CN112960113A - Orbital ring rotary flapping wing power device - Google Patents
Orbital ring rotary flapping wing power device Download PDFInfo
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- CN112960113A CN112960113A CN202110399016.4A CN202110399016A CN112960113A CN 112960113 A CN112960113 A CN 112960113A CN 202110399016 A CN202110399016 A CN 202110399016A CN 112960113 A CN112960113 A CN 112960113A
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- 230000000694 effects Effects 0.000 abstract description 8
- 238000010248 power generation Methods 0.000 abstract description 3
- 230000008092 positive effect Effects 0.000 abstract description 2
- 238000005516 engineering process Methods 0.000 description 3
- 238000010586 diagram Methods 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 230000002093 peripheral effect Effects 0.000 description 2
- 230000008569 process Effects 0.000 description 2
- 238000004364 calculation method Methods 0.000 description 1
- 230000008878 coupling Effects 0.000 description 1
- 238000010168 coupling process Methods 0.000 description 1
- 238000005859 coupling reaction Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 230000007246 mechanism Effects 0.000 description 1
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- 238000004088 simulation Methods 0.000 description 1
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C33/00—Ornithopters
- B64C33/02—Wings; Actuating mechanisms therefor
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C29/00—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
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Abstract
The invention relates to a track ring rotary flapping wing power device which comprises a support, an engine, a coupler, a main shaft, a track ring support frame, a track ring connector, a track ring connecting bearing, a core track ring, a sliding sleeve support, a sliding block shaft bearing, a small pulley, a driving rocker arm bearing, a middle shaft connecting block, a driven rocker arm, a driven shaft connecting block, a blade distribution wheel, blades, a blade support, a blade far-end bearing and sectional self-combined blades. The orbital ring rotating flapping wing power device can effectively provide vertical take-off and landing power for the aircraft, has the advantages of high power generation efficiency, good control effect, low cost, wide application scene and the like, and has very positive effects.
Description
Technical Field
The invention belongs to a reversing power device, and particularly relates to a track ring rotating flapping wing power device.
Background
The vertical take-off and landing technology is a technology which can take off and land without running; the vertical take-off and landing airplane reduces or basically gets rid of the dependence on a runway, can be pulled up and vertically landed only by a small flat ground, can be scattered and configured by the technology, is convenient to flexibly attack, transfer and disguise and conceal, and improves the survival rate of the airplane battlefield; vertical take-off and landing aircraft can be roughly classified into rotor-wing aircraft, jet engine thrust steering aircraft, tilt rotor aircraft, tail-stock propeller-powered aircraft, and ducted fan-powered aircraft.
However, the vertical take-off and landing aircraft has no way of large-area popularization and use due to the defects which can not be overcome by the vertical take-off and landing aircraft. For example, although a large propeller is used as a tiltrotor for vertical take-off and landing and flat flight power device, the large propeller can be used only in a wide and flat area, and cannot be deployed in a narrow space or a place with many obstacles, such as a building street, so that the propeller easily collides with peripheral objects. The vertical take-off and landing scheme based on the power of the jet engine has lower requirements on the use space, but the energy efficiency of the thrust is lower, and meanwhile, tail gas generated by high-temperature and high-pressure jet can cause damage to nearby objects; the vertical take-off and landing mode is low in energy efficiency and high in use risk, and the jet wake easily causes ground scorching or peripheral objects to be ignited, so that the vertical take-off and landing mode has high requirements on take-off and landing sites and cannot be used in other sites.
Disclosure of Invention
In order to solve the technical problem, the invention provides an orbital ring rotary flapping wing power device.
The technical scheme of the invention is as follows:
a track ring rotary flapping wing power device comprises a support, an engine, a coupler, a main shaft, a track ring support frame, a track ring connector, a track ring connecting bearing, a core track ring, a sliding sleeve support, a sliding block shaft bearing, a small pulley, a driving rocker arm bearing, a middle shaft connecting block, a driven rocker arm, a driven shaft connecting block, a blade distribution wheel, blades, a blade support, a blade far-end bearing and sectional self-combination blades; the engine is fixed on the support, the rotating shaft of the engine is connected with the coupler, and the coupler, the track ring connecting bearing, the sliding sleeve support, the blade support and the blade far-end bearing are respectively and fixedly arranged on the main shaft; the core track ring is fixed on the track ring connector, the track ring connector is fixed on the track ring support frame, and the track ring support frame is fixed on the support; the core track ring, the track ring connector, the track ring support frame and the track ring connecting bearing penetrate through the main shaft; the sliding block shaft penetrates through and is fixed on the sliding block, a sliding block shaft bearing is fixedly arranged at one end of the inner side of the sliding block shaft, and a driving rocker bearing is fixedly arranged at one end of the outer side of the sliding block shaft; each sliding block is fixedly provided with a plurality of small pulleys, and the sliding block can move in the sliding sleeve; the sliding block shaft bearing is internally tangent to the core orbit ring; the sliding sleeve is fixedly arranged on the sliding sleeve bracket; one end of the driving rocker arm is fixedly arranged on the sliding block shaft through a driving rocker arm bearing, and the other end of the driving rocker arm is arranged on the middle shaft connecting block; two ends of the driven rocker arm are respectively assembled on the middle shaft connecting block and the driven shaft connecting block; the middle shaft connecting block and the slave shaft connecting block are fixedly arranged on the sliding sleeve bracket; the blade distribution wheel is fixedly arranged on the middle shaft connecting block and the driven shaft connecting block; one end of each blade is fixedly arranged on the blade distribution wheel, the other end of each blade is arranged on the blade support, and the sectional type self-combination fan blades are composed of the blades.
The sliding sleeve support, the blade support and the sectional type self-combination fan blade are in a cross shape.
Each sliding block is fixedly provided with 16 small pulleys.
The core orbital ring is upwardly convex relative to the orbital ring interface.
The core orbital ring is an irregular annular orbital ring and consists of an upper circular arc section and a lower circular arc section and a straight line section part with two sides connected with the two circular arc sections, and the circular arc radius of the upper part is larger than that of the lower part.
When the engine drives the main shaft to rotate to work, the sliding sleeve support rotates to operate, a sliding block in the sliding sleeve support and the sliding sleeve moves along the core track ring through a sliding block shaft bearing, so that the sliding block is driven to move in the sliding sleeve, the sliding block shaft drives the driving rocker arm to act while moving in the sliding sleeve, the middle shaft connecting block rotates to drive the driven rocker arm to act, and the middle shaft connecting block rotates to pull the driven rocker arm to act, so that the driven rocker arm rotates; the middle shaft connecting block and the driven shaft connecting block rotate to drive the blade distribution wheel to rotate, and the rotary flapping wings of the blades and the sectional type self-combination fan blades are realized.
According to the orbital ring rotating flapping wing power device, the opening and closing of the blades are realized through the orbital ring which is a simpler structure, and the grouped small blades can be combined and connected through the connecting rod mechanism under the control of the orbital ring, so that the number of the blades can be arbitrarily increased, and the effect of increasing and reducing the area of the blades is achieved. The grouped blades have the advantages that one large blade is divided into a plurality of small blades, and the blades are automatically separated and combined when working, so that the rotating force arm of the blades in the opening and closing process is greatly reduced, and the purpose of reducing resistance is achieved. The invention can effectively provide the vertical take-off and landing power for the aircraft and has the advantages of high power generation efficiency, good control effect, low cost, wide application scene and the like.
Drawings
FIG. 1 is a schematic structural view of the present invention;
FIG. 2 is a schematic view of the internal structure of the present invention 1;
FIG. 3 is a schematic view of the internal structure of the present invention in FIG. 2;
FIG. 4 is a schematic view of the internal structure of the present invention, FIG. 3;
FIG. 5 is a schematic diagram of a first application of the present invention;
FIG. 6 is a schematic diagram of a second application of the present invention;
FIG. 7 is a schematic view of a third mode of application of the present invention;
in the figure, 1 support, 2 engines, 3 couplings, 4 main shafts, 5 orbital ring support frames, 6 orbital ring connectors, 7 orbital ring connecting bearings, 8 core orbital rings, 9 sliding sleeves, 10 sliding sleeve supports, 11 sliding blocks, 12 sliding block shafts, 13 sliding block shaft bearings, 14 small pulleys, 15 driving rocker arms, 16 driving rocker arm bearings, 17 middle shaft connecting blocks, 18 driven rocker arms, 19 driven shaft connecting blocks, 20 blade distribution wheels, 21 blades, 22 blade supports, 23 blade distal end bearings, 24 segmented self-combination blades, 25 orbital ring rotary flapping wing power devices and 26 aircrafts are adopted.
Detailed Description
The present invention will be described in detail with reference to the accompanying drawings.
As shown in fig. 1, 2, 3 and 4, the orbital ring rotary flapping wing power device of the invention comprises a support 1, an engine 2, a coupler 3, a main shaft 4, an orbital ring support frame 5, an orbital ring connector 6, an orbital ring connector bearing 7, a core orbital ring 8, a sliding sleeve 9, a sliding sleeve support 10, a sliding block 11, a sliding block shaft 12, a sliding block shaft bearing 13, a small pulley 14, a driving rocker arm 15, a driving rocker arm bearing 16, a middle shaft connector block 17, a driven rocker arm 18, a middle shaft connector block 19, a blade distribution wheel 20, blades 21, a blade support 22, a blade distal end bearing 23 and segmented self-assembled blades 24.
The engine 2 is fixed on the support 1, the engine rotating shaft is connected with the coupler 3, and the coupler 3, the track ring connecting bearing 7, the sliding sleeve support 10, the blade support 22 and the blade far-end bearing 23 are respectively and fixedly arranged on the main shaft 4; the core track ring 8 is fixed on the track ring connector 6, the track ring connector 6 is fixed on the track ring support frame 5, and the track ring support frame 5 is fixed on the support 1; the core orbital ring 8, the orbital ring connector 6, the orbital ring support frame 5 and the orbital ring connecting bearing 7 penetrate through the main shaft 4; the slider shaft 12 penetrates and is fixed on the slider 11, the slider shaft bearing 13 is fixedly installed at one end of the inner side of the slider shaft 12, and the driving rocker bearing 16 is fixedly installed at one end of the outer side of the slider shaft 12. The sliding sleeve support 10, the blade support 22 and the segmented self-assembled fan blades 24 are cruciform.
As shown in fig. 1, 2, 3 and 4, each sliding block is fixedly provided with 16 small pulleys 14, and the sliding block 11 can move in the sliding sleeve 9; the slider shaft bearing 13 is internally tangent to the core orbital ring 8; the sliding sleeve 9 is fixedly arranged on the sliding sleeve bracket 10; one end of an active rocker arm 15 is fixedly arranged on the slider shaft 12 through an active rocker arm bearing 16, and the other end of the active rocker arm 15 is arranged on a middle shaft connecting block 17; two ends of the driven rocker arm 18 are respectively assembled on the middle shaft connecting block 17 and the driven shaft connecting block 19; the middle shaft connecting block 17 and the slave shaft connecting block 19 are fixedly arranged on the sliding sleeve bracket 10; the blade distribution wheel 20 is fixedly arranged on the middle shaft connecting block 17 and the slave shaft connecting block 19; the blades 21 are fixedly mounted at one end to the blade distribution wheel 20 and at the other end to the blade support 22.
When the engine 2 drives the main shaft 4 to rotate through the coupler 3, the sliding sleeve support 10 rotates and operates, the sliding block 11 in the sliding sleeve 9 on the sliding sleeve support 10 moves along the core track ring 8 through the sliding block shaft bearing 13, so that the sliding block 11 is driven to move in the sliding sleeve 9, the sliding block shaft 12 drives the driving rocker arm 15 to act while the sliding block 11 moves in the sliding sleeve 9, the middle shaft connecting block 17 rotates and rotates, and the middle shaft connecting block 17 rotates and drives the driven rocker arm 18 to act, so that the driven rocker arm 19 rotates and rotates; rotation of the central shaft connection block 17 and the rotating driven blade distribution wheel 20 from the shaft connection block 19 effects a rotary flapping of the blades 21.
As shown in fig. 4, the core orbital ring 8 is an irregular annular orbital ring subjected to simulation calculation, the core orbital ring 8 protrudes upward relative to the orbital ring connector 6, the core orbital ring 8 is composed of an upper circular arc section and a lower circular arc section and a straight line section part with two sides connected with the two circular arc sections, and the circular arc radius of the upper part is larger than that of the lower part; the slider 11, by running along the core orbital ring 8, can effect a rotation of the blade 21 from 0 to 90 degrees when encountering orbital arc path changes; the sectional type self-combination fan blade 24 is composed of blades 21, and the rotation of the blades 21 from 0 to 90 degrees realizes the rotary flapping wing of the sectional type self-combination fan blade 24, so that the power effect of vertical take-off and landing is achieved. Through a system formed by the track ring control and the grouped blades, the blades are automatically combined into a whole to be pressed down to do work under the control of the inherent track of the track, and the blades are folded to be not acted with air in the other half process, so that the continuous work and the folding are alternately performed in a cycle period, the whole machine obtains an effective upward lifting power, and the whole aircraft obtains the vertical take-off and landing effect.
As shown in fig. 5, 6 and 7, the orbital ring rotary flapping wing power device of the invention can be symmetrically installed and applied to different aircrafts in various ways according to actual needs to provide vertical take-off and landing power for the aircrafts.
The orbital ring rotating flapping wing power device provided by the invention can effectively provide vertical take-off and landing power for an aircraft, has the advantages of high power generation efficiency, good control effect, easiness in operation, low cost, wide application scene, flexibility in flying and the like, and has very positive effects.
The above description is only for the purpose of illustrating the preferred embodiments of the present invention and is not to be construed as limiting the invention, and any modifications, equivalents and improvements made within the spirit and principle of the present invention are included in the scope of the present invention.
Claims (6)
1. A track ring rotating flapping wing power device is characterized by consisting of a support (1), an engine (2), a coupler (3), a main shaft (4), a track ring support frame (5), a track ring connector (6), a track ring connecting bearing (7), a core track ring (8), a sliding sleeve (9), a sliding sleeve support (10), a sliding block (11), a sliding block shaft (12), a sliding block shaft bearing (13), a small pulley (14), a driving rocker arm (15), a driving rocker arm bearing (16), a middle shaft connecting block (17), a driven rocker arm (18), a driven shaft connecting block (19), a blade distribution wheel (20), blades (21), a blade support (22), a blade far-end bearing (23) and segmented self-combined blades (24); the engine (2) is fixed on the support (1), an engine rotating shaft is connected with the coupler (3), and the coupler (3), the track ring connecting bearing (7), the sliding sleeve support (10), the blade support (22) and the blade far-end bearing (23) are respectively and fixedly installed on the main shaft (4); the core track ring (8) is fixed on the track ring connector (6), the track ring connector (6) is fixed on the track ring support frame (5), and the track ring support frame (5) is fixed on the support (1); the core track ring (8), the track ring connector (6), the track ring support frame (5) and the track ring connecting bearing (7) penetrate through the main shaft (4); the sliding block shaft (12) is fixedly penetrated on the sliding block (11), the sliding block shaft bearing (13) is fixedly arranged at one end of the inner side of the sliding block shaft (12), and the driving rocker bearing (16) is fixedly arranged at one end of the outer side of the sliding block shaft (12); each sliding block (11) is fixedly provided with a plurality of small pulleys (14), and the sliding block (11) can move in the sliding sleeve (9); the slide block shaft bearing (13) is internally tangent to the core orbit ring (8); the sliding sleeve (9) is fixedly arranged on the sliding sleeve bracket (10); one end of an active rocker arm (15) is fixedly arranged on the sliding block shaft (12) through an active rocker arm bearing (16), and the other end of the active rocker arm (15) is arranged on a middle shaft connecting block (17); two ends of the driven rocker arm (18) are respectively assembled on the middle shaft connecting block (17) and the driven shaft connecting block (19); the middle shaft connecting block (17) and the slave shaft connecting block (19) are fixedly arranged on the sliding sleeve bracket (10); the blade distribution wheel (20) is fixedly arranged on the middle shaft connecting block (17) and the driven shaft connecting block (19); one end of each blade (21) is fixedly arranged on the blade distribution wheel (20), the other end of each blade is arranged on the blade support (22), and each sectional type self-combination fan blade (24) consists of the blades (21).
2. An orbital ring rotary flapping wing power unit according to claim 1, wherein said sliding sleeve support (10), vane support (22), segmented self assembling vanes (24) are cruciform.
3. An orbital ring rotary flapping wing power unit according to claim 1, wherein each of said sliding blocks (11) is fixedly equipped with 16 small pulleys (14).
4. An orbital ring rotary flapping wing power unit according to claim 1 wherein said core orbital ring (8) is upwardly convex with respect to orbital ring connecting body (6).
5. The orbital ring rotary flapping wing power unit of claim 1, wherein said core orbital ring (8) is an irregular annular orbital ring comprised of upper and lower circular arc segments and a straight segment portion connecting the two circular arc segments at both sides, and wherein the circular arc radius of the upper segment is greater than the circular arc radius of the lower segment.
6. The orbital ring rotary flapping wing power plant according to claim 1, wherein when the engine (2) drives the main shaft (4) to rotate, the sliding sleeve support (10) rotates, the sliding block (11) in the sliding sleeve (9) on the sliding sleeve support (10) moves along the core orbital ring (8) through the sliding block shaft bearing (13) to drive the sliding block (11) to move in the sliding sleeve (9), the sliding block shaft (12) drives the driving rocker (15) to move at the same time of moving the sliding block (11) in the sliding sleeve (9), so that the middle shaft connecting block (17) rotates, and the middle shaft connecting block (17) rotates to drive the driven rocker (18) to rotate, so that the middle shaft connecting block (19) rotates; the rotation of the blade distribution wheel (20) is driven by the rotation of the middle shaft connecting block (17) and the rotation of the middle shaft connecting block (19), so that the rotary flapping wings of the blades (21) and the sectional self-combination fan blades (24) are realized.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110399016.4A CN112960113A (en) | 2021-04-14 | 2021-04-14 | Orbital ring rotary flapping wing power device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110399016.4A CN112960113A (en) | 2021-04-14 | 2021-04-14 | Orbital ring rotary flapping wing power device |
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| Publication Number | Publication Date |
|---|---|
| CN112960113A true CN112960113A (en) | 2021-06-15 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202110399016.4A Pending CN112960113A (en) | 2021-04-14 | 2021-04-14 | Orbital ring rotary flapping wing power device |
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| CN (1) | CN112960113A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114987758A (en) * | 2022-06-16 | 2022-09-02 | 杭州宝桐科技有限公司 | Cycloidal propeller duct power device and aircraft using same |
-
2021
- 2021-04-14 CN CN202110399016.4A patent/CN112960113A/en active Pending
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114987758A (en) * | 2022-06-16 | 2022-09-02 | 杭州宝桐科技有限公司 | Cycloidal propeller duct power device and aircraft using same |
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Application publication date: 20210615 |
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| RJ01 | Rejection of invention patent application after publication |