WO2024093481A1 - Pale de rotor à vitesse de rotation variable, hélicoptère sans pilote coaxial et hélicoptère sans pilote à rotor unique - Google Patents

Pale de rotor à vitesse de rotation variable, hélicoptère sans pilote coaxial et hélicoptère sans pilote à rotor unique Download PDF

Info

Publication number
WO2024093481A1
WO2024093481A1 PCT/CN2023/115622 CN2023115622W WO2024093481A1 WO 2024093481 A1 WO2024093481 A1 WO 2024093481A1 CN 2023115622 W CN2023115622 W CN 2023115622W WO 2024093481 A1 WO2024093481 A1 WO 2024093481A1
Authority
WO
WIPO (PCT)
Prior art keywords
blade
pitch
variable speed
speed rotor
tip
Prior art date
Application number
PCT/CN2023/115622
Other languages
English (en)
Chinese (zh)
Inventor
王玉林
李东达
董斌
Original Assignee
苏州览众科技有限公司
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 苏州览众科技有限公司 filed Critical 苏州览众科技有限公司
Publication of WO2024093481A1 publication Critical patent/WO2024093481A1/fr

Links

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
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/04—Helicopters
    • B64C27/06—Helicopters with single rotor
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/04—Helicopters
    • B64C27/08—Helicopters with two or more rotors
    • B64C27/10—Helicopters with two or more rotors arranged coaxially

Definitions

  • the present invention relates to the field of aircraft, and in particular to a variable speed rotor blade, a coaxial unmanned helicopter and a single-rotor unmanned helicopter.
  • Coaxial helicopters have the advantages of small size, no tail rotor, high hovering efficiency, etc., and are the most suitable layout form for lightweight and miniaturized unmanned helicopters.
  • Lightweight and miniature coaxial drones have certain advantages over multi-rotor drones in terms of portability, both in civil and military applications.
  • variable speed rotor blades of the light and micro coaxial UAVs in the prior art have a weak control torque under the effect of only cyclic pitch variation.
  • the main purpose of the present invention is to provide a variable speed rotor blade, a coaxial unmanned helicopter and a single-rotor unmanned helicopter to solve the problem of weak control torque of the variable speed rotor blade in the prior art under the action of only cyclic pitch change.
  • a variable speed rotor blade comprising: a blade root, a blade middle section and a blade tip connected in sequence, the pitch curve L of the variable speed rotor blade comprising a root pitch segment L1, a middle pitch segment L2 and a tip pitch segment L3 corresponding to the blade root, the blade middle section and the blade tip respectively, the pitch corresponding to the connection point of the middle pitch segment L2 and the tip pitch segment L3 is used as the standard pitch L4, and the pitch corresponding to each point in the tip pitch segment L3 is smaller than the standard pitch L4.
  • the tip corresponding to the outermost side of the blade tip has a maximum negative twist c, which is the difference between the pitch of the tip corresponding to the outermost side of the blade tip and the standard pitch L4, and the maximum negative twist c is between 1.6 inches and 2.2 inches.
  • the tip pitch segment L3 includes a first straight line segment L5.
  • the slope is between -10 and -20, and the pitch corresponding to the end of the first straight line segment L5 is the pitch of the tip corresponding to the outermost side of the blade tip.
  • the tip pitch segment L3 further includes a first arc transition segment L6 connected between the end of the middle pitch segment L2 and the starting end of the first straight segment L5.
  • the pitch corresponding to each point in the middle pitch section L2 is greater than the standard pitch L4.
  • connection point between the root and the middle section of the blade has a maximum positive twist d, which is the difference between the pitch corresponding to the connection point between the root and the middle section of the blade and the standard pitch L4, and the maximum positive twist d is between 0.2 inches and 1.1 inches.
  • the middle pitch segment L2 includes a second straight line segment L7, the slope of the second straight line segment L7 is less than 0 and greater than or equal to -0.9, the pitch corresponding to the end of the second straight line segment L7 is the standard pitch L4, and the difference between the pitch corresponding to the starting end of the second straight line segment L7 and the standard pitch L4 is between 0.15-0.25.
  • the middle pitch segment L2 further includes a second arc transition segment L8 connected between the end of the root pitch segment L1 and the starting end of the second straight segment L7.
  • the portion of the variable speed rotor blade with a relative radius between 0 and 0.27 is the overhang e
  • the portion of the variable speed rotor blade with a relative radius between 0.27 and 0.4 corresponds to the blade root
  • the portion of the variable speed rotor blade with a relative radius between 0.4 and 0.75 corresponds to the middle section of the blade
  • the portion of the variable speed rotor blade with a relative radius between 0.75 and 1 corresponds to the blade tip.
  • the maximum value of the blade element angle of attack at the blade root is between 16° and 25°.
  • the pitch axis L9 of the variable speed rotor blade is between the first 35% and 47% of the average chord length of the variable speed rotor blade.
  • the airfoil of the variable speed rotor blade is an airfoil with a Reynolds number less than or equal to 10 6 .
  • the projection of the variable speed rotor blade in the reference plane is used as the blade plane.
  • the leading edge of the blade plan shape includes the root leading edge projection, the middle section leading edge projection and the tip leading edge projection corresponding to the blade root, the blade middle section and the blade tip respectively
  • the trailing edge of the blade plan shape includes the root trailing edge projection, the middle section trailing edge projection and the tip trailing edge projection corresponding to the blade root, the blade middle section and the blade tip respectively
  • the root leading edge projection and the root trailing edge projection are parallel to the pitch axis L9
  • the middle section leading edge projection and the tip leading edge projection are swept backward
  • the middle section trailing edge projection and the tip trailing edge projection are swept forward
  • the forward sweep angle of the tip trailing edge projection is smaller than the forward sweep angle of the middle section trailing edge projection.
  • the blade tip leading edge projection includes a third straight line segment and a third arc transition segment sequentially connected in a direction from the blade root to the blade tip.
  • a coaxial unmanned helicopter comprising: variable speed rotor blades, wherein the variable speed rotor blades are the variable speed rotor blades mentioned above.
  • the rotor solidity of the coaxial unmanned helicopter ranges from 0.98 to 1.1.
  • a single-rotor unmanned helicopter comprising: a variable speed rotor blade, wherein the variable speed rotor blade is the variable speed rotor blade mentioned above.
  • the rotor solidity of the single-rotor unmanned helicopter ranges from 0.49 to 0.55.
  • the pitch corresponding to each point in the tip pitch section L3 is smaller than the standard pitch L4, that is, the tip of the variable speed rotor blade has a larger negative twist and the blade element angle of attack is smaller, which makes the tip of the blade produce a larger change in lift coefficient during the cyclic pitch change, that is, a larger lift difference.
  • a lift difference provides the torque of the cyclic pitch change of the aircraft in forward flight, so the larger lift difference can improve the control ability of the cyclic pitch change.
  • FIG1 is a schematic diagram showing a three-dimensional structure of an embodiment of a variable speed rotor blade according to the present invention, wherein FIG1 shows blade elements at different radii;
  • FIG2 shows the blade plane shape of the variable speed rotor blade of FIG1 ;
  • FIG3 shows the blade plane shape of the variable speed rotor blade of FIG1 ;
  • FIG4 is a schematic diagram showing a pitch curve L of the variable speed rotor blade of FIG1 ;
  • FIG5 shows a pitch distribution diagram of the variable speed rotor blade of FIG1 after the coordinate system is transformed
  • FIG6 shows a lift coefficient curve corresponding to the airfoil of the variable speed rotor blade of FIG1 and other low Reynolds number airfoils
  • FIG7 shows a polar curve diagram corresponding to the airfoil of the variable speed rotor blade of FIG1 and other low Reynolds number airfoils
  • FIG8 shows an example rotor chord length distribution diagram of the variable speed rotor blade of FIG1 ;
  • FIG9 shows a distribution diagram of the vertical component of the slipstream at 0.65R downstream of the rotor blade disk of the variable speed rotor blade of FIG1 ;
  • FIG. 10 shows a curve diagram of the installation angle of the variable speed rotor blade of FIG. 1 ;
  • FIG. 11 shows a design flow chart of the variable speed rotor blades of FIG. 1 .
  • the above drawings include the following reference numerals: 10. Blade root; 11. Projection of the leading edge of the blade root; 12. Projection of the trailing edge of the blade root; 20. Middle section of the blade; 21. Projection of the leading edge of the middle section; 22, projection of the trailing edge of the middle section; 30, blade tip; 31, projection of the leading edge of the blade tip; 311, the third straight line segment; 312, the third arc transition segment; 32, projection of the trailing edge of the blade tip.
  • the variable speed rotor blade of this embodiment includes: a blade root 10, a blade middle section 20 and a blade tip 30 connected in sequence, and the pitch curve L of the variable speed rotor blade includes a root pitch segment L1, a middle pitch segment L2 and a tip pitch segment L3 corresponding to the blade root 10, the blade middle section 20 and the blade tip 30 respectively.
  • the pitch corresponding to the connection point of the middle pitch segment L2 and the tip pitch segment L3 is used as the standard pitch L4, and the pitch corresponding to each point in the tip pitch segment L3 is smaller than the standard pitch L4.
  • the pitch corresponding to each point in the tip pitch section L3 is smaller than the standard pitch L4, that is, the tip of the variable speed rotor blade has a larger negative twist and the blade element angle of attack is smaller, which makes the tip of the blade generate a larger lift coefficient during the periodic pitch change process.
  • Such a lift difference provides a moment of cyclic pitch change in the forward flight of the aircraft, so a larger lift difference can improve the control ability of cyclic pitch change.
  • the tip corresponding to the outermost side of the blade tip 30 has a maximum negative twist c, which is the difference between the pitch of the tip corresponding to the outermost side of the blade tip 30 and the standard pitch L4, and the maximum negative twist c is between 1.6 inches and 2.2 inches. If the maximum negative twist c is too small, the improvement in lift difference is not obvious, and the improvement in the control ability of cyclic pitch change is limited. If the maximum negative twist c is too large, the blade efficiency will be lost. Preferably, in this embodiment, the maximum negative twist c is 2 inches.
  • the tip pitch segment L3 includes a first straight segment L5, the slope of the first straight segment L5 is between -10 and -20 (i.e., linear negative torsion), and the pitch corresponding to the end of the first straight segment L5 is the pitch of the tip corresponding to the outermost side of the blade tip 30.
  • the above structure makes the slope of the first straight segment L5 larger, so that the blade element angle of attack is smaller, and further increases the lift difference, thereby improving the control ability of cyclic pitch change. It should be noted that if the slope of the first straight segment L5 is too small, it will affect the control ability of cyclic pitch change, and if the slope of the first straight segment L5 is too large, the blade efficiency will be lost.
  • the slope of the first straight line segment L5 is -14.2. It should be noted that when adjusting the blade element angle of attack, only the maximum negative twist amount c or only the slope of the first straight line segment L5 can be adjusted, or the maximum negative twist amount c and the first straight line segment L5 can be adjusted in combination. Compared with the two, the maximum negative twist amount c has a greater impact on the blade element angle of attack.
  • the tip pitch segment L3 also includes a first arc transition segment L6 connected between the end of the middle pitch segment L2 and the starting end of the first straight segment L5.
  • the above structure prevents the blade element angle of attack from changing suddenly, which is beneficial to subsequent lofting modeling.
  • the pitch corresponding to each point in the middle pitch section L2 is greater than the standard pitch L4, that is, the middle section 20 of the blade is positively twisted.
  • the closer to the blade root 10 the greater the pitch.
  • the closer to the blade root 10 the smaller the linear velocity, and the closer to the blade tip 30, the larger the linear velocity. Since the linear velocity at the blade root 10 is small, the lift is insufficient, so We increase the positive twist in the middle pitch section L2 connected to the blade root 10 in order to increase the angle of attack and thus enhance the lift.
  • the connection point between the blade root 10 and the blade middle section 20 has a maximum positive twist d, which is the difference between the pitch corresponding to the connection point between the blade root 10 and the blade middle section 20 and the standard pitch L4, and the maximum positive twist d is between 0.2 inches and 1.1 inches. If the maximum positive twist d is too small, the blade element angle of attack does not increase significantly, resulting in an insignificant lift effect. If the maximum positive twist d is too large, the resistance at the blade root 10 increases, which in turn causes the blade root 10 to stall. Preferably, in this embodiment, the maximum positive twist d is 1 inch.
  • the transitional modification is performed from the root of the propeller root 10 to the maximum pitch.
  • the blade root 10 and the blade midsection 20 are twisted, so that the vertical component of the slipstream downstream of the impeller disk is relatively evenly distributed from the blade root to 80% of the relative radius (r/R), thereby improving the efficiency of hovering and low-speed forward flight.
  • R is the distance between the center of rotation O and the tip of the blade tip 30.
  • the axis where the center of rotation O is located is the axis of rotation Q.
  • the middle pitch segment L2 includes a second straight segment L7, the slope of the second straight segment L7 is less than 0 and greater than or equal to -0.9 (i.e., linear negative torsion), the pitch corresponding to the end of the second straight segment L7 is the standard pitch L4, and the difference between the pitch corresponding to the starting end of the second straight segment L7 and the standard pitch L4 is between 0.15-0.25.
  • the above structure makes the second straight segment L7 as close to the standard pitch L4 as possible, thereby effectively inheriting the variable speed advantage of the standard pitch propeller.
  • the difference between the endpoint of L7 and L4 is 0.2.
  • the middle pitch segment L2 also includes a second arc transition segment L8 connected between the end of the root pitch segment L1 and the starting end of the second straight segment L7.
  • the above structure prevents the blade element angle of attack from changing suddenly, which is beneficial to subsequent lofting modeling.
  • variable speed rotor blade has nonlinear negative torsion as a whole. However, its overall size is small, and it is easy to manufacture using a composite material molding process, which is not difficult.
  • the portion of the variable speed rotor blade with a relative radius between 0 and 0.27 is the overhang e
  • the portion of the variable speed rotor blade with a relative radius between 0.27 and 0.4 corresponds to the blade root 10
  • the portion of the variable speed rotor blade with a relative radius between 0.4 and 0.75 corresponds to the blade middle section 20
  • the portion of the variable speed rotor blade with a relative radius between 0.75 and 1 corresponds to the blade tip 30.
  • the range of its installation angle from the relative radius 0.75 to the outermost side is 7.7 to 2.8 degrees. If the rotor is subjected to a cyclic pitch change of ⁇ 10 degrees.
  • the blade element angle of attack range of the blade tip 30 is between -7.2 and 17.7. According to Figure 6, in a cyclic pitch change, the blade tip portion will produce a larger lift coefficient change, that is, a larger lift difference. Such a lift difference provides a torque for the cyclic pitch change of the rotorcraft forward flight.
  • the overhang e is the distance between the center of rotation O and the vertical hinge P of the variable speed rotor blade.
  • FIG. 10 shows the installation angle curve of the variable speed rotor blade, which can be obtained by the pitch curve L of FIG. 4 and the formula
  • the relative radius of each blade element is r 1
  • the pitch is a 1
  • the installation angle is ⁇ .
  • the blade element installation angle curve is calculated through the pitch curve L, and then the plotting is performed.
  • the maximum value of the blade element angle of attack of the blade root 10 is between 16° and 25°. Too small a blade element angle of attack will result in insufficient lift, while too large a blade element angle of attack will increase the resistance of the blade root 10, leading to stall.
  • the maximum blade element angle of attack is not necessarily at the maximum pitch.
  • the pitch axis L9 of the variable speed rotor blade is between the first 35% and 47% of the average chord length of the variable speed rotor blade.
  • the above description refers to that in the direction from the leading edge to the trailing edge of the variable speed rotor blade, a point within the first 35% to 47% of the average chord length of the variable speed rotor blade is used as a reference point, and the pitch axis L9 is perpendicular to the chord length and passes through the reference point.
  • the above structure makes the pitch axis L9 near the aerodynamic center, so that the torque around the pitch axis L9 generated during the pitch change process is small, thereby reducing the load on the pitch change mechanism.
  • the pitch axis L9 of the blade is located at the front 46% of the average chord length.
  • the inventor found that the main reason for the insufficient endurance of light and micro coaxial drones is that the rotor blades are mostly model-grade blades, and the airfoils are mostly symmetrical airfoils without optimized design, resulting in low hovering efficiency and not suitable for variable speed control.
  • the airfoil of the variable speed rotor blade is an airfoil with a Reynolds number less than or equal to 10 6.
  • the airfoil of the variable speed rotor blade is NACA3412.
  • the airfoil of the variable speed rotor blade may also be an airfoil with a low Reynolds number such as Eppler387 or A18. The following is a detailed description of the airfoil selection method:
  • the lift coefficient curves and polar curves of several target airfoils should be compared.
  • the lift coefficient should have a larger angle of attack at the maximum lift coefficient.
  • the angle of attack of the NACA3412 airfoil at the maximum lift coefficient is greater than that of the other two airfoils.
  • the polar curve should have a larger opening, that is, at a smaller drag coefficient, there is a larger range of lift coefficient variation.
  • the polar curve of the NACA3412 airfoil has a larger opening. Therefore, this embodiment selects the NACA3412 airfoil as the airfoil for the variable speed rotor blade.
  • the projection of the variable speed rotor blade in the reference plane is used as the blade plane shape
  • the leading edge of the blade plane shape includes a root leading edge projection 11, a middle section leading edge projection 21 and a tip leading edge projection 31 corresponding to the blade root 10, the blade middle section 20 and the blade tip 30 respectively
  • the trailing edge of the blade plane shape includes a root trailing edge projection 12, a middle section trailing edge projection 22 and a tip trailing edge projection 32 corresponding to the blade root 10, the blade middle section 20 and the blade tip 30 respectively
  • the root leading edge projection 11 and the root trailing edge projection 12 are parallel to the variable pitch axis L9
  • the middle section leading edge projection 21 and the tip leading edge projection 31 are swept backward
  • the middle section trailing edge projection 22 and the tip trailing edge projection 32 are swept forward
  • the forward sweep angle of the tip trailing edge projection 32 is smaller than the forward sweep angle of the middle section trailing edge projection 22.
  • the difference in the vertical component of the slipstream downstream of the impeller disk can be reduced, so that the distribution of the vertical component of the slipstream downstream of the impeller disk from the root to 80% of the relative radius (r/R) is relatively uniform, thereby improving the efficiency of hovering and low-speed forward flight.
  • chord length of the blade gradually decreases from the blade root 10 to the blade tip 30 , which helps to reduce the rotor drag and blade tip loss.
  • the blade tip leading edge projection 31 includes a third straight line segment 311 and a third arc transition segment 312 sequentially connected in the direction from the blade root 10 to the blade tip 30.
  • the above structure reduces the chord length of the variable speed rotor blade, thereby reducing resistance; on the other hand, it has the effect of reducing noise.
  • FIG11 shows a design flow chart of the variable speed rotor blades of this embodiment.
  • the present application also provides a coaxial unmanned helicopter.
  • the coaxial unmanned helicopter includes a variable speed rotor blade, and the variable speed rotor blade is the above-mentioned variable speed rotor blade. Since the above-mentioned variable speed rotor blade has a strong control torque under the action of only cyclic pitch change, the coaxial unmanned helicopter having the same also has the above-mentioned advantages.
  • the rotor solidity of the coaxial unmanned helicopter ranges from 0.98 to 1.1.
  • the solidity is the ratio of the vertical projection area of a pair of blades to the area of the propeller disc. When the solidity is within this range, the rotor efficiency of the coaxial unmanned helicopter is the highest and the flight time is the longest.
  • the present application also provides a single-rotor unmanned helicopter.
  • the single-rotor unmanned helicopter includes a variable speed rotor blade, and the variable speed rotor blade is the above-mentioned variable speed rotor blade. Since the above-mentioned variable speed rotor blade has a strong control torque under the action of only cyclic pitch change, the single-rotor unmanned helicopter having the same also has the above-mentioned advantages.
  • the rotor solidity of the single-rotor unmanned helicopter ranges from 0.49 to 0.55. When the solidity is within this range, the rotor efficiency of the single-rotor unmanned helicopter is the highest and the flight time is the longest.
  • spatially relative terms such as “above”, “above”, “on the upper surface of”, “above”, etc. may be used here to describe the spatial positional relationship between a device or feature and other devices or features as shown in the figure. It should be understood that spatially relative terms are intended to include different orientations of the device in use or operation in addition to the orientation described in the figure. For example, if the device in the accompanying drawings is inverted, the device described as “above other devices or structures” or “above other devices or structures” will be positioned as “below other devices or structures” or “below other devices or structures”. Thus, the exemplary term “above” can include both “above” and “below”. The device can also be positioned in other different ways (rotated 90 degrees or in other orientations), and the spatially relative descriptions used here are interpreted accordingly.

Landscapes

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

Abstract

La présente invention concerne une pale de rotor à vitesse de rotation variable, un hélicoptère sans pilote coaxial et un hélicoptère sans pilote à rotor unique. La pale de rotor à vitesse de rotation variable comprend : une emplanture de pale (10), une section intermédiaire de pale (20) et une extrémité de pale (30) qui sont raccordées les unes après les autres. Une courbe de pas L de la pale de rotor à vitesse de rotation variable comprend une section pas d'emplanture L1, une section pas intermédiaire L2, et une section pas d'extrémité L3 correspondant respectivement à l'emplanture de pale (10), à la section intermédiaire de pale (20) et à l'extrémité de pale (30) ; un pas correspondant à un point raccordant la section pas intermédiaire L2 à la section pas d'extrémité L3 est utilisé en tant que pas standard L4 ; un pas correspondant à chaque point dans la section pas d'extrémité L3 est inférieur au pas standard L4. L'extrémité de pale (30) de la pale de rotor à vitesse de rotation variable présente une grande torsion négative, et l'angle d'attaque d'un élément pale est petit, de telle sorte que dans un processus de changement de pas cyclique, l'extrémité de pale (30) peut générer un grand changement du coefficient de portance, ce qui permet d'améliorer la capacité de réglage de changement de pas cyclique.
PCT/CN2023/115622 2022-11-01 2023-08-29 Pale de rotor à vitesse de rotation variable, hélicoptère sans pilote coaxial et hélicoptère sans pilote à rotor unique WO2024093481A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
CN202211358567.7A CN115610648A (zh) 2022-11-01 2022-11-01 变转速旋翼桨叶、共轴无人直升机及单旋翼无人直升机
CN202211358567.7 2022-11-01

Publications (1)

Publication Number Publication Date
WO2024093481A1 true WO2024093481A1 (fr) 2024-05-10

Family

ID=84877477

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/CN2023/115622 WO2024093481A1 (fr) 2022-11-01 2023-08-29 Pale de rotor à vitesse de rotation variable, hélicoptère sans pilote coaxial et hélicoptère sans pilote à rotor unique

Country Status (2)

Country Link
CN (1) CN115610648A (fr)
WO (1) WO2024093481A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN118246157A (zh) * 2024-05-29 2024-06-25 中国人民解放军陆军指挥学院 一种旋翼无人机的三维桨叶设计方法

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN115610648A (zh) * 2022-11-01 2023-01-17 苏州览众科技有限公司 变转速旋翼桨叶、共轴无人直升机及单旋翼无人直升机

Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN207631487U (zh) * 2017-12-21 2018-07-20 深圳市大疆创新科技有限公司 螺旋桨、动力组件及无人飞行器
CN207826548U (zh) * 2017-12-29 2018-09-07 江苏方阔航空科技有限公司 一种高效低噪旋翼
CN109110124A (zh) * 2018-09-03 2019-01-01 南京航空航天大学 一种新型旋翼桨叶
US10415581B1 (en) * 2018-04-25 2019-09-17 Brien Aven Seeley Ultra-quiet propeller system
CN110844064A (zh) * 2019-10-10 2020-02-28 中国直升机设计研究所 一种低雷诺数旋翼桨叶
CN112173075A (zh) * 2020-09-25 2021-01-05 中国直升机设计研究所 一种直升机低噪声旋翼桨叶气动外形
CN114228988A (zh) * 2021-11-26 2022-03-25 南昌三瑞智能科技有限公司 一种大推力高升阻比螺旋桨及该螺旋桨桨叶设计方法
CN115610648A (zh) * 2022-11-01 2023-01-17 苏州览众科技有限公司 变转速旋翼桨叶、共轴无人直升机及单旋翼无人直升机

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4248572A (en) * 1978-12-11 1981-02-03 United Technologies Corporation Helicopter blade
EP2253836A1 (fr) * 2009-05-18 2010-11-24 Lm Glasfiber A/S Pale d'éolienne
CN203685493U (zh) * 2013-12-26 2014-07-02 中国科学院工程热物理研究所 一种大厚度钝尾缘风力机叶片
FR3045564B1 (fr) * 2015-12-21 2018-08-17 Airbus Helicopters Pale de rotor d'aeronef a geometrie adaptee pour l'amelioration acoustique lors de vols d'approche et l'amelioration des performances en vols stationnaire et d'avancement

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN207631487U (zh) * 2017-12-21 2018-07-20 深圳市大疆创新科技有限公司 螺旋桨、动力组件及无人飞行器
CN207826548U (zh) * 2017-12-29 2018-09-07 江苏方阔航空科技有限公司 一种高效低噪旋翼
US10415581B1 (en) * 2018-04-25 2019-09-17 Brien Aven Seeley Ultra-quiet propeller system
CN109110124A (zh) * 2018-09-03 2019-01-01 南京航空航天大学 一种新型旋翼桨叶
CN110844064A (zh) * 2019-10-10 2020-02-28 中国直升机设计研究所 一种低雷诺数旋翼桨叶
CN112173075A (zh) * 2020-09-25 2021-01-05 中国直升机设计研究所 一种直升机低噪声旋翼桨叶气动外形
CN114228988A (zh) * 2021-11-26 2022-03-25 南昌三瑞智能科技有限公司 一种大推力高升阻比螺旋桨及该螺旋桨桨叶设计方法
CN115610648A (zh) * 2022-11-01 2023-01-17 苏州览众科技有限公司 变转速旋翼桨叶、共轴无人直升机及单旋翼无人直升机

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN118246157A (zh) * 2024-05-29 2024-06-25 中国人民解放军陆军指挥学院 一种旋翼无人机的三维桨叶设计方法

Also Published As

Publication number Publication date
CN115610648A (zh) 2023-01-17

Similar Documents

Publication Publication Date Title
WO2024093481A1 (fr) Pale de rotor à vitesse de rotation variable, hélicoptère sans pilote coaxial et hélicoptère sans pilote à rotor unique
CN108163192B (zh) 一种高效低噪旋翼
JP5078883B2 (ja) 高速回転翼航空機のロータブレード
JP2933949B2 (ja) ヘリコプタ用ロータ・ブレード、ヘリコプタ用メイン・ロータ及びヘリコプタ
JP3998103B2 (ja) 航空機のロータ用のブレードプロフィルおよびこのプロフィルを有するロータ用のブレード
JP2583603B2 (ja) シュラウド付きプロペラ羽根、シュラウド付きプロペラ、及び回転翼航空機用尾部回転翼装置
CN207826548U (zh) 一种高效低噪旋翼
CN109969425B (zh) 一种针对复合推力构型直升机的两侧推进螺旋桨优化方法
JPH1199994A (ja) 航空機回転翼のための後退翼端付きの羽根
CN109110124A (zh) 一种新型旋翼桨叶
CN110155319B (zh) 改进桨叶以增大其负失速迎角的方法
JPH0341399B2 (fr)
US11214364B2 (en) Main rotor blade and helicopter
CN211364914U (zh) 旋翼飞行器的桨叶及旋翼飞行器
CN205524939U (zh) 螺旋桨、动力组件及飞行器
CN109071004A (zh) 螺旋桨、动力套装及无人飞行器
CN109263932A (zh) 一种可垂直升降的多旋翼飞行器
CN110155318B (zh) 确定桨叶的翼型的初始前缘圆的方法和改进桨叶以增大其负失速迎角的方法
WO2024156193A1 (fr) Structure de fuselage et engin volant sans pilote embarqué la comprenant
WO2020042983A1 (fr) Hélice, ensemble de puissance et véhicule aérien sans pilote
CN209905055U (zh) 一种旋翼桨及无人机
WO2023108817A1 (fr) Hélice, ensemble alimentation et aéronef
CN112918668B (zh) 旋翼飞行器的旋翼及旋翼飞行器
CN211364941U (zh) 旋翼飞行器的桨叶及旋翼飞行器
WO2021043330A1 (fr) Hélice et aéronef

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: 23884418

Country of ref document: EP

Kind code of ref document: A1