CN106986029B - Dish-shaped aircraft - Google Patents
Dish-shaped aircraft Download PDFInfo
- Publication number
- CN106986029B CN106986029B CN201710209314.6A CN201710209314A CN106986029B CN 106986029 B CN106986029 B CN 106986029B CN 201710209314 A CN201710209314 A CN 201710209314A CN 106986029 B CN106986029 B CN 106986029B
- Authority
- CN
- China
- Prior art keywords
- wings
- shaped
- wing
- disc
- climbing
- 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.)
- Active
Links
- 230000009194 climbing Effects 0.000 claims abstract description 29
- 230000007246 mechanism Effects 0.000 claims description 24
- 230000001154 acute effect Effects 0.000 claims description 3
- 238000005265 energy consumption Methods 0.000 abstract description 8
- 230000001133 acceleration Effects 0.000 abstract description 5
- 108010066278 cabin-4 Proteins 0.000 description 3
- 240000002836 Ipomoea tricolor Species 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000001105 regulatory effect Effects 0.000 description 1
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C39/00—Aircraft not otherwise provided for
- B64C39/06—Aircraft not otherwise provided for having disc- or ring-shaped wings
- B64C39/062—Aircraft not otherwise provided for having disc- or ring-shaped wings having annular wings
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/22—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft
- B64C27/28—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft with forward-propulsion propellers pivotable to act as lifting rotors
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/25—Fixed-wing aircraft
Abstract
The invention is suitable for the technical field of aircrafts, and discloses a dished aircraft, which comprises a frame and dished wings fixedly connected to the frame and in a shell shape, wherein annular diversion wings are arranged at the outer edges of the dished wings, the frame is connected with a lift force generating device, the lift force generating device is positioned below the dished wings, and climbing wings are arranged below the dished wings. The disk-shaped aircraft provided by the invention is provided with the disk-shaped wings and the climbing wings positioned below the disk-shaped wings, so that the lifting force can be provided when the disk-shaped aircraft has horizontal speed, the higher the horizontal speed of the disk-shaped aircraft is, the larger the lifting force obtained by the disk-shaped aircraft is, the lower the energy consumption of the disk-shaped aircraft is under the same condition, the acceleration performance of the disk-shaped aircraft is relatively higher, and the maneuvering performance of the disk-shaped aircraft is high.
Description
Technical Field
The invention belongs to the technical field of aircrafts, and particularly relates to a disc-shaped aircraft.
Background
The existing disc-shaped aircrafts generally adopt an integral disc-shaped structure, are generally provided with a lift force driving device and a thrust force driving device, and have high energy consumption and poor maneuvering performance.
Disclosure of Invention
The invention aims to overcome the defects of the prior art and provide a dish-shaped aircraft which has low energy consumption and good maneuvering performance.
The technical scheme of the invention is as follows: the utility model provides a dish aircraft, includes frame and fixed connection in the frame and be the dish wing of housing form, the outer fringe of dish wing is provided with annular water conservancy diversion wing, the frame is connected with lift generating device, just lift generating device is located the below of dish wing, the below of dish wing is provided with the wing that climbs.
Optionally, the trailing edge of the climbing wing is provided with a trailing edge flap, the frame is connected with a cabin, and the climbing wing is arranged in front of or behind the cabin, or the climbing wings are symmetrically arranged on two sides of the cabin respectively.
Optionally, the leading edge of the climbing wing is provided with a leading edge flap.
Optionally, a lift angle adjusting mechanism for adjusting the angle of the lift generating device is connected to the frame.
Alternatively, the lift force generating device comprises an engine or a motor, at least two lift force generating devices are provided, and each lift force generating device is symmetrically arranged along the center of the disc-shaped wing.
Optionally, two symmetrical sides of the guiding wing are fixedly connected with direction wings, the two direction wings are respectively located outside two sides of the climbing wing, a rudder plate is arranged at the rear end of the direction wings, and the rudder plate is connected with a direction control mechanism.
Optionally, at least two horizontal thrust devices are arranged below the disc-shaped wings, the horizontal thrust devices are symmetrically arranged at the centers of the disc-shaped wings, and the horizontal thrust devices are connected to the frame through a horizontal thrust angle adjusting mechanism.
Optionally, a guide cover is arranged below the guide wings, the two guide wings are symmetrically arranged with the guide cover as a center, and the front end of the guide cover is in an acute angle shape or an arc shape.
Optionally, a tail fin is arranged above one end of the guide vane, which is far away from the guide cover.
