CN112918669A - Rotor of rotor craft and rotor craft - Google Patents
Rotor of rotor craft and rotor craft Download PDFInfo
- Publication number
- CN112918669A CN112918669A CN201911245181.3A CN201911245181A CN112918669A CN 112918669 A CN112918669 A CN 112918669A CN 201911245181 A CN201911245181 A CN 201911245181A CN 112918669 A CN112918669 A CN 112918669A
- Authority
- CN
- China
- Prior art keywords
- rotor
- rotorcraft
- blade
- wing
- airfoil
- 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.)
- Granted
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 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 is a/229, wherein a is the radius value 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 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 without limiting the disclosure. In the drawings:
figure 1 is a perspective schematic 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 blade 11 leading edge 12 trailing edge
13 upper arc line 14 lower arc line 15 chord line
16-blade root 17-blade tip 171 sweep-back
18 upper wing surface and 19 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, including a blade 1 and a hub, the blade 1 being mounted on a driving assembly of the rotorcraft through the hub, the driving assembly being, for example, a rotating electrical machine mounted on a fuselage of the rotorcraft, an output shaft of the rotating electrical machine being connected to 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. Stamping, forging and other processing means in various related technologies.
The blade 1 comprises a root 16, a tip 17 and an upper airfoil surface 18 and a lower airfoil surface 19 which are arranged opposite to each other, one side of the upper airfoil surface 18 and one side of the lower airfoil surface 19 are connected to form a leading edge 11, the other side of the upper airfoil surface 18 and the other side of the lower airfoil surface 19 are connected to form a trailing edge 12, the upper airfoil surface 18 is defined by an upper airfoil surface characteristic line formed by (kx, ky, kz) defined by a plurality of coordinate pairs, the lower airfoil surface 19 is defined by a lower airfoil surface characteristic line formed by (kx, ky, kz) defined by a plurality of coordinate pairs, and the upper airfoil surface characteristic line and the lower airfoil surface characteristic line are defined according to the following formula:
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. And k is a/229, wherein a is the radius value 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 size of the blade is 600 mm, namely a is 600, k is 2.62009, then k is multiplied by the corresponding coordinate values in table 1 respectively, and finally a new set of feature point coordinates of the feature line is obtained, 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) … …; the corresponding coordinates in the lower airfoil characteristic line 5 in table 1b become (297.60030, -31.16505,7.31181), (297.60030, -31.01191,6.97195) … ….
The maximum error of each of the upper and lower airfoil characteristic lines is equal to ± 3%, i.e., 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 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 section (approximately the x section of 113-196), which is farther from the center, and the corresponding blade structure in the section is the main structure in the blade and is the important tension generation area, and by optimizing the value of the characteristic line in the area, the main part of the blade 1 can be located at a better working section in the extending direction, so as to reduce the resistance of air, improve the tension and efficiency, and thus 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 choice of a zone closer to the centre (zone approximately 27-69) continues to be optimised because the root 16 is intended to be connected 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 the root 16 portion, i.e., forming a ridge 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 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 feature line and the lower airfoil surface feature line are further defined according to:
TABLE 4a coordinates of feature points of the airfoil feature lines
TABLE 4b characteristic point coordinates of lower airfoil surface characteristic line
The present disclosure also further refines the area of the blade root 16 closer, and improves the smoothness at 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 characteristic point coordinates of lower airfoil surface characteristic line
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. And k is a/229, wherein a is the radius value 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 an exemplary way to provide 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 is 600, k is 2.62009, then k is multiplied by the corresponding coordinate values in table 5, and finally a new set of feature point coordinates of the feature line is obtained, for example, the corresponding coordinates in the upper airfoil feature line 10 in table 5a become (549.60056, -22.77924,2.38606), (549.60056, -22.77924,2.58626) … …; the corresponding coordinates in the lower airfoil characteristic line 10 in table 5b become (549.60056, -22.77924,2.38606), (549.60056, -22.67366,2.21162) … ….
The maximum error of each of the upper and lower airfoil characteristic lines is equal to ± 3%, i.e., 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 the present disclosure.
In the present disclosure, by designing the three-dimensional structure formed by the two airfoil characteristic lines, the swept-back portion 171 is configured, and the presence of the swept-back portion 171 can cut off the air flow in the direction of the blade 1 when the blade 1 rotates, thereby reducing the vortex formed by the blade tip 17 portion and the strength of the vortex at the blade tip 17 portion, and in addition, the swept-back 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 rotational 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 blade 1 of the present disclosure in improving the aerodynamic efficiency of a rotorcraft will be further illustrated by force versus effect testing of the blade of the present disclosure (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 tension of 1.8 kg. In addition, through experimental and numerical simulation, the noise of the blade 1 of the present disclosure is reduced by 3 decibels compared to a T-motor pure carbon blade. The test of the above-mentioned power effect of this disclosure adopts numerical simulation and wind tunnel test dual means, guarantees the accuracy of experimental result.
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 paddle 1 can integrated into one piece to can guarantee paddle 1's holistic structural strength, 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 that the center of rotation of paddle 1 was the propeller hub place 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 aircraft. 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 (10)
1. A rotor of a rotorcraft, comprising a blade (1) and a hub, the blade (1) being mounted on a drive assembly of the rotorcraft via the hub, the blade (1) comprising a root (16), a tip (17) and upper (18) and lower (19) oppositely disposed above and below, one side of the upper (18) and lower (19) airfoils being joined to form a leading edge (11) and the other side being joined to form a trailing edge (12), the upper (18) airfoil surface being defined by an upper airfoil surface characteristic line consisting of (kx, ky, kz) defined by a plurality of coordinate pairs, the lower (19) airfoil surface being defined by a lower airfoil surface characteristic line consisting of (kx, ky, kz) defined by a plurality of coordinate pairs, the upper and lower airfoil surface 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 is a/229, wherein a is the radius value of the rotor; the maximum error of each of the upper airfoil profile and the lower airfoil profile is equal to ± 3%.
2. A rotor for a rotary-wing aircraft according to claim 1, wherein the upper and lower wing surface characteristic lines are further defined according to:
3. a rotor of a rotary-wing aircraft according to claim 2, wherein the upper and lower wing characteristic lines are further defined according to:
4. a rotor of a rotary-wing aircraft according to claim 3, wherein the upper and lower wing characteristic lines are further defined according to:
5. a rotor of a rotorcraft according to any one of claims 1 to 4, wherein a swept portion (171) is formed at the tip (17), said swept portion (171) extending from the leading edge (11) towards the trailing edge (12) with a bend, said upper and lower profile lines of said swept portion (171) being defined according to the following:
6. a rotor of a rotorcraft according to claim 5, wherein the upper and lower profile lines of the swept back portion (171) are further defined according to:
7. a rotor of a rotorcraft according to claim 1, wherein there are at least two of said blades (1), at least two of said blades (1) being connected together by said root (16) and being centrally symmetrical with respect to a central point of connection.
8. A rotor of a rotorcraft according to claim 7, wherein at least two of the blades (1) are integrally or separately formed.
9. A rotorcraft, comprising a rotor of the rotorcraft according to any one of claims 1-8.
10. The rotary wing vehicle of claim 9, wherein the rotary wing vehicle is a multi-rotor vehicle.
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 true CN112918669A (en) | 2021-06-08 |
| CN112918669B 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) |
Citations (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 |
| CN108163192A (en) * | 2017-12-29 | 2018-06-15 | 江苏方阔航空科技有限公司 | A kind of 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 |
| CN109071006A (en) * | 2017-12-26 | 2018-12-21 | 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
Patent Citations (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 |
| CN109071006A (en) * | 2017-12-26 | 2018-12-21 | 深圳市大疆创新科技有限公司 | Propeller, Power Component and aircraft |
| CN108163192A (en) * | 2017-12-29 | 2018-06-15 | 江苏方阔航空科技有限公司 | A kind of 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 |
Also Published As
| Publication number | Publication date |
|---|---|
| CN112918669B (en) | 2022-12-20 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US8066219B2 (en) | Anhedral tip blades for tiltrotor aircraft | |
| JP5078883B2 (en) | Rotor blade of high speed rotorcraft | |
| EP3178739B1 (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 | |
| KR20110012445A (en) | Tip-irfoil of blade for wind power generator | |
| CN111674546B (en) | Rotor wing pneumatic appearance suitable for small and medium-sized unmanned tilt rotor wing aircraft | |
| CN110896624A (en) | Screw, power component and aircraft | |
| EP0262071A1 (en) | Helicopter blade airfoil | |
| CN211364941U (en) | Rotor craft's paddle and rotor craft | |
| 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 | |
| JPH10226397A (en) | Blade section for helicopter | |
| CN106564588B (en) | Unmanned helicopter blade and unmanned helicopter | |
| KR101067017B1 (en) | Rotor blade for rotorcraft to change sweep-back angle of the blade tip actively | |
| 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 | |
| CN113022849B (en) | Propeller and rotary wing aircraft | |
| CN112918668B (en) | Rotor of rotor craft and rotor craft | |
| JPH11124093A (en) | Aerofoil for helicopter blade | |
| WO2021109479A1 (en) | Blade and rotor for rotorcraft, and rotorcraft | |
| US10899440B2 (en) | Rotor blade tip design for improved hover and cruise performance | |
| CN112977814A (en) | Improved rotor pneumatic appearance suitable for small and medium-sized unmanned tilt rotor aircraft | |
| CN112298549A (en) | Tilt rotor with bionic wavy leading edge and tilt rotor aircraft |
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 |