CN114987758A - Cycloidal propeller duct power device and aircraft using same - Google Patents
Cycloidal propeller duct power device and aircraft using same Download PDFInfo
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- CN114987758A CN114987758A CN202210683480.0A CN202210683480A CN114987758A CN 114987758 A CN114987758 A CN 114987758A CN 202210683480 A CN202210683480 A CN 202210683480A CN 114987758 A CN114987758 A CN 114987758A
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- 230000007246 mechanism Effects 0.000 description 11
- 230000001360 synchronised effect Effects 0.000 description 5
- 238000010586 diagram Methods 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000005096 rolling process Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 244000309464 bull Species 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000005457 optimization Methods 0.000 description 1
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- 230000002441 reversible effect Effects 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C39/00—Aircraft not otherwise provided for
- B64C39/003—Aircraft not otherwise provided for with wings, paddle wheels, bladed wheels, moving or rotating in relation to the fuselage
- B64C39/008—Aircraft not otherwise provided for with wings, paddle wheels, bladed wheels, moving or rotating in relation to the fuselage about a longitudinal axis
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
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Abstract
The utility model provides a cycloidal propeller duct power device and use its aircraft, includes engine, cycloidal propeller system, support, apron and kuppe, the support includes first support and second support, the both ends at cycloidal propeller system are installed respectively to first support and second support, the apron includes first apron and second apron, the both sides at cycloidal propeller system are installed respectively to first apron and second apron, the kuppe includes first kuppe and second kuppe, first kuppe is installed respectively with the second kuppe the both ends of support, the engine is installed in first kuppe, and with cycloidal propeller system connection, with cycloidal propeller duct power device on the aircraft, has filled the vacancy in market.
Description
Technical Field
The invention relates to the technical field of aircrafts, in particular to a cycloidal propeller duct power device and an aircraft using the same.
Background
The cycloidal propeller is an omnidirectional vector propulsion device and generally comprises more than two blades, and the blade wing profile adopts a symmetrical subsonic wing profile. Different from the traditional propeller, the rotating axis of the blade is parallel to the plane of the blade, the moving track of the blade is a circumference in the hovering state, and the track of the blade is a cycloid in the advancing state, so the propeller is called as a cycloid paddle. The main principle is that the blades also do periodic pitching motion in the process of circular motion through the blade reversing mechanism, so that airflow is blown out in a stable direction to generate thrust. The current reversing mechanisms include a slide rail type, an eccentric mechanism type, an electronic control type, and the like. The first frame in the world successfully flies up and adopts an eccentric structure for the stably controllable wing rolling machine. The cycloidal propeller aircraft can achieve high propeller efficiency under the condition of low feed speed ratio.
The aircraft lift device or power device with the duct structure can obtain higher lift efficiency or power performance due to the optimization of the flow field of the duct wall, has been widely applied to the propeller power devices of rotor type aircrafts and fixed wing type aircrafts, but is not applied to rolling wing type aircrafts.
Disclosure of Invention
In view of the defects in the background art, the invention relates to a cycloidal propeller bypass power device and an aircraft using the same.
The invention relates to a cycloidal propeller bypass power device which comprises an engine, a cycloidal propeller system, a support, a cover plate and a flow guide cover, wherein the support comprises a first support and a second support, the first support and the second support are respectively installed at two ends of the cycloidal propeller system, the cover plate comprises a first cover plate and a second cover plate, the first cover plate and the second cover plate are respectively installed at two sides of the cycloidal propeller system, the flow guide cover comprises a first flow guide cover and a second flow guide cover, the first flow guide cover and the second flow guide cover are respectively installed at two ends of the support, and the engine is installed in the first flow guide cover and is connected with the cycloidal propeller system.
Furthermore, the bracket and the cover plate are fixed around the power device to form an annular closed duct structure.
Further, the inner wall of the duct structure is smooth.
Furthermore, the air guide sleeve is fixed at two ends of the first support and the second support.
Furthermore, the inside of the air guide sleeve is hollow, the engine is installed on the first support, the engine part is installed inside the air guide sleeve, and the engine provides power for the cycloidal propeller system.
The invention also provides an aircraft which is provided with two pairs of wing plates, wherein the root part of each wing plate is provided with a cycloidal propeller bypass power device.
The invention also provides an aircraft which is provided with two pairs of bracket plates, wherein one end of each bracket plate is fixedly connected with the aircraft, and the other end of each bracket plate is fixedly connected with a cycloidal propeller culvert power device.
The invention has the main beneficial effects that the cycloidal propeller device is embedded into the duct, the overall efficiency under the condition of lower speed ratio is optimized, the safety of the overall structure is improved, the noise and the vibration of the power device are reduced, the advantages of simple operation and control and large lifting force and thrust are also achieved, the flight reliability is higher, meanwhile, the vertical take-off and landing power is effectively provided for the aircraft, and the invention has the advantages of high production power efficiency, good control effect, low cost, wide application scene and the like.
Drawings
FIG. 1 is a schematic view of a cycloidal-oar ducted power plant in an embodiment of the present invention;
FIG. 2 is a schematic view of a duct structure in embodiment 1 of the present invention;
FIG. 3 is a side view of a cycloidal-oar ducted power plant in embodiment 1 of the present invention;
FIG. 4 is a schematic view of the engine mounting in embodiment 1 of the invention;
FIG. 5 is a schematic view of a cycloidal propeller system according to embodiment 1 of the present invention;
fig. 6 is a schematic diagram of the disc type cycloidal propeller synchronous rotating mechanism in embodiment 1 of the present invention;
FIG. 7 is a schematic view showing the matching of the eccentric shaft, the gear and the ring gear in embodiment 1 of the present invention;
FIG. 8 is a schematic view of a first mode of application of embodiment 2 of the present invention;
fig. 9 is a schematic diagram of a second application mode in embodiment 3 of the present invention.
Reference numerals: 1. a first bracket; 2. a second bracket; 3. a first cover plate; 4. a second cover plate; 5. a first pod; 6. a second pod; 7. an engine; 8. a cycloidal-paddle system; 81. a proximal paddle mount; 82. a distal paddle support; 83. a hollow main shaft; 84. a paddle; 85. an eccentric shaft; 86. a bull gear; 87. a large inner gear ring; 88. a pinion gear; 89. a small inner gear ring; 810. a gear connecting shaft; 811. a blade pull rod; 812. a paddle rocker arm; 813. a pull rod tray; 9. a cycloidal-oar ducted power plant; 10. an aircraft.
Detailed Description
While the embodiments of the present invention will be described and illustrated in detail with reference to the accompanying drawings, it is to be understood that the invention is not limited to the specific embodiments disclosed, but is intended to cover various modifications, equivalents, and alternatives falling within the scope of the invention as defined by the appended claims.
For the convenience of understanding the embodiments of the present invention, the following description will be further explained by taking specific embodiments as examples with reference to the drawings, and the embodiments are not to be construed as limiting the embodiments of the present invention.
The first support 1 and the second support 2 are fixedly installed at two ends of a cycloidal propeller system 8, the first cover plate 3 and the second cover plate 4 are installed on two sides of the cycloidal propeller system 8 respectively, the engine 7 is fixedly installed on the first support 1 and connected with the cycloidal propeller system 8 through a gear, and the first guide cover 5 and the second guide cover 6 are fixedly installed on the first support 1 and the second support 2 respectively.
The first support 1, the second support 2, the first cover plate 3 and the second cover plate 4 are respectively arranged around the cycloidal propeller system 8 and are connected end to form a closed duct structure.
The shapes of the first cover plate 3 and the second cover plate 4 can be adjusted as required, the inner wall of the duct keeps smooth, and the flow field in the duct can be more stable. The heights of the first cover plate 3 and the second cover plate 4 are slightly larger than the height of the cycloidal propeller culvert power device 9, so that the overall efficiency can be effectively improved during working.
The first guide cover 5 and the second guide cover 6 are respectively arranged on two sides of the first support 1 and the second support 2, and when the cycloidal propeller bypass power device 9 runs horizontally, air resistance and energy loss are reduced.
The cycloidal propeller system 8 may be any cycloidal propeller system 8 known in the art. The cycloidal propeller system 8 can adopt the cycloidal propeller system 8 shown in fig. 6 and 7, wherein the cycloidal propeller system 8 comprises a power system and a cycloidal propeller mechanism, the cycloidal propeller mechanism comprises a synchronous rotating mechanism, a near-end blade support 81, a far-end blade support 82, a hollow main shaft 83 and blades 84, the synchronous rotating mechanism comprises an eccentric shaft 85, a large gear 86, a large inner gear ring 87, a small gear 88, a small inner gear ring 89, a gear connecting shaft 810, a blade pull rod 811, a blade rocker arm 812 and a pull rod disk 813, the number of the outer end fixing holes of the blade pull rod 811 disk 813, the number of the blade pull rod 811 and the number of the blade rocker arm 812 correspond to the number of the blades 84 one by one, one end of the blade pull rod 811 is connected with one end of the corresponding blade 84, one end of the blade pull rod 811 is connected with the outer end fixing hole of the pull rod disk through a bearing, the large inner gear ring 87 is fixed on the near-end blade support 81, the blade driving mechanism is meshed with a large gear 86, a small inner gear ring 89 is fixed on a pull rod disc 813 and meshed with a small gear 88, the large gear 86 and the small gear 88 are connected on the same axis through a gear connecting shaft 810, the gear connecting shaft 810 is fixed at the lower end of an eccentric shaft 85 through a bearing, the hollow main shaft 83 is coaxially and fixedly connected with a near-end blade support 81 and a far-end blade support 82, one end of the eccentric shaft 85 is fixed inside one end of the hollow main shaft 83 through a bearing, the power system is used for providing power for the hollow main shaft 83, two ends of the blade 84 are respectively connected with the near-end blade support 81 and the far-end blade support 82 through blade 84 bearings and form a self rotating shaft which rotates and moves after being connected with the near-end blade support 81 and the far-end blade support 82, and the blade 84 is driven by a synchronous rotating mechanism to revolve.
Wherein the segmented self-assembling fan blade is composed of blades 84 connected by blade rocker arms 812. The cycloidal propeller system 8 is adopted to realize the control of the turning angle of the blades by taking an eccentric shaft and a gear as a main reversing mechanism, the number of connecting points of blade rocker arms 812 on a pull rod disc 813 can be controlled under the control of a synchronous rotating device, and the blade pull rods 811 carry out combined connection on grouped small blades, so that the number of the blades can be increased at will. The sectional type self-combination fan blade has the advantage that a large blade is divided into a plurality of sections of small blades so as to achieve the purpose of reducing resistance.
The working principle of the invention is as follows:
when the main shaft of the cycloidal propeller system 8 is driven by the engine 7 to rotate and work, air in a duct structure formed by the first support 1, the second support 2, the first cover plate 3 and the second cover plate 4 is accelerated by the cycloidal propeller system 8, and airflow is output from the lower part of the cycloidal propeller duct power device 9 to form stable reverse thrust to provide power for vertical take-off and landing of the whole cycloidal propeller duct power device 9 and the aircraft 10.
In embodiment 2 of the present invention, referring to fig. 8, based on embodiment 1, a cycloidal-propeller duct power device is installed on an aircraft, the aircraft is provided with two pairs of wing plates, and the root of each wing plate is provided with one cycloidal-propeller duct power device to provide power for vertical take-off and landing of the aircraft.
In embodiment 3 of the present invention, referring to fig. 9, based on embodiment 1, a cycloidal-propeller duct power device is installed on an aircraft, the aircraft is provided with two pairs of bracket plates, and each bracket plate is provided with one cycloidal-propeller duct power device, which can also provide power for vertical take-off and landing of the aircraft.
Finally, it should be noted that: although the present invention has been described in detail with reference to the foregoing embodiments, it should be understood by those skilled in the art that: any person skilled in the art can modify or easily conceive the technical solutions described in the foregoing embodiments or equivalent substitutes for some technical features within the technical scope of the present disclosure; such modifications, changes or substitutions do not depart from the spirit and scope of the embodiments of the present invention, and they should be construed as being included therein. Therefore, the protection scope of the present invention shall be subject to the protection scope of the claims.
Claims (7)
1. The utility model provides a cycloidal propeller duct power device which characterized in that: including engine, cycloid oar system, support, apron and kuppe, the support includes first support and second support, the both ends at cycloid oar system are installed respectively to first support and second support, the apron includes first apron and second apron, the both sides at cycloid oar system are installed respectively to first apron and second apron, the kuppe includes first kuppe and second kuppe, first kuppe is installed respectively with the second kuppe the both ends of support, the engine is installed in first kuppe, and with cycloid oar headtotail.
2. The cycloidal-paddle ducted power plant of claim 1, wherein: the bracket and the cover plate are fixed around the power device to form an annular closed duct structure.
3. The cycloidal propeller bypass power plant of claim 2, further comprising: the inner wall of the duct structure is smooth.
4. The cycloidal propeller bypass power plant of claim 3, wherein: the air guide sleeve is fixed at two ends of the first support and the second support.
5. The cycloidal-paddle ducted power plant of claim 4, wherein: the inside of the air guide sleeve is hollow, the engine is installed on the first support, the engine is partially installed inside the air guide sleeve, and the engine provides power for the cycloidal propeller system.
6. An aircraft employing the cycloidal-paddle ducted power plant of any one of claims 1-5, characterized in that: the aircraft is provided with two pairs of wing plates, wherein the root of each wing plate is provided with a cycloidal propeller ducted power device.
7. An aircraft employing the cycloidal-oar ducted power plant of any one of claims 1-5, wherein: the aircraft is provided with two pairs of bracket plates, one end of each bracket plate is fixedly connected with the aircraft, and the other end of each bracket plate is fixedly connected with a cycloidal propeller duct power device.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210683480.0A CN114987758A (en) | 2022-06-16 | 2022-06-16 | Cycloidal propeller duct power device and aircraft using same |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210683480.0A CN114987758A (en) | 2022-06-16 | 2022-06-16 | Cycloidal propeller duct power device and aircraft using same |
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| Publication Number | Publication Date |
|---|---|
| CN114987758A true CN114987758A (en) | 2022-09-02 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210683480.0A Pending CN114987758A (en) | 2022-06-16 | 2022-06-16 | Cycloidal propeller duct power device and aircraft using same |
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| CN (1) | CN114987758A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115258150A (en) * | 2022-09-19 | 2022-11-01 | 吴拥军 | Novel aircraft |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN202481313U (en) * | 2012-01-30 | 2012-10-10 | 西北工业大学 | Flying wing aircraft with cycloidal rotor thrusters installed |
| CN109229367A (en) * | 2018-10-30 | 2019-01-18 | 南京航空航天大学 | A kind of new configuration vertical take-off and landing drone and its flight control method |
| CN109515704A (en) * | 2018-12-18 | 2019-03-26 | 南京航空航天大学 | Duct plume rotor craft based on cycloid propeller technology |
| KR20200018837A (en) * | 2018-08-13 | 2020-02-21 | 김하영 | A Guiding Duct for a Wind Generator and the Wind Generator with the Same |
| CN112960113A (en) * | 2021-04-14 | 2021-06-15 | 杭州宝桐科技有限公司 | Orbital ring rotary flapping wing power device |
| CN113895617A (en) * | 2021-04-14 | 2022-01-07 | 杭州宝桐科技有限公司 | Concave rail controlled rotary flapping wing power device |
| CN218229412U (en) * | 2022-06-16 | 2023-01-06 | 杭州宝桐科技有限公司 | Cycloidal propeller duct power device and aircraft using same |
-
2022
- 2022-06-16 CN CN202210683480.0A patent/CN114987758A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN202481313U (en) * | 2012-01-30 | 2012-10-10 | 西北工业大学 | Flying wing aircraft with cycloidal rotor thrusters installed |
| KR20200018837A (en) * | 2018-08-13 | 2020-02-21 | 김하영 | A Guiding Duct for a Wind Generator and the Wind Generator with the Same |
| CN109229367A (en) * | 2018-10-30 | 2019-01-18 | 南京航空航天大学 | A kind of new configuration vertical take-off and landing drone and its flight control method |
| CN109515704A (en) * | 2018-12-18 | 2019-03-26 | 南京航空航天大学 | Duct plume rotor craft based on cycloid propeller technology |
| CN112960113A (en) * | 2021-04-14 | 2021-06-15 | 杭州宝桐科技有限公司 | Orbital ring rotary flapping wing power device |
| CN113895617A (en) * | 2021-04-14 | 2022-01-07 | 杭州宝桐科技有限公司 | Concave rail controlled rotary flapping wing power device |
| CN218229412U (en) * | 2022-06-16 | 2023-01-06 | 杭州宝桐科技有限公司 | Cycloidal propeller duct power device and aircraft using same |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115258150A (en) * | 2022-09-19 | 2022-11-01 | 吴拥军 | Novel aircraft |
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