CN112173097A - Coaxial double-rotor wing with unequal diameters - Google Patents
Coaxial double-rotor wing with unequal diameters Download PDFInfo
- Publication number
- CN112173097A CN112173097A CN202011021217.2A CN202011021217A CN112173097A CN 112173097 A CN112173097 A CN 112173097A CN 202011021217 A CN202011021217 A CN 202011021217A CN 112173097 A CN112173097 A CN 112173097A
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- rotor
- coaxial
- diameter
- blades
- lower rotor
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- 230000009977 dual effect Effects 0.000 claims abstract description 23
- 230000002349 favourable effect Effects 0.000 abstract description 2
- 238000009434 installation Methods 0.000 description 3
- 238000010586 diagram Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000007796 conventional method Methods 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
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Classifications
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- 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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/32—Rotors
- B64C27/46—Blades
-
- 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
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Wind Motors (AREA)
- Toys (AREA)
Abstract
The invention belongs to the technical field of rotor wing pneumatic design and discloses a coaxial double rotor wing with unequal diameters. The dual rotor includes: go up rotor and lower rotor, go up rotor and lower rotor are coaxial, just the diameter of going up the rotor is greater than the diameter of lower rotor. The coaxial dual rotors are adopted, the diameters of the upper rotor and the lower rotor are different, the favorable interference of the lower rotor to the upper rotor is fully utilized, meanwhile, the unfavorable interference of the upper rotor to the lower rotor can be reduced, and the coaxial dual rotors have the obvious hovering efficiency advantage compared with the conventional coaxial dual rotors with equal diameters.
Description
Technical Field
The invention belongs to the technical field of rotor pneumatic design, and particularly relates to a coaxial double rotor with unequal diameters.
Background
To this end, almost all helicopters have an engine mounted in the fuselage, which drives a rotating shaft to rotate, and in turn drives a rotor fixed to the rotating shaft to rotate and generate lift. If a single rotor wing is adopted, a tail rotor needs to be added to balance torque brought by rotation of the rotor wing, and power consumption of the tail rotor is increased, so that the drive type is the most popular type at present; if a coaxial type reverse double rotor wing is adopted, the two rotor wings are on the same axis and rotate in opposite directions, the reactive torques are offset, a tail rotor is not needed, and the efficiency is high. A coaxial dual-rotor helicopter represented by SB-1 is a main flow direction for the development of helicopters in the world today.
The coaxial double rotors which are published at present all adopt a pneumatic design with the same diameter of the upper rotor and the lower rotor.
Disclosure of Invention
The purpose of the invention is as follows: the coaxial dual-rotor pneumatic design with unequal diameters is provided, the coaxial dual rotors are adopted, the diameters of the upper rotor and the lower rotor are different, the favorable interference of the lower rotor to the upper rotor is fully utilized, meanwhile, the unfavorable interference of the upper rotor to the lower rotor can be reduced, and the coaxial dual-rotor pneumatic design with unequal diameters has an obvious hovering efficiency advantage compared with the conventional coaxial dual rotors with equal diameters.
The technical scheme of the invention is as follows:
a dual, non-diametric, coaxial rotor, the dual rotor comprising: go up rotor and lower rotor, go up rotor and lower rotor are coaxial, just the diameter of going up the rotor is greater than the diameter of lower rotor.
The technical scheme of the invention has the characteristics and further improvements that:
(1) the rotation direction of the upper rotor is opposite to that of the lower rotor.
(2) The number of blades of the upper rotor and the number of blades of the lower rotor are at least two, and the number of blades of the lower rotor is less than or equal to the number of blades of the upper rotor.
(3) The blades of the upper rotor and the blades of the lower rotor adopt different aerodynamic shapes.
(4) The ratio of the upper rotor wing and the lower rotor wing to the diameter of the upper rotor wing is greater than or equal to 0.05.
