所述 过渡部外侧端面的弦长。
特别地， 所述翼尖部的厚度薄于所述过渡部。
特别地， 所述翼尖部的翼尖弦长小于其翼根弦长。 更特别地， 所述翼尖 部为弦长渐缩的翼尖部。 ' 更特别地， 所述过渡部为弦长渐缩的过渡部。
特比地， 所述过渡部的上曲面和下曲面为光滑曲面。
特别地， 所述过渡部与所述飞机机翼的远端光滑连接。
特别地， 所述飞机翼尖装置与所述飞机机翼一体成型。
特别地， 所述翼尖部的后缘线和所述过渡部的后缘线对齐。
特别地， 所述翼尖装置的过渡部的起始端位于所述机翼沿展向的展长的
85%- 100%。
特别地， 所述翼尖部的翼根的弦长为所述过渡部外侧端部弦长的
10%- 100%。
特别地， 所述翼尖部的前缘线是圓锥曲线线段、样条线、直线或折线段。 更特别地， 所述圆锥曲线线段是抛物线、 双曲线或椭圓。
由于本发明的翼尖装置呈阶梯状设置， 所以其翼尖上增加了一个以上的 间断面， 从而使翼尖诱导出的翼尖涡互相抑制， 减弱了涡流强度， 从而达到 了减阻效果， 另外， 本发明的翼根弯矩增量较小， 从而减轻了飞机的结构重 量， 对颤振特性影响也较小。 附图说明
图 1是本发明的一个后缘对齐的小翼实施例的主视图；
图 2是如图 1所示小翼的示意图；
图 3是本发明的一个前缘对齐的小翼实施例的主视图；
图 4是如图 3所示小翼的示意图；
图 5是本发明另一个小翼实施例的主视图， 在该实施例中， 所述阶梯状 翼尖部设置在中间；
图 6是如图 5所示的小翼的示意图；
图 7示出了本发明另一个后缘对齐小翼的实施例， 在该实施例中， 第 n+1个翼尖段的翼根弦长和第 n个翼尖段的翼尖弦长相等。 具体实施方式
如图 1和图 2所示， 在本发明的一个实施例中， 飞机翼尖装置呈多阶梯 形状， 其包括过渡部 1和翼尖部 2 , 所述过渡部 1的内侧端部与飞机机翼 6 的远端连接， 所述过渡部 1的外侧端部与所述翼尖部 2的连接， 其中， 所述 翼尖部包括多个翼尖段 3n， 每个翼尖段都分别包括翼尖 4„和翼根 5n, 所述 第一个翼尖段 3 ,的翼根 5,与所述过渡部 1的外侧端部连接， 并且与所述过 渡部 1外侧端部的后缘对齐， 第 n+1个翼尖段 3n+I的翼才艮 5n+I位于第 n个翼 尖段 3n的翼尖 4n上， 并且所述第 n+1个翼尖段 311+1的翼根 5n+1弦长小于第 n 个翼尖段 3n的翼尖 4n弦长， 其中 n>0。 另外， 如图 1所示， 所述翼尖部 2 的后缘线和所述过渡部 1的后缘线对齐。 （图 2中需要增加标示 3„和 3n+1 ) 在本发明的优选实施例中， 所述第 n+1个翼尖部 3n+1的厚度薄于所述第 n个翼尖部 3n。 所述每个翼尖段 3的翼尖 4的弦长都小于其翼根 5的弦长， 并形成弦长渐缩的翼尖段 3。所述第一个翼尖段 3 ,的翼根 5 ,的弦长小于等于 所述过渡部 1的外侧端部的弦长。 所述过渡部 1的内侧端部弦长大于所述过 渡部 1的外侧端部弦长， 并形成弦长渐缩的过渡部 1。 所述过渡部 1的上曲 面和下曲面为光滑曲面。 所述过渡部 1与所述飞机机翼的远端光滑连接。 所 述飞机翼尖装置与所述飞机机翼一体成型。
另外， 在本发明的一个优选实施例中， 所述翼尖装置的过渡部 1的起始 端位于所述机翼沿展向的展长的 85%-100% , 所述翼尖部 2的第一段翼根 5, 的弦长为所述过渡部 1的外侧端部弦长的 10%-100%。
