CN206766315U - A kind of novel airbag type multi-rotor aerocraft - Google Patents
A kind of novel airbag type multi-rotor aerocraft Download PDFInfo
- Publication number
- CN206766315U CN206766315U CN201720184758.4U CN201720184758U CN206766315U CN 206766315 U CN206766315 U CN 206766315U CN 201720184758 U CN201720184758 U CN 201720184758U CN 206766315 U CN206766315 U CN 206766315U
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- rotor
- air bag
- cross
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- flight control
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Abstract
The utility model discloses a kind of novel airbag type multi-rotor aerocraft, is designed to solve the problems such as unmanned plane payload is small, cruising time is shorter, antijamming capability is weak.It mainly includes the double paddle mechanisms of air bag, four rotor mechanisms, cross-arranging type and gondola.The shortcomings that air bag provides prevailing lift, overcomes unmanned plane payload small for unmanned plane.Part lift, can also reversely rotate offer falling pressure, height and elevating control for change of flight when the double oars of cross-arranging type provide rising for aircraft.By changing four rotor rotating speeds of different azimuth, the heading of aircraft can be adjusted in time, and the power that flown before being provided for aircraft, improve wind resistance.The aircraft is applicable not only to Aero Geophysical Survey, but also can take photo by plane observation, agrisilviculture and matter transportation etc., have the advantages that heavy duty, efficiently, stably, conveniently, safely, it is cheap.
Description
Technical field
A kind of unmanned vehicle suitable for large aerospace physical prospecting field is the utility model is related to, it is characterized in that with reference to rotor
Technology and balloon principle, the composite power of efficient heavy duty is provided for unmanned vehicle.
Background technology
Early in the thirties in last century, people just start to be directed to Aerobiz being combined with geological prospecting work, in the hope of
Bigger achievement is obtained on Geophysical Work.The development course of passing airborne geophysical prospecting is looked back, obvious, the flying platform selection of early stage
Mainly or based on fixed wing aircraft and helicopter, until reaching its maturity recently as aviation items technology, due to tool
Have safe, flight efficiency is high, and the plurality of advantages such as cost is low, the aircraft such as four rotor wing unmanned aerial vehicles and dirigible is in geological prospecting
The advantage that is highlighted of application and its development prospect also more get more and more people's extensive concerning.Airborne geophysical prospecting is become for ground
One of constantly progressive mark constantly modernized of matter exploration engineering.
However, some shortcomings are also individually present in they.Though such as four rotor wing unmanned aerial vehicles with good mobility and efficiently
Property, but the shortcomings that its low load and low endurance but also leverage the development of Geophysical Work.Relative to quadrotor, float
Pocket seems to compensate for these weak points.Captive balloon, HAA are all to make full use of air uplift to provide lift
Lighter-than-air flight device, they have the advantages of airborne period is long, cheap, energy resource consumption is minimum, can utilize therein
The buoyancy of helium is risen in the air, it is not necessary to extra power, but the mobility of captive balloon is excessively poor, HAA
Because volume is big, there is no good power set in side, therefore influenceed by crosswind very big, it is difficult to manipulated.If certain flies
Row device can be combined rotor technology with the Dominant Facies of air buoyancy lift, then the design just can meet Aero Geophysical Survey to flying
The technical requirements of row device.
The content of the invention
The purpose of this utility model is to provide a kind of novel airbag type multi-rotor aerocraft, a kind of described gasbag
Formula multi-rotor aerocraft can substantially reduce the power consumption of rotor compared with simple multi-rotor unmanned aerial vehicle, in the identical energy
Under, the unmanned function flight longer time, while increase the load of aircraft, improve antijamming capability.With traditional aviation thing
Airborne vehicle is compared used in spy, and the aircraft has that simple in construction, manufacturing cost is low, flying height is low, detection accuracy and
Safe, environmental pollution is small, the advantages of being widely used.
The technical solution adopted in the utility model is as follows：A kind of novel airbag type multi-rotor aerocraft, including the first rotor,
Air bag, the second brushless electric machine, the second rotor, gondola, receiver, electron speed regulator, flight control panel, lithium battery, wire, charging
Device and remote control, the round bearing with pipe clamp, the first brushless electric machine, carbon fiber bar, cross-arranging type double paddle mechanism, rotor mechanisms；
It is characterized in that：The gondola is located at near-spherical air bag lower end, and double paddle mechanism symmetrical placements of cross-arranging type, itself and critical piece shape
Into entity.Flight control panel is installed with inside the gondola, the flight control panel is connected with receiver；It is described to fly
The upper end of row control panel is provided with lithium battery, and the receiver, flight control panel, lithium battery are respectively positioned on the inside of gondola；It is described
The double paddle mechanisms of cross-arranging type and four rotor mechanisms by the way that seccotine and Buddhist nun are used between round bearing and air bag with pipe clamp respectively
Imperial hasp connection.The double paddle mechanisms of described cross-arranging type are located at the top of air bag, are passed through by the first brushless electric machine and the first rotor
Carbon fiber bar and the round bearing composition with pipe clamp.Carbon fiber bar passes through the pipe clamp of round bearing and is connected with air bag, two rotations
The wing is separately fixed at carbon fiber bar both ends with cross-arranging type.First brushless electric machine is connected by No.1 wire with electron speed regulator
Connect, the No.1 wire is entered in gondola along air bag, and the another of No.1 wire is terminated on flight control panel；Described four
Individual rotor mechanism is composed of a fixed connection by the second brushless electric machine and the second rotor, positioned at air bag central axis surrounding, symmetrically
It is distributed in the four direction around of body.Second brushless electric machine is connected by No. two wires with electron speed regulator,
No. two wires are entered in gondola along air bag, and No. two the another of wire are terminated on flight control panel；Described electronics
Speed regulator is connected by wire with receiver.
The double paddle mechanisms of cross-arranging type of the present utility model are located at near-spherical air bag top, and four rotor mechanisms are in air bag center
On the sustained height of axis surrounding, the four direction around of body is symmetrically distributed in；Wherein, the double paddle mechanism of cross-arranging type and
It is connected between rotor mechanism and air bag by the round bearing with pipe clamp, air bag provides main lift, and the double oars of cross-arranging type are winged
Row device provides part lift,, can by changing four rotor rotating speeds of different azimuth for the height and elevating control of change of flight
To adjust the heading of aircraft in time, and the power that flown before being provided for aircraft.
The utility model bladder shape can be designed to the near-sphericals such as circle, taper, spindle according to requirements.
The utility model carbon fiber bar passes through the pipe clamp of round bearing and is connected with air bag, and two rotors are distinguished with cross-arranging type
It is fixed on carbon fiber bar both ends.
The utility model has the advantages that：Compared with airborne vehicle used in traditional airborne geophysical prospecting, the aircraft has structure
Simply, manufacturing cost is low, and flying height is low, detection accuracy and safe, and environmental pollution is small, the advantages of being widely used.
Brief description of the drawings
Fig. 1 is overall structure front view of the present utility model.
Fig. 2 is overall structure top view of the present utility model.
Fig. 3 is control schematic diagram of the present utility model.
In figure, the first rotor（The double oars of cross-arranging type are used）1st, air bag 2, the second brushless electric machine（Four rotors are used）3rd, the second rotor
（Four rotors are used）4th, gondola 5, receiver 6, electron speed regulator 7, flight control panel 8, lithium battery 9, wire, charger and remote control
Device 10, the round bearing 11 with pipe clamp, the first brushless electric machine（The double oars of cross-arranging type are used）12nd, the double oar machines of carbon fiber bar 13, cross-arranging type
Structure 14, rotor mechanism 15.
Embodiment
The utility model is described in detail below in conjunction with accompanying drawing.
With reference to 1-3 accompanying drawings, the utility model is by including the first rotor（The double oars of cross-arranging type are used）1st, air bag 2, the second brushless electricity
Machine（Four rotors are used）3rd, the second rotor（Four rotors are used）4th, gondola 5, receiver 6, electron speed regulator 7, flight control panel 8, lithium electricity
Pond 9, wire, charger and remote control 10, the round bearing 11 with pipe clamp, the first brushless electric machine（The double oars of cross-arranging type are used）12、
Carbon fiber bar 13, cross-arranging type double paddle mechanism 14, rotor mechanisms 15.
The gondola 5 is located at near-spherical air bag lower end, and with the double paddle mechanism symmetrical placements of cross-arranging type, it is formed with critical piece
Entity.Flight control panel 8 is installed with inside the gondola 5, the flight control panel 8 is connected with receiver 6；It is described
The upper end of flight control panel 8 is provided with lithium battery 9, and the receiver 6, flight control panel 8, lithium battery 9 are respectively positioned on the interior of gondola 5
Portion；The double paddle mechanisms 14 of described cross-arranging type and four rotor mechanisms 15 pass through between round bearing 11 and air bag 2 with pipe clamp points
Not Yong seccotine connected with velcro.The double paddle mechanisms 14 of described cross-arranging type are located at the top of air bag 2, are by the first brushless electricity
Machine（The double oars of cross-arranging type are used）12 and first rotor（The double oars of cross-arranging type are used）1 by carbon fiber bar 13 and the round bearing with pipe clamp 11
Composition.Carbon fiber bar 13 passes through the pipe clamp of the round bearing 11 with pipe clamp and is connected with air bag 2, and two rotors 1 are with cross-arranging type point
The both ends of carbon fiber bar 13 are not fixed on.First brushless electric machine（The double oars of cross-arranging type are used）12 pass through No.1 wire and electronic speed regulation
Device 7 is connected, and the No.1 wire is entered in gondola 5 along air bag 2, and the another of No.1 wire terminates at flight control panel 8
On；Four described rotor mechanisms 15 are by the second brushless electric machine（Four rotors are used）3 and second rotor 4 be composed of a fixed connection,
Positioned at the central axis surrounding of air bag 2, the four direction around of body is symmetrically distributed in.Second brushless electric machine（Four rotations
The wing is used）3 are connected by No. two wires with electron speed regulator 7, and No. two wires are entered in gondola 5 along air bag 2, and No. two
The another of wire is terminated on flight control panel 8；Described electron speed regulator 7 is connected by wire with receiver 6.
Claims (3)
1. a kind of novel airbag type multi-rotor aerocraft, including the first rotor, air bag, the second brushless electric machine, the second rotor, hang
Cabin, receiver, electron speed regulator, flight control panel, lithium battery, wire, charger and remote control, the circular branch with pipe clamp
Seat, the first brushless electric machine, carbon fiber bar, cross-arranging type double paddle mechanism, rotor mechanisms；It is characterized in that：The gondola is located at class ball
Shape air bag lower end, with the double paddle mechanism symmetrical placements of cross-arranging type, it forms entity with critical piece；Fixed peace inside the gondola
Equipped with flight control panel, the flight control panel is connected with receiver；The upper end of the flight control panel is provided with lithium battery,
The receiver, flight control panel, lithium battery are respectively positioned on the inside of gondola；The double paddle mechanisms of described cross-arranging type and four gyroplanes
Structure with seccotine and velcro by being connected respectively between round bearing and air bag with pipe clamp；The double oar machines of described cross-arranging type
Structure is located at the top of air bag, is to pass through carbon fiber bar and the round bearing group with pipe clamp by the first brushless electric machine and the first rotor
Into；Carbon fiber bar passes through the pipe clamp of round bearing and is connected with air bag, and two rotors are separately fixed at carbon fiber bar with cross-arranging type
Both ends；First brushless electric machine is connected by No.1 wire with electron speed regulator, and the No.1 wire enters along air bag
In gondola, and the another of No.1 wire is terminated on flight control panel；Four described rotor mechanisms are by the second brushless electric machine
It is composed of a fixed connection with the second rotor, positioned at air bag central axis surrounding, is symmetrically distributed in four sides around of body
To；Second brushless electric machine is connected by No. two wires with electron speed regulator, and No. two wires enter along air bag to be hung
In cabin, and No. two the another of wire are terminated on flight control panel；Described electron speed regulator is connected by wire with receiver.
A kind of 2. novel airbag type multi-rotor aerocraft according to claim 1, it is characterised in that：Bladder shape can basis
Requirement is designed to circle, taper, spindle.
A kind of 3. novel airbag type multi-rotor aerocraft according to claim 1, it is characterised in that：Carbon fiber bar passes through circle
The pipe clamp of shape bearing is simultaneously connected with air bag, and two rotors are separately fixed at carbon fiber bar both ends with cross-arranging type.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720184758.4U CN206766315U (en) | 2017-02-28 | 2017-02-28 | A kind of novel airbag type multi-rotor aerocraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720184758.4U CN206766315U (en) | 2017-02-28 | 2017-02-28 | A kind of novel airbag type multi-rotor aerocraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN206766315U true CN206766315U (en) | 2017-12-19 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201720184758.4U Expired - Fee Related CN206766315U (en) | 2017-02-28 | 2017-02-28 | A kind of novel airbag type multi-rotor aerocraft |
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| CN (1) | CN206766315U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108622393A (en) * | 2018-05-10 | 2018-10-09 | 唐晓刚 | A kind of multiple-energy-source fusion aircraft and its control method |
-
2017
- 2017-02-28 CN CN201720184758.4U patent/CN206766315U/en not_active Expired - Fee Related
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108622393A (en) * | 2018-05-10 | 2018-10-09 | 唐晓刚 | A kind of multiple-energy-source fusion aircraft and its control method |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20171219 Termination date: 20190228 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |