WO2017070978A1 - 一种螺旋桨及飞行器 - Google Patents

一种螺旋桨及飞行器 Download PDF

Info

Publication number
WO2017070978A1
WO2017070978A1 PCT/CN2015/093836 CN2015093836W WO2017070978A1 WO 2017070978 A1 WO2017070978 A1 WO 2017070978A1 CN 2015093836 W CN2015093836 W CN 2015093836W WO 2017070978 A1 WO2017070978 A1 WO 2017070978A1
Authority
WO
WIPO (PCT)
Prior art keywords
blade
length
main body
propeller
root
Prior art date
Legal status (The legal status 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 status listed.)
Ceased
Application number
PCT/CN2015/093836
Other languages
English (en)
French (fr)
Inventor
李晓亮
梁智颖
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Autel Robotics Co Ltd
Original Assignee
Autel Robotics Co Ltd
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
Application filed by Autel Robotics Co Ltd filed Critical Autel Robotics Co Ltd
Publication of WO2017070978A1 publication Critical patent/WO2017070978A1/zh
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

Links

Images

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
    • B64C11/16—Blades
    • B64C11/18—Aerodynamic features

Definitions

  • the invention relates to the technical field of drones, in particular to a propeller and an aircraft.
  • the propeller is the power component that generates the lift, tension and operating force necessary for the UAV to fly. Increasing the efficiency of the propeller can greatly improve the flight performance of the UAV.
  • the existing propeller has large resistance and low efficiency, resulting in a small flying speed of the unmanned aerial vehicle and a short cruising distance.
  • the present invention is directed to overcoming the deficiencies of the prior art, providing an improved propeller having reduced drag and improved efficiency and an aircraft using the propeller.
  • the present invention provides the following technical solutions:
  • the root portion has a thickness greater than the body portion, and the root portion is provided with a reinforcing chamfer at the junction with the paddle.
  • the length L1 of the root portion is 22%-26% of the length L of the blade
  • the installation inclination angle of the root portion is 11-13°
  • the length L2 of the main body portion is the blade 62%-66% of the length L
  • the length L3 of the blade tip is 10%-12% of the blade length L.
  • the root portion has a length L1 of 25 mm to 35 mm
  • the body portion has a length of 73 mm to 83 mm
  • the body portion has a maximum leaf width of 29 mm to 33 mm.
  • the length of the root portion is 30 mm
  • the length of the main body portion is 78 mm
  • the maximum leaf width of the main body portion is 31 mm
  • the leaf width of the main body portion is 21 mm at a distance of 83 mm from the center of the paddle. .
  • the structural stiffness of the blade tapers in the first direction.
  • the paddle includes upper and lower blade faces, and a first side edge face and a second side edge face respectively connected between the upper and lower blade faces on both sides of the paddle,
  • the upper and lower leaf surfaces and the first side edge surface and the second side edge surface are smooth curved surfaces and smoothly transition between them.
  • the first side edge face includes a first protruding portion that protrudes outward
  • the second side edge face includes a second protruding portion that protrudes outward
  • the second protruding portion The degree of outward convexity is smaller than the first convex portion, and the first convex portion and the second convex portion are located at one end of the main body portion close to the root portion.
  • the present invention provides an aircraft comprising a fuselage, a flight control device disposed to the fuselage, and a propeller as described above, the flight control device for controlling rotation of the propeller.
  • the invention has the beneficial effects that the propeller is arranged in the ARA-D airfoil by the blade, and the length ratio of the root portion, the main body portion and the blade tip portion is set in a certain ratio, so that the whole of the propeller
  • the Reynolds number is the largest, and the air resistance is reduced, which increases the efficiency and thus improves the flying speed and flight distance of the UAV.
  • Figure 1 is a right side elevational view of a first embodiment of a propeller according to an embodiment of the present invention
  • Figure 2 is a front elevational view of the propeller shown in Figure 1;
  • FIG. 3 is a schematic cross-sectional view showing an ARA-D airfoil of a propeller according to an embodiment of the present invention
  • Figure 4 is a cross-sectional view taken along line A-A of Figure 2;
  • Figure 5 is a schematic view showing the structure of the root of the propeller shown in Figure 2;
  • FIG. 6 is a schematic structural view of a second embodiment of a propeller according to an embodiment of the present invention.
  • Fig. 7 is a schematic structural view of an unmanned aerial vehicle according to an embodiment of the present invention.
  • an embodiment of the present invention provides a propeller 100 including a paddle 110 and at least two blades 120 connected to the paddle 110; the airfoil of the blade 120 is ARA-D, paddle
  • the 110 includes a root portion 121, a body portion 122, and a blade tip portion 123 which are sequentially connected.
  • the root portion 121 and the body portion 122 are bounded by a broken line
  • the body portion 122 and the blade tip portion 123 are bounded by a broken line.
  • the paddle has a length L that is the length of the paddle 110 in a first direction from the center of the paddle to the most distal end of the blade tip 123.
  • the length L1 of the root portion 121 is 20% to 30% of the blade length L.
  • the length L1 of the root portion 121 is 20%, 22%, 24%, 26%, 28%, 30%, or the like of the blade length L.
  • the length L1 of the root portion 121 is the length from the center of the paddle to the most distal end of the root portion 121.
  • the mounting inclination angle ⁇ of the root portion 121 is 10-15°.
  • the mounting inclination angle ⁇ of the root portion 121 may be 10°, 11°, 12°, 13°, 14°, 15°; preferably, the mounting inclination angle of the root portion 121 is 12°.
  • the leaf width of the root portion 121 gradually increases in the first direction.
  • the length L2 of the main body portion 122 is 60% to 70% of the blade length L.
  • the length L2 of the main body portion 122 is 60%, 62%, 64%, 66%, 68%, 70%, or the like of the blade length L.
  • the length L2 of the main body portion 122 is the length from the closest end to the farthest end of the main body portion 122 from the center of the paddle, the leaf width of the main body portion 122 is gradually reduced in the first direction, and the minimum leaf width of the main body portion 122 is 55 of its maximum leaf width.
  • %-65% for example, the minimum leaf width of the main body portion 122 is 55%, 57%, 59%, 60%, 61%, 63%, 65%, etc. of the maximum leaf width.
  • the blade width of the body portion 122 varies smoothly along a first direction away from the center of the paddle.
  • the length L3 of the blade tip portion 123 is 8%-15% of the blade length L.
  • the length L3 of the blade tip portion 123 is 8%, 10%, 12%, 14%, 15%, etc. of the blade length L.
  • L L1 + L2 + L3.
  • the length L3 of the blade tip portion 123 is the length of the blade tip portion 123 from the closest end of the blade center to the most distal end thereof, and the blade width of the blade tip portion 123 is gradually reduced in the first direction.
  • the leaf width of the leaf tip portion 123 varies smoothly in the first direction, and the leaf distal end of the leaf tip portion has a width of zero.
  • the propeller 100 is disposed in the ARA-D airfoil by the blade 110, and the length ratio of the root portion 111, the main body portion 112, and the blade tip portion 113 is set in a certain ratio so that the overall Reynolds of the propeller 100 The largest number, less air resistance, increased efficiency, which increased the flight speed and flight distance of the UAV.
  • the root portion 121 has a thickness greater than the main body portion 122 and smoothly transitions from the root portion 121 to the main body portion 122.
  • the joint of the root portion 121 and the paddle 110 is provided with a reinforcing chamfer 130, and the reinforcing chamfer 130 further enhances the strength of the propeller 100. Thereby improving the stability of the propeller 100.
  • the length L1 of the root portion 121 is 22%-26% of the blade length L, for example, the length L1 of the root portion 121 is 22%, 23%, 24%, 25%, 26% of the blade length L; the root portion 121
  • the installation inclination angle ⁇ is 11°-13°, for example, the installation inclination angle ⁇ of the root portion 121 is 11°, 12°, 13°, etc.
  • the length of the main body portion 122 is 62%-66% of the blade length, for example, the main body portion
  • the length of 122 is 62%, 63%, 64%, 65%, 66%, etc. of the length of the blade;
  • the length of the blade tip 123 is 10%-12% of the length of the blade, and the length of the blade tip 123 is the blade. 10%, 11%, 12%, etc. of the length.
  • the length of the root portion 121 is 25 mm to 35 mm, for example, the length of the root portion 121 is 25 mm, 26 mm, 27 mm, 28 mm, 29 mm, 30 mm, 31 mm, 32 mm, 33 mm, 34 mm, 35 mm, etc., preferably, the length of the root portion 121 is 30 mm.
  • the length of the main body portion 122 is 73 mm to 83 mm, for example, the length of the main body portion 122 is 73 mm, 74 mm, 75 mm, 76 mm, 77 mm, 78 mm, 79 mm, 80 mm, 81 mm, 82 mm, 83 mm, etc., preferably, the length of the main body portion 122 is 78 mm; the maximum leaf width of the main body portion 122 is 29 mm - 33 mm, for example, the maximum leaf width of the main body portion 122 is 29 mm, 30 mm, 31 mm, 32 mm, 33 mm, or the like.
  • the leaf width of the body portion is 21 mm at a distance of 83 mm from the center of the paddle.
  • the structural stiffness of the blade 120 tapers in a first direction away from the center of the trowel.
  • the blade 120 includes upper and lower leaf surfaces 124, and a first side edge surface 125 and a second side edge surface 126, which are respectively connected between the upper and lower leaf surfaces 124 on both sides of the blade 120, and the leaf surface 124.
  • the first side edge surface 125 and the second side edge surface 126 are smooth curved surfaces with a smooth transition therebetween.
  • first side edge surface 125 includes a first protruding portion 125a that protrudes outward
  • second side edge 126 includes a second protruding portion 126a that protrudes outward
  • the second protruding portion 126a is convex outward.
  • the extent of the exit is smaller than the first projection 125a, and the first projection 125a and the second projection 126a are both located at one end of the main body portion 122 near the root 121 of the blade 120.
  • an embodiment of the present invention also proposes a second embodiment.
  • an embodiment of the present invention further provides an aircraft including a fuselage 200, a flight control device 300 disposed in the fuselage 200, and a propeller 100 as described above, and the flight control device 300 is configured to control the rotation of the propeller 100.
  • the body 200 includes a main housing 210 and four arms 220 connected to the main housing, and the four arms 220 are distributed in a crisscross pattern.

Landscapes

  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Toys (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

一种螺旋桨及飞行器。螺旋桨（100）包括桨箍（110）及与桨箍相连的至少两个桨叶（120）；桨叶的翼型为ARA-D，桨叶由依次相连的根部（121）、主体部（122）和叶梢部（123）构成，根部的长度L1为桨叶长度L的20%-30%，根部的安装倾斜角度为10-15°，根部的叶宽沿第一方向逐渐增大；主体部的长度L2为桨叶长度L的60%-70%，主体部的叶宽沿第一方向逐渐减小，主体部的最小叶宽为其最大叶宽的55%-65%；叶梢部的长度L3＝(L-L1-L2)，叶梢部的叶宽沿第一方向逐渐减小。该螺旋桨减少了空气阻力，提高了效率，从而提高了飞行器的飞行速度和飞行距离。

Description

一种螺旋桨及飞行器 技术领域
本发明涉及无人机技术领域，尤其涉及一种螺旋桨及飞行器。
背景技术
螺旋桨是产生无人飞行器飞行所必需的升力、拉力和操作力的动力部件，提高螺旋桨的效率可以极大的改善无人飞行器的飞行性能。
现有的螺旋桨阻力大、效率低，导致无人飞行器的飞行速度小、续航距离短。
发明内容
本发明旨在克服现有技术中存在的缺陷，提供一种改进的、具有减小的阻力和提高的效率的螺旋桨及使用该螺旋桨的飞行器。
为解决上述技术问题，本发明提供以下技术方案：
一方面，本发明提供一种螺旋桨，包括桨箍及与所述桨箍相连的至少两个桨叶；所述桨叶的翼型为ARA-D，所述桨叶由依次相连的根部、主体部和叶梢部构成，所述根部的长度L1为桨叶长度L的20％-30％，所述桨叶长度L为所述桨叶在沿从所述桨箍中心至所述叶梢部最远端的第一方向上的长度，所述根部的安装倾斜角度为10-15°，所述根部的叶宽沿所述第一方向逐渐增大；所述主体部的长度L2为所述桨叶长度的60％-70％，所述主体部的叶宽沿所述第一方向逐渐减小，所述主体部的最小叶宽为其最大叶宽的55％-65％；所述叶梢部的长度L3为所述桨叶长度的8％-15％，并且满足L＝(L1+L2+L3)，所述叶梢部的叶宽沿所述第一方向逐渐减小。
一些实施例中，所述根部的厚度大于所述主体部，所述根部与所述桨箍的连接处设置有加强倒角。
一些实施例中，所述根部的长度L1为所述桨叶长度L的22％-26％，所述根部的安装倾斜角度为11-13°，所述主体部的长度L2为所述桨叶长度L的62％-66％，所述叶梢部的长度L3为所述桨叶长度L的10％-12％。
一些实施例中，所述根部的长度L1为25mm-35mm，所述主体部的长度为73mm-83mm，所述主体部的最大叶宽为29mm-33mm。
优选地，所述根部的长度为30mm，所述主体部的长度为78mm，所述主体部的最大叶宽为31mm，在距离所述桨箍中心83mm处，所述主体部的叶宽为21mm。
一些实施例中，所述桨叶的结构刚度沿所述第一方向逐渐缩小。
一些实施例中，所述桨叶包括上下两叶面，以及分别在所述桨叶的两侧连接于所述上下两叶面之间的第一侧缘面和第二侧缘面，所述上下两叶面及所述第一侧缘面和所述第二侧缘面均为光滑曲面并且它们之间平滑过渡。
一些实施例中，所述第一侧缘面包括向外凸出的第一凸出部，所述第二侧缘面包括向外凸出的第二凸出部，所述第二凸出部向外凸出的程度小于所述第一凸出部，所述第一凸出部和所述第二凸出部位于所述主体部上靠近所述根部的一端。
一些实施例中，所述桨叶有两个，所述两个桨叶关于所述桨箍的中心呈中心对称。
另一方面，本发明提供一种飞行器，包括机身、设置于所述机身的飞行控制装置和如上所述的螺旋桨，所述飞行控制装置用于控制所述螺旋桨旋转。
与现有技术相比，本发明的有益效果在于：该螺旋桨通过桨叶设置成ARA-D翼型，以及按照一定的比例设置根部、主体部和叶梢部的长度比例，使得该螺旋桨的整体雷诺数最大，并较少了空气阻力，提高了效率，从而提高了无人飞行器的飞行速度和飞行距离。
附图说明
为了更清楚地说明本发明的技术方案，下面将对实施方式中所需要使用的附图作简单地介绍，显而易见地，下面描述中的附图仅仅是本发明的一些实施方式，对于本领域普通技术人员来讲，在不付出创造性劳动的前提下，还可以根据这些附图获得其他的附图。
图1是本发明实施例的螺旋桨第一实施方式的右视图；
图2是图1所示的螺旋桨的主视图；
图3是本发明实施例的螺旋桨的ARA-D翼型截面示意图；
图4是图2中A-A处的剖视图；
图5是图2所示的螺旋桨的根部结构示意图；
图6是本发明实施例的螺旋桨第二实施方式的结构示意图；
图7是本发明实施例的无人飞行器的结构示意图。
具体实施方式
为了使本发明的目的、技术方案及优点更加清楚明白，以下结合附图及实施例，对本发明进行进一步详细说明。应当理解，此处所描述的具体实施例仅用以解释本发明，并不用于限定本发明。
参照图1至图5，本发明实施例提出了一种螺旋桨100，包括一桨箍110及与桨箍110相连的至少两个桨叶120；桨叶120的翼型为ARA-D，桨叶110包括依次相连的根部121、主体部122和叶梢部123，在图中，根部121与主体部122以虚线为界，主体部122与叶梢部123以虚线为界。
桨叶具有长度L，该长度为桨叶110在沿从桨箍中心至叶梢部123最远端的第一方向上的长度。
根部121的长度L1为桨叶长度L的20％-30％，例如，根部121的长度L1为桨叶长度L的20％、22％、24％、26％、28％、30％等。根部121的长度L1为桨箍中心至根部121最远端的长度。
根部121的安装倾斜角度β为10-15°。例如根部121的安装倾斜角度β可以为10°、11°、12°、13°、14°、15°；优选地，根部121的安装倾斜角度为12°。根部121的叶宽沿第一方向逐渐增大。
主体部122的长度L2为桨叶长度L的60％-70％。例如，主体部122的长度L2为桨叶长度L的60％、62％、64％、66％、68％、70％等。主体部122的长度L2为主体部122距桨箍中心最近端至最远端的长度，主体部122的叶宽沿第一方向逐渐缩小，主体部122的最小叶宽为其最大叶宽的55％-65％，例如主体部122的最小叶宽为其最大叶宽的55％、57％、59％、60％、61％、63％、65％等。优选地，主体部122的叶宽沿远离桨箍中心的第一方向平滑变化。
叶梢部123的长度L3为桨叶长度L的8％-15％，例如叶梢部123的长度L3为桨叶长度L的8％、10％、12％、14％、15％等。显然地，L＝L1+L2+L3。叶梢部123的长度L3为叶梢部123距桨箍中心最近端至其最远端的长度，叶梢部123的叶宽沿第一方向逐渐缩小。优选地，叶梢部123的叶宽沿第一方向平滑变化，且叶梢部最远端的叶宽为0。
螺旋桨100通过桨叶110设置成ARA-D翼型，以及按照一定的比例设置根部111、主体部112和叶梢部113的长度比例，使得螺旋桨100的整体雷诺 数最大，并较少了空气阻力，提高了效率，从而提高了无人飞行器的飞行速度和飞行距离。
优选地，根部121的厚度大于主体部122，且由根部121至主体部122平滑过渡，根部121与桨箍110的连接处设置有加强倒角130，加强倒角130进一步增强了螺旋桨100的强度，从而提高了螺旋桨100的稳定性。
进一步而言，根部121的长度L1为桨叶长度L的22％-26％，例如根部121的长度L1为桨叶长度L的22％、23％、24％、25％、26％；根部121的安装倾斜角度β为11°-13°，例如根部121的安装倾斜角度β为11°、12°、13°等；主体部122的长度为桨叶长度的62％-66％，例如主体部122的长度为桨叶长度的62％、63％、64％、65％、66％等；叶梢部123的长度为桨叶长度的10％-12％，叶梢部123的长度为桨叶长度的10％、11％、12％等。
具体地，根部121的长度为25mm-35mm，例如根部121的长度为25mm、26mm、27mm、28mm、29mm、30mm、31mm、32mm、33mm、34mm、35mm等，优选地，根部121的长度为30mm；主体部122的长度为73mm-83mm，例如主体部122的长度为73mm、74mm、75mm、76mm、77mm、78mm、79mm、80mm、81mm、82mm、83mm等，优选地，主体部122的长度为78mm；主体部122的最大叶宽为29mm-33mm，例如主体部122的最大叶宽为29mm、30mm、31mm、32mm、33mm等。
更优选地，在距离桨箍中心83mm处，主体部的叶宽为21mm。
进一步而言，桨叶120的结构刚度沿远离浆箍中心的第一方向逐渐缩小。
进一步参照图2，桨叶120包括上下两叶面124，以及分别在桨叶120的两侧连接于上下两叶面124之间的第一侧缘面125和第二侧缘面126，叶面124、第一侧缘面125和第二侧缘面126均为光滑曲面，且它们之间平滑过渡。
进一步而言，第一侧缘面125包括向外凸出的第一凸出部125a，第二侧缘126包括向外凸出的第二凸出部126a，第二凸出部126a向外凸出的程度小于第一凸出部125a，第一凸出部125a和第二凸出部126a均位于主体部122上靠近桨叶120的根部121的一端。
在本发明实施例的第一实施方式中，桨叶120有两个，两个桨叶120关于桨箍110的中心呈中心对称。
参照图6，本发明实施例还提出了第二实施方式，桨叶120有三个，三个桨叶120关于桨箍110的中心呈中心对称。
参照图7，本发明实施例还提出了一种飞行器，包括机身200、设置于机身200的飞行控制装置300和如上所述的螺旋桨100，飞行控制装置300用于控制螺旋桨100旋转。在本实施例中，机身200包括主壳体210和连接于主壳体的四个机臂220，四个机臂220呈十字交叉分布。
以上所述仅为本发明的较佳实施例而已，并不用以限制本发明，凡在本发明的精神和原则之内所作的任何修改、等同替换和改进等，均应包含在本发明的保护范围之内。

Claims (10)

  1. 一种螺旋桨，其特征在于，包括桨箍及与所述桨箍相连的至少两个桨叶；所述桨叶的翼型为ARA-D，所述桨叶由依次相连的根部、主体部和叶梢部构成，
    所述根部的长度L1为桨叶长度L的20％-30％，所述桨叶长度L为所述桨叶在沿从所述桨箍中心至所述叶梢部最远端的第一方向上的长度，所述根部的安装倾斜角度为10-15°，所述根部的叶宽沿所述第一方向逐渐增大；
    所述主体部的长度L2为所述桨叶长度L的60％-70％，所述主体部的叶宽沿所述第一方向逐渐减小，所述主体部的最小叶宽为其最大叶宽的55％-65％；
    所述叶梢部的长度L3为所述桨叶长度L的8％-15％，并且满足L＝(L1+L2+L3)，所述叶梢部的叶宽沿所述第一方向逐渐减小。
  2. 根据权利要求1所述的螺旋桨，其特征在于，所述根部的厚度大于所述主体部，所述根部与所述桨箍的连接处设置有加强倒角。
  3. 根据权利要求1所述的螺旋桨，其特征在于，所述根部的长度L1为所述桨叶长度L的22％-26％，所述根部的安装倾斜角度为11-13°，所述主体部的长度L2为所述桨叶长度L的62％-66％，所述叶梢部的长度L3为所述桨叶长度L的10％-12％。
  4. 根据权利要求1所述的螺旋桨，其特征在于，所述根部的长度为25mm-35mm，所述主体部的长度为73mm-83mm，所述主体部的最大叶宽为29mm-33mm。
  5. 根据权利要求4所述的螺旋桨，其特征在于，所述根部的长度L1为30mm，所述主体部的长度L2为78mm，所述主体部的最大叶宽为31mm，在距离所述桨箍中心83mm处，所述主体部的叶宽为21mm。
  6. 根据权利要求1所述的螺旋桨，其特征在于，所述桨叶的结构刚度沿所述第一方向逐渐缩小。
  7. 根据权利要求1所述的螺旋桨，其特征在于，所述桨叶包括上下两叶面，以及分别在所述桨叶的两侧连接于所述上下两叶面之间的第一侧缘面和第二侧缘面，所述上下两叶面及所述第一侧缘面和所述第二侧缘面均为光滑曲面并且它们之间平滑过渡。
  8. 根据权利要求7所述的螺旋桨，其特征在于，所述第一侧缘面包括向外凸出的第一凸出部，所述第二侧缘面包括向外凸出的第二凸出部，所述第二凸出部向外凸出的程度小于所述第一凸出部，所述第一凸出部和所述第二凸出部位于所述主体部上靠近所述根部的一端。
  9. 根据权利要求1所述的螺旋桨，其特征在于，所述桨叶有两个，所述两个桨叶关于所述桨箍的中心呈中心对称。
  10. 一种飞行器，其特征在于，包括机身、设置于所述机身的飞行控制装置和如权利要求1-9任一项所述的螺旋桨，所述飞行控制装置用于控制所述螺旋桨旋转。
PCT/CN2015/093836 2015-10-27 2015-11-05 一种螺旋桨及飞行器 Ceased WO2017070978A1 (zh)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
CN201510706722.3 2015-10-27
CN201510706722.3A CN105235893B (zh) 2015-10-27 2015-10-27 一种螺旋桨及飞行器

Publications (1)

Publication Number Publication Date
WO2017070978A1 true WO2017070978A1 (zh) 2017-05-04

Family

ID=55033809

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/CN2015/093836 Ceased WO2017070978A1 (zh) 2015-10-27 2015-11-05 一种螺旋桨及飞行器

Country Status (2)

Country Link
CN (1) CN105235893B (zh)
WO (1) WO2017070978A1 (zh)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN109969389A (zh) * 2017-12-28 2019-07-05 昆山优尼电能运动科技有限公司 一种桨叶连接结构
CN110337404A (zh) * 2018-05-28 2019-10-15 深圳市大疆创新科技有限公司 螺旋桨组件、动力组件及飞行器

Families Citing this family (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN205345320U (zh) * 2016-01-27 2016-06-29 深圳市大疆创新科技有限公司 螺旋桨、动力组件及飞行器
CN205524940U (zh) * 2016-02-29 2016-08-31 深圳市大疆创新科技有限公司 螺旋桨、动力组件及飞行器
CN107434038A (zh) * 2016-05-25 2017-12-05 天津宏宇天翔科技有限公司 一种无人机旋翼
CN106628112A (zh) * 2017-01-16 2017-05-10 顺丰科技有限公司 机翼
CN106938696B (zh) * 2017-02-20 2019-08-13 西安爱生技术集团公司 一种马刀型低噪声螺旋桨桨叶设计方法
CN109071006B (zh) * 2017-12-26 2022-04-08 深圳市大疆创新科技有限公司 螺旋桨、动力组件及飞行器
CN209241318U (zh) * 2018-08-28 2019-08-13 深圳市道通智能航空技术有限公司 螺旋桨、动力组件及无人机
CN110750839A (zh) * 2019-08-26 2020-02-04 深圳市道通智能航空技术有限公司 一种螺旋桨翼型的设计方法及终端设备

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4455003A (en) * 1977-03-23 1984-06-19 Vfw Supercritical air-foil profile
US4773825A (en) * 1985-11-19 1988-09-27 Office National D'etudes Et De Recherche Aerospatiales (Onera) Air propellers in so far as the profile of their blades is concerned
US20120189457A1 (en) * 2011-01-25 2012-07-26 Occhipinti Anthony C Propeller slipstream enhancer
CN202642093U (zh) * 2012-04-10 2013-01-02 深圳市大疆创新科技有限公司 螺旋桨及具有该螺旋桨的飞行器
CN203558202U (zh) * 2013-09-27 2014-04-23 保利科技（珠海）有限公司 螺旋桨及具有该螺旋桨的飞行器
CN203996873U (zh) * 2014-07-30 2014-12-10 深圳市大疆创新科技有限公司 飞行器及其螺旋桨
CN104583073A (zh) * 2013-05-31 2015-04-29 深圳市大疆创新科技有限公司 自紧固旋翼

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB190664A (en) * 1922-02-13 1922-12-28 Robert Leparmentier Improvements in variable pitch screw propellers for aerial machines
CN203486144U (zh) * 2013-09-25 2014-03-19 重庆金泰航空工业有限公司 农用无人飞行器
CN204173156U (zh) * 2014-08-25 2015-02-25 深圳市兴天翼科技有限公司 螺旋桨

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4455003A (en) * 1977-03-23 1984-06-19 Vfw Supercritical air-foil profile
US4773825A (en) * 1985-11-19 1988-09-27 Office National D'etudes Et De Recherche Aerospatiales (Onera) Air propellers in so far as the profile of their blades is concerned
US20120189457A1 (en) * 2011-01-25 2012-07-26 Occhipinti Anthony C Propeller slipstream enhancer
CN202642093U (zh) * 2012-04-10 2013-01-02 深圳市大疆创新科技有限公司 螺旋桨及具有该螺旋桨的飞行器
CN104583073A (zh) * 2013-05-31 2015-04-29 深圳市大疆创新科技有限公司 自紧固旋翼
CN203558202U (zh) * 2013-09-27 2014-04-23 保利科技（珠海）有限公司 螺旋桨及具有该螺旋桨的飞行器
CN203996873U (zh) * 2014-07-30 2014-12-10 深圳市大疆创新科技有限公司 飞行器及其螺旋桨

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN109969389A (zh) * 2017-12-28 2019-07-05 昆山优尼电能运动科技有限公司 一种桨叶连接结构
CN110337404A (zh) * 2018-05-28 2019-10-15 深圳市大疆创新科技有限公司 螺旋桨组件、动力组件及飞行器

Also Published As

Publication number Publication date
CN105235893A (zh) 2016-01-13
CN105235893B (zh) 2018-01-16

Similar Documents

Publication Publication Date Title
WO2017070978A1 (zh) 一种螺旋桨及飞行器
CN205345321U (zh) 螺旋桨、动力套装及无人飞行器
CN107428410B (zh) 与机身集成的螺旋桨驱动的推进系统
WO2017070980A1 (zh) 一种螺旋桨及飞行器
CN205554565U (zh) 螺旋桨、动力组件及飞行器
CN106184710B (zh) 飞机机翼的翼尖装置
CN206141830U (zh) 螺旋桨、动力套装及无人飞行器
EP3168459A1 (en) Vortex generator, wind turbine blade, and wind turbine power generating apparatus
CN103171766A (zh) 短距起降无人飞翼
CN107757871B (zh) 一种轻小型固定翼无人机用翼型
US6899525B2 (en) Blade and wing configuration
CN104044736A (zh) 无人直升机旋翼桨尖
JP3472799B2 (ja) ブレード用翼型
CN102167152B (zh) 前缘对齐的飞机翼尖装置
CN207000809U (zh) 桨叶、螺旋桨、动力套装及无人飞行器
CN205366050U (zh) 一种固定翼无人飞行器
CN209905055U (zh) 一种旋翼桨及无人机
JP2002166891A (ja) ブレード用高性能翼型
CN217416091U (zh) 一种用于飞行器的机翼及配备有该机翼的飞行器
CN206344996U (zh) 螺旋桨翼片
CN103569351B (zh) 具有双后掠角前缘的鸭翼
CN102167153B (zh) 后缘对齐的飞机翼尖装置
CN106741858A (zh) 螺旋桨翼片
CN206202683U (zh) 多旋翼机桨叶以及多旋翼机
CN206202682U (zh) 桨叶、螺旋桨、动力套装及无人飞行器

Legal Events

Date Code Title Description
121 Ep: the epo has been informed by wipo that ep was designated in this application

Ref document number: 15907039

Country of ref document: EP

Kind code of ref document: A1

NENP Non-entry into the national phase

Ref country code: DE

122 Ep: pct application non-entry in european phase

Ref document number: 15907039

Country of ref document: EP

Kind code of ref document: A1