CN103693195A - Miniature aircraft - Google Patents
Miniature aircraft Download PDFInfo
- Publication number
- CN103693195A CN103693195A CN201310691367.8A CN201310691367A CN103693195A CN 103693195 A CN103693195 A CN 103693195A CN 201310691367 A CN201310691367 A CN 201310691367A CN 103693195 A CN103693195 A CN 103693195A
- Authority
- CN
- China
- Prior art keywords
- motor
- frame
- wing
- steering wheel
- gear
- 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
Images
Landscapes
- Toys (AREA)
Abstract
The invention discloses a miniature aircraft. The miniature aircraft comprises a steering engine, a wing, an airframe, a propeller and a motor, wherein the airframe consists of a linear airframe and an arc-shaped airframe; the steering engine is arranged on the linear airframe; the wing is connected with the steering engine; the motor is arranged at one end, far away from the steering engine, of the arc-shaped airframe; the propeller is arranged on the motor; the propeller and the wing are positioned on two sides of the airframe. The miniature aircraft can vertically take off and land, is simple in structure, high in aerodynamic efficiency and convenient to carry, can be used as an investigation and mapping flight platform carried by an individual solder, and can be used for completing tasks of mapping and investigation, particularly covert investigation, within a task time.
Description
Technical field
The present invention is a kind of aircraft, belongs to airmanship field.
Background technology
Since the mid-90 in 20th century, unmanned plane technology has obtained vigorous growth, wherein miniature unmanned vehicle because volume is little, good concealment, lightweight, cost is low, alerting ability is strong, the outstanding feature such as simple to operate, no matter, at military field or civil area, minute vehicle has very tempting application prospect.At present, there is the minute vehicle of various exploration, had miniature fixedly aerofoil profile, flapping wing type, rotor type, ring aerofoil profile, tail to flutter type etc.But or cruise duration is short or mission payload is not up to standard or mechanism is complicated not portable.
Summary of the invention
In order to overcome these difficulties, in comprehensive research after the weight distribution and aerodynamic arrangement of maple seed, the present invention copies maple seed to design a like this miniature unmanned vehicle, it is comprised of parts such as leafy oar, servomechanism, motors.Driven by motor screw propeller produces pulling force makes wing produce lift around the centre of gration rotation of body, and it has the advantages such as simple in structure, pneumatic efficiency is high, be easy to carry.
The present invention realizes the technical scheme that its function adopts: a kind of minute vehicle, comprise steering wheel, wing, frame, screw propeller, motor, frame is comprised of straight line frame and arc frame, steering wheel is arranged in straight line frame, wing is connected with steering wheel, motor is arranged on arc frame away from one end of steering wheel, and screw propeller is arranged on motor, and screw propeller and wing lay respectively at two sides of frame.
Preferably: between the centre of gration of aircraft and center of gravity, there is certain distance.
Preferably: steering wheel is arranged near arc frame place.
Preferably: wing is leading edge near a side of motor, and opposite side is trailing edge, and leading edge is straight line, trailing edge is spoon shape curve.
Preferably: wing is part hollow.
Preferably: also comprise motor fixing frame, arc frame is provided with motor fixing frame away from one end of steering wheel, and motor is arranged on motor fixing frame.
Preferably:: also comprise battery, wire, battery is arranged on straight line frame away from one end of motor, and battery is connected with steering wheel and motor by wire.
Preferably: also comprise control chip, control chip is arranged on straight line frame away from one end of motor, and battery is connected with control chip, and control chip is connected with steering wheel and motor by wire.
Preferably: also comprise gear, connect boss, rubber headring, pipe, gear, connecting boss is arranged near the frame of steering wheel, connect on boss and be provided with through hole, pipe one end passes from through hole, rubber headring is arranged on one end of pipe, and the other end of pipe is connected with wing, and wing is also provided with gear with on the pipe being connected between boss, steering wheel is also provided with gear, and the gear on steering wheel is meshed with the gear on pipe.
Preferably: manage as carbon fiber pipe.
The invention has the beneficial effects as follows: this miniature unmanned vehicle is simple in structure, pneumatic efficiency is high, be easy to carry, can vertical takeoff and landing, can be used as investigation, mapping flying platform that individual soldier carries, the task that can complete mapping and scout within mission time, in especially hidden scouting.
Accompanying drawing explanation
Fig. 1 is complete machine schematic layout pattern of the present invention.
Fig. 2 is the schematic diagram at wing and frame jointing place.
Reference numeral title is as follows: 1, battery; 2, straight line frame; 3, steering wheel; 4, wing; 5, gear; 6, connect boss; 7, frame; 8, arc frame; 9, screw propeller; 10, motor fixing frame; 11, motor; 12, rubber headring; 13, pipe; 14, gear; 15, control chip; 16, box.
The specific embodiment
Below in conjunction with drawings and Examples, the present invention is further described.
A minute vehicle, comprises battery 1, steering wheel 3, wing 4, frame 7, screw propeller 9, motor 11, control chip 15.Frame 7 is comprised of straight line frame 2 and arc frame 8.Steering wheel 3 is arranged in straight line frame 2, near arc frame 8 places.Wing 4 is connected with steering wheel 3, and motor 11 is arranged on arc frame 8 away from one end (one end of frame 7) of steering wheel 3, and screw propeller 9 is arranged on motor 11, and screw propeller 9 and wing 4 lay respectively at two sides of frame 7.Frame 7 is strip shape, battery 1 is arranged on straight line frame 2 away from one end (other end of frame 7) of motor 11, battery 1 is connected with steering wheel 3, motor 11 by wire, control chip 15, steering wheel 3 is arranged in frame 7, wing 4 is connected with steering wheel 3, and motor 11 and wing 4 lay respectively at two sides of frame 7.Steering wheel 3 is arranged near arc frame 8 places, is more conducive to the flight of aircraft.Motor 11 is positioned at the top of wing 4.One side of wing 4 (near a side of motor) is leading edge of a wing section, and leading edge is straight line,, opposite side (near a side of battery) is trailing edge section, trailing edge is spoon shape curve.In order to alleviate the weight of aircraft, wing 4 is part hollow.
In near the frame 7 steering wheel 3, be also provided with and connect boss 6, connect boss 6 and can be arranged on the side near motor 11, also can be arranged on the side away from motor 11.Connect on boss 6 and be provided with through hole, one end of carbon fiber pipe 13 penetrates from one end of through hole, from the other end of through hole, passes.In one end of carbon fiber pipe 13, from the other end of through hole passes, rubber headring 12 is arranged on one end of carbon fiber pipe 13, rubber headring 12 makes the carbon fiber pipe 13 can be to wing 4 one side vibrations.Like this carbon fiber pipe 13 can be rotated in through hole.The other end of carbon fiber pipe 13 stretches into the hollow space of wing 4, is connected with wing 4, can not relatively rotate, thereby wing 4 can be rotated between wing 4 and carbon fiber pipe 13.At wing 4, with on the carbon fiber pipe 13 being connected between boss 6, gear 5 is also installed, between carbon fiber pipe 13 and gear 5, do not have and relatively rotate, and gear 5 can make the carbon fiber pipe 13 can be to the side vibration away from wing 4, steering wheel 3 is provided with gear 14 in the side near wing 4, and gear 14 is meshed with gear 5.By steering wheel 3 transmission gears 14, gear 14 transmission gears 5, gear 5 transmission carbon fiber pipes 13, carbon fiber pipe 13 transmission wings 4, realize transmission and the control of 3 pairs of wings 4 of steering wheel.Steering wheel 3 is digital rudder controller.
Arc frame 8 is provided with motor fixing frame 10 away from one end (one end of frame 7) of steering wheel 3, and motor 11 is arranged on motor fixing frame 10, and screw propeller 9 is arranged on motor 11.The object of pipe 13 use carbon fibers is to alleviate the weight of aircraft, the pipe that can certainly use other solid materials to make.
Further, in straight line frame 2, away from one end (other end of frame 7) of motor 11, be provided with box 16, the interior placing battery 1 of box 16 and control chip 15.That is to say that battery 1, control chip 15 are arranged on straight line frame 2 away from one end (other end of frame 7) of motor 11.Battery 1 is connected with control chip 15, and control chip 15 is connected with steering wheel 3, motor 11, thereby controls steering wheel 3 and motor 11.
During aircraft takeoff, thereby by motor 11, driving the screw propeller 9 rotation generation pull strap motivation wings 4 to rotate generation lift around centre of gration takes off, when want travel direction when flight by steering wheel 3 periodically driven gear 5 make wing 4 change the angles of attack, thereby the cycle of realizing aircraft lift changes, change the direction of tilt of the oar dish that whole aircraft rotate to form, carry out the directional control in 360 degree orientation, guaranteed that the aircraft destination of can flying accurately carries out scouting, the tasks such as mapping safety are returned, when aircraft need to land, as long as it is operated to overhead, appointed place, reduce until disable motor 11, it just can autorotative glide.
When carrying, rubber headring 12 in Fig. 2 can be taken off, aircraft is divided into frame 7, motor 11 and separated the carrying of wing 4 parts.
Because this is imitative, " " minute vehicle is simple in structure for maple seed, only there are 3 two servomechanisms of motor 11 and steering wheel, and adopted the wing 4 of high lift aerofoil profile only to have a slice wing 4 simultaneously in rotation, reduced the aerodynamic interference of multi-rotor aerocraft trailing vortex, therefore its mission payload improves greatly, extended cruise duration, and owing to self being among continuous rotation, can investigation, 360 ° of orientation of mapping are achieved without dead angle by existing image processing techniques.
Designed minute vehicle profile is bionical, wing 4 part profiles are just as the blade-section of maple seed, adopt high lift aerofoil profile to improve 1ift-drag ratio, the pneumatic efficiency of bonding leaf, wing 4 links together by the carbon fiber pipe 13 extending with frame 7, in junction, there is a steering wheel 3 simultaneously, gear 14 by steering wheel 3 drives gear fixing on carbon fiber pipe 13 5, thereby the angle of attack of periodic Control wing 4, change the lift size that complete machine is subject to, the oar dish direction of tilt that the full machine while controlling rotation forms carries out directional control.At the other end of frame 7 near wing 4 places battery-mounted 1, control convenience and investigation instrument of surveying and mapping unit, one end is provided with motor 11, the unnecessary concussion that while adopting three leaf oars and above screw propeller 9 to eliminate rotation, screw propeller 9 causes about continuous variation of rotating shaft vertical direction rotor inertia, the pulling force that drives screw propeller 9 to produce by motor 11 makes wing 4 rotate to produce lift around the centre of gration of body, drive whole body to rise, and its centre of gration and center of gravity have certain displacement difference to make aircraft have flight stability to guarantee certain eccentricity, that is to say between the centre of gration of aircraft and center of gravity and there is certain distance, in other part of frame, can carry counterweight allocates the center of gravity of whole aircraft and makes aircraft have auto stability.
Claims (10)
1. a minute vehicle, it is characterized in that: comprise steering wheel (3), wing (4), frame (7), screw propeller (9), motor (11), frame (7) is comprised of straight line frame (2) and arc frame (8), steering wheel (3) is arranged in straight line frame (2), wing (4) is connected with steering wheel (3), motor (11) is arranged on arc frame (8) away from one end of steering wheel (3), it is upper that screw propeller (9) is arranged on motor (11), and screw propeller (9) and wing (4) lay respectively at two sides of frame (7).
2. aircraft according to claim 1, is characterized in that: between the centre of gration of aircraft and center of gravity, have certain distance.
3. aircraft according to claim 1, is characterized in that: steering wheel (3) is arranged near arc frame (8) and locates.
4. aircraft according to claim 1, is characterized in that: wing (4) is leading edge near a side of motor (11), and opposite side is trailing edge, and leading edge is straight line, and trailing edge is spoon shape curve.
5. aircraft according to claim 1, is characterized in that: wing (4) is part hollow.
6. aircraft according to claim 1, is characterized in that: also comprise motor fixing frame (10), arc frame (8) is provided with motor fixing frame (10) away from one end of steering wheel (3), and motor (11) is arranged on motor fixing frame (10).
7. aircraft according to claim 1, is characterized in that: also comprise battery (1), wire, battery (1) is arranged on straight line frame (2) away from one end of motor (11), and battery (1) is connected with steering wheel (3) and motor (11) by wire.
8. aircraft according to claim 7, it is characterized in that: also comprise control chip (15), control chip (15) is arranged on straight line frame (2) away from one end of motor (11), battery (1) is connected with control chip (15), and control chip (15) is connected with steering wheel (3) and motor (11) by wire.
9. aircraft according to claim 1, it is characterized in that: also comprise gear (5), connect boss (6), rubber headring (12), pipe (13), gear (14), connecting boss (6) is arranged near the frame (7) of steering wheel (3), connect on boss (6) and be provided with through hole, pipe (13) one end passes from through hole, rubber headring (12) is arranged on one end of pipe (13), the other end of pipe (13) is connected with wing (4), wing (4) is also provided with gear (5) with on the pipe (13) being connected between boss (6), gear (14) is arranged on steering wheel (3), gear (5) is meshed with gear (14).
