CN113911317A - Wing and fixed wing aircraft - Google Patents
Wing and fixed wing aircraft Download PDFInfo
- Publication number
- CN113911317A CN113911317A CN202111313999.1A CN202111313999A CN113911317A CN 113911317 A CN113911317 A CN 113911317A CN 202111313999 A CN202111313999 A CN 202111313999A CN 113911317 A CN113911317 A CN 113911317A
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- wing
- shaped
- rotating shaft
- fixed
- plates
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- 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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- 230000000694 effects Effects 0.000 abstract description 10
- 238000000034 method Methods 0.000 description 8
- 238000009434 installation Methods 0.000 description 4
- 238000005452 bending Methods 0.000 description 3
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Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/58—Wings provided with fences or spoilers
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/10—Shape of wings
- B64C3/14—Aerofoil profile
- B64C3/141—Circulation Control Airfoils
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/18—Spars; Ribs; Stringers
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/18—Spars; Ribs; Stringers
- B64C3/187—Ribs
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/26—Construction, shape, or attachment of separate skins, e.g. panels
Abstract
The invention relates to a wing and a fixed wing aircraft, wherein the wing comprises a wing body extending left and right and a self-rotating rectifying device, and the self-rotating rectifying device comprises a rotating shaft and an S-shaped plate arranged on the rotating shaft; the wing body comprises a right supporting wing and a left supporting wing, a plurality of S-shaped plates are arranged on the right supporting wing, a plurality of S-shaped plates are arranged on the left supporting wing, and the S-shaped plates on the right supporting wing and the S-shaped plates on the left supporting wing are symmetrically arranged; the projection of the S-shaped plate on each right supporting wing in a plane perpendicular to the rotating shaft is uniformly distributed along the circumferential direction of the rotating shaft by taking the rotating shaft as the center; the S-shaped plate comprises two bent plates respectively positioned at two sides of the rotating shaft, and when the S-shaped plate is in a vertical state, the middle part of the bent plate positioned at the upper side protrudes backwards. The wing provided by the invention provides lift force for the wing through the Magnus effect generated by the rotating S-shaped plate, and the problem of insufficient lift force of the existing small-sized fixed wing aircraft is solved.
Description
Technical Field
The invention relates to a wing and a fixed wing aircraft, and belongs to the field of aircrafts.
Background
The small fixed wing aircraft has the main characteristics of high maximum flying speed, high load capacity, relatively simple design structure and large cruising radius. However, compared with the traditional fixed wing aircraft, the small fixed wing aircraft is smaller in size and lighter in weight, the minimum speed required by the small fixed wing aircraft for taking off is lower, the viscous effect is prominent under the low Reynolds number, so that the viscous force cannot be ignored, the lift-drag ratio is sharply reduced, and the small fixed wing aircraft faces the problem of insufficient lift force.
Disclosure of Invention
The invention aims to provide a wing which is used for solving the problem that the existing small-sized fixed wing aircraft is insufficient in lift force. The invention also provides a fixed-wing aircraft comprising the wing.
In order to achieve the purpose, the technical scheme of the wing provided by the invention is as follows:
the wing comprises a wing body extending left and right and a self-rotating rectifying device, wherein the self-rotating rectifying device comprises a rotating shaft and an S-shaped plate arranged on the rotating shaft; the wing body comprises a right supporting wing and a left supporting wing, at least two S-shaped plates are arranged on the right supporting wing, at least two S-shaped plates are arranged on the left supporting wing, and the S-shaped plates on the right supporting wing and the S-shaped plates on the left supporting wing are symmetrically arranged; the projection of each S-shaped plate on the right branch wing in a plane vertical to the rotating shaft is uniformly arranged along the circumferential direction of the rotating shaft by taking the rotating shaft as the center; the S-shaped plate comprises two bent plates respectively positioned at two sides of the rotating shaft, and when the S-shaped plate is in a vertical state, the middle part of the bent plate positioned at the upper side protrudes backwards.
Has the advantages that: when the S-shaped plate of the wing is subjected to the airflow from front to back, the stress of the concave surface at the convex part of the bent plate is always larger than the stress of the convex surface, so that the S-shaped plate can always rotate anticlockwise around the axis of the rotating shaft (observed from the right side of the self-rotating rectifying device), the Magnus effect generated by the anticlockwise rotating S-shaped plate can provide lift force for the wing, and the problem of insufficient lift force of the existing small fixed wing aircraft is solved.
Further, the S-shaped plates share the rotating shaft.
Has the advantages that: the S-shaped plates share the rotating shaft, so that the self-rotating rectifying device is simple in overall structure and more convenient to mount.
Further, the bent plate is an arc-shaped plate.
Has the advantages that: the bent plate adopts the structural style of an arc-shaped plate, so that the bent plate is easier to process.
Furthermore, the left side and the right side of the S-shaped plate are both fixed with connecting plates.
Has the advantages that: the connecting plates arranged on the two sides of the S-shaped plate increase the structural strength of the S-shaped plate, and in addition, the connecting plates have a flow guiding effect, namely, the air flows passing through the S-shaped plates cannot interfere with each other.
Furthermore, a U-shaped through groove is formed in the right supporting wing, the groove bottom of the U-shaped through groove faces forwards, and the rotating shaft is fixed to the groove walls of the left side and the right side of the U-shaped through groove, so that the part, fixed to the S-shaped plate, of the rotating shaft is located in the U-shaped through groove.
Has the advantages that: the U-shaped through groove is convenient for the installation of the self-rotating rectifying device and enables air flow to smoothly flow through the self-rotating rectifying device.
In order to achieve the purpose, the technical scheme of the fixed-wing aircraft provided by the invention is as follows:
the fixed wing aircraft comprises a fuselage and wings fixed on the fuselage, wherein the wings comprise wing bodies extending leftwards and rightwards and a self-rotating rectifying device, and the self-rotating rectifying device comprises a rotating shaft and an S-shaped plate arranged on the rotating shaft; the wing body comprises a right supporting wing and a left supporting wing, at least two S-shaped plates are arranged on the right supporting wing, at least two S-shaped plates are arranged on the left supporting wing, and the S-shaped plates on the right supporting wing and the S-shaped plates on the left supporting wing are symmetrically arranged; the projection of each S-shaped plate on the right branch wing in a plane vertical to the rotating shaft is uniformly arranged along the circumferential direction of the rotating shaft by taking the rotating shaft as the center; the S-shaped plate comprises two bent plates which are respectively arranged at two sides of the rotating shaft, and when the S-shaped plate is in a vertical state, the middle part of the bent plate at the upper side is protruded backwards.
Has the advantages that: when the S-shaped plate of the fixed-wing aircraft is subjected to the airflow from front to back, the stress of the concave surface at the convex part of the bent plate is always larger than the stress of the convex surface, so that the S-shaped plate can always rotate anticlockwise around the axis of the rotating shaft (observed from the right side of the self-rotating rectifying device), the Magnus effect generated by the anticlockwise rotating S-shaped plate can provide lift force for the wings, and the problem of insufficient lift force of the existing small fixed-wing aircraft is solved.
Further, the S-shaped plates share the rotating shaft.
Has the advantages that: the S-shaped plates share the rotating shaft, so that the self-rotating rectifying device is simple in overall structure and more convenient to mount.
Further, the bent plate is an arc-shaped plate.
Has the advantages that: the bent plate adopts the structural style of an arc-shaped plate, so that the bent plate is easier to process.
Furthermore, the left side and the right side of the S-shaped plate are both fixed with connecting plates.
Has the advantages that: the connecting plates arranged on the two sides of the S-shaped plate increase the structural strength of the S-shaped plate, and in addition, the connecting plates have a flow guiding effect, namely, the air flows passing through the S-shaped plates cannot interfere with each other.
Furthermore, a U-shaped through groove is formed in the right supporting wing, the groove bottom of the U-shaped through groove faces forwards, and the rotating shaft is fixed to the groove walls of the left side and the right side of the U-shaped through groove, so that the part, fixed to the S-shaped plate, of the rotating shaft is located in the U-shaped through groove.
Has the advantages that: the U-shaped through groove is convenient for the installation of the self-rotating rectifying device and enables air flow to smoothly flow through the self-rotating rectifying device.
Drawings
FIG. 1 is an exploded view of a fixed wing aircraft embodiment 1 of the present invention;
FIG. 2 is a schematic structural view of a fixed wing aircraft embodiment 1 of the present invention;
FIG. 3 is a schematic view of the connection of the rotating shaft, S-shaped plate and connecting plate of the self-rotating rectifying device;
FIG. 4 is a perspective view of a wing body.
Description of reference numerals: 1. a wing body; 2. a self-rotating rectifying device; 3. a wing shell; 4. covering a skin; 5. an arc-shaped upper panel; 6. a rib; 7. a movable flap; 8. a rotating shaft; 9. an S-shaped plate; 901. bending a plate; 10. a right arm; 11. a left arm; 12. a connecting plate; 13. a deep groove ball bearing; 14. a rotating shaft connecting hole; 15. the rotating shaft is perforated; 16. a bearing fixing hole; 17. u-shaped through groove.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention is described in further detail below with reference to the accompanying drawings and embodiments. It should be understood that the detailed description and specific examples, while indicating the preferred embodiment of the invention, are intended for purposes of illustration only and are not intended to limit the scope of the invention. The components of embodiments of the present invention generally described and illustrated in the figures herein may be arranged and designed in a wide variety of different configurations.
Thus, the following detailed description of the embodiments of the present invention, presented in the figures, is not intended to limit the scope of the invention, as claimed, but is merely representative of selected embodiments of the invention. All other embodiments, which can be derived by a person skilled in the art from the embodiments of the present invention without making any creative effort, shall fall within the protection scope of the present invention.
It is to be noted that, in the embodiments of the present invention, relational terms such as "first" and "second", and the like, which may be present in the embodiments, are only used for distinguishing one entity or operation from another entity or operation, and do not necessarily require or imply that such actual relationships or orders between the entities or operations exist. Also, terms such as "comprises," "comprising," or any other variation thereof, which may be present, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus. Without further limitation, the appearances of the phrase "comprising an … …" or similar limitation may be present without necessarily excluding the presence of additional identical elements in the process, method, article, or apparatus that comprises the same elements.
In the description of the present invention, unless otherwise explicitly specified or limited, terms such as "mounted," "connected," and "connected" that may be present are to be construed broadly, e.g., as a fixed connection, a releasable connection, or an integral connection; can be mechanically or electrically connected; either directly or indirectly through intervening media, or may be interconnected between two elements. The specific meaning of the above terms in the present invention can be understood by those skilled in the art from specific situations.
In the description of the present invention, unless otherwise specifically stated or limited, the term "provided" may be used in a broad sense, for example, the object of "provided" may be a part of the body, or may be arranged separately from the body and connected to the body, and the connection may be detachable or non-detachable. The specific meaning of the above terms in the present invention can be understood by those skilled in the art from specific situations.
The present invention will be described in further detail with reference to examples.
the fixed wing aircraft comprises a fuselage and a wing fixed on the fuselage, and as shown in fig. 1 to 4, the wing comprises a wing body 1 extending left and right and a self-rotating rectifying device 2 assembled on the wing body 1. When the fixed-wing aircraft is subjected to the airflow from front to back, the self-rotating rectifying device 2 can generate the Magnus effect to increase the lift force on the wings, so that the flight performance of the fixed-wing aircraft is improved.
The wing body 1 comprises a wing shell 3 and a skin 4 covering the surface of the wing shell 3, the wing shell 3 comprises an arc-shaped upper panel 5, a horizontal lower panel, a rib 6 connecting the arc-shaped upper panel 5 and the horizontal lower panel and a movable aileron 7, and the movable aileron 7 is connected with the rear side of the horizontal lower panel. The movable aileron 7 can swing up and down within a certain angle range to adjust the maneuvering capability of the aircraft, and the specific structure of the movable aileron 7 for realizing the up-and-down swing is a conventional structure in the prior art, and is not described again here.
The self-rotating rectifying device 2 comprises a rotating shaft 8 rotatably assembled on the wing shell 3 and an S-shaped plate 9 arranged on the rotating shaft 8, wherein the S-shaped plate 9 comprises two bent plates 901. The rotating shaft 8 penetrates through the S-shaped plate 9 and is located in the middle of the S-shaped plate 9, and the two bent plates 901 are respectively located on two sides of the rotating shaft 8 and are centrosymmetric with respect to the axis of the rotating shaft 8. When the S-shaped plate 9 is in the vertical state, the middle of the bent plate 901 at the upper side is protruded backward, and correspondingly, the middle of the bent plate 901 at the lower side is protruded forward. In this embodiment, the bending plate 901 is an arc plate, and in other embodiments, the bending plate may also be a flap having a certain angle, for example, a flap having an included angle of 90 °.
When the curved plate 901 is subjected to the airflow from front to back, the stress of the concave surface at the convex part of the curved plate 901 is always larger than the stress of the convex surface, so that the S-shaped plate 9 always rotates anticlockwise around the axis of the rotating shaft 8 (as viewed from the right side of the self-rotating rectifying device 2), and the magnus effect generated by the anticlockwise rotating S-shaped plate 9 can provide lift force for the wings, so that the lift force for the fixed-wing aircraft is increased, and the flight performance of the fixed-wing aircraft is improved.
In order to ensure the continuity of rotation of the S-shaped plate 9 and further improve the lift provided by the self-rotating fairing 2 for the fixed-wing aircraft, the S-shaped plate 9 is provided in plurality. The wing body 1 comprises a right supporting wing 10 and a left supporting wing 11, in this embodiment, three S-shaped plates 9 are disposed on the right supporting wing 10 and the left supporting wing 11, and the S-shaped plates 9 on the right supporting wing 10 and the left supporting wing 11 are symmetrically arranged. Taking the right supporting wing 10 as an example, the projection of each S-shaped plate 9 on the right supporting wing 10 in the plane perpendicular to the rotating shaft 8 is uniformly arranged along the circumferential direction of the rotating shaft 8 with the rotating shaft 8 as the center, and in this embodiment, the three S-shaped plates 9 on the right supporting wing 10 are arranged at an angle of 60 ° with respect to each other. The S-shaped plate 9 is arranged in such a way that the continuity of the rotation of the S-shaped plate 9 is further ensured.
In order to increase the structural strength of the S-shaped plate 9, circular connecting plates 12 are provided on both sides of the S-shaped plate 9. In addition, the connecting plates 12 have a flow guiding effect so that the air flows through the S-shaped plates 9 do not interfere with each other.
In particular, in the present embodiment, taking the right branch wing 10 as an example, the connection plate 12 between each adjacent S-shaped plates 9 on the right branch wing 10 is a common connection plate. The arrangement of the common connecting plate simplifies the structure of the self-rotating rectifying device 2 and facilitates processing.
In the present embodiment, in order to simplify the overall structure of the self-rotating rectifying device 2 and facilitate the installation of the self-rotating rectifying device 2, the S-shaped plates 9 share the same rotating shaft 8.
In order to facilitate the installation of the self-rotating rectifying device 2 and enable the airflow to smoothly flow through the self-rotating rectifying device 2, the wing body 1 is provided with a U-shaped through groove 17, the bottom of the U-shaped through groove 17 faces forwards, and the rotating shaft 8 is fixed with the left side groove wall and the right side groove wall of the U-shaped through groove 17, so that the part of the rotating shaft 8 fixed with the S-shaped plate 9 is positioned in the U-shaped through groove 17. Specifically, in this embodiment, two U-shaped through slots 17 are provided, the left and right ends of the rotating shaft 8 are rotatably mounted in the rotating shaft connecting holes 14 on the wing body 1, and the middle part of the rotating shaft 8 passes through the rotating shaft through hole 15 on the wing body 1. The rotating shaft 8 is supported by the wing body 1 at the middle part and the two ends of the rotating shaft 8 by adopting the arrangement mode, so that the phenomenon that the rotating shaft 8 is deformed under stress is reduced.
More specifically, in the present embodiment, in order to make the rotation of the rotation shaft 8 smoother, the rotation shaft 8 is rotatably fitted on the wing body 1 by means of the deep groove ball bearing 13, and the deep groove ball bearing 13 is fitted in the bearing fixing hole 16. In addition, the rotating shaft 8 is in interference fit with the deep groove ball bearing 13, the deep groove ball bearing 13 and the wing body 1.
The self-rotating fairing 2 provides a part of lift force for the fixed wing aircraft, and sacrifices a part of maneuverability of the aircraft, so that the adjustable range of the angle of the movable aileron 7 needs to be enlarged, and in the embodiment, the movable aileron 7 has a +/-60 degree angle relative to the horizontal lower panel.
The working principle of the self-rotating rectifying device 2 of the fixed-wing aircraft is as follows: when the self-rotating rectifying device 2 receives the air current from front to back, the air current can pass through the surface of each S-shaped plate 9 of the self-rotating rectifying device 2, the stress of the concave surface of the convex part of the bent plate 901 is always greater than that of the convex surface, the S-shaped plates 9 can rotate anticlockwise around the axis of the rotating shaft 8 all the time, the Magnus effect generated by the S-shaped plates 9 rotating anticlockwise can provide extra lift force for the wings, and further the flight performance of the fixed wing aircraft is improved, and the problem that the lift force of the existing small fixed wing aircraft is insufficient is solved.
The embodiment 2 of the fixed-wing aircraft provided by the invention is different from the embodiment 1, in that two rotating shafts are provided, one rotating shaft is arranged in the U-shaped through groove on the right branch wing, and the other rotating shaft is arranged in the U-shaped through groove on the left branch wing.
The embodiment 3 of the fixed wing aircraft provided by the invention is different from the embodiment 1, connecting plates are not arranged on the left side and the right side of the S-shaped plates, and the S-shaped plates are arranged at intervals.
The embodiment 4 of the fixed-wing aircraft provided in the present invention is different from the embodiment 1 described above in that the connecting plates between adjacent S-shaped plates on the right branch wing and the left branch wing are not shared connecting plates, that is, the connecting plates on both sides of each S-shaped plate are all independent of each S-shaped plate.
In the embodiments of the wing provided in the present invention, the specific structure of the wing is the same as that of the wing in each embodiment of the fixed-wing aircraft described above, and details are not repeated here.
The above description is only a preferred embodiment of the present invention, and not intended to limit the present invention, the scope of the present invention is defined by the appended claims, and all structural changes that can be made by using the contents of the description and the drawings of the present invention are intended to be embraced therein.
Claims (10)
1. The wing is characterized by comprising a wing body (1) extending left and right and a self-rotating rectifying device (2), wherein the self-rotating rectifying device (2) comprises a rotating shaft (8) and an S-shaped plate (9) arranged on the rotating shaft (8); the wing body (1) comprises a right supporting wing (10) and a left supporting wing (11), at least two S-shaped plates (9) are arranged on the right supporting wing (10), at least two S-shaped plates (9) are arranged on the left supporting wing (11), and the S-shaped plates (9) on the right supporting wing (10) and the S-shaped plates (9) on the left supporting wing (11) are symmetrically arranged; the projections of the S-shaped plates (9) on the right branch wing (10) in the plane vertical to the rotating shaft (8) are uniformly distributed along the circumferential direction of the rotating shaft (8) by taking the rotating shaft (8) as the center; the S-shaped plate (9) comprises two bent plates (901) which are respectively arranged at two sides of the rotating shaft (8), and when the S-shaped plate (9) is in a vertical state, the middle part of the bent plate (901) arranged at the upper side protrudes backwards.
2. Wing according to claim 1, characterized in that each S-shaped plate (9) shares the shaft (8).
3. The wing as claimed in claim 1, characterized in that the curved plate (901) is an arc-shaped plate.
4. Wing according to claim 1, 2 or 3, characterized in that the S-shaped plate (9) is fixed with connecting plates (12) on both the left and right sides.
5. The wing as claimed in claim 1, 2 or 3, characterized in that the right supporting wing (10) is provided with a U-shaped through groove (17), the bottom of the U-shaped through groove (17) faces forward, and the rotating shaft (8) is fixed to the left and right side groove walls of the U-shaped through groove (17), so that the part of the rotating shaft (8) fixed to the S-shaped plate (9) is located in the U-shaped through groove (17).
6. The fixed wing aircraft is characterized by comprising a fuselage and wings fixed on the fuselage, wherein the wings comprise wing bodies (1) extending left and right and self-rotating rectifying devices (2), and the self-rotating rectifying devices (2) comprise rotating shafts (8) and S-shaped plates (9) arranged on the rotating shafts (8); the wing body (1) comprises a right supporting wing (10) and a left supporting wing (11), at least two S-shaped plates (9) are arranged on the right supporting wing (10), at least two S-shaped plates (9) are arranged on the left supporting wing (11), and the S-shaped plates (9) on the right supporting wing (10) and the S-shaped plates (9) on the left supporting wing (11) are symmetrically arranged; the projections of the S-shaped plates (9) on the right branch wing (10) in the plane vertical to the rotating shaft (8) are uniformly distributed along the circumferential direction of the rotating shaft (8) by taking the rotating shaft (8) as the center; the S-shaped plate (9) comprises two bent plates (901) which are respectively arranged at two sides of the rotating shaft (8), and when the S-shaped plate (9) is in a vertical state, the middle part of the bent plate (901) arranged at the upper side is protruded backwards.
7. The fixed-wing aircraft according to claim 6, characterized in that each S-shaped plate (9) shares the rotation axis (8).
8. The fixed-wing aircraft according to claim 6, characterized in that the curved plate (901) is an arc-shaped plate.
9. The fixed-wing aircraft according to claim 6, 7 or 8, characterized in that the S-shaped panels (9) are fixed with connection plates (12) on both the left and right sides.
10. The fixed-wing aircraft according to claim 6, 7 or 8, characterized in that the right supporting wing (10) is provided with a U-shaped through slot (17), the bottom of the U-shaped through slot (17) faces forward, and the rotating shaft (8) is fixed to the left and right side slot walls of the U-shaped through slot (17), so that the part of the rotating shaft (8) fixed to the S-shaped plate (9) is located in the U-shaped through slot (17).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111313999.1A CN113911317A (en) | 2021-11-08 | 2021-11-08 | Wing and fixed wing aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111313999.1A CN113911317A (en) | 2021-11-08 | 2021-11-08 | Wing and fixed wing aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN113911317A true CN113911317A (en) | 2022-01-11 |
Family
ID=79245573
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202111313999.1A Pending CN113911317A (en) | 2021-11-08 | 2021-11-08 | Wing and fixed wing aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN113911317A (en) |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE2503918A1 (en) * | 1975-01-31 | 1976-08-05 | Christian Klepsch | Rotating wing flying machine - has cylindrical rotors comprised of aerofoil sections carried between rotating discs |
| DE19715827A1 (en) * | 1997-04-16 | 1998-10-22 | Peter Dr Faber | Aircraft taking off and landing vertically |
| US6666650B1 (en) * | 1999-05-05 | 2003-12-23 | Ramona Themel | Wind power facility with a verticle rotor |
| US20120160955A1 (en) * | 2010-12-22 | 2012-06-28 | Eads Deutschland Gmbh | Hybrid Rotor |
| CN103434640A (en) * | 2013-08-25 | 2013-12-11 | 西北工业大学 | High-altitude unmanned plane equipped with Magnus effect propulsion system |
| WO2020145677A1 (en) * | 2019-01-11 | 2020-07-16 | 최영준 | Drone |
| CN112498741A (en) * | 2020-10-30 | 2021-03-16 | 中南大学 | Detection aircraft and Mars cruise detection method |
-
2021
- 2021-11-08 CN CN202111313999.1A patent/CN113911317A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE2503918A1 (en) * | 1975-01-31 | 1976-08-05 | Christian Klepsch | Rotating wing flying machine - has cylindrical rotors comprised of aerofoil sections carried between rotating discs |
| DE19715827A1 (en) * | 1997-04-16 | 1998-10-22 | Peter Dr Faber | Aircraft taking off and landing vertically |
| US6666650B1 (en) * | 1999-05-05 | 2003-12-23 | Ramona Themel | Wind power facility with a verticle rotor |
| US20120160955A1 (en) * | 2010-12-22 | 2012-06-28 | Eads Deutschland Gmbh | Hybrid Rotor |
| CN103434640A (en) * | 2013-08-25 | 2013-12-11 | 西北工业大学 | High-altitude unmanned plane equipped with Magnus effect propulsion system |
| WO2020145677A1 (en) * | 2019-01-11 | 2020-07-16 | 최영준 | Drone |
| CN112498741A (en) * | 2020-10-30 | 2021-03-16 | 中南大学 | Detection aircraft and Mars cruise detection method |
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