CN116552774A - Cycloidal propeller and aircraft with cycloidal propeller - Google Patents
Cycloidal propeller and aircraft with cycloidal propeller Download PDFInfo
- Publication number
- CN116552774A CN116552774A CN202310841269.1A CN202310841269A CN116552774A CN 116552774 A CN116552774 A CN 116552774A CN 202310841269 A CN202310841269 A CN 202310841269A CN 116552774 A CN116552774 A CN 116552774A
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- China
- Prior art keywords
- medium
- deformation
- storage bag
- blades
- fixedly connected
- 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.)
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Links
- 238000004140 cleaning Methods 0.000 claims abstract description 41
- 238000004804 winding Methods 0.000 claims description 4
- 230000005540 biological transmission Effects 0.000 claims description 3
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 claims description 3
- 239000000463 material Substances 0.000 description 6
- 238000000034 method Methods 0.000 description 5
- 239000007789 gas Substances 0.000 description 4
- 230000005611 electricity Effects 0.000 description 3
- 239000007788 liquid Substances 0.000 description 3
- 230000033001 locomotion Effects 0.000 description 3
- IJGRMHOSHXDMSA-UHFFFAOYSA-N Atomic nitrogen Chemical compound N#N IJGRMHOSHXDMSA-UHFFFAOYSA-N 0.000 description 2
- XEEYBQQBJWHFJM-UHFFFAOYSA-N Iron Chemical compound [Fe] XEEYBQQBJWHFJM-UHFFFAOYSA-N 0.000 description 2
- 230000000737 periodic effect Effects 0.000 description 2
- RYGMFSIKBFXOCR-UHFFFAOYSA-N Copper Chemical compound [Cu] RYGMFSIKBFXOCR-UHFFFAOYSA-N 0.000 description 1
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 1
- 229910052782 aluminium Inorganic materials 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 229910052802 copper Inorganic materials 0.000 description 1
- 239000010949 copper Substances 0.000 description 1
- 229920001971 elastomer Polymers 0.000 description 1
- 230000003993 interaction Effects 0.000 description 1
- 229910052742 iron Inorganic materials 0.000 description 1
- 239000004816 latex Substances 0.000 description 1
- 229920000126 latex Polymers 0.000 description 1
- 229910052757 nitrogen Inorganic materials 0.000 description 1
- 230000000149 penetrating effect Effects 0.000 description 1
- 238000007789 sealing Methods 0.000 description 1
- 229910001220 stainless steel Inorganic materials 0.000 description 1
- 239000010935 stainless steel Substances 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D47/00—Equipment not otherwise provided for
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Cleaning In General (AREA)
Abstract
The invention relates to the technical field of cycloidal propellers, in particular to a cycloidal propeller and an aircraft with the cycloidal propeller. The blade is a plurality of, and the axis is all vertical setting, evenly is fixed in the bottom surface of carousel around the axis of carousel. The deformation part is sleeved on the blades, the top end of the deformation part is fixedly connected with the bottom surface of the turntable, and the deformation of a preset degree can be generated to completely cover the blades. The cleaning part is fixed at the bottom end of the deformation part. The cleaning part is provided with a abdication hole for the blade to pass through. During the deformation of the deformation portion, the cleaning portion is forced to move downward along the axis of the blade. The cleaning part moving downwards can force sundries wound on the blades to fall off from the blades. Therefore, the difficulty of regular cleaning is greatly reduced, and the cycloidal propeller is convenient to clean.
Description
Technical Field
The invention relates to the technical field of cycloidal propellers, in particular to a cycloidal propeller and an aircraft with the cycloidal propeller.
Background
The cycloidal propeller is composed of a set of shaped straight blades which do circular motion around a central axis perpendicular to the aircraft body, and the blades generate propelling force when doing circular motion around the central axis.
When the cycloidal propeller works, sundries are easy to wind on the blades of the cycloidal propeller, so that part of power of the cycloidal propeller can be lost. Therefore, periodic cleaning of the blades of the gerotor is required.
At present, when blades of the cycloidal propeller are cleaned regularly, the cycloidal propeller is difficult to clean.
Disclosure of Invention
The invention provides a cycloidal propeller and an aircraft with the cycloidal propeller, and aims to solve the problem that blades of the cycloidal propeller are difficult to clean regularly.
In order to achieve the object of the present invention, there is provided a cycloidal propeller comprising:
a turntable;
the plurality of blades are vertically arranged on the axis and uniformly fixed on the bottom surface of the turntable around the axis of the turntable;
the deformation part is sleeved on the blades, the top end of the deformation part is fixedly connected with the bottom surface of the turntable, and the deformation part can deform to a preset degree so as to completely cover the blades;
the cleaning part is fixed at the bottom end of the deformation part; the cleaning part is provided with a yielding hole for the blade to pass through.
In some embodiments, the deformation portion includes:
the first medium storage bag is sleeved on the blades, the top end of the first medium storage bag is fixedly connected with the bottom surface of the rotary table, and the bottom end of the first medium storage bag is fixedly connected with the cleaning part.
In some embodiments, the deformation portion further comprises:
the second medium storage bag is penetrated in the first medium storage bag, the top end is a medium inflow port, and the bottom end is a medium outflow port; the bottom end of the second medium storage bag is fixedly connected with the inner bottom surface of the first medium storage bag through a supporting rod; the medium outflow port communicates with the interior of the first medium reservoir bag.
In some embodiments, the method further comprises:
the rotary shaft, the vertical setting of axis, the top is the medium and draws the entry, bottom and carousel fixed connection, can rotate along with the carousel, inside be the water conservancy diversion chamber that is linked together with the medium inflow mouth.
In some embodiments, the method further comprises:
the first chain wheel is sleeved on the rotating shaft;
the first generator is suitable for being arranged on the aircraft body, and the input shaft is sleeved with a second sprocket; the second sprocket is connected with the first sprocket through a transmission chain.
In some embodiments, the cleaning portion is a squeegee.
In some embodiments, the method further comprises:
a second generator adapted to be mounted on the aircraft body;
one end of the ratchet wheel is fixedly connected with the input end of the second generator;
the coil spring is arranged on the inner side of the ratchet wheel;
the winding drum shaft is fixedly connected with the outer side of the ratchet wheel;
one end of the driving rope is wound on the winding drum shaft, and the other end of the driving rope is fixedly connected with the cleaning part.
An aircraft with cycloidal propellers based on the same concept comprises an aircraft body and cycloidal propellers provided by any of the specific embodiments described above;
the rotating shaft of the cycloidal propeller is rotationally connected with the bottom of the aircraft body.
In some embodiments, the method further comprises:
the mounting seat is fixed on the inner bottom surface of the aircraft body, and the inner top surface is rotationally connected with the top end of the rotating shaft through a rotary joint.
In some embodiments, the method further comprises:
and the medium drives the pump to be communicated with the rotary joint.
The invention has the beneficial effects that: according to the cycloidal propeller disclosed by the invention, the deformation parts are arranged and sleeved on the blades, the top ends of the deformation parts are fixedly connected with the bottom surface of the turntable, and the deformation of a preset degree can be generated so as to completely cover the blades. The cleaning part is fixed at the bottom end of the deformation part. The cleaning part is provided with a abdication hole for the blade to pass through. During the deformation of the deformation portion, the cleaning portion is forced to move downward along the axis of the blade. The cleaning part moving downwards can force sundries wound on the blades to fall off from the blades. Therefore, the difficulty of regular cleaning is greatly reduced, and the cycloidal propeller is convenient to clean.
Drawings
FIG. 1 is a schematic illustration of the construction of some embodiments of a gerotor of the present invention;
FIG. 2 is a schematic view of the gerotor of FIG. 1 during cleaning;
FIG. 3 is a cross-sectional view of the gerotor of FIG. 2 taken along line A-A;
fig. 4 is a schematic structural view of some embodiments of an aircraft with cycloidal propellers according to the invention.
110, a turntable in the drawing; 120. a blade; 130. a deformation section; 131. a first media storage bladder; 132. a second media storage bladder; 140. a cleaning section; 150. a support rod; 160. a rotation shaft; 171. a first sprocket; 172. a first generator; 173. a second sprocket; 174. a drive chain; 181. a ratchet wheel; 182. a coil spring; 183. a spool shaft; 184. a driving rope; 200. an aircraft body; 300. a mounting base; 400. and (5) rotating the joint.
Detailed Description
The following description of the embodiments of the present invention will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present invention, but not all embodiments.
Examples of the embodiments are illustrated in the accompanying drawings, wherein like or similar symbols indicate like or similar elements or elements having like or similar functions throughout. The embodiments described below by referring to the drawings are illustrative and intended to explain the present invention and should not be construed as limiting the invention.
In the description of the present invention, it should be understood that the terms "top," "bottom," "inner," "outer," "axis," "circumferential," and the like indicate an orientation or a positional relationship based on that shown in the drawings, and are merely for convenience in describing the present invention or simplifying the description, and do not indicate or imply that the devices or elements referred to must have a specific orientation, be constructed and operated in a specific orientation, and thus should not be construed as limiting the present invention.
Furthermore, the terms "first," "second," and the like, are used for descriptive purposes only and are not to be construed as indicating or implying a relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defining "a first" or "a second" may explicitly or implicitly include one or more such feature. In the description of the present invention, the meaning of "a plurality" is two or more, unless explicitly defined otherwise.
In the present invention, unless explicitly specified and limited otherwise, the terms "mounted," "connected," "secured," "engaged," "hinged," and the like are to be construed broadly, and may be, for example, fixedly connected, detachably connected, or integrally formed; can be mechanically or electrically connected; can be directly connected or indirectly connected through an intermediate medium, and can be communicated with the inside of two elements or the interaction relationship of the two elements. The specific meaning of the above terms in the present invention can be understood by those of ordinary skill in the art according to the specific circumstances.
As in the background art, as the cycloidal propeller works, sundries are very easy to wind on the blades of the cycloidal propeller, so that the cycloidal propeller can lose part of power. Therefore, periodic cleaning of the blades of the gerotor is required. At present, when blades of the cycloidal propeller are cleaned regularly, the cycloidal propeller is difficult to clean.
In order to improve the above problems, referring to fig. 1, 2 and 3, there is provided a cycloidal propeller including a turntable 110, a blade 120, a deformation part 130 and a cleaning part 140. The plurality of blades 120 are vertically arranged on the axis, and are uniformly fixed on the bottom surface of the turntable 110 around the axis of the turntable 110. The deformation part 130 is sleeved on the plurality of blades 120, and the top end of the deformation part is fixedly connected with the bottom surface of the turntable 110, so that the deformation part can deform to a preset degree to completely cover the blades 120. The cleaning part 140 is fixed to the bottom end of the deformation part 130. The cleaning portion 140 is provided with a relief hole through which the blade 120 passes. During the deformation of the deformation portion 130, the cleaning portion 140 is forced to move downward along the axis of the blade 120. The cleaning part 140 moved downward can force the foreign materials wound around the blade 120 to be separated from the blade 120. Therefore, the difficulty of regular cleaning is greatly reduced, and the cycloidal propeller is convenient to clean.
Specifically, in the illustrated example, the deformation portion 130 includes a first medium reservoir 131 and a second medium reservoir 132. The first medium storage bag 131 is sleeved on the plurality of blades 120, the top end is fixedly connected with the bottom surface of the turntable 110, and the bottom end is fixedly connected with the cleaning part 140. A relief hole through which the blade 120 passes is opened in the middle of the first medium storage bladder 131. The second medium storage bag 132 is disposed in the first medium storage bag 131 in a penetrating manner, and has a medium inlet at a top end and a medium outlet at a bottom end. The bottom end of the second medium storage bag 132 is fixedly connected to the inner bottom surface of the first medium storage bag 131 through a support bar 150. The medium outflow port communicates with the inside of the first medium reservoir bag 131.
It should be understood that the materials used for the first medium storing bag 131 and the second medium storing bag 132 are flexible materials such as rubber or latex, and similar to the bellows structure, the medium on which the expansion depends may be liquid or gas. The liquid may be water or oil and the gas may be nitrogen. The liquid originates from the tank. The gas originates from a gas storage tank.
Specifically, in the illustrated example, the gerotor further includes a rotation shaft 160. The axis of the rotating shaft 160 is vertically arranged, the top end is a medium inlet, the bottom end is fixedly connected with the turntable 110, the rotating shaft can rotate along with the turntable 110, and a diversion cavity communicated with the medium inlet is formed inside the rotating shaft. The medium can flow into the first medium reservoir bag 131 after flowing through the medium inlet, the flow guide chamber, the medium inflow port, the inside of the second medium reservoir bag 132, and the medium outflow port in this order. The first medium reservoir bag 131 is inflated by inflation of the second medium reservoir bag 132 and the medium flowing into the first medium reservoir bag 131. During the inflation of the first and second medium storing bags 131 and 132, the cleaning part 140 is forced to move downward along the axis of the blade 120, and the cleaning part 140 moved downward can force the foreign matters wound around the blade 120 to be removed from the blade 120. The cleaning part 140 is a rigid scraper, and may be made of iron, copper, aluminum or stainless steel. The foreign materials wound around the blade 120 can be scraped off. The media in the first and second media storage bags 131 and 132 are drawn out, and the first and second media storage bags 131 and 132 drive the cleaning part 140 to move upward along the axis of the blade 120 to reset the cleaning part 140. In this way, multiple cleaning of the blade 120 can be achieved in a short period of time.
Specifically, in the illustrated example, the gerotor further includes a first sprocket 171, a second sprocket 173, a drive chain 174, and a first generator 172. The first sprocket 171 is sleeved on the rotating shaft 160. The first generator 172 is adapted to be mounted on the aircraft body 200 with the second sprocket 173 sleeved on the input shaft. The second sprocket 173 is in driving connection with the first sprocket 171 through a driving chain 174. When the vane 120 rotates, the rotation shaft 160 rotates along with the turntable 110, so as to drive the first sprocket 171 and the second sprocket 173 to rotate, and further enable the first generator 172 to generate electricity, and the generated electricity can be stored. At this time, the first medium storage bladder 131 and the second medium storage bladder 132 are in a contracted state.
Specifically, in the illustrated example, the gerotor further includes a second generator (not shown), a ratchet 181, a coil spring 182, a spool shaft 183, and a drive string 184. The second generator is adapted to be mounted on the aircraft body 200. One end of the ratchet wheel 181 is fixedly connected with the input end of the second generator. A coil spring 182 is provided inside the ratchet 181. The spool shaft 183 is fixedly connected to the outer side of the ratchet 181. One end of the driving rope 184 is wound around the spool shaft 183, and the other end is fixedly connected to the cleaning section 140. When the blade 120 is in the standby state, the traction driving rope 184 is released from the spool shaft 183 during the downward movement of the cleaning section 140 along the axis of the blade 120, driving the spool shaft 183 to rotate clockwise. The spool shaft 183 rotates the ratchet wheel 181 and the input shaft of the generator to cause the second generator to generate electricity. After the cleaning part 140 is in place, the media in the first media storage bag 131 and the second media storage bag 132 are drawn out, the cleaning part 140 moves upwards along the axis of the blade 120, the redundant length of the driving rope 184 appears, the force of the coil spring 182 restoring deformation drives the ratchet wheel 181 to rotate anticlockwise, and then drives the drum shaft 183 to rotate anticlockwise, so that the redundant driving rope 184 is wound on the drum shaft 183.
Referring to fig. 3 and 4, the present invention also provides an aircraft having a gerotor, including an aircraft body 200, a gerotor provided by any of the embodiments described above, a mount 300, and a media-driven pump. The rotation shaft 160 of the cycloidal propeller is rotatably connected to the bottom of the aircraft body 200. Specifically, a bearing housing is fixed to the bottom of the aircraft body 200, a bearing is installed in the bearing housing, and the rotation shaft 160 is rotatably connected to the bottom of the aircraft body 200 through the bearing. The mounting base 300 is fixed to an inner bottom surface of the aircraft body 200, and the inner top surface is rotatably connected to a top end of the rotation shaft 160 through a rotary joint 400. The rotary joint 400 includes a fixing portion and a rotating portion, and a top end of the fixing portion is fixedly connected with an inner bottom surface of the mounting seat 300. The top end of the rotating part is rotatably connected with the bottom end of the fixing part, and the top end is fixedly connected with the top end of the rotating shaft 160. The medium driven pump is fixed on the aircraft and communicated with the rotary joint 400, and can provide power for the medium flowing into the deformation part 130 and provide power to pump the medium in the deformation part 130 away. In addition, the bottom pad at the bearing frame is equipped with the sealing washer to improve the leakproofness of junction. Additionally, the aircraft body 200 may be a hull.
In the description of the present specification, reference to the terms "one embodiment," "some embodiments," "examples," "particular examples," "one particular embodiment," or "some examples," etc., means that a particular feature, structure, material, or characteristic described in connection with the embodiment or example is included in at least one embodiment or example of the invention. In this specification, schematic representations of the terms do not necessarily refer to the same embodiment or example. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples.
The foregoing description is only a preferred embodiment of the present invention, but the scope of the present invention is not limited thereto, and any person skilled in the art, within the scope of the present invention, should be covered by the protection scope of the present invention by equally replacing or changing the technical scheme and the inventive concept thereof.
Claims (10)
1. A cycloidal propeller comprising:
a turntable;
the plurality of blades are vertically arranged on the axis, and uniformly fixed on the bottom surface of the turntable around the axis of the turntable;
the deformation part is sleeved on the blades, the top ends of the deformation parts are fixedly connected with the bottom surface of the turntable, and the deformation parts can deform to a preset degree so as to completely cover the blades;
the cleaning part is fixed at the bottom end of the deformation part; and the cleaning part is provided with a yielding hole for the blade to pass through.
2. The gerotor of claim 1, wherein the deformation comprises:
and the first medium storage bag is sleeved on the blades, the top end of the first medium storage bag is fixedly connected with the bottom surface of the turntable, and the bottom end of the first medium storage bag is fixedly connected with the cleaning part.
3. The gerotor of claim 2, wherein the deformation further comprises:
the second medium storage bag is penetrated in the first medium storage bag, the top end of the second medium storage bag is provided with a medium inflow port, and the bottom end of the second medium storage bag is provided with a medium outflow port; the bottom end of the second medium storage bag is fixedly connected with the inner bottom surface of the first medium storage bag through a supporting rod; the medium outflow port communicates with the interior of the first medium reservoir bag.
4. The gerotor of claim 3, further comprising:
the rotary shaft, the vertical setting of axis, the top be the medium draw-in mouth, the bottom with carousel fixed connection can be followed the carousel rotates, inside be with the water conservancy diversion chamber that the medium inflow mouth is linked together.
5. The gerotor of claim 4, further comprising:
the first chain wheel is sleeved on the rotating shaft;
the first generator is suitable for being arranged on the aircraft body, and the input shaft is sleeved with a second sprocket; the second sprocket is in transmission connection with the first sprocket through a transmission chain.
6. The gerotor of any one of claims 1-5, wherein the cleaning portion is a scraper.
7. The gerotor of any one of claims 1-5, further comprising:
a second generator adapted to be mounted on the aircraft body;
one end of the ratchet wheel is fixedly connected with the input end of the second generator;
the coil spring is arranged on the inner side of the ratchet wheel;
the winding drum shaft is fixedly connected with the outer side of the ratchet wheel;
one end of the driving rope is wound on the winding drum shaft, and the other end of the driving rope is fixedly connected with the cleaning part.
8. An aircraft having a cycloidal propeller, comprising an aircraft body and the cycloidal propeller of any one of claims 1 to 7;
the rotating shaft of the cycloidal propeller is rotationally connected with the bottom of the aircraft body.
9. The aircraft with cycloidal propeller of claim 8 further comprising:
the mounting seat is fixed on the inner bottom surface of the aircraft body, and the inner top surface is rotationally connected with the top end of the rotating shaft through a rotary joint.
10. The aircraft with cycloidal propeller of claim 9 further comprising:
and the medium drives the pump to be communicated with the rotary joint.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310841269.1A CN116552774B (en) | 2023-07-11 | 2023-07-11 | Cycloidal propeller and aircraft with cycloidal propeller |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310841269.1A CN116552774B (en) | 2023-07-11 | 2023-07-11 | Cycloidal propeller and aircraft with cycloidal propeller |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN116552774A true CN116552774A (en) | 2023-08-08 |
| CN116552774B CN116552774B (en) | 2023-09-22 |
Family
ID=87491895
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202310841269.1A Active CN116552774B (en) | 2023-07-11 | 2023-07-11 | Cycloidal propeller and aircraft with cycloidal propeller |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN116552774B (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116873194A (en) * | 2023-09-07 | 2023-10-13 | 北京威浮科技有限责任公司 | Cycloidal propeller and aircraft with cycloidal propeller |
| CN116906248A (en) * | 2023-09-13 | 2023-10-20 | 烟台威浮海洋科技有限公司 | Device for generating electricity by means of water flow |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB580231A (en) * | 1944-06-23 | 1946-08-30 | Bell Aircraft Corp | Improvements in aircraft |
| US3326296A (en) * | 1965-08-31 | 1967-06-20 | Hovercraft Dev Ltd | Cycloidal propeller |
| US5985127A (en) * | 1997-01-16 | 1999-11-16 | Gkn Westland Helicopters Limited | Method of and apparatus for removing a metallic erosion shield from attachment to a helicopter rotor blade |
| KR20050034486A (en) * | 2003-10-09 | 2005-04-14 | 재단법인서울대학교산학협력재단 | A vertical takeoff and landing aircraft |
| CN202481313U (en) * | 2012-01-30 | 2012-10-10 | 西北工业大学 | Flying wing aircraft with cycloidal rotor thrusters installed |
| DE202019106302U1 (en) * | 2019-11-12 | 2021-02-15 | Christian Stephan Berner | Cleaning device for rotor blades |
| EP4144637A1 (en) * | 2021-09-06 | 2023-03-08 | Paolo Becchi | Aircraft provided with supporting wings for the cruise flight |
-
2023
- 2023-07-11 CN CN202310841269.1A patent/CN116552774B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB580231A (en) * | 1944-06-23 | 1946-08-30 | Bell Aircraft Corp | Improvements in aircraft |
| US3326296A (en) * | 1965-08-31 | 1967-06-20 | Hovercraft Dev Ltd | Cycloidal propeller |
| US5985127A (en) * | 1997-01-16 | 1999-11-16 | Gkn Westland Helicopters Limited | Method of and apparatus for removing a metallic erosion shield from attachment to a helicopter rotor blade |
| KR20050034486A (en) * | 2003-10-09 | 2005-04-14 | 재단법인서울대학교산학협력재단 | A vertical takeoff and landing aircraft |
| CN202481313U (en) * | 2012-01-30 | 2012-10-10 | 西北工业大学 | Flying wing aircraft with cycloidal rotor thrusters installed |
| DE202019106302U1 (en) * | 2019-11-12 | 2021-02-15 | Christian Stephan Berner | Cleaning device for rotor blades |
| EP4144637A1 (en) * | 2021-09-06 | 2023-03-08 | Paolo Becchi | Aircraft provided with supporting wings for the cruise flight |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116873194A (en) * | 2023-09-07 | 2023-10-13 | 北京威浮科技有限责任公司 | Cycloidal propeller and aircraft with cycloidal propeller |
| CN116873194B (en) * | 2023-09-07 | 2024-01-26 | 北京威浮科技有限责任公司 | Cycloidal propeller and aircraft with cycloidal propeller |
| CN116906248A (en) * | 2023-09-13 | 2023-10-20 | 烟台威浮海洋科技有限公司 | Device for generating electricity by means of water flow |
Also Published As
| Publication number | Publication date |
|---|---|
| CN116552774B (en) | 2023-09-22 |
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