CN105775098A - Unmanned aerial vehicle with rotor and air bag hybrid power - Google Patents
Unmanned aerial vehicle with rotor and air bag hybrid power Download PDFInfo
- Publication number
- CN105775098A CN105775098A CN201610229525.1A CN201610229525A CN105775098A CN 105775098 A CN105775098 A CN 105775098A CN 201610229525 A CN201610229525 A CN 201610229525A CN 105775098 A CN105775098 A CN 105775098A
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- China
- Prior art keywords
- rotor
- air bag
- aerial vehicle
- oar
- coaxial double
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- 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.)
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64B—LIGHTER-THAN AIR AIRCRAFT
- B64B1/00—Lighter-than-air aircraft
- B64B1/58—Arrangements or construction of gas-bags; Filling arrangements
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/10—Rotorcrafts
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/30—Lighter-than-air aircraft, e.g. aerostatic aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U2101/00—UAVs specially adapted for particular uses or applications
Abstract
The invention discloses an unmanned aerial vehicle with rotor and air bag hybrid power. The unmanned aerial vehicle with the rotor and air bag hybrid power is designed against the problems of small effective load, short endurance and weak antijamming capability of an unmanned aerial vehicle and the shortcomings of aeronautical facilities and pilots in an aerogeophysical survey technology. The unmanned aerial vehicle mainly comprises an air bag, four rotor mechanisms, a coaxial twin propeller mechanism and a pod. The air bag provides main lift force for the unmanned aerial vehicle and overcomes the shortcoming of small effective load of the unmanned aerial vehicle. The coaxial twin propeller mechanism provides part of lift force for the aerial vehicle during the lift and can also rotate reversely to provide descending pressure, to be used for changing flight height and lifting control. By the changing of quad-rotor rotating speeds in different directions, the flight direction of the unmanned aerial vehicle can be adjusted timely, forward flying power is provided for the aerial vehicle, and the air resistance is improved. The unmanned aerial vehicle not only is suitable for the field of aerogeophysical survey, but also can be used for the aspects of aerial photography observation, agriculture and forestry operation, material transport and earthquake relief work, and has the advantages of heavy load, high efficiency, stability, safety, convenience and cheapness and the like.
Description
Technical field
The present invention relates to a kind of unmanned vehicle suitable in large aerospace physical prospecting field, be specifically related to one and there is rotor and air bag composite power unmanned vehicle.
Background technology
At present, China's Aero Geophysical Survey mainly uses airborne vehicle equipped with dedicated probe instrument (such as fixed-wing, helicopter etc.), from the change of the various physical field of the aerial survety earth, thus understanding subsurface geology and mineral reserve distribution situation.Pod propulsion time domain aviation electromagnetic system experimentation is reconnoitred and is succeeded in China, it is mainly by means of helicopter, by a cable tens meters long, the annular emission of a set of diameter several meters to tens meter being received equipment and pulls on sky, helicopter keeps the low altitude flight of about hundred meters.Technique has bright prospects, but the restriction being subject to helicopter and pilot is difficult to promote.On the one hand, weight of equipment is big, requires significantly high to helicopter, and in certain areas it is difficult to ensure that its required low flight height；On the other hand, because flying height is low, density big, the airmanship of pilot is required significantly high.This field solves the difficulty existed in current Detection Techniques in the urgent need to a kind of unmanned vehicle.
Captive balloon, HAA are all the lighter-than-air flight devices making full use of air uplift to provide lift, the advantage that they have airborne period length, cheap, energy resource consumption is minimum, the buoyancy that can utilize therein helium is risen in the air, do not need extra power, but the mobility of captive balloon is excessively poor, HAA is big due to volume, does not have good power set in side, therefore the impact by crosswind is very big, it is difficult to handle.If the Dominant Facies of rotor technology with air buoyancy lift can be combined by certain aircraft, then this design just can meet the Aero Geophysical Survey technology requirement to aircraft.
Summary of the invention
It is an object of the invention to provide one and there is rotor and air bag composite power unmanned vehicle, solve the problems such as unmanned plane payload is little, cruising time is shorter, capacity of resisting disturbance is weak and the aerogeophysical object-detected technology deficiency on air equipment and pilot and design；This unmanned vehicle, in conjunction with rotor technology and balloon principle, provides efficient, heavily loaded composite power for unmanned vehicle.
The technical scheme is that one has rotor and air bag composite power unmanned vehicle, including air bag, gondola, control system, coaxial double-oar mechanism and rotor mechanism；Coaxial double-oar mechanism includes coaxial double-oar and coaxial double-oar brushless electric machine composition, and coaxial double-oar brushless electric machine is fixing with coaxial double-oar to be connected, and rotor mechanism includes rotor and four rotor brushless electric machines form；Four rotor brushless electric machines are fixing with rotor to be connected, and described control system includes receiver, electron speed regulator, flight panel, lithium battery, wire, charger and remote controller；It is characterized in that: gondola is positioned at air bag lower end, coaxial double-oar mechanism is positioned at air bag upper end, with coaxial pair of paddle mechanism symmetrical placement, air bag is provided with spherical base, coaxial double-oar mechanism and four rotor mechanisms are by being connected between spherical base with air bag, and four rotor mechanisms are positioned at air bag central axis surrounding, are symmetrically distributed in all around four direction of body, being installed with flight panel inside gondola, described flight panel is connected with receiver；The upper end of flight panel is provided with lithium battery, and described receiver, flight control version, lithium battery and electron speed regulator and be respectively positioned on the inside of gondola；Described coaxial double-oar brushless electric machine is connected with electron speed regulator by a wire, and a described wire enters in gondola along air bag, and the other end of a wire is connected on flight panel；Described four rotor brushless electric machines are connected with electron speed regulator by No. two wires, and described No. two wires enter in gondola along air bag, and the other end of No. two wires is connected on flight panel；Described electron speed regulator is connected with receiver by wire.
Coaxial double-oar mechanism of the present invention is that seccotine hasp is connected by what be connected by between spherical base with air bag.
Four rotor mechanisms of the present invention are that seccotine hasp is connected by what be connected by between spherical base with air bag.
Bladder shape of the present invention can be designed to the near-sphericals such as circle, taper, spindle according to requirements.
The invention have the advantage that the present invention is compared with simple many rotor wing unmanned aerial vehicles, it is possible to be substantially reduced the power consumption of rotor, under the identical energy, the unmanned function flight longer time, increase the load of aircraft simultaneously, improve capacity of resisting disturbance.Compared with the airborne vehicle that tradition airborne geophysical prospecting uses, this aircraft has simple in construction, low cost of manufacture, and flying height is low, detect degree of accuracy and safety is high, and environmental pollution is little, widely used advantage.
Accompanying drawing explanation
Fig. 1 is the structural front view of the present invention.
Fig. 2 is the structure top view of the present invention.
Fig. 3 is principles of the invention FB(flow block).
Detailed description of the invention
In the drawings, coaxial double-oar 1, air bag 2, rotor 3, four rotor brushless electric machine 4, gondola 5, receiver 6, electron speed regulator 7, flight panel 8, lithium battery 9, coaxial double-oar brushless electric machine 11, coaxial double-oar mechanism 12, rotor mechanism 13.
Below in conjunction with accompanying drawing, the present invention is described in detail.
The present invention is such to work and enforcement, with reference to accompanying drawing 1-3, the present invention is by including coaxial double-oar 1, air bag 2, rotor 3, four rotor brushless electric machine 4, gondola 5, receiver 6, electron speed regulator 7, flight panel 8, lithium battery 9, wire, coaxial double-oar brushless electric machine 11, coaxial double-oar mechanism 12, rotor mechanism 13.Described gondola 5 is positioned at near-spherical air bag 2 lower end, and with coaxial double-oar 1 symmetrical placement, it forms entity with critical piece.Described gondola 5 is internal is installed with flight panel 8, and described flight panel 8 is connected with receiver 6；The upper end of described flight panel 8 is provided with lithium battery 9, and described receiver 6, flight control version 8, lithium battery 9 are respectively positioned on the inside of gondola 5；Described coaxial double-oar mechanism 12 and four rotor mechanisms 13 are by being connected with seccotine and velcro respectively between spherical base 1 with air bag 2.Described coaxial double-oar mechanism 12 is composed of a fixed connection by coaxial double-oar brushless electric machine 11 and coaxial double-oar 1, is positioned at the top of air bag 2.Described coaxial double-oar brushless electric machine 11 is connected with electron speed regulator 7 by a wire, and a described wire enters in gondola 5 along air bag 2, and the other end of a wire is connected on flight panel 8；Four described rotor mechanisms 13 are composed of a fixed connection with rotor 3 by four rotor brushless electric machines 4, are positioned at air bag 2 central axis surrounding, are symmetrically distributed in all around four direction of body.Described four rotor brushless electric machines 4 are connected with electron speed regulator 7 by No. two wires, and described No. two wires enter in gondola 5 along air bag 2, and the other end of No. two wires is connected on flight panel 8；Described electron speed regulator 7 is connected with receiver 6 by wire.Described air bag provides main lift, and coaxial double-oar provides downforce when auxiliary lifting when taking off and landing；Four rotor major control flight attitudes and heading.
Claims (4)
1. there is rotor and an air bag composite power unmanned vehicle, including air bag, gondola, control system, coaxial double-oar mechanism and rotor mechanism；Coaxial double-oar mechanism includes coaxial double-oar and coaxial double-oar brushless electric machine composition, and coaxial double-oar brushless electric machine is fixing with coaxial double-oar to be connected, and rotor mechanism includes rotor and four rotor brushless electric machines form；Four rotor brushless electric machines are fixing with rotor to be connected, and described control system includes receiver, electron speed regulator, flight panel, lithium battery, wire, charger and remote controller；It is characterized in that: gondola is positioned at air bag lower end, coaxial double-oar mechanism is positioned at air bag upper end, with coaxial pair of paddle mechanism symmetrical placement, air bag is provided with spherical base, coaxial double-oar mechanism and four rotor mechanisms are by being connected between spherical base with air bag, and four rotor mechanisms are positioned at air bag central axis surrounding, are symmetrically distributed in all around four direction of body, being installed with flight panel inside gondola, described flight panel is connected with receiver；The upper end of flight panel is provided with lithium battery, and described receiver, flight control version, lithium battery and electron speed regulator and be respectively positioned on the inside of gondola；Described coaxial double-oar brushless electric machine is connected with electron speed regulator by a wire, and a described wire enters in gondola along air bag, and the other end of a wire is connected on flight panel；Described four rotor brushless electric machines are connected with electron speed regulator by No. two wires, and described No. two wires enter in gondola along air bag, and the other end of No. two wires is connected on flight panel；Described electron speed regulator is connected with receiver by wire.
2. one according to claim 1 has rotor and air bag composite power unmanned vehicle, it is characterised in that: described coaxial double-oar mechanism is that seccotine hasp is connected by what be connected by between spherical base with air bag.
3. one according to claim 1 has rotor and air bag composite power unmanned vehicle, it is characterised in that: described four rotor mechanisms are that seccotine hasp is connected by what be connected by between spherical base with air bag.
4. one according to claim 1 has rotor and air bag composite power unmanned vehicle, it is characterised in that: described bladder shape or the circle that is designed to, taper, spindle are spherical.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610229525.1A CN105775098A (en) | 2016-04-14 | 2016-04-14 | Unmanned aerial vehicle with rotor and air bag hybrid power |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610229525.1A CN105775098A (en) | 2016-04-14 | 2016-04-14 | Unmanned aerial vehicle with rotor and air bag hybrid power |
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| Publication Number | Publication Date |
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| CN105775098A true CN105775098A (en) | 2016-07-20 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201610229525.1A Pending CN105775098A (en) | 2016-04-14 | 2016-04-14 | Unmanned aerial vehicle with rotor and air bag hybrid power |
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Cited By (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106081047A (en) * | 2016-07-28 | 2016-11-09 | 无锡信大气象传感网科技有限公司 | A kind of sounding balloon of adjustable point monitoring |
| CN106240786A (en) * | 2016-07-28 | 2016-12-21 | 无锡信大气象传感网科技有限公司 | A kind of highly controllable sounding balloon |
| CN106240787A (en) * | 2016-07-28 | 2016-12-21 | 无锡信大气象传感网科技有限公司 | A kind of using method of highly controllable sounding balloon |
| CN106291759A (en) * | 2016-07-28 | 2017-01-04 | 无锡信大气象传感网科技有限公司 | A kind of using method of pinpoint sounding balloon |
| CN106291757A (en) * | 2016-07-28 | 2017-01-04 | 无锡信大气象传感网科技有限公司 | A kind of using method of the sounding balloon of adjustable point monitoring |
