CN114348254A - Aircraft with double row wheel pair rotation aerodynamic effect - Google Patents
Aircraft with double row wheel pair rotation aerodynamic effect Download PDFInfo
- Publication number
- CN114348254A CN114348254A CN202111661834.3A CN202111661834A CN114348254A CN 114348254 A CN114348254 A CN 114348254A CN 202111661834 A CN202111661834 A CN 202111661834A CN 114348254 A CN114348254 A CN 114348254A
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- rotating
- wing plate
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- assemblies
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- 230000000694 effects Effects 0.000 title claims abstract description 19
- 230000000712 assembly Effects 0.000 claims abstract description 25
- 238000000429 assembly Methods 0.000 claims abstract description 25
- 230000009977 dual effect Effects 0.000 claims description 6
- 239000000463 material Substances 0.000 claims description 2
- 238000009987 spinning Methods 0.000 claims 2
- 238000013461 design Methods 0.000 abstract description 8
- 238000004519 manufacturing process Methods 0.000 abstract description 4
- 238000005265 energy consumption Methods 0.000 abstract description 2
- 238000001514 detection method Methods 0.000 description 6
- 230000009286 beneficial effect Effects 0.000 description 3
- 241000282414 Homo sapiens Species 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 229920000049 Carbon (fiber) Polymers 0.000 description 1
- 208000035473 Communicable disease Diseases 0.000 description 1
- 241001465754 Metazoa Species 0.000 description 1
- 230000001154 acute effect Effects 0.000 description 1
- 239000004917 carbon fiber Substances 0.000 description 1
- 238000013016 damping Methods 0.000 description 1
- 208000015181 infectious disease Diseases 0.000 description 1
- 238000007689 inspection Methods 0.000 description 1
- 239000003562 lightweight material Substances 0.000 description 1
- 238000013507 mapping Methods 0.000 description 1
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000012544 monitoring process Methods 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 230000000630 rising effect Effects 0.000 description 1
- 230000004083 survival effect Effects 0.000 description 1
Images
Classifications
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- 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
- B64C11/16—Blades
- B64C11/18—Aerodynamic features
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/02—Undercarriages
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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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plant in aircraft; Aircraft characterised thereby
- B64D27/02—Aircraft characterised by the type or position of power plant
- B64D27/24—Aircraft characterised by the type or position of power plant using steam, electricity, or spring force
Abstract
The invention provides an aircraft with a double-row wheel pair rotation aerodynamic effect, which comprises wing plates, a rotating assembly and an undercarriage; the wing plate is connected to the position right above the rotating assembly; the upper projection area of the wing plate is larger than the area of the rotating assembly; the middle position of the outer side surface of the wing plate is provided with a first convex end surface; the number of the rotating assemblies is two, the two rotating assemblies are respectively connected to the left side and the right side of the inner side face of the wing plate, the two rotating assemblies rotate towards the same direction of the inner side face a, and a gap is formed between the two rotating assemblies; the rotating assembly comprises a driver, a propeller and a rotating wheel; the propeller and the rotating wheel are both connected with the power output end of the driver; the undercarriage is connected with the bottoms of the two rotating wheels of the two rotating assemblies. The invention drives the airflow to rotate through the rotating blades, the upward airflow impacts the inner side of the wing plate to provide the lift force, and the invention has the advantages of reasonable structural design, novel design, low energy consumption, low manufacturing cost and popularization application prospect.
Description
Technical Field
The invention belongs to the technical field of aircrafts, and particularly relates to an aircraft with double row wheel pairs and a rotary aerodynamic effect.
Background
An aircraft is an instrumental flying object which is manufactured by human beings, can fly off the ground, flies in space and is controlled by human beings, and flies in the atmosphere or out of the atmosphere space. The unmanned aerial vehicle is used as one of aircrafts, has wide application, low cost, high efficiency, no casualty risk, strong survival capability, good maneuverability and convenient use, plays an extremely important role in modern war and has wider prospect in the civil field.
In military terms, unmanned aerial vehicles are divided into reconnaissance aircraft and target aircraft. In the civil aspect, the unmanned aerial vehicle is applied to the industry and is really just needed by the unmanned aerial vehicle; the unmanned aerial vehicle is applied to the fields of aerial photography, agriculture, plant protection, miniature self-timer, express transportation, disaster relief, wild animal observation, infectious disease monitoring, surveying and mapping, news reporting, power inspection, disaster relief, movie and television shooting, romantic manufacturing and the like, and the application of the unmanned aerial vehicle is greatly expanded.
However, the existing unmanned aerial vehicle has unreasonable internal structure design, generates large noise when being started, has certain influence on the surrounding environment, and is not beneficial to detection; when the unmanned aerial vehicle is started, large energy needs to be consumed, and the use cost is high; especially when unmanned aerial vehicle is applied to disposable field, consumed a large amount of unmanned aerial vehicle use cost.
Disclosure of Invention
In view of the above, the invention aims to provide an aircraft with a double-row wheel pair aerodynamic effect, so as to solve the problems that in the prior art, the internal structural design of an unmanned aerial vehicle is unreasonable, the noise generated during starting is high, the surrounding environment is affected, detection and detection are not facilitated, and high energy consumption is needed, so that the use cost is high; especially be applied to disposable field, consumed a large amount of unmanned aerial vehicle use cost's technical problem.
In order to achieve the purpose, the technical scheme of the invention is realized as follows:
an aircraft with double rows of wheel pairs and a rotary aerodynamic effect comprises wing plates, a rotating assembly and an undercarriage;
the wing plate is connected to the position right above the rotating assembly; the upper projection area of the wing plate is larger than the area of the rotating assembly; the middle position of the outer side surface of the wing plate is provided with a first convex end surface which is convex upwards;
the number of the rotating assemblies is two, the two rotating assemblies are respectively connected to the left side and the right side of the inner side face of the wing plate, the two rotating assemblies rotate towards the same direction of the inner side face a, and a gap is formed between the two rotating assemblies;
the rotating assembly comprises a driver, a propeller and a rotating wheel; the propeller and the rotating wheel are both connected with the power output end of the driver;
the undercarriage is connected with the bottoms of the two rotating wheels of the two rotating assemblies.
Furthermore, both ends of the outer side surface of the wing plate are provided with cambered surface structures which are bent downwards, and the thickness of each cambered surface structure is gradually thinned from the upper end to the lower end.
Furthermore, a second convex end face which is convex downwards is arranged in the middle of the inner side face of the wing plate.
Further, a plurality of blades are provided on the outer surface of the rotating wheel along the length direction of the rotating wheel.
Furthermore, the blades are provided with aerodynamic curves, and the front ends and the rear ends of the blades are provided with torsion angles, so that backward airflow power can be provided.
Furthermore, the inner side surface of the rotating wheel is connected with the side surface of the second protrusion end surface through a first connecting rod;
the upper side surface of the rotating wheel is connected with the inner side of the cambered surface structure through a second connecting rod.
Furthermore, the wing plate and the rotating assembly are made of light materials.
Compared with the prior art, the aircraft with double rows of wheels to achieve the aerodynamic effect has the following advantages:
according to the invention, the first convex end face protruding upwards is formed in the middle of the outer side face of the wing plate, so that the rising resistance is reduced; the left side and the right side of the inner side surface of the wing plate are respectively connected with a rotating assembly, the two rotating assemblies rotate inwards, and upward high-pressure airflow is formed in a gap between the two rotating assemblies, so that the inner side surface of the wing plate is pushed, the wing plate moves upwards and flies, and meanwhile, the internal moment is balanced by the oppositely-rotating assemblies; the rotating assembly adopts a structure combining a driver, propellers, rotating wheels and blades, the propellers and the rotating wheels are driven to rotate by starting the driver, upward high-pressure airflow is generated in a gap between the two rotating wheels by utilizing the rotation of the two propellers and the two rotating wheels, and the airflow pushes wing plates to move upwards; the outer sides of the two rotating assemblies drive airflow downwards to generate upward aerodynamic force on the aircraft; meanwhile, a high-pressure area is formed in an airflow hedging area below the aircraft, and upward lift force is provided for the aircraft. The internal structure of the invention is reasonable in design; utilize two to rotate the wheel and upwards rotate and provide lift, the rotational speed is faster, and lift is bigger, through adjusting the different speeds of controlling the runner assembly, adjusts the aerodynamic force of second bellying left and right sides direction, provides the lateral force of left and right sides direction.
The rotating blade has a pneumatic streamline design, so that aerodynamic force can be increased, and the front end and the rear end of the rotating blade are provided with rotating angles, so that backward aerodynamic force can be provided while the rotating blade rotates; alternatively, the drive simultaneously rotates the propeller to provide rearward aerodynamic force. In the process of the vertical descending of the aircraft, due to the magnus pneumatic effect of the windward side, the pressure difference of a high-pressure area below the aircraft is increased rapidly, the lift force of the aircraft is increased, and at the moment, when the rotating speed of the rotating assembly is relatively small, the stable control of the aircraft can be realized. The invention has no other starting equipment, and the noise generated during starting is greatly reduced, thereby being beneficial to detection; in addition, the wing plates are pushed only by the airflow generated by the upward rotation of the two rotating wheels, so that the consumed energy is low; the undercarriage is connected with the bottoms of the two rotating wheels, so that the whole aircraft is low in manufacturing cost and high in energy utilization rate, and no much cost is generated; the design of the aircraft can realize slow vertical multi-time take-off and landing, and the utilization efficiency is high.
Drawings
The accompanying drawings, which are incorporated in and constitute a part of this specification, illustrate an embodiment of the invention and, together with the description, serve to explain the invention and not to limit the invention. In the drawings:
FIG. 1 is a schematic illustration of a front side of an aircraft with a double row pair aerodynamic effect according to an embodiment of the present disclosure;
FIG. 2 is a schematic illustration of a rear side of a dual row pair cyclonic aerodynamic effect aircraft in an embodiment of the present invention;
FIG. 3 is a front view of a dual row pair-roller rotorcraft effect aircraft, according to an embodiment of the present disclosure;
FIG. 4 is a rear view of a dual row pair-roller rotorcraft aircraft in accordance with an embodiment of the present invention;
FIG. 5 is a front view of a dual row pair-roller rotorcraft aircraft, according to an embodiment of the present invention.
Description of reference numerals:
100-wing plate; 200-a rotating assembly; 300-a landing gear;
101-a first convex end face; 102-cambered surface structure; 103-a second convex end face;
201-a driver; 202-a propeller; 203-a rotating wheel;
204-blade; 205-a first link; 206-second link.
Detailed Description
It should be noted that the embodiments and features of the embodiments may be combined with each other without conflict.
In the description of the present invention, it is to be understood that the terms "center", "longitudinal", "lateral", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like, indicate orientations or positional relationships based on those shown in the drawings, and are used only for convenience in describing the present invention and for simplicity in description, and do not indicate or imply that the referenced devices or elements must have a particular orientation, be constructed and operated in a particular orientation, and thus, are not to be construed as limiting the present invention. Furthermore, the terms "first", "second", etc. are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first," "second," etc. may explicitly or implicitly include one or more of that feature. In the description of the present invention, "a plurality" means two or more unless otherwise specified.
In the description of the present invention, it should be noted that, unless otherwise explicitly specified or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, e.g., as meaning either a fixed connection, a removable connection, or an integral connection; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meaning of the above terms in the present invention can be understood by those of ordinary skill in the art through specific situations.
The present invention will be described in detail below with reference to the embodiments with reference to the attached drawings.
As shown in fig. 1 to 5, the aircraft with double row wheel pair aerodynamic effect provided by the present invention includes a wing plate 100, a rotating assembly 200 and a landing gear 300;
the wing plate 100 is connected to a position right above the rotating assembly 200; the upper projected area of the wing plate 100 is larger than the area of the rotating assembly 200; a first convex end surface 101 which is convex upwards is arranged at the middle position of the outer side surface of the wing plate 100;
the number of the rotating assemblies 200 is two, the two rotating assemblies 200 are respectively connected to the left side and the right side of the inner side of the wing plate 100, the two rotating assemblies 200 both rotate towards the same direction of the inner side a, and a gap is formed between the two rotating assemblies 200;
the rotating assembly 200 comprises a driver 201, a propeller 202 and a rotating wheel 203; the propeller 202 and the rotating wheel 203 are both connected with the power output end of the driver 201;
In an embodiment of the present application, referring to fig. 1 and 2, the wing plate 100 is positioned above the double row rotating assembly 200 and receives upward aerodynamic force. The inner side of the wing plate 100 forms an enveloping arrangement for the rotating assembly 200, with a small spacing, and can maximally withstand aerodynamic forces. The first raised end surface 101 has an upwardly pointed shape in the middle to guide the air flow on both sides of the outer side of the wing plate 100. The driver 201 employs a drive motor. The two rotating wheels 203 are respectively fixedly connected to the left and right sides of the inner side surface of the wing plate 100, and when the two driving motors are started, the two rotating wheels 203 both rotate towards the direction of the inner side surface a.
When the wing plate 100 is used, the two driving motors are started simultaneously, the two propellers 202 and the two rotating wheels 203 rotate towards the direction of the inner side face a simultaneously, upward high-pressure airflow is formed at the gap between the two rotating wheels 203, the high-pressure airflow impacts the inner side face of the wing plate 100, upward lifting force is provided for the wing plate 100 by utilizing the inner side face of the wing plate 100, and therefore the undercarriage 300 at the bottom is driven to fly upwards, and the flying mode is achieved.
The internal structure of the aircraft is reasonable in design, when the aircraft is started, the two rotating wheels 203 rotate to generate upward high-pressure airflow to drive the wing plates 100 to move upwards, so that the whole aircraft is driven to move, the generated noise is low, the surrounding environment cannot be influenced, and the aircraft is suitable for the fields of detection, detection and the like; and this application utilizes the air current to strike the start-up, need not to consume great energy, and low in manufacturing cost is particularly suitable for being applied to disposable field.
Further, both ends of the outer side surface of the wing plate 100 are provided with arc structures 102 bent downwards, and the thickness of the arc structures 102 becomes thinner gradually from the upper end to the lower end.
In this embodiment, referring to fig. 3 and 4, two ends of the outer side surface of the wing plate 100 are formed with arc structures 102 bent downward to reduce resistance on two sides of the wing plate 100, so that the airflow guided by the first convex end surface 101 moves downward along the two arc structures 102, and at the same time, an upward damping force is respectively formed on two ends of the inner side surface of the wing plate 100.
The thickness of camber structure 102 tapers from the upper end to the lower end, which not only facilitates guiding the air flow, but also reduces the weight of the overall wing panel 100.
Further, the wing plate 100 has a second convex end surface 103 protruding downward at a middle position of the inner side surface thereof, and forms an envelope for the lower counter rotating assembly 200, and aerodynamic force is increased by designing a gap distance. By adjusting the respective speeds of the left and right turn assemblies 200, the second lobe faces 103 are generally subjected to one-sided pneumatic forces that are either left or right sided.
In this embodiment, referring to fig. 3 and 4, a second protrusion end surface 103 is provided at a middle position of an inner side surface of the wing plate 100, and the second protrusion end surface 103 is sharp, so that the high-pressure air flow entering the middle position of the inner side surface of the wing plate 100 can move upward along two side arc surfaces of the second protrusion end surface 103 and then be dispersed outward. And provides lateral power when the left and right rotating speeds are different.
Further, a plurality of blades 204 are provided on the outer surface of the rotary wheel 203 along the longitudinal direction of the rotary wheel 203.
In this embodiment, referring to fig. 3 and 4, a plurality of blades 204 are disposed on an outer surface of the rotating wheel 203, the blades 204 are elongated plates, and the plurality of blades 204 drive the rotating wheel 203 to rotate, so that the air flow in the middle of the inner side of the wing plate 100 moves upward and the air flows at two ends of the inner side of the wing plate 100 move downward. The blade 204 has an aerodynamic curved surface. The front and rear end faces of the blades 204 have a rotation angle, and the rotation can provide a backward aerodynamic force.
Further, the blades 204 have aerodynamic curves with twist angles at the front and rear ends to provide backward airflow power when rotating.
In this embodiment, referring to fig. 3, an acute angle or a right angle is formed between the blade 204 and the outer surface of the rotating wheel 203, so that the rotating force is increased, which is beneficial to driving the rotating wheel 203 to rotate upwards.
Further, the inner side surface of the rotating wheel 203 is connected with the side surface of the second convex end surface 103 through a first connecting rod 205;
the upper side of the turning wheel 203 is connected to the inside of the arc-shaped structure 102 by a second link 206.
In this embodiment, referring to fig. 1, the inner side surface of the rotating wheel 203 is connected to the side surface of the second convex end surface 103 through two first links 205, the upper side surface of the rotating wheel 203 is connected to the inner side surface of the arc-shaped structure 102 through two second links 206, and the four links are used to fix the rotating wheel 203 from two positions of the inner side surface and the upper side surface, respectively, so as to ensure smooth rotation of the rotating wheel 203 in the outer side direction.
Further, the wing plate 100 and the rotating assembly 200 are made of lightweight materials.
Alternatively, the rear of the aircraft may be provided with vertical control surfaces.
In the present embodiment, the wing panel 100 and the rotating assembly 200 may adopt a carbon fiber skin structure or a lightweight film skeleton structure, which ensures the structural strength of the wing panel 100 and the rotating assembly 200 and also reduces the weight of the entire wing panel 100 and the rotating assembly 200.
The invention provides a novel aerodynamic configuration of an aircraft, wherein the rotating blades 204 drive airflow to rotate, the upward airflow impacts the inner sides of wing plates 100 to provide lift force, the wing plates 100 are connected with the rotating shafts, and the lift force and the reverse force of the airflow to the blades 204 are balanced in a counteracting manner; the reverse force brought by the downward airflow provides lift force for the aircraft; the counter-rotating assembly 200 drives the airflow to form a high pressure region below the aircraft while providing lift to the aircraft.
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 present invention, but is intended to cover all modifications, equivalents, and improvements falling within the spirit and scope of the present invention as defined by the appended claims: the modification of aerodynamic shape at the front end of the cover plate, the addition of horizontal rudders, vertical rudders and the like at the front end and the rear end of the aircraft are all included in the protection scope of the invention.
Claims (7)
1. The utility model provides an aircraft of double wheel pair whirling aerodynamic effect which characterized in that: comprises a wing plate (100), a rotating assembly (200) and a landing gear (300);
the wing plate (100) is connected to a position right above the rotating assembly (200); the upper projection area of the wing plate (100) is larger than the area of the rotating assembly (200); a first convex end face (101) which is convex upwards is arranged in the middle of the outer side face of the wing plate (100);
the number of the rotating assemblies (200) is two, the two rotating assemblies (200) are respectively connected to the left side and the right side of the inner side face of the wing plate (100), the two rotating assemblies (200) rotate towards the same direction of the inner side face a, and a gap is formed between the two rotating assemblies (200);
the rotating assembly (200) comprises a driver (201), a propeller (202) and a rotating wheel (203); the propeller (202) and the rotating wheel (203) are both connected with the power output end of the driver (201);
the landing gear (300) is connected with the bottoms of the two rotating wheels (203) of the two rotating assemblies (200).
2. The dual-row wheelset rotorcraft effect aircraft of claim 1, wherein: both ends of the outer side surface of the wing plate (100) are provided with cambered surface structures (102) which are bent downwards, and the thickness of each cambered surface structure (102) becomes thinner gradually from the upper end to the lower end.
3. The dual row pair-spinning aerodynamic effect aircraft of claim 2, wherein: and a second convex end surface (103) which is convex downwards is arranged in the middle of the inner side surface of the wing plate (100).
4. The dual-row wheelset rotorcraft effect aircraft of claim 3, wherein: the outer surface of the rotating wheel (203) is provided with a plurality of blades (204) along the length direction of the rotating wheel (203).
5. The dual row pair-wheel-spinning aerodynamic effect aircraft of claim 4, wherein: the blades (204) have aerodynamic curves, and the front ends and the rear ends have torsion angles, so that backward airflow power can be provided.
6. The dual-row wheelset rotorcraft effect aircraft of claim 5, wherein: the inner side surface of the rotating wheel (203) is connected with the side surface of the second convex end surface (103) through a first connecting rod (205);
the upper side surface of the rotating wheel (203) is connected with the inner side of the cambered surface structure (102) through a second connecting rod (206).
7. The dual-row wheelset aerodynamic effect aircraft of claim 6, wherein: the wing plate (100) and the rotating assembly (200) are both made of light materials.
Priority Applications (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111661834.3A CN114348254A (en) | 2021-12-30 | 2021-12-30 | Aircraft with double row wheel pair rotation aerodynamic effect |
| PCT/CN2022/080610 WO2023123682A1 (en) | 2021-12-30 | 2022-03-14 | Aircraft having double-row wheel counter-rotating pneumatic effect |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111661834.3A CN114348254A (en) | 2021-12-30 | 2021-12-30 | Aircraft with double row wheel pair rotation aerodynamic effect |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN114348254A true CN114348254A (en) | 2022-04-15 |
Family
ID=81106235
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202111661834.3A Pending CN114348254A (en) | 2021-12-30 | 2021-12-30 | Aircraft with double row wheel pair rotation aerodynamic effect |
Country Status (2)
| Country | Link |
|---|---|
| CN (1) | CN114348254A (en) |
| WO (1) | WO2023123682A1 (en) |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB273524A (en) * | 1926-08-30 | 1927-07-07 | Adelheid Hanschke | Improvements in flying machines |
| GB360275A (en) * | 1931-01-16 | 1931-11-05 | Wilhelm Muss | Improvements in or relating to heavier than air aircraft |
| EP1541465A1 (en) * | 2003-12-09 | 2005-06-15 | Christof Hegger | Ultralight aircraft capable of travelling in the air and on the ground |
| US20090008510A1 (en) * | 2006-03-03 | 2009-01-08 | David Posva | Aircraft having the ability for hovering flight, fast forward flight, gliding flight, short take-off, short landing, vertical take-off and vertical landing |
| CN201872950U (en) * | 2010-12-03 | 2011-06-22 | 李定忠 | Paraglider |
| US20120187241A1 (en) * | 2011-01-20 | 2012-07-26 | Matte Francois | Hang glider electric propulsion system and method |
| US20180334243A1 (en) * | 2017-05-19 | 2018-11-22 | Yao-Chang Lin | Propulsion device |
-
2021
- 2021-12-30 CN CN202111661834.3A patent/CN114348254A/en active Pending
-
2022
- 2022-03-14 WO PCT/CN2022/080610 patent/WO2023123682A1/en unknown
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB273524A (en) * | 1926-08-30 | 1927-07-07 | Adelheid Hanschke | Improvements in flying machines |
| GB360275A (en) * | 1931-01-16 | 1931-11-05 | Wilhelm Muss | Improvements in or relating to heavier than air aircraft |
| EP1541465A1 (en) * | 2003-12-09 | 2005-06-15 | Christof Hegger | Ultralight aircraft capable of travelling in the air and on the ground |
| US20090008510A1 (en) * | 2006-03-03 | 2009-01-08 | David Posva | Aircraft having the ability for hovering flight, fast forward flight, gliding flight, short take-off, short landing, vertical take-off and vertical landing |
| CN201872950U (en) * | 2010-12-03 | 2011-06-22 | 李定忠 | Paraglider |
| US20120187241A1 (en) * | 2011-01-20 | 2012-07-26 | Matte Francois | Hang glider electric propulsion system and method |
| US20180334243A1 (en) * | 2017-05-19 | 2018-11-22 | Yao-Chang Lin | Propulsion device |
Also Published As
| Publication number | Publication date |
|---|---|
| WO2023123682A1 (en) | 2023-07-06 |
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Application publication date: 20220415 |