CN110077592A - A kind of aircraft - Google Patents
A kind of aircraft Download PDFInfo
- Publication number
- CN110077592A CN110077592A CN201910351809.1A CN201910351809A CN110077592A CN 110077592 A CN110077592 A CN 110077592A CN 201910351809 A CN201910351809 A CN 201910351809A CN 110077592 A CN110077592 A CN 110077592A
- Authority
- CN
- China
- Prior art keywords
- frame body
- driver
- fan
- aircraft
- booster
- 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.)
- Granted
Links
- 230000001012 protector Effects 0.000 claims abstract description 14
- 238000004804 winding Methods 0.000 claims description 11
- 241000883990 Flabellum Species 0.000 claims description 4
- 238000009434 installation Methods 0.000 claims description 2
- 230000006378 damage Effects 0.000 abstract description 6
- 208000027418 Wounds and injury Diseases 0.000 abstract description 3
- 208000014674 injury Diseases 0.000 abstract description 3
- 230000000694 effects Effects 0.000 description 10
- 239000012530 fluid Substances 0.000 description 2
- 239000006260 foam Substances 0.000 description 2
- 239000000203 mixture Substances 0.000 description 2
- 230000001681 protective effect Effects 0.000 description 2
- 239000007787 solid Substances 0.000 description 2
- 240000005561 Musa balbisiana Species 0.000 description 1
- 235000018290 Musa x paradisiaca Nutrition 0.000 description 1
- 238000004026 adhesive bonding Methods 0.000 description 1
- 230000002860 competitive effect Effects 0.000 description 1
- 238000005265 energy consumption Methods 0.000 description 1
- 230000006698 induction Effects 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 230000003068 static effect Effects 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
- B64C1/061—Frames
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C39/00—Aircraft not otherwise provided for
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C39/00—Aircraft not otherwise provided for
- B64C39/02—Aircraft not otherwise provided for characterised by special use
- B64C39/024—Aircraft not otherwise provided for characterised by special use of the remote controlled vehicle type, i.e. RPV
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D45/00—Aircraft indicators or protectors not otherwise provided for
- B64D45/04—Landing aids; Safety measures to prevent collision with earth's surface
- B64D45/06—Landing aids; Safety measures to prevent collision with earth's surface mechanical
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U50/00—Propulsion; Power supply
- B64U50/10—Propulsion
- B64U50/19—Propulsion using electrically powered motors
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- Toys (AREA)
Abstract
The application belongs to special-shaped field of flight vehicle design, in particular to a kind of aircraft, including fan-shaped booster, horizontal driver, vertical driver, end protector, frame body and power device, the frame body is a polygon-prism body frame, fan-shaped booster is installed on frame body upper beam, vertical driver is installed on frame body vertical beam, horizontal driver is installed on frame body lower beam, fan-shaped booster, horizontal driver and vertical driver are driven by power device, and the correspondence beam axis rotation on frame body, end protector is installed on the corner of frame body.The flying instrument of the application moves ahead whether there is or not runway landing, by Cross Wind Force, simultaneously can when falling self-protection, the characteristics of not causing serious injury to it when bumping against people or object, structure is simple, safe and reliable, has boundless application prospect in art sports of transporting, take photo by plane and race.
Description
Technical field
The application belongs to special-shaped field of flight vehicle design, in particular to a kind of aircraft.
Background technique
Conventional aircraft generally comprises Fixed Wing AirVehicle, rotor craft, fixed wing aircraft generally by thrust device,
Lifting body and control surface composition, structure arrangement routinize, provide horizontal thrust by thrust device, be made of body and aerofoil
Lifting body provides lift, and the adjustment of flight attitude is realized by the manipulation to control surface, and take-off and landing needs runway environment；Rotation
Wing aircraft is common in helicopter and multi-rotor unmanned aerial vehicle, and the ability with VTOL passes through the control to blade direction
Or flight attitude adjustment is carried out to the control of single propeller, but when encountering the influence of natural wind, can only often fight wind-force
Flight, economy is poor, simultaneously because can cause to people around or object after flight is out of control the characteristics of itself Components Shape
Fatal harm can also cause the injury of ontology when falling.
In recent years the whole world occur consumer level unmanned plane heat, since it does not need special airport, can VTOL, be easy to grasp
The features such as making is largely used to short-distance transport, is taken photo by plane in competitive sport, but its pendant out of control hits safety problem and greatly limits
Its application range is made.Meanwhile in terms of having the long-distance transportation under wind environment, energy consumption problem is also highlighted.
Summary of the invention
At least one in order to solve the above-mentioned technical problem, this application provides a kind of aircraft.
This application discloses a kind of aircraft, including fan-shaped booster, horizontal driver, vertical driver, end protection
Device, frame body and power device, the frame body are a polygon-prism body frame, and fan-shaped booster is installed on frame body upper lateral
Beam, vertical driver are installed on frame body vertical beam, and horizontal driver is installed on frame body lower beam, fan-shaped booster, horizontal drive
Dynamic device and vertical driver are driven by power device, and the correspondence beam axis rotation on frame body, end protector is installed on frame body
Corner.
According at least one embodiment of the application, the sector booster is a rotation body structure, outer surface one
Week is laid with flabellum.
According at least one embodiment of the application, the sector booster outer rim is provided with the protection in semi-circumference section
Shell, the protecting crust can be rotated around corresponding frame body upper beam.
According at least one embodiment of the application, the protecting crust by motor drive, the stator of motor around
Group is fixed on upper beam, and rotor windings are in conjunction with the inner surface of the protecting crust.
According at least one embodiment of the application, the horizontal driver and vertical driver are cylindrical tube knot
Structure.
According at least one embodiment of the application, the end protector is flexible chondritic.
According at least one embodiment of the application, the power device is motor, and stator winding is fixed on frame
On the beam of body, rotor windings and horizontal driver, vertical driver, fan-shaped driver inner surface in conjunction with.
According at least one embodiment of the application, the aircraft further include wireless transceiver, controller and solely
Vertical power supply, the wireless transceiver receive control signal, and the controller is used to control the power device according to control signal,
The independent current source is used for as the wireless transceiver, controller and power device power supply.
According at least one embodiment of the application, the vacant area in the centre of the frame body is provided with objective table, the nothing
Line transceiver, controller and independent current source are arranged on the objective table.
According at least one embodiment of the application, the frame body is polygon prismoid frame.
At least there are following advantageous effects in the application:
The aircraft of the application is realized vertical, oblique function of taking off by the way that fan-shaped booster is arranged, is not needed by race
Road does not need the special environment that takes off；By the way that horizontal driver is arranged, additional lift is obtained using Magnus effect, by setting
Vertical driver is set, additional horizontal thrust is obtained using Magnus effect；By the way that protective cover is arranged in fan-shaped booster
It is damaged when preventing from falling and injures other people；It is damaged when preventing from falling by the way that end protector is arranged and injures him
People；For ontology without high-speed rotary body sharp, outstanding, frame body is solid reliable, can reduce causality loss to the maximum extent；The present invention
Structure is simple, safe and reliable, has boundless application prospect in art sports of transporting, take photo by plane and race.
Detailed description of the invention
Fig. 1 is the mechanism principle figure of the application aircraft；
Fig. 2 is the structure principle chart of the fan-shaped booster of the application aircraft；
Fig. 3 is that the frame body of the application aircraft is the structure chart of four-prism frame；
Fig. 4 is that the frame body of the application aircraft is the structure chart of Three-frustum-shaped frame；
Wherein:
1- sector booster；The vertical driver of 2-；3- horizontal driver；The end 4- protector；5- frame body；11- protecting crust；
51- upper beam；52- vertical beam；53- lower beam；The corner 54-.
Specific embodiment
To keep the purposes, technical schemes and advantages of the application implementation clearer, below in conjunction in the embodiment of the present application
Attached drawing, technical solutions in the embodiments of the present application is further described in more detail.In the accompanying drawings, identical from beginning to end or class
As label indicate same or similar element or element with the same or similar functions.Described embodiment is the application
A part of the embodiment, instead of all the embodiments.The embodiments described below with reference to the accompanying drawings are exemplary, it is intended to use
In explanation the application, and it should not be understood as the limitation to the application.Based on the embodiment in the application, ordinary skill people
Member's every other embodiment obtained without creative efforts, shall fall in the protection scope of this application.Under
Face is described in detail embodiments herein in conjunction with attached drawing.
In the description of the present application, it is to be understood that term " center ", " longitudinal direction ", " transverse direction ", "front", "rear",
The orientation or positional relationship of the instructions such as "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outside" is based on attached drawing institute
The orientation or positional relationship shown is merely for convenience of description the application and simplifies description, rather than the dress of indication or suggestion meaning
It sets or element must have a particular orientation, be constructed and operated in a specific orientation, therefore should not be understood as protecting the application
The limitation of range.
Firstly the need of explanation, Magnus effect is that hydrodynamics one of works as universal phenomenon, an object and exists
It is rotated in fluid, will receive a special fluid force, the explanation of science are as follows: when the angular velocity of rotation arrow of a rotating object
When amount is not overlapped with the flight velocity vector of object, mutually hang down in the plane with rotational angular velocity vector and translation velocity vector composition
A cross force will be generated on straight direction.Such as the table tennis track of rotation can drift about, the banana on football pitch
Ball effect etc..Referring to Magnus effect principle, the application provides a kind of aircraft, can without runway landing, by lateral wind
Power move ahead, while can when falling self-protection, do not cause serious injury to it when bumping against people or object.
The aircraft of the application is further described in 1- Fig. 4 with reference to the accompanying drawing.
Embodiment one:
The present embodiment is the implementation that the application aircraft is used for shipping using square prism frame body, including fan-shaped lift-rising
Device 1, horizontal driver 3, vertical driver 2, end protector 4, frame body 5 and power device, frame body 5 are a four-prism
Frame, fan-shaped booster 1 are installed on 5 upper beam 51 of frame body, and vertical driver 2 is installed on frame body vertical beam 52, horizontal drive
Device 3 is installed on frame body lower beam 53, and fan-shaped booster 1, horizontal driver 3 and vertical driver 2 are driven by power device,
Correspondence beam axis rotation on frame body 5, end protector 4 are installed on the corner 54 of frame body.
Further, fan-shaped booster 1 is a rotation body structure, and outer surface is laid with flabellum in one week, can fly
The static windless condition of device provides very much lift and lateral thrust.
Further, fan-shaped 1 outer rim of booster is provided with the protecting crust 11 in semi-circumference section, and protecting crust can be around corresponding
5 upper beam 51 of frame body rotation, for adjusting the direction windward of aircraft and the flabellum of fan-shaped booster 1 being protected not hit by foreign matter
Hit damage.
Specifically, protecting crust 11 can be rotatably installed in upper beam 51 by bearing, and pass through motor drive；Its
In, the stator winding of motor is fixed on upper beam 51, and rotor windings are in conjunction with the inner surface of protecting crust 11.
Further, horizontal driver 3 and vertical driver 2 are cylindrical tube structure, specially a hollow hard bubble
Foam stick.
Further, end protector 4 is chondritic, has elastic buffer characteristic, specially a rigid foam ball.
Further, the power device of fan-shaped booster 1, horizontal driver 3 and vertical driver 2 is motor, is determined
Sub- winding is fixed on the correspondence beam of frame body 5 (the corresponding upper beam 51 of fan-shaped booster 1, the corresponding lower beam of horizontal driver 3
53, the corresponding vertical beam 52 of vertical driver 2), rotor windings and horizontal driver 3, vertical driver 2, sector driver 1 it is interior
Surface is combined by gluing.It should be noted that fan-shaped booster 1, horizontal driver 3 and vertical driver 2 can pass through axis
On the correspondence beam for holding the frame body 5 of rotational installation.
By above structure, so that vertical driver 2 can be obtained under the driving of motor by Magnus effect
The driving force of horizontal direction, while several groups of vertical drivers 2 match the direction windward for realizing aircraft by revolving speed and the side that moves ahead
To；Horizontal driver 3 can obtain the driving of lift and horizontal direction under the driving of motor by Magnus effect
Power, several groups of horizontal drivers 3 match the height control for realizing aircraft and lateral pitch angle control by revolving speed, in conjunction with fan-shaped lift-rising
The revolving speed of device 1 matches, and the height for capableing of higher precision realization aircraft controls and lateral pitch angle control.
Further, aircraft further includes wireless transceiver, controller and independent current source；There can be gyro in controller
Instrument, accelerometer, earth induction, baroceptor, ultrasonic sensor, light stream sensor, GPS module and control circuit etc.
Component adjusts the power device output power of aircraft by controller, realizes the gesture stability to aircraft.Specifically, nothing
Line transceiver receives control signal, and controller is used to control power device according to control signal, and independent current source is used to receive to be wireless
Send out device, controller and power device power supply.
It should be noted that position suitable on board the aircraft can be set in wireless transceiver, controller and independent current source
It sets, such as can be set inside protector 4, corresponding booster or internal drive etc.；In the present embodiment, preferably exist
The vacant area in the centre of frame body 5 is provided with objective table, and above-mentioned wireless transceiver, controller and independent current source, which can be set, to be carried
Corresponding position on object platform；In addition, cargo box can also be fixed by cutting on object platform, to place other cargos.
Embodiment two:
The present embodiment is that the application aircraft using Three-frustum-shaped frame body is used for the implementation taken photo by plane, in fact part with
Embodiment is identical；Frame body 5 is Three-frustum-shaped frame, and the vacant area in the centre of frame body 5 is provided with objective table, and objective table lower surface can be with
It is hung with Three Degree Of Freedom holder for aerial photographing camera.
In conclusion the aircraft of the application, realizes vertical, oblique function of taking off by the way that fan-shaped booster is arranged, is not required to
The special environment that takes off is not needed by runway；By the way that horizontal driver is arranged, additional rise is obtained using Magnus effect
Power obtains additional horizontal thrust using Magnus effect by the way that vertical driver is arranged；By being set in fan-shaped booster
It sets protective cover and is damaged when preventing from falling and injures other people；By be arranged end protector prevent from falling when be damaged with
And injure other people；For ontology without high-speed rotary body sharp, outstanding, frame body is solid reliable, can reduce accident damage to the maximum extent
It loses；It is the configuration of the present invention is simple, safe and reliable, in art sports of transporting, take photo by plane and race with boundless application before
Scape.
The above, the only specific embodiment of the application, but the protection scope of the application is not limited thereto, it is any
Within the technical scope of the present application, any changes or substitutions that can be easily thought of by those familiar with the art, all answers
Cover within the scope of protection of this application.Therefore, the protection scope of the application should be with the scope of protection of the claims
It is quasi-.
Claims (10)
1. a kind of aircraft, it is characterised in that: including fan-shaped booster (1), horizontal driver (3), vertical driver (2), end
Portion's protector (4), frame body (5) and power device, the frame body (5) are a polygon-prism body frame, fan-shaped booster (1)
It is installed on frame body (5) upper beam (51), vertical driver (2) is installed on frame body vertical beam (52), horizontal driver (3) installation
In frame body lower beam (53), fan-shaped booster (1), horizontal driver (3) and vertical driver (2) are driven by power device
Dynamic, the correspondence beam axis rotation on frame body (5), end protector (4) is installed on the corner (54) of frame body.
2. aircraft according to claim 1, which is characterized in that the sector booster (1) is a rotation body structure,
Outer surface is laid with flabellum in one week.
3. aircraft according to claim 2, which is characterized in that described sector booster (1) outer rim is provided with semi-circumference
The protecting crust (11) in section, the protecting crust (11) can rotate around corresponding frame body (5) upper beam (51).
4. aircraft according to claim 3, which is characterized in that the protecting crust (11) is electronic by motor drive
The stator winding of machine is fixed on upper beam (51), and rotor windings are in conjunction with the inner surface of the protecting crust (11).
5. aircraft according to claim 1, which is characterized in that the horizontal driver (3) and vertical driver (2) are
Cylindrical tube structure.
6. aircraft according to claim 1, which is characterized in that the end protector (4) is flexible spherical
Structure.
7. aircraft according to claim 1-6, which is characterized in that the power device is motor, is determined
Sub- winding is fixed on the beam of frame body (5), rotor windings and horizontal driver (3), vertical driver (2), fan-shaped driver (1)
Inner surface combine.
8. aircraft according to claim 7, which is characterized in that the aircraft further includes wireless transceiver, controller
And independent current source, the wireless transceiver receive control signal, the controller is used for described dynamic according to control signal control
Power device, the independent current source are used for as the wireless transceiver, controller and power device power supply.
9. aircraft according to claim 8, which is characterized in that the vacant area in centre of the frame body (5) is provided with loading
Platform, the wireless transceiver, controller and independent current source are arranged on the objective table.
10. aircraft according to claim 1, which is characterized in that the frame body (5) is polygon prismoid frame.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910351809.1A CN110077592B (en) | 2019-04-28 | 2019-04-28 | Aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910351809.1A CN110077592B (en) | 2019-04-28 | 2019-04-28 | Aircraft |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN110077592A true CN110077592A (en) | 2019-08-02 |
| CN110077592B CN110077592B (en) | 2022-04-01 |
Family
ID=67417451
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910351809.1A Active CN110077592B (en) | 2019-04-28 | 2019-04-28 | Aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN110077592B (en) |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101898635A (en) * | 2010-07-26 | 2010-12-01 | 哈尔滨工业大学 | Duct single screw aircraft based on Magnus effect |
| CN202071984U (en) * | 2011-05-02 | 2011-12-14 | 刘自拔 | Movable wing airplane with wind wheels at leading edges |
| CN102616376A (en) * | 2010-12-22 | 2012-08-01 | 伊德斯德国股份有限公司 | Hybrid rotor |
| CN102951289A (en) * | 2011-08-29 | 2013-03-06 | 顾一明 | Low speed safety aircraft capable of controlling flight attitude by utilizing aerodynamic force |
| CN103434637A (en) * | 2013-08-25 | 2013-12-11 | 西北工业大学 | Novel aerofoil by utilizing magnus effect |
| CN103863562A (en) * | 2014-03-29 | 2014-06-18 | 郑全逸 | Vertical-lifting device with combined propellers |
| CN108860599A (en) * | 2018-06-19 | 2018-11-23 | 温和 | A kind of roller fan wing |
-
2019
- 2019-04-28 CN CN201910351809.1A patent/CN110077592B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101898635A (en) * | 2010-07-26 | 2010-12-01 | 哈尔滨工业大学 | Duct single screw aircraft based on Magnus effect |
| CN102616376A (en) * | 2010-12-22 | 2012-08-01 | 伊德斯德国股份有限公司 | Hybrid rotor |
| CN202071984U (en) * | 2011-05-02 | 2011-12-14 | 刘自拔 | Movable wing airplane with wind wheels at leading edges |
| CN102951289A (en) * | 2011-08-29 | 2013-03-06 | 顾一明 | Low speed safety aircraft capable of controlling flight attitude by utilizing aerodynamic force |
| CN103434637A (en) * | 2013-08-25 | 2013-12-11 | 西北工业大学 | Novel aerofoil by utilizing magnus effect |
| CN103863562A (en) * | 2014-03-29 | 2014-06-18 | 郑全逸 | Vertical-lifting device with combined propellers |
| CN108860599A (en) * | 2018-06-19 | 2018-11-23 | 温和 | A kind of roller fan wing |
Also Published As
| Publication number | Publication date |
|---|---|
| CN110077592B (en) | 2022-04-01 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN105473443B (en) | Using the VTOL aircraft of the multipurpose of new air force and technical solution and safety | |
| JP6547117B2 (en) | Vertical take-off and landing aircraft | |
| US10773802B2 (en) | Tilt-rotor vertical takeoff and landing aircraft | |
| ES2746980T3 (en) | Unmanned aerial vehicle | |
| US9108728B2 (en) | Modular flying vehicle | |
| KR101682670B1 (en) | Convertible Wing Type Hybrid UAV | |
| JP2019206333A (en) | Flying body and method for controlling flying body | |
| US20120119016A1 (en) | Modular Flight Vehicle With Wings | |
| US20160304193A1 (en) | Multi-rotor personal air vehicle with a central lifting fan | |
| US20170253325A1 (en) | Unmanned aerial vehicle (uav) and a method of improving the performance thereof | |
| CN105752320A (en) | Duct type unmanned aerial vehicle and control method thereof | |
| US20210016877A1 (en) | A structure construction for an aircraft and aircraft comprising the structure construction | |
| WO2014195660A1 (en) | Flying platform | |
| CN111098649A (en) | Aerocar control system and method and aerocar | |
| WO2018004325A1 (en) | Octocopter | |
| GB2423971A (en) | Autogyro hovercraft | |
| CN110077592A (en) | A kind of aircraft | |
| JP6721191B2 (en) | Rotorcraft | |
| GB2483785A (en) | Small unmanned aerial vehicle | |
| CN202753709U (en) | Upright vertical take-off and landing aircraft | |
| US20210331797A1 (en) | Flying saucer aircraft | |
| CN109987221B (en) | Unmanned aerial vehicle | |
| CN106927033A (en) | A kind of vertical coaxial dual-rotor helicopter | |
| CN102756806A (en) | Upright-standing vertical take-off and landing airplane | |
| CN206900650U (en) | A kind of vertical coaxial dual-rotor helicopter |
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 |