10. aircraft according to claim 9, is characterized in that: pipe (13) is carbon fiber pipe.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310691367.8A CN103693195B (en) | 2013-12-17 | 2013-12-17 | A kind of minute vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310691367.8A CN103693195B (en) | 2013-12-17 | 2013-12-17 | A kind of minute vehicle |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN103693195A true CN103693195A (en) | 2014-04-02 |
| CN103693195B CN103693195B (en) | 2015-08-12 |
Family
ID=50354904
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201310691367.8A Expired - Fee Related CN103693195B (en) | 2013-12-17 | 2013-12-17 | A kind of minute vehicle |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN103693195B (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2016137150A (en) * | 2015-01-28 | 2016-08-04 | 株式会社 学研ホールディングス | Missile |
| CN105905296A (en) * | 2016-05-18 | 2016-08-31 | 北京理工大学 | Single-wing gyrating aircraft lift force optimized design method based on spinning stability |
| CN107697282A (en) * | 2017-09-30 | 2018-02-16 | 江阴市翔诺电子科技有限公司 | A kind of new concept vertically taking off and landing flyer and its control method |
| WO2023043378A3 (en) * | 2021-09-17 | 2023-04-27 | Singapore University Of Technology And Design | Monocopter |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3915414A (en) * | 1974-05-06 | 1975-10-28 | Kenneth R Shoulders | Rotating aircraft and aircraft control system |
| US20110062278A1 (en) * | 2009-06-19 | 2011-03-17 | University Of Maryland | Controllable miniature mono-wing aircraft |
| CN203638094U (en) * | 2013-12-17 | 2014-06-11 | 南京航空航天大学 | Micro aerial vehicle |
-
2013
- 2013-12-17 CN CN201310691367.8A patent/CN103693195B/en not_active Expired - Fee Related
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3915414A (en) * | 1974-05-06 | 1975-10-28 | Kenneth R Shoulders | Rotating aircraft and aircraft control system |
| US20110062278A1 (en) * | 2009-06-19 | 2011-03-17 | University Of Maryland | Controllable miniature mono-wing aircraft |
| CN203638094U (en) * | 2013-12-17 | 2014-06-11 | 南京航空航天大学 | Micro aerial vehicle |
Non-Patent Citations (1)
| Title |
|---|
| EVAN R. ULRICH 等: "Control Model for Robotic Samara: Dynamics about a Coordinated Helical Turn", 《AMERICAN CONTROL CONFERENCE (ACC), 2010》 * |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2016137150A (en) * | 2015-01-28 | 2016-08-04 | 株式会社 学研ホールディングス | Missile |
| CN105905296A (en) * | 2016-05-18 | 2016-08-31 | 北京理工大学 | Single-wing gyrating aircraft lift force optimized design method based on spinning stability |
| CN107697282A (en) * | 2017-09-30 | 2018-02-16 | 江阴市翔诺电子科技有限公司 | A kind of new concept vertically taking off and landing flyer and its control method |
| WO2023043378A3 (en) * | 2021-09-17 | 2023-04-27 | Singapore University Of Technology And Design | Monocopter |
Also Published As
| Publication number | Publication date |
|---|---|
| CN103693195B (en) | 2015-08-12 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN106927030B (en) | Oil-electricity hybrid power multi-rotor aircraft and flight control method thereof | |
| EP3299290B1 (en) | Rotating proprotor arrangement for a tiltrotor aircraft | |
| CN101559702B (en) | Longitudinal-line-type dual-culvert vertical-lifting air-ground vehicle | |
| AU2015374294B2 (en) | Rotary wing VTOL with fixed wing forward flight mode | |
| US10967964B2 (en) | Air wheel rotor, a gyro stabilized aircraft and a wind-driven power generator using the air wheel rotor, and a stationary launching device | |
| CN101837195B (en) | Model airplane with vertical takeoff and landing | |
| US20200010182A1 (en) | Pivoting wing system for vtol aircraft | |
| RU2563921C1 (en) | Rotorcraft with vertical takeoff | |
| CN106379532B (en) | A kind of change of flapping wing is fluttered angle changing mechanism | |
| CN204473140U (en) | New vertical landing tilting rotor two axle aircraft | |
| CA3057560A1 (en) | Vertical takeoff and landing aircraft | |
| CN103318410A (en) | Vertical take-off and landing micro aerial vehicle without control surface | |
| CN103693195B (en) | A kind of minute vehicle | |
| CN102490897A (en) | Multi-driving embedded rotor manned helicopter | |
| CN107985583B (en) | Tilt rotor unmanned aerial vehicle | |
| CN105173076B (en) | A kind of vertical take-off and landing drone | |
| CN102673787A (en) | Small-sized combined type air vehicle adopting layout combining disk swing with variable wings and airbag | |
| CN208484828U (en) | A kind of Fixed Wing AirVehicle of energy VTOL | |
| CN103991540A (en) | Conical rotary flapping wing aircraft | |
| CN206552261U (en) | A kind of tilting rotor wing unmanned aerial vehicle | |
| CN103991543B (en) | A kind of rotary flapping wing aircraft with spring | |
| CN203638094U (en) | Micro aerial vehicle | |
| CN107662703B (en) | Electric double-coaxial same-side reverse tilting rotor aircraft | |
| CN202414159U (en) | Multi-drive embedded rotor manned helicopter | |
| CN210942215U (en) | Civil light aircraft |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20150812 Termination date: 20161217 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |