CN210416960U - Dish-shaped five-shaft multi-rotor aircraft - Google Patents
Dish-shaped five-shaft multi-rotor aircraft Download PDFInfo
- Publication number
- CN210416960U CN210416960U CN201921262999.1U CN201921262999U CN210416960U CN 210416960 U CN210416960 U CN 210416960U CN 201921262999 U CN201921262999 U CN 201921262999U CN 210416960 U CN210416960 U CN 210416960U
- Authority
- CN
- China
- Prior art keywords
- rotor
- control
- dish
- shaped
- ducted fan
- 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.)
- Expired - Fee Related
Links
Images
Classifications
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
Landscapes
- Toys (AREA)
Abstract
The utility model discloses a dish-shaped five-shaft multi-gyroplane, which comprises a fuselage; the shell is covered and fixed outside the machine body; a main rotor system including an electric counter-rotating ducted fan capable of counter-rotating the upper and lower stages of fans at a constant speed; the electric contra-rotating ducted fan is used for providing main flight power for the multi-rotor aircraft; an auxiliary rotor system comprising four control rotors that provide attitude control for a multi-rotor aircraft; a control system for effecting control of the main rotor system and the auxiliary rotor system. Compared with the existing multi-rotor aircraft, all the rotors of the dish-shaped five-shaft multi-rotor aircraft are wrapped in the casing and cannot contact with the human body to hurt the human body; meanwhile, the dish-shaped appearance is cool, and the dish-shaped glass can be applied to multiple fields of consumption, entertainment and the like.
Description
Technical Field
The utility model relates to a many gyroplanes manufacturing and designing technical field, specifically speaking relates to a five many gyroplanes of dish.
Background
The existing multi-rotor aircraft generally drives the propellers by a motor to generate power, the propellers occupy a large space, and the propellers are exposed outside the aircraft body, so that if the propellers rotating at a high speed contact the human body, the human body is greatly injured, and the safety is great.
Therefore, how to overcome the above technical defects of the existing electric multi-rotor aircraft is one direction that needs to be researched by those skilled in the art.
SUMMERY OF THE UTILITY MODEL
The utility model discloses aim at solving one of the above-mentioned technical problem among the prior art to a certain extent at least.
Therefore, the utility model aims to provide a five many gyroplanes of dish specifically adopt following technical scheme: comprises the steps of (a) preparing a mixture of a plurality of raw materials,
a body;
the shell is covered and fixed outside the machine body and comprises an upper cover with a narrow appearance and an opening at the top and a lower cover with a wide appearance and an opening at the bottom;
the main rotor system is arranged in the center above the fuselage and is wrapped by the upper cover of the casing, and the main rotor system comprises electric contra-rotating ducted fans which can make the upper and lower fans contra-rotate oppositely at a constant speed; the electric contra-rotating ducted fan is used for providing main flight power for the multi-rotor aircraft;
the auxiliary rotor wing system is positioned below the main rotor wing system and is wrapped by the lower cover of the machine shell, the auxiliary rotor wing system comprises four control rotor wings, the four control rotor wings are uniformly distributed on four corners of the machine body, which are away from the center of gravity of the machine body by a certain distance, by taking the center of gravity of the machine body as a center, and the outsides of the four control rotor wings are respectively covered with a flow guide cover; the four control rotors provide attitude control for the multi-rotor aircraft;
a control system located below the main rotor system at a central location of the lower shroud, and the control system is fixed with the fuselage, the control system being configured to effect control of the main rotor system and the auxiliary rotor system.
The utility model discloses use electronic contra-rotating ducted fan as the core, two-stage fan constant speed is contrarotated in opposite directions about making by it, produces main power, has configured four control rotors simultaneously to the control mode similar to many gyroplanes adjusts the gesture of fuselage, in order to reach control flight direction's purpose.
The utility model provides an including electronic contra-rotating ducted fan and control rotor all wrapped up by the casing, can not with human direct contact, improved the security of many gyroplanes.
The utility model provides an electronic contra-rotating ducted fan includes lazytongs, actuating mechanism, blade.
The synchronous mechanism comprises a flyover coaxial bracket, two linkage gears, at least one (generally two) synchronous gear and a front rotary table and a rear rotary table; the linkage gear and the synchronous gear are respectively fixed on vertically crossed shafts of the overpass coaxial bracket through bearings, and are tightly meshed to form a transmission structure; the front turntable and the rear turntable are respectively connected with the two linkage gears into a whole through fasteners.
Preferably, all the gears used in the above-described synchronizing mechanism are bevel gears.
The driving mechanism comprises a stator winding, a front driving ring, a rear driving ring and a stator support, wherein permanent magnets are arranged at the positions of the driving rings corresponding to the stator winding.
The stator winding in the driving mechanism is divided into single bodies which are respectively fixed on each slot position of the stator support.
Preferably, the stator windings are arranged in a ring shape, and the central radius of the stator windings is the same as that of the permanent magnets arranged in the upper driving ring and the lower driving ring; two magnetic poles of the stator winding are respectively opposite to the permanent magnets in the front driving ring and the rear driving ring.
The permanent magnets mounted on the front and rear driving rings in the driving mechanism are identical in number and position and are in mirror symmetry.
Preferably, three Hall sensors are arranged on the stator bracket, the sensors can be arranged at 120 degrees or 60 degrees, and the outputs of the Hall sensors are connected to a rotating speed controller. In some occasions with low requirements on stability, a Hall sensor can be omitted, and a corresponding Hall-free rotating speed controller is adopted to control the rotation of the motor.
The fan blades are arranged between the rotary disc and the driving ring, the rotating directions of the front fan blades and the rear fan blades are opposite, and the number of the fan blades is determined according to actual requirements;
preferably, the fan blades are tightly connected with the rotating disc and the driving ring into a whole by using fasteners.
The overpass coaxial bracket and the stator bracket are tightly connected into a whole through a fastener.
The utility model provides an electronic contra-rotating ducted fan needs to cooperate corresponding BLDC controller to use.
The front and back rotating discs, the front and back driving rings and the front and back fan blades are defined according to the air flowing direction when the electric contra-rotating ducted fan runs.
The electric contra-rotating ducted fan enables the front and rear (upper and lower) fans to be contra-rotated in a constant speed and opposite directions through the synchronizing mechanism, achieves the purpose of simultaneously driving the front and rear fans by one set of stator winding, and has the advantages of light weight and high efficiency. Compared with a single-stage electric fan, the electric contra-rotating ducted fan can obtain higher thrust at the same rotating speed or achieve the same thrust at a lower rotating speed, so that the efficiency is higher; compared with the counter-rotating fan realized in a pure mechanical mode, the electric counter-rotating ducted fan is simple in structure and easy to realize and control.
On the basis of the technical scheme, the utility model discloses still can make following improvement:
preferably, the distances between the four control rotors and the center of gravity of the fuselage are all equal to ensure the stability of the center of gravity of the multi-rotor aircraft, and the distances can be designed according to actual conditions so as to generate enough lever effect to control the flight attitude of the multi-rotor aircraft.
Preferably, the electric contra-rotating ducted fan is controlled by a high-power motor, and the control rotor is controlled by a low-power motor.
Preferably, the motor used for controlling the rotor wing is a hollow cup motor.
Preferably, the propellers adopted in the electric contra-rotating ducted fan are long screw propellers, and the propellers adopted by the control rotor wing are short propellers.
The utility model discloses in, electronic contra-rotating ducted fan disposes powerful motor and longer screw to it provides sufficient power for the lift of many gyroplanes. The control rotor is provided with a motor with low power and shorter propellers, and the control rotor is placed at four corners with a certain distance away from the center of gravity of the aircraft body, so that the multi-rotor aircraft has the advantages of flexibility in control and precision in flight attitude control.
Preferably, the upper cover is cylindrical in shape, so that the whole electric contra-rotating ducted fan is just matched with the upper cover to cover the upper cover.
Preferably, the lower cover appearance is the dish, and dished space is great, can hold whole control system and vice rotor system to can arrange each system in the most reasonable position, guarantee the stable flight of many gyroplanes.
Preferably, install the undercarriage on the outside bottom surface of fuselage, play the effect of supporting many gyroplanes to ensure many gyroplanes and stabilize the landing.
Can know via foretell technical scheme, compare with prior art, the utility model provides a technical scheme of five many gyroplanes of dish, for current many gyroplanes, all rotors of this many gyroplanes of dish are all wrapped up in the casing, thereby can not harm the human body with human contact. Additionally, the utility model discloses a dish-shaped outward appearance not only can reduce the fluid resistance when many gyroplanes fly, makes many gyroplanes can compromise the flight effect of various speeds, and dish-shaped outward appearance personality, cool in addition easily attract consumer's eye, can be used to amusement, take a picture, also can be used as many-sided such as film stage property, can also replace current gyroplane to be used for various usage such as commodity circulation, tour.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required to be used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to the provided drawings without creative efforts.
Fig. 1 is a front view of an embodiment of the present invention.
Fig. 2 is a side view of an embodiment of the present invention.
Fig. 3 is a bottom view of an embodiment of the present invention.
Fig. 4 is a top view of an embodiment of the present invention.
FIG. 5 is a schematic view of the electric counter-rotating ducted fan according to the present invention;
FIG. 6 is a schematic view of the electric driving mechanism of the electric contra-rotating ducted fan according to the present invention;
FIG. 7 is a schematic top view of a stator frame structure of an electric counter-rotating ducted fan according to the present invention;
FIG. 8 is a schematic side view of the stator support structure of the electric counter-rotating ducted fan of the present invention
FIG. 9 is a schematic view of a driving ring structure of the electric counter-rotating ducted fan of the present invention
Wherein, in the figure,
1-a fuselage; 2-machine shell, 21-upper cover, 22-lower cover; 3-electric contra-rotating ducted fan; 4-control rotor; 5-a flow guide cover; 6-undercarriage.
101-grade separation coaxial support, 102-linkage gear, 103-synchronous gear, 104-bearing, 105-turntable, 201-stator winding, 202-permanent magnet, 203-stator support, 204-driving ring, 301-front fan blade and 302-rear fan blade.
Detailed Description
The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative work belong to the protection scope of the present invention.
In the description of the present invention, it should be noted that the terms "center of gravity", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, and are only for convenience of description and simplification of description, but do not indicate or imply that the device or element 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 "third" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.
In the description of the present invention, it is to be noted that, unless otherwise explicitly specified or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, and may be, for example, fixedly connected, detachably connected, or integrally connected; 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 in specific cases to those skilled in the art.
Example (b):
a five-axis multi-rotor disk-shaped aircraft according to an embodiment of the present invention is described in detail below with reference to fig. 1-4.
As shown in fig. 1-4, the embodiment of the utility model discloses many gyroplanes of dish five, specifically include: the aircraft comprises an airframe 1, a casing 2, a main rotor system, an auxiliary rotor system and a control system,
the housing 2 is covered and fixed to the outside of the body 1, and includes an upper cover 21 having a narrow shape and an open top, and a lower cover 22 having a wide shape and an open bottom.
The main rotor system is arranged at the center above the fuselage 1 and is wrapped by the upper cover 21 of the casing, and comprises an electric contra-rotating ducted fan 3 which can make the upper and lower fans contra-rotate oppositely at a constant speed; the electric counter-rotating ducted fan 3 is used to provide the main flight power for the multi-rotor aircraft.
Vice rotor system is located main rotor system's below and by including casing lower shroud 22 parcel, vice rotor system includes four control rotors 4, four control rotors 4 use the focus of fuselage 1 as the center equipartition at fuselage 1 apart from its focus have four angles of certain distance to four control rotors 4 outsides all cover and are equipped with a kuppe 5, this kuppe 5 can let the air current of entering more stable, make the thrust that control rotor 4 produced more stable. The four control rotors 4 provide attitude control for the multi-rotor aircraft.
The distances from the four control rotors 4 to the center of gravity of the airframe 1 need to be determined comprehensively by combining factors such as the weight and the size of the multi-rotor aircraft, so that the four control rotors 4 generate enough lever effect to control the flight attitude of the multi-rotor aircraft.
The control system is positioned below the main rotor system and at the center of the lower cover 22 and is fixed with the fuselage 1, and the control system is used for realizing the control of the main rotor system and the auxiliary rotor system.
Electronic contra-rotating duct fan 3 can produce the air current certainly, and whole gyroplane equipment has all been wrapped up now, must leave a passageway for the air current so, has put gyroplane equipment focus position because of control system, so this application has just put the wind channel in the periphery, puts simultaneously in the periphery position and can also let the wind channel sectional area crescent. The utility model discloses 4 outsides at individual control rotor all cover and are equipped with a kuppe 5, will control rotor 4 and put in kuppe 5, the air current is more stable like this, and the air current gets into from both sides, and downstream under the rotor effect, the rotor can obtain reaction force like this to play auxiliary motor's effect, reach the purpose of energy saving.
In order to further optimize the technical scheme of the embodiment, the distances between the centers of gravity of the four control rotors 4 and the airframe 1 are equal, so that the center of gravity of the multi-rotor aircraft is ensured to be stable, and the control rotors 4 can more accurately and effectively adjust the postures of the multi-rotor aircraft.
In order to further optimize the technical scheme of the embodiment, the electric rotary ducted fan 3 is controlled by a high-power motor, and the control rotor 4 is controlled by a low-power motor. The propeller adopted in the electric contra-rotating ducted fan 3 is a long propeller, and the propeller adopted in the control rotor 4 is a short propeller.
The high-power motor and the electric contra-rotating ducted fan 3 with a longer propeller work cooperatively to generate enough power. The small-power motor and the control rotor 4 with the shorter propeller work cooperatively, and the attitude of the multi-rotor aircraft can be adjusted sufficiently, so that the aim of controlling the flight direction is fulfilled.
In order to further optimize the technical solution of the above embodiment, the motor used for controlling the rotor 4 is a coreless motor.
The coreless motor has the following advantages: maximum energy conversion efficiency; the activation and the braking are rapid, and the response is extremely rapid; reliable operation stability; the electromagnetic interference is less; the energy density is large. The control of the flight attitude of the multi-rotor aircraft can be quickly realized by taking the hollow cup motor as the motor for controlling the rotor 4, and the stability and the safety of taking off, landing and hovering of the multi-rotor aircraft are ensured.
In order to further optimize the technical solution of the above embodiment, the upper cover 21 is cylindrical in shape. The lower cover 22 is disc-shaped in shape. An undercarriage 6 is mounted on the outer bottom surface of the fuselage 1.
Specifically, the electric contra-rotating ducted fan 3 used by the utility model comprises a synchronizing mechanism, a driving mechanism and blades, wherein the synchronizing mechanism comprises a flyover coaxial bracket, two linkage gears, at least one (generally two) synchronizing gear and a front turntable and a rear turntable; the linkage gear and the synchronous gear are respectively fixed on vertically crossed shafts of the overpass coaxial bracket through bearings, and are tightly meshed to form a transmission structure; the front turntable and the rear turntable are respectively connected with the two linkage gears into a whole through fasteners.
The front and rear parts of the front and rear turntables in the above-mentioned embodiments are defined according to the air flow direction when the electric counter-rotating ducted fan operates.
The electric contra-rotating ducted fan 3 enables the front and rear (upper and lower) fans to be contra-rotated in a constant speed and opposite directions through the synchronizing mechanism, achieves the purpose of simultaneously driving the front and rear fans by one set of stator winding, and has the advantages of light weight and high efficiency. Compared with a single-stage electric fan, the electric contra-rotating ducted fan 3 can obtain higher thrust at the same rotating speed or achieve the same thrust at a lower rotating speed, so that the efficiency is higher; compared with the counter-rotating fan realized in a pure mechanical mode, the electric counter-rotating ducted fan is simple in structure and easy to realize and control. For a more detailed description of the structure and operation thereof, reference is made to the following description and accompanying drawings of FIGS. 5-9.
An electric contra-rotating ducted fan comprises a synchronizing mechanism, a driving mechanism and blades.
The figure shows an electrically-driven counter-rotating ducted fan with 36 slots and 42 poles.
The synchronous mechanism comprises a flyover coaxial bracket, two linkage gears, at least one (generally two) synchronous gear and a front rotary table and a rear rotary table; the linkage gear and the synchronous gear are respectively fixed on vertically crossed shafts of the overpass coaxial bracket through bearings; the linkage gear and the synchronous gear are tightly meshed to form a transmission structure; the front turntable and the rear turntable are respectively connected with the two linkage gears into a whole through fasteners.
The gears used in the synchronous mechanism are all conical gears.
The synchronous mechanism has the function of limiting the rotating speed of the front turntable and the rear turntable, so that the front turntable and the rear turntable can only rotate in opposite directions at the same speed, and the purpose of driving the front fan and the rear fan by one set of stator winding is achieved.
The driving mechanism comprises a stator winding, a front driving ring, a rear driving ring and a stator support, wherein permanent magnets are arranged at the positions of the driving rings corresponding to the stator winding.
The driving mechanism shown in the attached drawings is provided with a 36-slot stator winding, each slot is provided with an independent magnetic core and a coil wound on the magnetic core, and the independent magnetic core and the coil are respectively fixed on 36 slot positions of a stator bracket; permanent magnets are arranged on the driving ring at positions corresponding to the stator windings, and in the embodiment, the number of the permanent magnets is 42; the 36-slot electronic winding and 42 magnetic poles in the upper and lower driving rings jointly form a driving mechanism, so that the purpose of converting electric energy into mechanical energy is achieved, and the driving mechanism is a power source of the ducted fan.
The stator windings are arranged in a ring shape, and the central radius of the stator windings is the same as that of the permanent magnets arranged in the upper driving ring and the lower driving ring;
and two magnetic poles of the stator winding are respectively opposite to the permanent magnets in the front driving ring and the rear driving ring.
The permanent magnets mounted on the front and rear driving rings in the driving mechanism are identical in number and position and are in mirror symmetry.
The stator support is provided with three Hall sensors which can be distributed at 120 degrees or 60 degrees, and the output of the Hall sensors is connected to a rotating speed controller. In some occasions with low requirements on stability, a Hall sensor can be omitted, and a corresponding Hall-free rotating speed controller is adopted to control the rotation of the motor.
The fan blades are arranged between the rotary disc and the driving ring, and the rotating directions of the front fan blades and the rear fan blades are opposite;
the fan blades are tightly connected with the rotary disc and the driving ring into a whole by fasteners.
The overpass coaxial bracket and the stator bracket are tightly connected into a whole through a fastener.
The utility model provides an electronic contra-rotating ducted fan needs to cooperate corresponding BLDC controller to use.
The utility model discloses use electronic contra-rotating ducted fan 3 as the core, by its main power that produces, configured four very little rotors of power simultaneously as control rotor 4 to the control mode similar to many gyroplanes adjusts the gesture of fuselage 1, in order to reach the purpose of control flight direction. Electronic contrarotating ducted fan 3 and control rotor 4 are all by including casing 2 parcel for all rotor all can not with human direct contact, have improved the security of product.
The utility model discloses a dish outward appearance not only can reduce the fluid resistance when many gyroplanes fly, makes many gyroplanes can compromise the flight effect of various speeds, and dish outward appearance personality, cool moreover, change the eye that attracts the consumer, can be used to amusement, take a picture, also can be as many-sided such as film stage property, can also replace current gyroplane to be used for the commodity circulation, various usage such as tour, and the practicality is strong, is fit for wideling popularize and apply.
The embodiments in the present description are described in a progressive manner, each embodiment focuses on differences from other embodiments, and the same and similar parts among the embodiments are referred to each other. The device disclosed by the embodiment corresponds to the method disclosed by the embodiment, so that the description is simple, and the relevant points can be referred to the method part for description.
The previous description of the disclosed embodiments is provided to enable any person skilled in the art to make or use the present invention. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the generic principles defined herein may be applied to other embodiments without departing from the spirit or scope of the invention. Thus, the present invention is not intended to be limited to the embodiments shown herein but is to be accorded the widest scope consistent with the principles and novel features disclosed herein.
Claims (8)
1. A five-axis multi-gyroplane that is dish-shaped, comprising:
a fuselage (1);
the machine shell (2) is covered and fixed on the outer part of the machine body (1) and comprises an upper cover (21) with a narrow appearance and an opening at the top and a lower cover (22) with a wide appearance and an opening at the bottom;
the main rotor system is arranged in the center above the fuselage (1) and is wrapped by an upper cover (21) of the casing, and the main rotor system comprises an electric contra-rotating ducted fan (3) which can make the upper and lower fans contra-rotate oppositely at a constant speed; the electric contra-rotating ducted fan (3) is used for providing main flight power for the multi-rotor aircraft;
the auxiliary rotor system is positioned below the main rotor system and is wrapped by a lower cover (22) of the machine shell, the auxiliary rotor system comprises four control rotors (4), the four control rotors (4) are uniformly distributed on four corners of the machine body (1) which are away from the center of gravity of the machine body (1) by a certain distance by taking the center of gravity of the machine body (1) as the center, and a diversion cover (5) is covered outside each of the four control rotors (4); the four control rotors (4) provide attitude control for the multi-rotor aircraft;
a control system located at a central position of the lower cowl (22) below the main rotor system and fixed to the fuselage (1), the control system being configured to enable control of the main rotor system and the auxiliary rotor system.
2. The five-axis multi-rotor disk-shaped aircraft according to claim 1, characterized in that the distances between the four control rotors (4) and the center of gravity of the fuselage (1) are all equal.
3. The five-axis multi-rotor wing dish according to claim 1, characterized in that the electrically operated counter-rotating ducted fan (3) is controlled with a high power motor and the control rotor (4) is controlled with a low power motor.
4. The five-axis multi-rotor disk-shaped aircraft according to claim 3, characterized in that the motor used for the control rotor (4) is a coreless motor.
5. The five-axis multi-rotor wing dish according to claim 1, characterized in that the propellers used in the electrically counter-rotating ducted fan (3) are long propellers and the propellers used in the control rotor (4) are short propellers.
6. The dish-shaped five-axis multi-rotor aircraft according to claim 1, wherein the upper cowl (21) is cylindrical in shape.
7. The dish-shaped five-axis multi-rotor aircraft according to claim 1 or 6, wherein the lower cowl (22) is dish-shaped in shape.
8. The dish-shaped five-axis multi-rotor aircraft according to claim 1, characterized in that an undercarriage (6) is mounted on the bottom outside surface of the fuselage (1).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921262999.1U CN210416960U (en) | 2019-08-06 | 2019-08-06 | Dish-shaped five-shaft multi-rotor aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921262999.1U CN210416960U (en) | 2019-08-06 | 2019-08-06 | Dish-shaped five-shaft multi-rotor aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN210416960U true CN210416960U (en) | 2020-04-28 |
Family
ID=70386241
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201921262999.1U Expired - Fee Related CN210416960U (en) | 2019-08-06 | 2019-08-06 | Dish-shaped five-shaft multi-rotor aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN210416960U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112631321A (en) * | 2020-10-12 | 2021-04-09 | 北京理工大学 | Multi-shaft rotor unmanned aerial vehicle and flight control method thereof |
-
2019
- 2019-08-06 CN CN201921262999.1U patent/CN210416960U/en not_active Expired - Fee Related
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112631321A (en) * | 2020-10-12 | 2021-04-09 | 北京理工大学 | Multi-shaft rotor unmanned aerial vehicle and flight control method thereof |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US9174728B2 (en) | Electrical powered tail rotor of a helicopter | |
| KR101947335B1 (en) | Coaxial double propeller double-motor aircraft | |
| US8752787B2 (en) | Electrical driven flying saucer based on magnetic suspension | |
| CN107458598A (en) | The reaction torque of the matrix for the motor module fixed using blade pitch is controlled | |
| WO2005072233A3 (en) | Quiet vertical takeoff and landing aircraft using ducted, magnetic induction air-impeller rotors | |
| CN210416960U (en) | Dish-shaped five-shaft multi-rotor aircraft | |
| WO2020261102A1 (en) | Aircraft, in particular a drone or an aircraft for personal air mobility, with high efficiency propeller rotors | |
| CN108116672A (en) | A kind of DCB Specimen Electrostatic Absorption unmanned plane | |
| CA2794077C (en) | Electrical powered tail rotor of a helicopter | |
| CN112339992A (en) | Dish-shaped five-shaft multi-rotor aircraft | |
| CN105846600B (en) | A kind of motor and the aeromodelling aerocraft with the motor | |
| CN106741910A (en) | A kind of disc-shaped unmanned machine | |
| CN212149286U (en) | Unmanned aerial vehicle, propeller driving unit and motor unit thereof | |
| CN103213667A (en) | Flapping-wing aircraft | |
| CN206218208U (en) | Flying power system and aircraft | |
| CN210416974U (en) | Electric coaxial multi-rotor helicopter based on contra-rotating dual-rotor motor | |
| CN112340000A (en) | Electric coaxial multi-rotor helicopter based on contra-rotating dual-rotor motor | |
| CN203469472U (en) | Multi-shaft air vehicle with rotating vane protecting cover | |
| CN210289957U (en) | Electric contra-rotating ducted fan | |
| CN205418104U (en) | Disk -type aircraft | |
| CN110683041A (en) | Disc-shaped aircraft | |
| CN105947199B (en) | Autoroatation self-flinging antigravity butterfly-shaped aircraft | |
| CN220213904U (en) | Model airplane with fast switching propeller power and duct power | |
| CN203864995U (en) | Double-loop rotor wing used for helicopter | |
| CN110901907A (en) | Novel multi-rotor unmanned aerial vehicle, control method and unmanned aerial vehicle suite |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20200428 Termination date: 20210806 |