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CN109110124A - A kind of new Main Rotor Blade - Google Patents

A kind of new Main Rotor Blade Download PDF

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Publication number
CN109110124A
CN109110124A CN201811022512.2A CN201811022512A CN109110124A CN 109110124 A CN109110124 A CN 109110124A CN 201811022512 A CN201811022512 A CN 201811022512A CN 109110124 A CN109110124 A CN 109110124A
Authority
CN
China
Prior art keywords
blade
airfoil
section
airfoil section
paddle
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.)
Pending
Application number
CN201811022512.2A
Other languages
Chinese (zh)
Inventor
刘勇
余瑾
邹茂真
陈立道
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.)
Nanjing University of Aeronautics and Astronautics
Original Assignee
Nanjing University of Aeronautics and Astronautics
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 Nanjing University of Aeronautics and Astronautics filed Critical Nanjing University of Aeronautics and Astronautics
Priority to CN201811022512.2A priority Critical patent/CN109110124A/en
Publication of CN109110124A publication Critical patent/CN109110124A/en
Pending legal-status Critical Current

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/32—Rotors
    • B64C27/46—Blades
    • B64C27/467—Aerodynamic features

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

Abstract

本发明公开了一种新型旋翼桨叶，包括桨叶，所述桨叶的根部设有桨根接头，所述桨根接头的一侧设有螺栓孔，且螺栓孔的内壁连接有剪力螺栓，桨根接头通过剪力螺栓连接有桨榖，所述桨叶的主翼型段包括第一翼型段、第二翼型段和第三翼型段，且桨叶展向内段的第一翼型段采用相对厚度较厚的OA212翼型，桨叶外段的第二翼型段采用了相对厚度较薄的OA209翼型，且第一翼型段和第二翼型段之间设有过渡段，所述桨叶的一端为削尖结构，且桨叶为非矩形桨叶。本发明能够有效提高桨叶的升阻比，提升旋翼的气动效率，在给定拉力的的情况下，降低旋翼的需用功率，使旋翼产生良好的悬停和前飞性能。

The invention discloses a novel rotor blade, comprising a blade, a blade root joint is arranged at the root of the blade, a bolt hole is arranged on one side of the blade root joint, and the inner wall of the bolt hole is connected with a shear bolt , the blade root joint is connected with the blade through the shear bolt, the main airfoil section of the blade includes the first airfoil section, the second airfoil section and the third airfoil section, and the first airfoil section of the blade spanwise inner section The airfoil section adopts a relatively thick OA212 airfoil, and the second airfoil section of the outer section of the blade adopts a relatively thin OA209 airfoil, and there is a space between the first airfoil section and the second airfoil section. In the transition section, one end of the paddle is a sharpened structure, and the paddle is a non-rectangular paddle. The invention can effectively improve the lift-drag ratio of the blade, improve the aerodynamic efficiency of the rotor, and reduce the required power of the rotor under the condition of a given pulling force, so that the rotor can produce good hovering and forward flying performance.

Description

A kind of new Main Rotor Blade
Technical field
The present invention relates to a kind of novel rotor blades.It is specifically a kind of to be suitable for rotor class aircraft or unmanned plane The Design of Rotor Aerodynamics Shape used.
Background technique
Common multi-rotor unmanned aerial vehicle blade aerodynamic shape is consistent from propeller shank to blade tip aerofoil profile, for manufacture work Skill etc. considers that the chord length of blade and torsion distribution are very simple, causes pneumatic efficiency low.Aerofoil profile selection is single, not to chord length It being distributed with pretwist and carries out Synthetical Optimization, pneumatic efficiency and power efficiency are low, and rotor noise and level of vibration are big, and Rotary wing performance rapid fluctuation declines under different revolving speeds, seriously affects the working performance of aircraft and the working life of rotor.
Multi-rotor unmanned aerial vehicle currently on the market mostly uses the propeller of geometric spacing, and pneumatic efficiency is low, when speed reaches When arriving or being more than rated speed, the maximum pull that can be provided reaches capacity, and ultimately limits effective load of multi-rotor unmanned aerial vehicle Lotus performance.
Summary of the invention
Technical problems based on background technology, the invention proposes a kind of new Main Rotor Blades.
A kind of new Main Rotor Blade proposed by the present invention, including blade, the root of the blade is equipped with blade root connector, described The side of blade root connector is equipped with bolt hole, and the inner wall of bolt hole is connected with shear studs, and blade root connector is connected by shear studs It is connected to paddle Grains, the main airfoil section of the blade includes the first airfoil section, the second airfoil section and third airfoil section, and blade exhibition is inside First airfoil section of the section OA212 aerofoil profile thicker using relative thickness, the second airfoil section of blade outer segment use relative thickness Relatively thin OA209 aerofoil profile, and changeover portion is equipped between the first airfoil section and the second airfoil section, one end of the blade is knot of fining away Structure, and blade is non-rectangle blade.
Preferably, first airfoil section is located at relative radius 0.18R-0.575R, and the second airfoil section is located at opposite half At diameter 0.625R-R, changeover portion is at relative radius 0.575R-0.625R, and the shape of changeover portion is by the first airfoil section and second The direct setting-out of airfoil section generates.
Preferably, the chord length of blade section root is 45mm, and chord length is 63mm, blade tip string at relative radius 0.3R A length of 30mm, and chord length is linear transitions between three characteristic faces.
Preferably, the blade uses the negative twister design of piecewise linearity: airfoil section root established angle is 5 degree, and opposite half Established angle is 9 degree at diameter 0.3R, and blade tip established angle is -5 degree, and established angle is linear transitions between three characteristic faces.
Preferably, the blade main force support structure is composite material, and the rotor revolving speed of blade is 3000RPM- 4600RPM。
The invention has the benefit that
The pneumatic design of blade is turned using the configuration of aerofoil profile multistage, blade negative twist and the design of the big taper of blade tip can be mentioned effectively The lift resistance ratio of high blade promotes the pneumatic efficiency of rotor, given pulling force in the case where, reduce the required horsepower of rotor, make Rotor generates good hovering and preceding winged performance.
Detailed description of the invention
Fig. 1 is a kind of isometric views of new Main Rotor Blade proposed by the present invention；
Fig. 2 is the top view and aerofoil profile segmentation diagram of a kind of new Main Rotor Blade proposed by the present invention；
Fig. 3 be a kind of blade of new Main Rotor Blade proposed by the present invention extend to chord length distribution；
Fig. 4 is that a kind of blade of new Main Rotor Blade proposed by the present invention is extended to pretwist distribution.
Specific embodiment
Following will be combined with the drawings in the embodiments of the present invention, and technical solution in the embodiment of the present invention carries out clear, complete Site preparation description, it is clear that described embodiments are only a part of the embodiments of the present invention, instead of all the embodiments.
Referring to Fig.1, the root of a kind of new Main Rotor Blade, including blade, the blade is equipped with blade root connector, the blade root The side of connector is equipped with bolt hole, and the inner wall of bolt hole is connected with shear studs, and blade root connector has by shearing force bolt connection Paddle Grains, the main airfoil section of the blade includes the first airfoil section, the second airfoil section and third airfoil section, and blade opens up inward segment The first airfoil section OA212 aerofoil profile thicker using relative thickness, it is relatively thin that the second airfoil section of blade outer segment uses relative thickness OA209 aerofoil profile, and changeover portion is equipped between the first airfoil section and the second airfoil section, blade quotes taper design, and uses Non-rectangle blade design.
Referring to Fig. 2, a kind of new Main Rotor Blade, the first airfoil section is located at relative radius 0.18R-0.575R, first wing The type section OA212 aerofoil profile thicker using relative thickness, the second airfoil section of blade outer segment are located at relative radius 0.625R-R, adopt It is the relatively thin OA209 aerofoil profile of relative thickness, also one section of changeover portion between two airfoil sections is in relative radius At 0.575R-0.625R, the shape of changeover portion is generated by the first airfoil section and the direct setting-out of the second airfoil section.
Referring to Fig. 3, a kind of new Main Rotor Blade, the chord length distribution of blade are as follows: the chord length of airfoil section root is 45mm, relatively Chord length is 63mm at radius 0.3R, and blade tip chord length is 30mm.Chord length is linear transitions between three characteristic faces.
Referring to Fig. 4, a kind of new Main Rotor Blade, blade uses the negative twister design of piecewise linearity: airfoil section root installation Angle is 5 degree, and established angle is 9 degree at relative radius 0.3R, and blade tip established angle is -5 degree, and established angle is linear between three characteristic faces Transition.
The foregoing is only a preferred embodiment of the present invention, but scope of protection of the present invention is not limited thereto, Anyone skilled in the art in the technical scope disclosed by the present invention, according to the technique and scheme of the present invention and its Inventive concept is subject to equivalent substitution or change, should be covered by the protection scope of the present invention.

Claims (5)

1.一种新型旋翼桨叶，包括桨叶，其特征在于，所述桨叶的根部设有桨根接头，所述桨根接头的一侧设有螺栓孔，且螺栓孔的内壁连接有剪力螺栓，桨根接头通过剪力螺栓连接有桨榖，所述桨叶的主翼型段包括第一翼型段、第二翼型段和第三翼型段，且桨叶展向内段的第一翼型段采用相对厚度较厚的OA212翼型，桨叶外段的第二翼型段采用了相对厚度较薄的OA209翼型，且第一翼型段和第二翼型段之间设有过渡段，所述桨叶的一端为削尖结构，且桨叶为非矩形桨叶。1. a novel rotor blade, comprising a paddle, is characterized in that, the root of the paddle is provided with a paddle root joint, one side of the paddle root joint is provided with a bolt hole, and the inner wall of the bolt hole is connected with a shear force bolt, the blade root joint is connected with the propeller through the shear bolt, the main airfoil section of the blade includes a first airfoil section, a second airfoil section and a third airfoil section, and the spanwise inner section of the blade is The first airfoil section adopts a relatively thick OA212 airfoil, the second airfoil section of the outer blade section adopts a relatively thin OA209 airfoil, and the gap between the first airfoil section and the second airfoil section is A transition section is provided, one end of the paddle is a sharpened structure, and the paddle is a non-rectangular paddle. 2.根据权利要求1所述的一种新型旋翼桨叶，其特征在于，所述第一翼型段位于相对半径0.18R-0.575R处，第二翼型段位于相对半径0.625R-R处，过渡段处于相对半径0.575R-0.625R处，过渡段的外形由第一翼型段和第二翼型段直接放样生成。2. A novel rotor blade according to claim 1, wherein the first airfoil segment is located at a relative radius of 0.18R-0.575R, the second airfoil segment is located at a relative radius of 0.625R-R, and the transition The segment is at a relative radius of 0.575R-0.625R, and the shape of the transition segment is directly lofted by the first airfoil segment and the second airfoil segment. 3.根据权利要求1所述的一种新型旋翼桨叶，其特征在于，所述桨叶翼型段根部的弦长为45mm，相对半径0.3R处弦长为63mm，桨尖弦长为30mm，且三个特征面之间弦长为线性过渡。3. a kind of novel rotor blade according to claim 1 is characterized in that, the chord length of the root of the airfoil section of the blade is 45mm, the chord length at the relative radius 0.3R is 63mm, and the tip chord length is 30mm , and the chord length between the three characteristic surfaces is a linear transition. 4.根据权利要求1所述的一种新型旋翼桨叶，其特征在于，所述桨叶采用了分段线性负扭转设计：翼型段根部安装角为5度，相对半径0.3R处安装角为9度，桨尖安装角为-5度，三个特征面之间安装角为线性过渡。4. a kind of novel rotor blade according to claim 1, is characterized in that, described blade adopts piecewise linear negative torsion design: airfoil section root installation angle is 5 degrees, and relative radius 0.3R place installation angle is 9 degrees, the installation angle of the propeller tip is -5 degrees, and the installation angle between the three characteristic surfaces is a linear transition. 5.根据权利要求1所述的一种新型旋翼桨叶，其特征在于，所述桨叶主承力结构均为复合材料，且桨叶的旋翼转速为3000RPM-4600RPM。5 . A novel rotor blade according to claim 1 , wherein the main load-bearing structures of the blade are all composite materials, and the rotor speed of the blade is 3000RPM-4600RPM. 6 .
CN201811022512.2A 2018-09-03 2018-09-03 A kind of new Main Rotor Blade Pending CN109110124A (en)

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Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN109896009A (en) * 2019-02-20 2019-06-18 顺丰科技有限公司 Propellers and UAVs
CN110525644A (en) * 2019-07-12 2019-12-03 天津曙光天成科技有限公司 Lifting airscrew blade tip structure, the production method of rotor and blade tip
CN112977814A (en) * 2021-03-04 2021-06-18 南京航空航天大学 Improved rotor pneumatic appearance suitable for small and medium-sized unmanned tilt rotor aircraft
CN114476001A (en) * 2022-02-23 2022-05-13 深圳市苇渡智能科技有限公司 Laminar flow airfoil blade structure, application method thereof and propeller
CN114560082A (en) * 2022-02-16 2022-05-31 西南科技大学 Combined modification type propeller tip structure capable of effectively controlling propeller tip vortex and design method
CN115384765A (en) * 2022-10-31 2022-11-25 四川蓉远地测科技有限公司 Rotor unmanned aerial vehicle driving device and assembling method thereof
CN115610648A (en) * 2022-11-01 2023-01-17 苏州览众科技有限公司 Variable speed rotor blades, coaxial unmanned helicopters and single rotor unmanned helicopters
US20250223025A1 (en) * 2024-01-04 2025-07-10 United States Of America As Represented By The Administrator Of Nasa Improved propeller

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Cited By (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN109896009A (en) * 2019-02-20 2019-06-18 顺丰科技有限公司 Propellers and UAVs
CN110525644A (en) * 2019-07-12 2019-12-03 天津曙光天成科技有限公司 Lifting airscrew blade tip structure, the production method of rotor and blade tip
CN112977814A (en) * 2021-03-04 2021-06-18 南京航空航天大学 Improved rotor pneumatic appearance suitable for small and medium-sized unmanned tilt rotor aircraft
CN112977814B (en) * 2021-03-04 2022-03-08 南京航空航天大学 Improved rotor pneumatic appearance suitable for small and medium-sized unmanned tilt rotor aircraft
CN114560082A (en) * 2022-02-16 2022-05-31 西南科技大学 Combined modification type propeller tip structure capable of effectively controlling propeller tip vortex and design method
CN114560082B (en) * 2022-02-16 2023-07-04 西南科技大学 Combined shape-modifying blade tip structure capable of effectively controlling blade tip vortex and design method
CN114476001A (en) * 2022-02-23 2022-05-13 深圳市苇渡智能科技有限公司 Laminar flow airfoil blade structure, application method thereof and propeller
CN115384765A (en) * 2022-10-31 2022-11-25 四川蓉远地测科技有限公司 Rotor unmanned aerial vehicle driving device and assembling method thereof
CN115610648A (en) * 2022-11-01 2023-01-17 苏州览众科技有限公司 Variable speed rotor blades, coaxial unmanned helicopters and single rotor unmanned helicopters
WO2024093481A1 (en) * 2022-11-01 2024-05-10 苏州览众科技有限公司 Variable-rotating-speed rotor blade, coaxial unmanned helicopter, and single-rotor unmanned helicopter
CN115610648B (en) * 2022-11-01 2024-12-17 苏州览众科技有限公司 Variable-rotation-speed rotor blade, coaxial unmanned helicopter and single-rotor unmanned helicopter
US20250223025A1 (en) * 2024-01-04 2025-07-10 United States Of America As Represented By The Administrator Of Nasa Improved propeller

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