| CN106394859A (en) * | 2016-09-23 | 2017-02-15 | 广东天米教育科技有限公司 | Inflatable soft-body unmanned aerial vehicle |
| CN106892079A (en) * | 2017-03-13 | 2017-06-27 | 天峋（常州）智能科技有限公司 | One kind is tethered at unmanned plane |
| CN107792334A (en) * | 2016-08-31 | 2018-03-13 | 江苏金刚文化科技集团股份有限公司 | The bionic device that a kind of creeping motion type promotes |
| CN109058650A (en) * | 2018-09-28 | 2018-12-21 | 厦门理工学院 | A kind of submarine pipeline crusing robot and method for inspecting |
| CN110466780A (en) * | 2019-08-19 | 2019-11-19 | 西安长峰机电研究所 | A kind of Helios |
| CN112046724A (en) * | 2020-09-09 | 2020-12-08 | 重庆交通大学 | Self-rotating rotor type airship |
| CN112373691A (en) * | 2020-09-03 | 2021-02-19 | 红河学院 | Use indoor unmanned aerial vehicle of helium gasbag |
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| FR580657A (en) * | 1923-07-26 | 1924-11-13 | Helicopter | |
| US4269375A (en) * | 1979-10-31 | 1981-05-26 | Hickey John J | Hybrid annular airship |
| US7264202B2 (en) * | 2005-11-01 | 2007-09-04 | Information Systems Laboratories, Inc. | Tri-cycloidal airship |
| US20150078620A1 (en) * | 2012-04-20 | 2015-03-19 | Eth Zurich | Aircraft, Methods for Providing Optical Information, Method for Transmission of Acoustic Information and Method for Observing or Tracking an Object |
| CN204750561U (en) * | 2015-04-29 | 2015-11-11 | 南昌航空大学 | Four rotor crafts of area propulsion and steering control duct |
| CN205707277U (en) * | 2016-04-14 | 2016-11-23 | 南昌航空大学 | One has rotor and air bag composite power unmanned vehicle |
-
2016
- 2016-04-14 CN CN201610229525.1A patent/CN105775098A/en active Pending
Patent Citations (6)
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| FR580657A (en) * | 1923-07-26 | 1924-11-13 | Helicopter | |
| US4269375A (en) * | 1979-10-31 | 1981-05-26 | Hickey John J | Hybrid annular airship |
| US7264202B2 (en) * | 2005-11-01 | 2007-09-04 | Information Systems Laboratories, Inc. | Tri-cycloidal airship |
| US20150078620A1 (en) * | 2012-04-20 | 2015-03-19 | Eth Zurich | Aircraft, Methods for Providing Optical Information, Method for Transmission of Acoustic Information and Method for Observing or Tracking an Object |
| CN204750561U (en) * | 2015-04-29 | 2015-11-11 | 南昌航空大学 | Four rotor crafts of area propulsion and steering control duct |
| CN205707277U (en) * | 2016-04-14 | 2016-11-23 | 南昌航空大学 | One has rotor and air bag composite power unmanned vehicle |
Cited By (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106240786A (en) * | 2016-07-28 | 2016-12-21 | 无锡信大气象传感网科技有限公司 | A kind of highly controllable sounding balloon |
| CN106240787A (en) * | 2016-07-28 | 2016-12-21 | 无锡信大气象传感网科技有限公司 | A kind of using method of highly controllable sounding balloon |
| CN106291759A (en) * | 2016-07-28 | 2017-01-04 | 无锡信大气象传感网科技有限公司 | A kind of using method of pinpoint sounding balloon |
| CN106291757A (en) * | 2016-07-28 | 2017-01-04 | 无锡信大气象传感网科技有限公司 | A kind of using method of the sounding balloon of adjustable point monitoring |
| CN106081047A (en) * | 2016-07-28 | 2016-11-09 | 无锡信大气象传感网科技有限公司 | A kind of sounding balloon of adjustable point monitoring |
| CN107792334A (en) * | 2016-08-31 | 2018-03-13 | 江苏金刚文化科技集团股份有限公司 | The bionic device that a kind of creeping motion type promotes |
| CN106394859B (en) * | 2016-09-23 | 2019-03-15 | 广东天米教育科技有限公司 | A kind of inflation soft body unmanned plane |
| CN106394859A (en) * | 2016-09-23 | 2017-02-15 | 广东天米教育科技有限公司 | Inflatable soft-body unmanned aerial vehicle |
| CN106892079A (en) * | 2017-03-13 | 2017-06-27 | 天峋（常州）智能科技有限公司 | One kind is tethered at unmanned plane |
| CN109058650A (en) * | 2018-09-28 | 2018-12-21 | 厦门理工学院 | A kind of submarine pipeline crusing robot and method for inspecting |
| CN109058650B (en) * | 2018-09-28 | 2020-10-13 | 厦门理工学院 | Underwater pipeline inspection robot and inspection method |
| CN110466780A (en) * | 2019-08-19 | 2019-11-19 | 西安长峰机电研究所 | A kind of Helios |
| CN112373691A (en) * | 2020-09-03 | 2021-02-19 | 红河学院 | Use indoor unmanned aerial vehicle of helium gasbag |
| CN112046724A (en) * | 2020-09-09 | 2020-12-08 | 重庆交通大学 | Self-rotating rotor type airship |
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Application publication date: 20160720 |