Optionally, the lifting force generating device is characterized in that a through hole is formed in the disc-shaped wing, corresponding to the upper portion of the lifting force generating device, a movable cover plate is movably connected to the through hole, and an opening and closing driving mechanism used for driving the movable cover plate to rotate or move is connected to the movable cover plate.
The disk-shaped aircraft provided by the invention is provided with the disk-shaped wings and the climbing wings positioned below the disk-shaped wings, the climbing wings and the trailing edge flaps can provide lifting force when the disk-shaped aircraft has horizontal speed, the higher the horizontal speed of the disk-shaped aircraft is, the greater the lifting force obtained by the disk-shaped aircraft is, the lower the energy consumption of the disk-shaped aircraft is under the same condition, the acceleration performance of the disk-shaped aircraft is relatively higher, and the maneuvering performance of the disk-shaped aircraft is high.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings that are needed in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and other drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.
FIG. 1 is a front view of a dish aircraft provided in an embodiment of the invention;
FIG. 2 is a right side view of a dish aircraft provided in an embodiment of the invention;
FIG. 3 is a plan view of a dish aircraft provided in an embodiment of the invention;
FIG. 4 is a top view of a dish-shaped aircraft provided by an embodiment of the invention;
fig. 5 is a bottom view of a dish-shaped aircraft provided in an embodiment of the invention.
Detailed Description
The present invention will be described in further detail with reference to the drawings and examples, in order to make the objects, technical solutions and advantages of the present invention more apparent. It should be understood that the specific embodiments described herein are for purposes of illustration only and are not intended to limit the scope of the invention.
It will be understood that when an element is referred to as being "mounted" or "disposed" on another element, it can be directly on the other element or intervening elements may also be present. When an element is referred to as being "connected to" another element, it can be directly connected to the other element or intervening elements may also be present.
It should be noted that, in the embodiments of the present invention, terms such as left, right, up, and down are merely relative concepts or references to normal use states of the product, and should not be construed as limiting.
As shown in fig. 1 to 5, the disc-shaped aircraft provided by the embodiment of the invention comprises a frame 16 and a disc-shaped wing 1 fixedly connected to the frame 16, wherein the disc-shaped wing 1 is in a shell shape (flying saucer shape) arched upwards, the frame 16 is connected with a lift force generating device 2, the lift force generating device 2 is positioned below the disc-shaped wing 1, a climbing wing 3 is arranged below the disc-shaped wing 1, the climbing wing 3 provides lift force when the disc-shaped aircraft has horizontal speed, the higher the horizontal speed of the disc-shaped aircraft is, the higher the obtained lift force is, the lower the energy consumption of the disc-shaped aircraft is under the same condition, the acceleration performance of the disc-shaped aircraft is relatively higher, and the disc-shaped aircraft has high maneuvering performance and can be used as an unmanned aerial vehicle or a manned aircraft.
In particular, the climbing wing 3 may be connected to the frame 16 or the dished wing 1; the trailing edge of the climbing wing 3 is provided with a trailing edge flap 15, the frame 16 is connected with the engine room 4, the climbing wing 3 is arranged in front of or behind the engine room 4, or the climbing wings 3 are symmetrically arranged on two sides of the engine room 4 respectively, and the maneuvering performance of the disc-shaped aircraft is high.
In particular, the leading edge of the climbing wing 3 is provided with a leading edge flap (not shown in the figures) to further enhance the manoeuvrability of the disc-shaped aircraft.
Specifically, the edge of the dish-shaped wing 1 is provided with a guide wing 5, and the guide wing 5 is annular. The outer edge of the guide wing 5 is in a blade shape, in this embodiment, the bottom of the guide wing 5 is provided with a slope inclined downwards from the outer edge, the lower end face of the guide wing 5 and the periphery of the guide wing 5 are provided with slope structures for enabling the thickness of the guide wing 5 to be reduced, and by arranging the guide wing 5, the flying stability of the saucer-shaped aircraft is improved, the flying resistance is reduced, the aerodynamic performance of the saucer-shaped aircraft is optimized, and the energy consumption is reduced under the same condition.
Specifically, the upper part of the cabin 4 is penetrated out of the center of the dished wing 1, the frame 16 or the bottom of the cabin 4 is connected with a folding landing gear 6, and the lower end of the landing gear 6 is provided with a tire 7. The nacelle 4 may be provided with multiple layers to house equipment, occupants, etc. In a specific application, the upper layer of the cabin 4 may be a passenger cabin, and the middle or lower layer may be an equipment cabin, a cargo cabin, etc. The top of the nacelle 4 may be of a spherical structure with little resistance. The bottom of the nacelle 4 may also be of spherical construction to further reduce drag.
Specifically, the lift force generating device 2 may include an engine or/and a motor, and the lift force generating device 2 is provided with at least two, and each lift force generating device 2 is symmetrically arranged along the center of the disc-shaped wing 1. In this embodiment, the lift force generating devices 2 are provided in 4 numbers, which are uniformly distributed at intervals of 90 degrees with respect to the center of the disk-shaped wing 1. The lift force generation devices 2 may be all engines (jet engines), may be all motors, may be half engines, and may be half motors, and the engines and the motors may be alternately arranged at intervals.
Specifically, a lift angle adjusting mechanism (not shown) for adjusting the angle of the lift generating device 2 is connected to the frame 16, so that the angle of the lift generating device 2 can be adjusted. The lift force generation device 2 can be adjusted to a vertical state in the longitudinal direction, a horizontal state in the transverse direction, or an angular state of 45 degrees in the oblique direction. When the lift force generating device 2 is adjusted to be in a vertical state, the disc-shaped aircraft can be lifted off quickly, and the lifting time is short. When the lift force generating device 2 is adjusted to a horizontal state, the disc-shaped aircraft can obtain larger horizontal thrust, the horizontal flying speed is high, and the horizontal acceleration is high. When the lift force generating device 2 is regulated to be in a 45-degree inclined state, the horizontal speed can be increased during take-off, so that the lift force generating device is suitable for different use occasions and requirements.
Specifically, at least two horizontal thrust devices 8 are disposed below the dished wing 1, and each horizontal thrust device 8 is disposed in central symmetry with respect to the dished wing 1. The horizontal thrust means 8 are located between the two steering wings. In this embodiment, two horizontal thrust devices 8 are provided and are symmetrically disposed on both sides of the nacelle 4. The horizontal thrust means 8 may be a jet engine or an electric motor with a propeller attached.
Specifically, the horizontal thrust device 8 is connected to the frame 16 through a horizontal thrust angle adjusting mechanism, and the horizontal thrust device 8 can rotate horizontally or vertically.
Specifically, the lift angle adjustment mechanism may employ a mechanical rotation device or a hydraulic rotation device. The horizontal thrust angle adjusting mechanism can adopt a mechanical rotating device or a hydraulic rotating device.
Specifically, the two symmetrical sides of the guiding wing 5 are provided with direction wings 9, and the two direction wings 9 are respectively located outside the two sides of the climbing wing 3, that is, the direction of the direction wings 9 is the same as the direction of the front end of the climbing wing 3 (forward), the rear end of the direction wings 9 is provided with a rudder plate 10, the rudder plate 10 is connected with a direction control mechanism, and the direction control mechanism can adopt a hydraulic driving mechanism or a mechanical driving mechanism to control the heading of the dish-shaped aircraft, so that the maneuvering performance is good. The flying direction of the disc-shaped aircraft can be quickly adjusted without changing the horizontal thrust direction of the horizontal thrust device 8, and the flying direction of the disc-shaped aircraft can be changed. If the horizontal thrust direction of the horizontal thrust device 8 is changed in a matching way, the disc-shaped aircraft can be more flexible.
Specifically, a guide cover 11 is arranged below the guide wing 5, the guide cover 11 is located at the center of the front end of the dish-shaped aircraft, the two direction wings 9 are symmetrically and longitudinally arranged by taking the guide cover 11 as a center, and the front end of the guide cover 11 is in an acute angle shape or an arc shape so as to reduce airflow resistance and avoid forming turbulence. The air guide sleeve 11 can be of an integral structure, and can be arranged to be capable of being lifted and unfolded, namely, after the saucer-shaped aircraft is lifted off, the air guide sleeve 11 is unfolded downwards, the air guide area is large, and the air guide effect is better.
Specifically, the guiding wings 5 are provided with tail wings 12 above one end far away from the guiding cover 11, so as to improve the stability of flight. Namely, the air guide sleeve 11 is positioned at the front end of the disc-shaped aircraft, the tail wing 12 is positioned at the rear end, and the two direction wings 9 are respectively arranged at the left side and the right side.
Specifically, a through hole 13 is arranged above the disc-shaped wing 1 corresponding to the lift force generating device 2, a movable cover plate 14 is movably connected to the through hole 13, and the movable cover plate 14 is connected with an opening and closing driving mechanism for driving the movable cover plate 14 to rotate or move. When the lifting force is required to be high, the opening and closing driving mechanism can drive the movable cover plate 14 to keep the through hole 13 in an opening state. When the high lift force is not needed, such as in the air, the opening and closing driving mechanism can drive the movable cover plate 14 to keep the through hole 13 in a closed state, so that turbulence is avoided, air resistance is reduced, energy consumption is low, and the movable cover plate can be used as an unmanned aerial vehicle or a manned aircraft.
Specifically, the movable cover plate 14 may be rotatably connected to the dished wing 1 through a pin, and the opening and closing driving mechanism includes a motor or a motor connected to the movable cover plate 14 and a transmission assembly connected between the motor and the movable cover plate 14. The flap 14 can be turned along the surface of the dished wing 1 to open or close the through hole 13, or can be turned over to open or close the through hole 13.
Alternatively, the movable cover 14 may be connected to the disc-shaped wing 1 through a linear sliding rail, and the opening and closing driving mechanism may be a linear motion mechanism, for example, a linear motor, a hydraulic device, a rack and pinion mechanism, a screw mechanism, and the like. Of course, the removable cover 14 may be configured as a blind or the like.
The disc-shaped aircraft provided by the embodiment of the invention is provided with the disc-shaped wings 1 and the climbing wings 3 positioned below the disc-shaped wings 1, the climbing wings 3 and the trailing edge flaps can provide lifting force when the disc-shaped aircraft has horizontal speed, the higher the horizontal speed of the disc-shaped aircraft is, the higher the lifting force obtained by the disc-shaped aircraft is, the lower the energy consumption of the disc-shaped aircraft is under the same condition, the higher the acceleration performance of the disc-shaped aircraft is relatively, and the maneuverability of the disc-shaped aircraft is high.
The foregoing description of the preferred embodiments of the invention is not intended to be limiting, but rather is intended to cover all modifications, equivalents, or alternatives falling within the spirit and principles of the invention.
Claims (6)
1. The saucer-shaped aircraft is characterized by comprising a frame and saucer-shaped wings which are fixedly connected to the frame and are in a shell shape, wherein annular diversion wings are arranged at the outer edges of the saucer-shaped wings, the frame is connected with a lift force generating device, the lift force generating device is positioned below the saucer-shaped wings, and climbing wings are arranged below the saucer-shaped wings; the climbing wings are connected with the frame or the dish-shaped wings, and the climbing wings provide lift force when the dish-shaped aircraft has horizontal speed; the lift force generating device comprises an engine or/and a motor; the guide wing is annular, the outer edge of the guide wing is in a blade shape, the bottom of the guide wing is provided with an inclined plane which inclines downwards from the outer edge, and the lower end face of the guide wing and the part close to the outer periphery of the guide wing are provided with inclined plane structures for reducing the thickness of the guide wing; the trailing edge of the climbing wing is provided with a trailing edge flap, and the leading edge of the climbing wing is provided with a leading edge flap; the frame is connected with a cabin, the climbing wings are arranged in front of or behind the cabin, or the climbing wings are symmetrically arranged on two sides of the cabin respectively; the two symmetrical sides of the guide wing are provided with direction wings, the two direction wings are respectively positioned outside the two sides of the climbing wing, the directions of the front ends of the direction wings and the climbing wing are the same and forward, the rear ends of the direction wings are provided with direction rudder plates, and the direction rudder plates are connected with a direction control mechanism; at least two horizontal thrust devices are arranged below the disc-shaped wings, the horizontal thrust devices are symmetrically arranged at the centers of the disc-shaped wings, and the horizontal thrust devices are connected to the frame through horizontal thrust angle adjusting mechanisms.
2. The disc-shaped aircraft of claim 1 wherein the frame has attached thereto a lift angle adjustment mechanism for adjusting the angle of the lift generating device.
3. The disc-shaped aircraft of claim 1 wherein at least two lift generating devices are provided, each of the lift generating devices being symmetrically disposed along the center of the disc-shaped wing.
4. A dish-shaped aircraft as claimed in any one of claims 1 to 3, wherein a guide vane is arranged below the guide vane, the two direction vanes are symmetrically arranged with the guide vane as a center, and the front end of the guide vane is in an acute angle shape or an arc shape.
5. The disc-shaped aircraft of claim 4 wherein the deflector is provided with a tail over an end of the deflector remote from the deflector.
6. A disc-shaped aircraft according to any one of claims 1 to 3, wherein the disc-shaped wings are provided with through holes corresponding to the upper parts of the lift force generating devices, movable cover plates are movably connected to the through holes, and an opening and closing driving mechanism for driving the movable cover plates to rotate or move is connected to the movable cover plates.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710209314.6A CN106986029B (en) | 2017-03-31 | 2017-03-31 | Dish-shaped aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710209314.6A CN106986029B (en) | 2017-03-31 | 2017-03-31 | Dish-shaped aircraft |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106986029A CN106986029A (en) | 2017-07-28 |
| CN106986029B true CN106986029B (en) | 2024-01-12 |
Family
ID=59416354
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710209314.6A Active CN106986029B (en) | 2017-03-31 | 2017-03-31 | Dish-shaped aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106986029B (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111409820A (en) * | 2020-03-31 | 2020-07-14 | 兰安德 | Propelling device in air and propelling method thereof |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO1997012805A1 (en) * | 1995-10-04 | 1997-04-10 | Amorim Gagliardi Madeira Jonat | Aerodisk - atmospheric aeronautical vehicle |
| CN102582834A (en) * | 2012-03-09 | 2012-07-18 | 北京工业大学 | Saucer-shaped aircraft |
| CN202703888U (en) * | 2012-05-28 | 2013-01-30 | 严云北 | Fly ball with dish-shaped wing |
| CN204507260U (en) * | 2015-03-30 | 2015-07-29 | 河南金原碟科技有限公司 | A kind of dish-shaped manned quadrotor |
| CN106005402A (en) * | 2016-06-18 | 2016-10-12 | 夏建国 | Flying saucer type hypersonic stealth jet aircraft capable of realizing vertical take-off and landing |
| CN207015584U (en) * | 2017-03-31 | 2018-02-16 | 郭应辉 | Disc-shaped flying craft |
-
2017
- 2017-03-31 CN CN201710209314.6A patent/CN106986029B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO1997012805A1 (en) * | 1995-10-04 | 1997-04-10 | Amorim Gagliardi Madeira Jonat | Aerodisk - atmospheric aeronautical vehicle |
| CN102582834A (en) * | 2012-03-09 | 2012-07-18 | 北京工业大学 | Saucer-shaped aircraft |
| CN202703888U (en) * | 2012-05-28 | 2013-01-30 | 严云北 | Fly ball with dish-shaped wing |
| CN204507260U (en) * | 2015-03-30 | 2015-07-29 | 河南金原碟科技有限公司 | A kind of dish-shaped manned quadrotor |
| CN106005402A (en) * | 2016-06-18 | 2016-10-12 | 夏建国 | Flying saucer type hypersonic stealth jet aircraft capable of realizing vertical take-off and landing |
| CN207015584U (en) * | 2017-03-31 | 2018-02-16 | 郭应辉 | Disc-shaped flying craft |
Also Published As
| Publication number | Publication date |
|---|---|
| CN106986029A (en) | 2017-07-28 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US11673643B2 (en) | Low stall or minimum control speed aircraft | |
| RU2670356C2 (en) | Aircraft capable of vertical take-off | |
| CN108100212B (en) | Small aspect ratio self-adaptive variant flying wing layout fighter | |
| WO2016184358A1 (en) | Fixed structure type vertical take-off and landing aircraft based on dual flying control systems and control method therefor | |
| CN110077588A (en) | It is a kind of can the sea, land and air latent four of VTOL dwell aircraft | |
| CN103979104B (en) | One can variant X-type wing vertical landing minute vehicle | |
| CN202481309U (en) | Vector power vertical take-off and landing aircraft and vector power system thereof | |
| CN105083550A (en) | Fixed-wing aircraft realizing vertical take-off and landing | |
| WO2023000571A1 (en) | Flying car | |
| CN205150238U (en) | Unmanned aerial vehicle | |
| WO2015099603A1 (en) | An unmanned aerial vehicle | |
| WO2021103497A1 (en) | Airflow jet-type steering unmanned aerial vehicle | |
| US10953977B2 (en) | Aircraft with in-flight form varying apparatus | |
| KR101828924B1 (en) | An aircraft including an internal combustion engine and electric motors | |
| US20230086655A1 (en) | Variable-sweep wing aerial vehicle with vtol capabilites | |
| KR20170042952A (en) | Aircraft | |
| GB2504369A (en) | Aircraft wing with reciprocating outer aerofoil sections | |
| CN207015584U (en) | Disc-shaped flying craft | |
| CN106986029B (en) | Dish-shaped aircraft | |
| CN113277062A (en) | Telescopic wing, wing interval adjusting module, aircraft and control method | |
| CN104875875A (en) | Air wing type airflow directional load transportation air vehicle | |
| CN111762314A (en) | Rotor aircraft capable of vertically taking off and landing | |
| CN202526908U (en) | Double-leaf propeller of model plane | |
| CA3228095A1 (en) | Vertical take-off and landing craft systems and methods | |
| CN204642148U (en) | A kind of leading edge of a wing is equipped with the aircraft that wind ball drives wind wheel |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |