CN112918669B - Rotor of rotor craft and rotor craft - Google Patents
Rotor of rotor craft and rotor craft Download PDFInfo
- Publication number
- CN112918669B CN112918669B CN201911245181.3A CN201911245181A CN112918669B CN 112918669 B CN112918669 B CN 112918669B CN 201911245181 A CN201911245181 A CN 201911245181A CN 112918669 B CN112918669 B CN 112918669B
- Authority
- CN
- China
- Prior art keywords
- rotor
- airfoil
- rotorcraft
- blade
- present disclosure
- 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.)
- Active
Links
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/32—Rotors
-
- 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
- B64C27/32—Rotors
- B64C27/46—Blades
- B64C27/473—Constructional features
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The present disclosure relates to a rotor of a rotorcraft and a rotorcraft, wherein the rotor comprises a blade and a hub, the blade is mounted on a drive assembly of the rotorcraft via the hub, the blade comprises a root, a tip, and upper and lower wing surfaces arranged opposite one another, one side of the upper and lower wing surfaces is connected to form a leading edge, the other side is connected to form a trailing edge, the upper wing surface is defined by an upper wing surface characteristic line formed by (kx, ky, kz) defined by a plurality of coordinate pairs, and the lower wing surface is defined by a lower wing surface characteristic line formed by (kx, ky, kz) defined by a plurality of coordinate pairs. The rotor of this disclosure can reduce the resistance of air, improves pulling force and efficiency, increases rotor craft's duration, can also reduce the noise that the aircraft produced when flying in addition, promotes user experience.
Description
Technical Field
The utility model relates to an aircraft technical field specifically relates to a rotor and rotor craft of rotor craft.
Background
The rotor is an important part of the rotorcraft, and is used for converting the power of an output shaft of a motor or an engine into thrust or lift force so as to realize actions of taking off and landing, hovering, advancing or tilting of the rotorcraft. The blades of the rotor in the related art have low force efficiency due to the limitation of the three-dimensional outline and structure, and cannot meet the required propulsive force during working. In addition, the rotor noise level of the rotor craft in the related art is high, the rotor of the type can be used in the regions with relatively few population such as plant protection and electric power cruising, and when the rotor craft is applied to the regions with dense population for logistics distribution and the like, the noise generated by the rotor craft can generate great interference to the daily life of residents, and the user experience is influenced.
Disclosure of Invention
It is an object of the present disclosure to provide a rotor for a rotorcraft that improves the flight time, range capability of the rotorcraft while reducing the level of noise generated.
In order to achieve the above object, the present disclosure provides a rotor of a rotorcraft, comprising a blade and a hub, the blade being mounted to a drive assembly of the rotorcraft via the hub, the blade comprising a root, a tip, and upper and lower airfoils disposed opposite one another, the upper and lower airfoils being connected on one side to form the leading edge and on the other side to form the trailing edge, the upper airfoil being defined by an upper airfoil profile characteristic line defined by a plurality of coordinate pairs (kx, ky, kz), the lower airfoil being defined by a lower airfoil profile characteristic line defined by a plurality of coordinate pairs (kx, ky, kz), the upper and lower profile characteristic lines being defined according to:
wherein, the x direction is the unfolding direction of the rotor wing, the y direction is the chord length direction of the rotor wing, and the z direction is the thickness direction; k = a/229, wherein a is the radius of the rotor; the maximum error of each of the upper airfoil profile and the lower airfoil profile is equal to ± 3%.
Through above-mentioned technical scheme, this disclosure has carried out the optimization of upper and lower airfoil characteristic line to the main pulling force production district of paddle to make the rotor exhibition upwards be in the working section of preferred, with the resistance that reduces the air, improve pulling force and efficiency, thereby can increase rotor craft's time of endurance, can also reduce the noise that the aircraft produced in flight in addition, promote user experience.
Additional features and advantages of the present disclosure will be set forth in the detailed description which follows.
Drawings
The accompanying drawings, which are included to provide a further understanding of the disclosure and are incorporated in and constitute a part of this specification, illustrate embodiments of the disclosure and together with the description serve to explain the disclosure, but do not constitute a limitation of the disclosure. In the drawings:
figure 1 is a perspective view of a rotor shown according to an exemplary embodiment;
figure 2 is a plan view of a rotor shown according to an exemplary embodiment;
FIG. 3 is a force effect comparison graph of a blade of the present disclosure to a T-motor pure carbon blade.
Description of the reference numerals
1. The leading edge 12 and the trailing edge of the blade 11
13. Upper arc 14 and lower arc 15 chord
16. Heel 171 of blade root 17
18. Upper wing surface 19 and lower wing surface
Detailed Description
The following detailed description of specific embodiments of the present disclosure is provided in connection with the accompanying drawings. It should be understood that the detailed description and specific examples, while indicating the present disclosure, are given by way of illustration and explanation only, not limitation.
The terms upper and lower equal orientation as presented in this embodiment are with reference to the rotor after it is mounted on the aircraft and the normal operational attitude of the rotorcraft, and should not be considered limiting.
The rotor of the rotorcraft and the rotorcraft of the present disclosure will be described in detail below with reference to the accompanying drawings. The features of the following examples and embodiments may be combined with each other without conflict.
As shown in fig. 1 and 2, the present disclosure provides a rotor of a rotorcraft, which includes a blade 1 and a hub, the blade 1 is mounted on a driving assembly of the rotorcraft through the hub, the driving assembly may be, for example, a rotating electric machine mounted on a fuselage of the rotorcraft, and an output shaft of the rotating electric machine is connected with the hub to rotate the blade 1. The aircraft body of the rotor aircraft can be provided with a plurality of rotors, and the flight attitude of the rotor aircraft can be changed by adjusting the rotating speed and the attitude of the rotors so as to switch between actions of hovering, traveling or heeling.
The blade 1 of the present disclosure may be made of any material in the related art, including but not limited to metal materials, plastics, carbon fibers, and the like. In addition, molding may be employed in the manufacture. The processing technique means in various related technologies such as stamping, forging and the like.
The blade 1 comprises a root 16, a tip 17 and an upper airfoil surface 18 and a lower airfoil surface 19 arranged opposite one another, the upper airfoil surface 18 and the lower airfoil surface 19 being connected on one side to form a leading edge 11 and on the other side to form a trailing edge 12, the upper airfoil surface 18 being defined by an upper airfoil surface characteristic line defined by (kx, ky, kz) defined by a plurality of coordinate pairs, the lower airfoil surface 19 being defined by a lower airfoil surface characteristic line defined by (kx, ky, kz) defined by a plurality of coordinate pairs, the upper airfoil surface characteristic line and the lower airfoil surface characteristic line being defined according to the following:
table 1a coordinates of feature points of airfoil feature lines
TABLE 1b characteristic point coordinates of lower airfoil surface characteristic lines
Wherein, the x direction is the span direction of rotor, and the y direction is the chord length direction of rotor, and z is the thickness direction. k = a/229, wherein a is the value of the radius of the rotor. Table 1 is a three-dimensional profile data for an embodiment of a selected pitch radius of 229 mm, it being understood that clusters of curves scaled up or down using this data, with smooth transitions between the characteristic lines, are also within the scope of the practice of the present disclosure.
The following exemplary provides a way of mapping a blade having the same profile as the present disclosure, with other radius dimensions selected. When the radius dimension of the blade is 600 mm, i.e. a =600, k =2.62009, and then k is multiplied by the corresponding coordinate values in table 1 respectively, so as to obtain a new set of feature point coordinates of the feature line, for example, the corresponding coordinates in the upper airfoil feature line 5 in table 1a become (297.60030, -31.16505, 7.31181), (297.60030, -30.85444, 7.64422) \ 8230; \ 8230; the corresponding coordinates in the lower airfoil feature line 5 in table 1b become (297.60030, -31.16505, 7.31181), (297.60030, -31.01191, 6.97195) \8230;.
The maximum error of each of the upper and lower airfoil characteristic lines is equal to ± 3%, that is, the shape of the airfoil formed by the upper and lower airfoil characteristic lines within the tolerance of ± 3% error falls within the scope of protection claimed by the present disclosure.
According to the data in the above table, it can be seen that the blade 1 of the present disclosure has a three-dimensional structure defined by the above three characteristic lines in a distant interval from the center (approximately x interval of 113 to 196), and the corresponding blade structure in this interval is a main structure in the blade and is a relatively important tension generation area, and by optimizing the value of the characteristic line in this area, the main part of the blade 1 can be in a better working section in the span-wise direction, so as to reduce the resistance of air, improve the tension and efficiency, and increase the endurance time of the rotorcraft, and in addition, the noise generated by the rotorcraft during flight can be reduced, and the user experience can be improved.
In the present disclosure, the upper airfoil surface feature line and the lower airfoil surface feature line are further defined according to:
TABLE 2a coordinates of feature points of the airfoil feature lines
TABLE 2b characteristic point coordinates of lower airfoil surface characteristic lines
The selection of the interval closer to the centre (interval approximately 27-69) is continued to optimise as the root 16 is used to connect to the hub so that the blades can be rotated by the drive assembly. The root 16 is now located closer to the hub than the main part of the blade 1 and the tip 17 part and will therefore be subjected to a higher torque. The present disclosure provides for thickening at the root 16 portion, i.e., a bulge is formed outward along the chord of the root 16 to increase the structural strength of the root 16 portion.
In the present disclosure, the upper airfoil surface feature line and the lower airfoil surface feature line are further defined according to:
TABLE 3a coordinates of feature points of the airfoil feature lines
TABLE 3b coordinates of feature points of the airfoil feature lines
Thus, the present disclosure further refines the main body portion of the blade 1, so that the transition of the main body portion of the blade 1 is smoother and no sharp twisting occurs. The smooth transition structure can further improve the overall structural strength of the paddle 1, is not easy to break, improves the reliability of the main body part of the paddle 1 in work, and has higher tension and efficiency.
In the present disclosure, the upper airfoil surface characteristic line and the lower airfoil surface characteristic line are further defined according to:
TABLE 4a coordinates of feature points of the airfoil feature lines
TABLE 4b feature point coordinates of lower airfoil feature line
The present disclosure further refines the area of the blade root 16 closer to the blade root, and improves the smoothness of the blade root 16 to improve the structural strength of the blade 1.
Further, in order to enhance the noise reduction effect, according to an embodiment of the present disclosure, as shown in fig. 1 and 2, a swept portion 171 is further formed at the wing tip 17, the swept portion 171 is bent and extended from the leading edge 11 to the trailing edge 12, and an upper wing surface characteristic line and a lower wing surface characteristic line of the swept portion 171 are defined according to the following:
TABLE 5a coordinates of feature points of airfoil feature lines
TABLE 5b feature point coordinates of lower airfoil feature line
Wherein, the x direction is the spanwise direction of rotor, and the y direction is the chord length direction of rotor, and z is the thickness direction. k = a/229, wherein a is the value of the radius of the rotor. Table 5 is a three-dimensional profile data for an embodiment of a selected pitch radius of 229 mm, it being understood that clusters of curves scaled up or down using this data, with smooth transitions between the characteristic lines, are also within the scope of the practice of the present disclosure.
The following is exemplary of how to obtain a sweep 171 having the same profile as the present disclosure, with other selected radius blade sizes. For example, if the radius dimension of the blade is 600 mm, i.e., a =600, k =2.62009, and then k is multiplied by the corresponding coordinate values in table 5, respectively, to obtain a new set of feature point coordinates of the feature line, for example, the feature point coordinates in the upper airfoil feature line 10 in table 5a become (549.60056, -22.77924, 2.38606), (549.60056, -22.77924, 2.58626) \8230; 8230; the corresponding coordinates in the lower airfoil feature line 10 in Table 5b become (549.60056, -22.77924, 2.38606), (549.60056, -22.67366, 2.21162) \8230;.
The maximum error of each of the upper and lower airfoil characteristic lines is equal to ± 3%, that is, the shape of the airfoil formed by the upper and lower airfoil characteristic lines within the tolerance of ± 3% error falls within the scope of protection claimed by the present disclosure.
In the present disclosure, by designing the three-dimensional structure formed by the two airfoil characteristic lines, the sweepback portion 171 is constructed, and the presence of the sweepback portion 171 can cut off the air flowing in the direction of the blade 1 when the blade 1 rotates, thereby reducing the vortex formed by the tip 17 part and reducing the strength of the vortex of the tip 17 part, and in addition, the sweepback portion 171 can weaken the degree of air pressure change near the blade 1, weaken the degree of periodic cutting air flow of the blade 1 with a certain thickness, and further reduce the rotation noise generated when the blade 1 rotates.
In order to make the sweepback more effective, the present disclosure adds a wing surface characteristic line to define the sweepback. Specifically, as shown in table 6 below:
table 6a coordinates of feature points of airfoil feature lines
TABLE 6b characteristic point coordinates of lower airfoil surface characteristic line
By further limiting the characteristic lines of the upper and lower airfoils of the swept portion 171, the swept portion 171 is smoother, the vortex formed at the blade tip 17 is more stable, and the noise reduction effect can be further improved.
The beneficial effects of the disclosed blade 1 in improving the aerodynamic efficiency of a rotorcraft will be further illustrated by force effect comparison tests of the disclosed blade (18 inch bakelite) and a T-motor pure carbon blade.
As shown in fig. 3, the force efficiency of a rotorcraft using the blade 1 of the present disclosure is improved by 4.9% on average compared to a T-motor pure carbon blade. Specifically, under 1.5kg of tension, the force effect is improved by 2.7%; under the tension of 1.1kg, the force effect is improved by 5 percent; the pull force is improved by 7 percent under the pull force of 1.8 kg. In addition, through experiments and numerical simulation, compared with a T-motor pure carbon blade, the noise of the blade 1 is reduced by 3 decibels. According to the method, numerical simulation and wind tunnel test are adopted in the test of the force effect, and the accuracy of the test result is guaranteed.
According to one embodiment of the present disclosure, as shown in fig. 2, there may be at least two blades 1, and at least two blades 1 are connected together by a root 16 and are centrosymmetric with respect to a center point position of the connection. At least two paddles 1 can integrated into one piece to can guarantee the holistic structural strength of paddle 1, perhaps paddle 1 also can adopt the fashioned design of components of a whole that can function independently, for example install each paddle 1 respectively on the propeller hub, make the installation and the change of paddle 1 comparatively convenient, the axis at propeller hub place is promptly in the centre of rotation of paddle 1 this moment.
A second object of the present disclosure is to provide a rotorcraft comprising a rotor of the rotorcraft described above. The rotorcraft may be a multi-rotor rotorcraft. This rotor craft has all the beneficial effects of the rotor of above-mentioned rotor craft, and this disclosure is no longer repeated here.
The preferred embodiments of the present disclosure are described in detail with reference to the accompanying drawings, however, the present disclosure is not limited to the specific details of the above embodiments, and various simple modifications may be made to the technical solution of the present disclosure within the technical idea of the present disclosure, and these simple modifications all belong to the protection scope of the present disclosure.
It should be noted that the various features described in the above embodiments may be combined in any suitable manner without departing from the scope of the invention. In order to avoid unnecessary repetition, various possible combinations will not be separately described in this disclosure.
In addition, any combination of various embodiments of the present disclosure may be made, and the same should be considered as the disclosure of the present disclosure, as long as it does not depart from the spirit of the present disclosure.
Claims (4)
1. A rotor of a rotorcraft, comprising at least two blades (1) and a hub, the blades (1) being mounted on a drive assembly of the rotorcraft via the hub, the blades (1) comprising a root (16), a tip (17) and upper (18) and lower (19) oppositely disposed one above the other, the upper (18) and lower (19) airfoils being joined on one side to form a leading edge (11) and on the other side to form a trailing edge (12), the upper (18) airfoil being defined by an upper airfoil profile characteristic line defined by a plurality of coordinate pairs (kx, ky, kz), the lower (19) airfoil being defined by a lower airfoil characteristic line defined by a plurality of coordinate pairs (kx, ky, kz), the upper and lower profile characteristic lines being defined according to:
wherein, the x direction is the spanwise direction of the rotor wing, the y direction is the chord length direction of the rotor wing, and z is the thickness direction; k = a/229, wherein a is the radius of the rotor; a maximum error of each of the upper airfoil profile and the lower airfoil profile is equal to ± 3%;
a swept back portion (171) is formed at the blade tip (17), the swept back portion (171) extends from the leading edge (11) to the trailing edge (12) in a bending manner, and the upper airfoil characteristic line and the lower airfoil characteristic line of the swept back portion (171) are defined according to the following:
the upper and lower airfoil profile of the sweep (171) are further defined according to:
2. a rotor of a rotorcraft according to claim 1, wherein at least two of the blades (1) are integrally or separately formed.
3. A rotorcraft, comprising a rotor of the rotorcraft according to claim 1 or 2.
4. The rotary wing aircraft of claim 3, wherein the rotary wing aircraft is a multi-rotor aircraft.
Priority Applications (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911245181.3A CN112918669B (en) | 2019-12-06 | 2019-12-06 | Rotor of rotor craft and rotor craft |
| PCT/CN2020/091310 WO2021109479A1 (en) | 2019-12-06 | 2020-05-20 | Blade and rotor for rotorcraft, and rotorcraft |
| US17/541,728 US20220089278A1 (en) | 2019-12-06 | 2021-12-03 | Blade and rotor of rotor craft, and rotor craft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911245181.3A CN112918669B (en) | 2019-12-06 | 2019-12-06 | Rotor of rotor craft and rotor craft |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN112918669A CN112918669A (en) | 2021-06-08 |
| CN112918669B true CN112918669B (en) | 2022-12-20 |
Family
ID=76162003
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201911245181.3A Active CN112918669B (en) | 2019-12-06 | 2019-12-06 | Rotor of rotor craft and rotor craft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN112918669B (en) |
Family Cites Families (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN206367596U (en) * | 2016-09-22 | 2017-08-01 | 上海未来伙伴机器人有限公司 | Many rotor blade devices |
| WO2019127028A1 (en) * | 2017-12-26 | 2019-07-04 | 深圳市大疆创新科技有限公司 | Propeller, power assembly and aircraft |
| CN108163192B (en) * | 2017-12-29 | 2024-05-24 | 重庆驼航科技有限公司 | High-efficient low noise rotor |
| CN208149614U (en) * | 2018-04-25 | 2018-11-27 | 深圳市大疆创新科技有限公司 | Propeller, Power Component and aircraft |
| CN208291466U (en) * | 2018-05-25 | 2018-12-28 | 深圳市大疆创新科技有限公司 | Propeller, Power Component and aircraft |
| CN209023104U (en) * | 2018-06-15 | 2019-06-25 | 深圳远行智能航空科技有限公司 | A kind of high efficiency propeller and unmanned vehicle |
| CN110435877A (en) * | 2019-08-30 | 2019-11-12 | 西安倾云无人机技术有限公司 | A kind of adaptive pneumatic variable-pitch propeller |
| CN211364941U (en) * | 2019-12-06 | 2020-08-28 | 北京二郎神科技有限公司 | Rotor craft's paddle and rotor craft |
-
2019
- 2019-12-06 CN CN201911245181.3A patent/CN112918669B/en active Active
Also Published As
| Publication number | Publication date |
|---|---|
| CN112918669A (en) | 2021-06-08 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US8066219B2 (en) | Anhedral tip blades for tiltrotor aircraft | |
| JP5078883B2 (en) | Rotor blade of high speed rotorcraft | |
| JP4535550B2 (en) | Rotor blade of rotorcraft | |
| US7600976B2 (en) | Rotor blade twist distribution for a high speed rotary-wing aircraft | |
| CN108163192B (en) | High-efficient low noise rotor | |
| CN211364914U (en) | Rotor craft's paddle and rotor craft | |
| CN110155319B (en) | Method for modifying a blade to increase its negative stall angle of attack | |
| KR101051575B1 (en) | Tip airfoil on blade for 2 megawatt wind generator | |
| CN104002966B (en) | Rotor blade structure design capable of inhibiting rotation chattering of tilt rotor | |
| CN111907699A (en) | Helicopter rotor dynamic stall control structure based on whale fin-imitated leading edge | |
| CN112572787A (en) | Coaxial dual-rotor high-speed helicopter tip airfoil with low resistance and high divergence Mach number | |
| EP0262071A1 (en) | Helicopter blade airfoil | |
| CN111674546A (en) | Rotor wing pneumatic appearance suitable for small and medium-sized unmanned tilt rotor wing aircraft | |
| CN110155318B (en) | Method for determining the initial leading edge circle of the airfoil of a blade and method for modifying a blade to increase its negative stall angle of attack | |
| CN211364941U (en) | Rotor craft's paddle and rotor craft | |
| WO2005105570A1 (en) | Leading edge slat airfoil for multi-element rotor blade airfoils | |
| JPH10226397A (en) | Blade section for helicopter | |
| CN106564588B (en) | Unmanned helicopter blade and unmanned helicopter | |
| CN112918669B (en) | Rotor of rotor craft and rotor craft | |
| CN209905055U (en) | Rotor oar and unmanned aerial vehicle | |
| CN112173077A (en) | Big front-back sweeping combined helicopter rotor blade | |
| JP6186549B2 (en) | Wings imitating part of the dragonfly wing structure | |
| CN106218886A (en) | Many rotorcraft blades and many gyroplanes | |
| WO2021109479A1 (en) | Blade and rotor for rotorcraft, and rotorcraft | |
| JPH11124093A (en) | Aerofoil for helicopter blade |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |