CN218229412U

CN218229412U - Cycloidal propeller duct power device and aircraft using same

Info

Publication number: CN218229412U
Application number: CN202221510106.2U
Authority: CN
Inventors: 张旭生; 陈晓春; 刘盛辉; 芦威涛
Original assignee: Hangzhou Baotong Technology Co ltd
Current assignee: Hangzhou Baotong Technology Co ltd
Priority date: 2022-06-16
Filing date: 2022-06-16
Publication date: 2023-01-06
Anticipated expiration: 2032-06-16

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

Cycloidal propeller duct power device and aircraft using same

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, and the main reason is that the thrust of the traditional cycloidal propeller is smaller.

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 ducted 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 cycloid 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 feed 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 lift 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 showing the engine mounting in embodiment 1 of the invention;

FIG. 5 is a schematic view of a system of cycloid paddles in 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 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.

Embodiment 1 of the invention is shown with reference to fig. 1, fig. 2, fig. 3, fig. 4, and fig. 5, and relates to a cycloidal-propeller bypass power device, which is composed of a first bracket 1, a second bracket 2, a first cover plate 3, a second cover plate 4, a first air guide sleeve 5, a second air guide sleeve 6, an engine 7, and a cycloidal-propeller system 8.

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 prior art cycloidal propeller system 8. The cycloidal propeller system 8 can adopt a cycloidal propeller system 8 as shown in figures 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 propeller bracket 81, a far-end propeller bracket 82, a hollow main shaft 83 and propellers 84, the synchronous rotating mechanism comprises an eccentric shaft 85, a large gear 86, a large internal gear ring 87, a small gear 88, a small internal gear ring 89, a gear connecting shaft 810, a blade pull rod 811, a blade rocker 812 and a pull rod disc 813, the number of the outer end fixing holes of the paddle pull rod 811 disc 813, the number of the paddle pull rods 811 and the number of the paddle rocker arms 812 correspond to the number of the paddles 84 one by one, one end of the paddle pull rod 811 is connected with one end of the corresponding paddle 84, one end of the paddle pull rod 811 is connected with the outer end fixing hole of the pull rod disc 813 through a bearing, the large inner gear ring 87 is fixed on the near-end paddle support 81, the small inner gear ring 89 is fixed on the pull rod disc 813 and is meshed with the small gear 88, the large gear 86 and the small gear 88 are on the same axis, are connected through the gear connecting shaft 810, the gear connecting shaft 810 is fixed at the lower end of the eccentric shaft 85 through a bearing, the hollow main shaft 83 is coaxially and fixedly connected with the near-end blade support 81 and the 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, both ends of the paddle 84 are respectively connected with the near-end paddle support 81 and the far-end paddle support 82 through paddle 84 bearings, the rotating shafts of the paddles are connected with the near-end paddle support 81 and the far-end paddle support 82 to form self rotating shafts, and the paddles 84 are driven by the synchronous rotating mechanism to perform revolution motion.

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 self-combination fan blade has the advantage that one large blade is divided into a plurality of small blades 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 so as to provide power for vertical lifting 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, as shown in fig. 9, based on embodiment 1, a cycloidal-paddle ducted 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-paddle ducted power device, which can also provide power for vertical take-off and landing of the aircraft.

Finally, it should be noted that: the above-mentioned embodiments are only specific embodiments of the present invention, which are used for illustrating the technical solutions of the present invention and not for limiting the same, and the protection scope of the present invention is not limited thereto, although the present invention is described in detail with reference to the foregoing embodiments, those skilled in the art should understand that: those skilled in the art can still make modifications or changes to the embodiments described in the foregoing embodiments, or make equivalent substitutions for some features, within the scope of the 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

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-paddle ducted power plant of claim 2, characterized in that: 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, characterized in that: the inside hollow that is of kuppe, the engine is installed on first support, the engine part is installed inside the kuppe, the engine is for cycloid oar system provides power.

6. 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 wing plates, wherein the root part of each wing plate is provided with a cycloidal propeller culvert power device.

7. 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 support plates, one end of each support plate is fixedly connected with the aircraft, and the other end of each support plate is fixedly connected with a cycloidal propeller duct power device.