(5) The upper rotor wing comprises N1The included angle between adjacent blades is within the range of (360 DEG/N)1-360°/4N1，360°/N1+360°/4N1)，N1Is an even number greater than 2, and the lower rotor comprises N2The included angle between adjacent blades is within the range of (360 DEG/N)2-360°/4N2，360°/N2+360°/4N2)，N2An even number greater than 2.
(6) The ratio of the diameter of the lower rotor wing to the diameter of the upper rotor wing is a, and a is more than or equal to 0.25 and less than 1.
(7) The installation dislocation angle of the upper rotor and the lower rotor is 0-360 DEG/N1.
The invention has the beneficial effects that:
according to the technical scheme, the coaxial double rotors with unequal diameters are in a coaxial reverse double-rotor layout, a tail rotor is not needed to overcome a reactive torque, and the structure is simple; compared with the conventional equal-diameter coaxial double rotors, the double-rotor type wind driven generator has obvious hovering efficiency advantage; because the upper and lower rotor diameter is different, the paddle is more difficult to bump each other, and the security is higher.
Drawings
FIG. 1 is an axial view of a dual coaxial rotors of unequal diameter according to an embodiment of the present invention;
FIG. 2 is a schematic view of a blade according to an embodiment of the present invention in a rectangular plan layout with equal chord length;
FIG. 3 is a linear twist profile of a blade using a rectangular planform layout of equal chord length according to an embodiment of the present invention;
FIG. 4 is a side view of a dual coaxial rotors of unequal diameter according to an embodiment of the present invention;
FIG. 5 is a top view of a dual coaxial rotors of different diameters according to an embodiment of the present invention;
FIG. 6 is a schematic diagram illustrating lift coefficient and hovering efficiency of unequal-diameter coaxial dual rotors according to an embodiment of the present invention;
fig. 7 is a schematic diagram of lift coefficient and lift-drag ratio of unequal diameter coaxial dual rotors provided by an embodiment of the invention.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
An embodiment of the present invention provides a dual coaxial rotor with unequal diameters, as shown in fig. 1, the dual rotor includes: go up rotor and lower rotor, go up rotor and lower rotor are coaxial, just the diameter of going up the rotor is greater than the diameter of lower rotor.
Further:
(1) the rotation direction of the upper rotor is opposite to that of the lower rotor. The coaxial reverse rotation dual-rotor layout is adopted, the tail rotor is not needed to overcome the reactive torque, and the structure is simple; compared with the conventional equal-diameter coaxial double rotors, the double-rotor type wind driven generator has obvious hovering efficiency advantage; because the upper and lower rotor diameter is different, the paddle is more difficult to bump each other, and the security is higher.
(2) The number of blades of the upper rotor and the number of blades of the lower rotor are at least two, and the number of blades of the lower rotor is less than or equal to the number of blades of the upper rotor.
(3) The blades of the upper rotor and the blades of the lower rotor adopt different aerodynamic shapes.
(4) The ratio of the upper rotor wing and the lower rotor wing to the diameter of the upper rotor wing is greater than or equal to 0.05.
(5) The upper rotor wing comprises N1The included angle between adjacent blades is within the range of (360 DEG/N)1-360°/4N1，360°/N1+360°/4N1)，N1Is an even number greater than 2, and the lower rotor comprises N2The included angle between adjacent blades is within the range of (360 DEG/N)2-360°/4N2，360°/N2+360°/4N2)，N2An even number greater than 2.
When the upper rotor wing comprises 4 blades, under normal conditions, the included angle between the blades is 90 degrees, the two blades which are connected together are rotated, so that the included angle between the two blades which are connected together and the other two blades which are connected together is larger than 0 degree and smaller than 90 degrees, and the performance of the coaxial double rotor wing with unequal diameters designed by the invention can be met.
(6) The ratio of the diameter of the lower rotor wing to the diameter of the upper rotor wing is a, and a is more than or equal to 0.25 and less than 1.
(7) The installation dislocation angle of the upper rotor and the lower rotor is 0 degree to 360 degrees/N1In the meantime.
In a specific case, the blades are configured in a rectangular plane layout with equal chord length (as shown in fig. 2) and a linear torsion distribution (as shown in fig. 3), and other specific parameters of the rotor are shown in table 1.
TABLE 1
| Number of lower |
4 |
| Lower rotor radius R1 | 1.8m |
| Direction of rotation of the lower rotor | Looking down counterclockwise |
| Lower rotor speed N1 | 716rpm |
| Number of upper |
4 |
| Upper rotor radius R2 | 2.2m |
| Direction of rotation of the lower rotor | Looking down clockwise |
| Lower rotor speed N2 | 716rpm |
| Distance H between upper rotor wing and lower rotor wing | 0.3m |
| Upper and lower rotor wing installation dislocation angle alpha | 45° |
Fig. 4 and 5 are side and top views, respectively, of the rotor. Fig. 6 and 7 are a graph of lift coefficient versus hovering efficiency, a graph of lift coefficient versus lift-to-drag ratio, respectively, where R1 represents a lower rotor radius, R2 represents an upper rotor radius, fig. 6 is a data graph at a hovering state and at a rotational speed of 716rpm, and fig. 7 is a data graph at a forward flying state, at a rotational speed of 716rpm, and at a wind speed of 70 m/s.
According to the technical scheme, the coaxial double rotors with unequal diameters are in a coaxial reverse double-rotor layout, a tail rotor is not needed to overcome a reactive torque, and the structure is simple; compared with the conventional equal-diameter coaxial double rotors, the double-rotor type wind driven generator has obvious hovering efficiency advantage; because the upper and lower rotor diameter is different, the paddle is more difficult to bump each other, and the security is higher.
The foregoing is merely a detailed description of the embodiments of the present invention, and some of the conventional techniques are not detailed. The scope of the present invention is not limited thereto, and any changes or substitutions that can be easily made by those skilled in the art within the technical scope of the present invention will be covered by the scope of the present invention. The protection scope of the present invention shall be subject to the protection scope of the claims.
Claims (8)
1. Coaxial dual rotors of unequal diameter, characterized in that they comprise: go up rotor and lower rotor, go up rotor and lower rotor are coaxial, just the diameter of going up the rotor is greater than the diameter of lower rotor.
2. A dual differential diameter coaxial rotor according to claim 1, wherein said upper rotor rotates in a direction opposite to that of said lower rotor.
3. The dual, unequal diameter coaxial rotors according to claim 1, wherein the number of blades of the upper rotor and the number of blades of the lower rotor are at least two, and the number of blades of the lower rotor is less than or equal to the number of blades of the upper rotor.
4. Coaxial dual rotors according to claim 1, characterized in that the blades of said upper rotor and the blades of said lower rotor adopt different aerodynamic profiles.
5. A dual differential diameter coaxial rotor according to claim 1, wherein the ratio of the upper and lower rotor pitch to the diameter of the upper rotor is greater than or equal to 0.05.
6. Coaxial dual rotors according to claim 1, characterized in that said upper rotor comprises N1The included angle between adjacent blades is within the range of (360 DEG/N)1-360°/4N1，360°/N1+360°/4N1)，N1Is an even number greater than 2, and the lower rotor comprises N2The included angle between adjacent blades is within the range of (360 DEG/N)2-360°/4N2，360°/N2+360°/4N2)，N2An even number greater than 2.
7. A dual differential diameter coaxial rotors according to claim 1, wherein the ratio of the diameter of said lower rotor to the diameter of said upper rotor is a, 0.25 ≦ a < 1.
8. Coaxial dual rotors according to claim 1, characterized in that the misalignment angle of the upper rotor and the lower rotor is comprised between 0 ° and 360 °/N1In the meantime.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011021217.2A CN112173097A (en) | 2020-09-25 | 2020-09-25 | Coaxial double-rotor wing with unequal diameters |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011021217.2A CN112173097A (en) | 2020-09-25 | 2020-09-25 | Coaxial double-rotor wing with unequal diameters |
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| Publication Number | Publication Date |
|---|---|
| CN112173097A true CN112173097A (en) | 2021-01-05 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202011021217.2A Pending CN112173097A (en) | 2020-09-25 | 2020-09-25 | Coaxial double-rotor wing with unequal diameters |
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| Country | Link |
|---|---|
| CN (1) | CN112173097A (en) |
Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO1993001976A1 (en) * | 1991-07-19 | 1993-02-04 | Kunz Bernard P | Lift generating method and apparatus for aircraft |
| DE10125077A1 (en) * | 2001-05-14 | 2002-11-21 | Siegfried Pauli | Helicopter with concentric rotors has upper rotor of greater diameter than lower one |
| US20070084962A1 (en) * | 2005-10-18 | 2007-04-19 | The Boeing Company | An unloaded lift offset rotor system for a helicopter |
| CN202624632U (en) * | 2012-05-24 | 2012-12-26 | 孙朝辉 | Coaxial double-rotor structure of helicopter |
| CN105431352A (en) * | 2012-05-21 | 2016-03-23 | 保罗·E·阿尔托恩 | Rotary wing vehicle |
| CN105644777A (en) * | 2016-03-17 | 2016-06-08 | 中国直升机设计研究所 | Assembly type multi-rotor aerocraft |
| RU2658467C1 (en) * | 2016-12-27 | 2018-06-21 | Ростовский вертолетный производственный комплекс, Публичное акционерное общество "Роствертол" | High-speed twin screw helicopter of the coaxial scheme |
| CN108327899A (en) * | 2018-01-29 | 2018-07-27 | 陈铭 | A kind of coaxial double-oar helicopter rotor method for arranging and coaxial double-oar helicopter up and down |
| CN109334966A (en) * | 2018-09-17 | 2019-02-15 | 株洲格斯特动力机械有限责任公司 | Rotation coaxial double-rotary wing lift unit and the rotation coaxial double-rotary wing machine for applying it |
-
2020
- 2020-09-25 CN CN202011021217.2A patent/CN112173097A/en active Pending
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO1993001976A1 (en) * | 1991-07-19 | 1993-02-04 | Kunz Bernard P | Lift generating method and apparatus for aircraft |
| DE10125077A1 (en) * | 2001-05-14 | 2002-11-21 | Siegfried Pauli | Helicopter with concentric rotors has upper rotor of greater diameter than lower one |
| US20070084962A1 (en) * | 2005-10-18 | 2007-04-19 | The Boeing Company | An unloaded lift offset rotor system for a helicopter |
| CN105431352A (en) * | 2012-05-21 | 2016-03-23 | 保罗·E·阿尔托恩 | Rotary wing vehicle |
| CN202624632U (en) * | 2012-05-24 | 2012-12-26 | 孙朝辉 | Coaxial double-rotor structure of helicopter |
| CN105644777A (en) * | 2016-03-17 | 2016-06-08 | 中国直升机设计研究所 | Assembly type multi-rotor aerocraft |
| RU2658467C1 (en) * | 2016-12-27 | 2018-06-21 | Ростовский вертолетный производственный комплекс, Публичное акционерное общество "Роствертол" | High-speed twin screw helicopter of the coaxial scheme |
| CN108327899A (en) * | 2018-01-29 | 2018-07-27 | 陈铭 | A kind of coaxial double-oar helicopter rotor method for arranging and coaxial double-oar helicopter up and down |
| CN109334966A (en) * | 2018-09-17 | 2019-02-15 | 株洲格斯特动力机械有限责任公司 | Rotation coaxial double-rotary wing lift unit and the rotation coaxial double-rotary wing machine for applying it |
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Application publication date: 20210105 |