在本发明的另一实施例中， 所述翼尖装置也可以呈单阶梯形状， 包括过 渡部 1和翼尖部 2 , 所述过渡部 1的内侧端部与飞机机翼 6的远端连接， 所 述过渡部 1的外侧端部与所述翼尖部连接， 其特征在于， 所述翼尖部 2包括 翼根 5和翼尖 4 , 所述翼尖部 2的翼根 5与所述过渡部 1的外侧端面连接， 并且与所述过渡部 1外侧端部的后缘对齐， 并且所述翼根 5的弦长小于所述 过渡部 1外侧端面的弦长。
另夕卜，所述翼尖部 2的每个翼尖段 3的前缘线是圆锥曲线线段、样条线、 直线或折线段。 更特别地， 所述圓锥曲线线段是抛物线、 双曲线或椭圆。 如 图 1所示， 在本发明的一个实施例中所述翼尖部 2每个翼尖段 3的前缘是圓 锥曲线线段。
如图 3和图 4所示， 在本发明的另一个实施例中， 所述第一个翼尖段 3 t 的翼根 5t还可以与所述过渡部 1外侧端部的前缘对齐。 此时， 所述翼尖部 2 的前缘线和所述过渡部 1的前缘线对齐。
另外，所述翼尖部 2的每个翼尖段 3的后缘线是圆锥曲线线段、样条线、 直线或折线段。 更特别地， 所述圓锥曲线线段是抛物线、 曲线或椭圓。 而 如图 3所示， 在本发明的一个实施例中， 所述翼尖部 2的每个翼尖段 3的后 缘线是直线。
另外， 如图 5和图 6所示， 在本发明的另一个实施例中， 所述翼尖部 2 可以设置在所述过渡部 1外侧端部的中间， 即所述第一个翼尖段 3 !的翼根 5,既不与所述过渡部 1外侧端部的前缘对齐， 也不与所述过渡部 1外侧端部 的后缘对齐。
此时， 所述翼尖部 2的每个翼尖段的前缘线和后缘线可以分别是圓锥曲 线线段、 样条线、 直线或折线段， 更特别地， 所述圆锥曲线线段是抛物线、 双曲线或椭圓。 所述前缘线和后缘线可以采用同一种类型的线段， 也可以采 用不同类型的线段。 而如图 5和图 6所示， 在本发明的一个实施例中所述翼 尖部 2的翼尖段 3的后缘线是直线， 前缘线是圆锥曲线段。
上述如图 3-6所述的设置方式也可以用于单阶梯状的小翼， 其设置方法 与上述多阶梯状小翼的类似， 在此不再赘述。
此外， 如图 7所示 （图中需要增加 4n ) , 在一个实施例中， 第 n+1个翼尖段 3n+1的翼根 5n+1弦长和第 n个翼尖段 3n的翼尖 4n弦长相等，在 这种情况中， 在每个翼尖段的连接处将弦长切割， 所以其还是可以产生阶梯 的形状。
本发明的技术内容及技术特点已揭示如上， 然而可以理解， 在本发明的 创作思想下， 本领域的技术人员可以对上述结构作各种变化和改进， 但都属 于本发明的保护范围。 上述实施例的描述是例示性的而不是限制性的， 本发 明的保护范围由权利要求所确定。

Claims

权利要求书
1. 一种飞机翼尖装置， 所述飞机翼尖装置包括过渡部和翼尖部， 所述过 渡部的内侧端部与飞机机翼的远端连接， 所述过渡部的外侧端部与所述翼尖 部连接， 其特征在于， 所述翼尖部包括多个翼尖段， 每个翼尖段都分别包括 翼尖和翼根，所述第一个翼尖段的翼根与所述过渡部的外侧端部连接，第 n+1 个翼尖段的翼根位于第 n个翼尖段的翼尖上， 并且所述第 n+1个翼尖段的翼 根弦长小于等于第 η个翼尖段的翼尖弦长， 其中 η>0。
2. 如权利要求 1所述的飞机翼尖装置，其特征在于， 所述第 n+1个翼尖 段的厚度薄于所述第 n个翼尖段。
3. 如权利要求 1所述的飞机翼尖装置， 其特征在于， 所述每个翼尖段的 翼尖的弦长都小于其翼根的弦长。
4. 如权利要求 3所述的飞机翼尖装置， 其特征在于， 所述每个翼尖段都 为弦长渐缩的翼尖段。
5. 如权利要求 1所述的飞机翼尖装置， 其特征在于， 所述第一个翼尖段 的翼根的弦长小于等于所述过渡部的外侧端部的弦长。
6. 如权利要求 1所述的飞机翼尖装置， 其特征在于， 所述过渡部的内侧 端部弦长大于所述过渡部的外侧端部弦长。
7. 如权利要求 5所述的飞机翼尖装置， 其特征在于， 所述过渡部为弦长 渐缩的过渡部。
8. 如权利要求 1所述的飞机翼尖装置， 其特征在于， 所述过渡部的上曲 面和下曲面为光滑曲面。
9. 如权利要求 1所述的飞机翼尖装置， 其特征在于， 所述过渡部与所述 飞机机翼的远端光滑连接。
10. 如权利要求 1所述的飞机翼尖装置， 其特征在于， 所述飞机翼尖装 置与所述飞机机翼一体成型。
11. 如权利要求 1所述的飞机翼尖装置， 其特征在于， 所述翼尖部的后 缘线和所述过渡部的后缘线对齐。
12. 如权利要求 1所述的飞机翼尖装置， 其特征在于， 所述翼尖装置的 过渡部的起始端位于所述机翼沿展向的展长的 85%-100%。
13. 如权利要求 1所述的飞机翼尖装置， 其特征在于， 所述翼尖部的第 一个翼尖段的翼根的弦长为所述过渡部外侧端部弦长的 10%-100%。
14. 如权利要求 1所述的飞机翼尖装置， 其特征在于， 所述翼尖部每个 翼尖段的前缘线是圆锥曲线线段、 样条线、 直线或折线段。
15. 如权利要求 14所述的飞机翼尖装置， 其特征在于， 所述圆锥曲线线 段是抛物线、 双曲线或椭圆。
16. 一种飞机翼尖装置， 所述飞机翼尖装置包括过渡部和翼尖部， 所述 过渡部的内侧端部与飞机机翼的远端连接， 所述过渡部的外侧端部与所述翼 尖部连接， 其特征在于， 所述翼尖部包括翼根和翼尖， 所述翼尖部的翼根与 所述过渡部的外侧端面连接， 所述翼根的弦长小于等于所述过渡部外侧端面 的弦长。
17. 如权利要求 16所述的飞机翼尖装置， 其特征在于， 所述翼尖部的厚 度薄于所述过渡部。
18. 如权利要求 16所述的飞机翼尖装置， 其特征在于， 所述翼尖部的翼 尖弦长小于其翼根弦长。
19. 如权利要求 18所述的飞机翼尖装置， 其特征在于， 所述翼尖部为弦 长渐缩的翼尖部。
20. 如权利要求 16所述的飞机翼尖装置， 其特征在于， 所述过渡部的内 侧端部弦长大于所述过渡部的外侧端部弦长。
21. 如权利要求 20所述的飞机翼尖装置， 其特征在于， 所述过渡部为弦 长渐缩的过渡部。
22. 如权利要求 16所述的飞机翼尖装置， 其特征在于， 所述过渡部的上 曲面和下曲面为光滑曲面。
23. 如权利要求 16所述的飞机翼尖装置， 其特征在于， 所述过渡部与所 述飞机机翼的远端光滑连接。
24. 如权利要求 16所述的飞机翼尖装置， 其特征在于， 所述飞机翼尖装 置与所述飞机机翼一体成型。
25. 如权利要求 16所述的飞机翼尖装置， 其特征在于， 所述翼尖部的后 缘线和所述过渡部的后缘线对齐。
26. 如权利要求 16所述的飞机翼尖装置， 其特征在于， 所述翼尖装置的 过渡部的起始端位于所述机翼沿展向的展长的 85%-100%。
27. 如权利要求 16所述的飞机翼尖装置， 其特征在于， 所述翼尖部的翼 根的弦长为所述过渡部外侧端部弦长的 10%-100%。
28. 如权利要求 16所述的飞机翼尖装置， 其特征在于， 所述翼尖部的 前缘线是圓锥曲线线段、 样条线、 直线或折线段。
29. 如权利要求 28所述的飞机翼尖装置， 其特征在于， 所述圆锥曲线线 段是抛物线、 汉曲线或橢圓。
PCT/CN2012/072188 2011-03-11 2012-03-12 飞机翼尖装置 WO2012122925A1 (zh)

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