CN106167091A - Inflation rotor wing unmanned aerial vehicle - Google Patents
Inflation rotor wing unmanned aerial vehicle Download PDFInfo
- Publication number
- CN106167091A CN106167091A CN201610764396.6A CN201610764396A CN106167091A CN 106167091 A CN106167091 A CN 106167091A CN 201610764396 A CN201610764396 A CN 201610764396A CN 106167091 A CN106167091 A CN 106167091A
- Authority
- CN
- China
- Prior art keywords
- middle deck
- fuselage
- collection middle
- aerial vehicle
- unmanned aerial
- 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.)
- Pending
Links
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/08—Helicopters with two or more rotors
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- 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
- B64C1/34—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like comprising inflatable structural components
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/32—Rotors
-
- 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
- B64U2101/00—UAVs specially adapted for particular uses or applications
-
- 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
- B64U2101/30—UAVs specially adapted for particular uses or applications for imaging, photography or videography
Abstract
The present invention is inflation rotor wing unmanned aerial vehicle, solve the shortcoming that the existing rotor wing unmanned aerial vehicle hang time do not grows, at least one spherical sealed chamber (11) is connected with collection middle deck (12), form Inflatable fuselage, it is mounted with in collection middle deck (12) to fly to control module, remote control module, battery, electricity mode transfer block, collection middle deck (12) is outside to be connected with power set, power set are by brushless electric machine (14), blade (15) is constituted, Inflatable back has position height sensor (13), bottom has goods to link up with (16), the buoyancy that fuselage produces is less than the weight that unmanned plane is overall.
Description
Technical field:
The present invention is relevant with rotor wing unmanned aerial vehicle.
Background technology:
Existing rotor wing unmanned aerial vehicle industry, agricultural, environment, fire-fighting, measurement, emergency management and rescue, take photo by plane, photography and vedio recording, electric power patrol
The industry-by-industry such as inspection is applied widely, but the problem facing maximum at present is unmanned plane stays aloft execution task time
The shortest, need a kind of technology that can increase the unmanned plane hang time to solve this problem.
Summary of the invention:
The purpose of the present invention is to propose to a kind of inflation rotor wing unmanned aerial vehicle overcoming short shortcoming of existing rotor wing unmanned aerial vehicle hang time.
The present invention is achieved in that
At least one spherical sealed chamber 11 of the present invention is connected with collection middle deck 12, forms Inflatable fuselage, peace in collection middle deck 12
Having filled and flown to control module, remote control module, battery, electricity mode transfer block, collection middle deck 12 is outside to be connected with power set, and power set are by brushless
Motor 14, blade 15 is constituted, and Inflatable back has position height sensor 13, and goods hook 16 is arranged at bottom.Fuselage produces
Raw buoyancy is less than the weight that unmanned plane is overall.
Annular seal space 11 thin wire and carbon fiber bar do keel shoe, and outside keel shoe, on set, thin film is made, at collection
The both direction up and down of middle deck 12 is each fixes an annular seal space 11, forms Inflatable fuselage.Collection middle deck 12 is outside to be moved with four
Power apparatus connects.
The principle of technical solution of the present invention is:
Doing keel shoe with thin wire and carbon fiber bar, outside keel shoe, thin film on set, forms an annular seal space, is concentrating
The both direction up and down in cabin is each fixes an annular seal space, forms Inflatable fuselage, and Inflatable fuselage possesses certain volume,
It is full of after the gas lighter than air specific weight (such as helium, hydrogen etc.), buoyancy upwards can be produced in atmosphere, produced
When buoyancy is less than aircraft weight, aircraft is controlled flight.As a example by hydrogen, at room temperature, the hydrogen of 1 cubic meter volume
Gas can be produced as 1.58Kg, is deducting weight 0.8Kg of Os Draconis and thin film, then can produce the buoyancy of 0.78Kg.Therefore pass through
The energy expenditure when buoyancy that inflation fuselage produces can reduce blade 15 and motor 14 produces lift, thus it is stagnant to improve unmanned plane
The empty time.
Advantages of the present invention and beneficial effect:
The present invention, on the basis of existing rotor wing unmanned aerial vehicle, designs Inflatable fuselage, and this fuselage is generally closed
Or several air bag, the rotor support of unmanned plane becomes to organically combine with inflator figure, and the construction features of inflation fuselage does not interferes with
Aerodynamic characteristics during rotor rotational.Utilize inflation fuselage produce to buoyancy, alleviate the load of motor, thus reduce electricity
Pond supply current output, extends aircraft flying time.It is few that the present invention increases material, low cost；It is stagnant that the present invention can increase unmanned plane
The empty time, effect is obvious.
Accompanying drawing explanation
Fig. 1 is present configuration figure.
Detailed description of the invention:
At least one spherical sealed chamber 11 is connected with collection middle deck 12, forms Inflatable fuselage, it is mounted with to fly in collection middle deck 12
Control module, remote control module, battery, electricity mode transfer block, collection middle deck 12 is outside to be connected with power set, and power set are by brushless electric machine
14, blade 15 is constituted, and Inflatable back has position height sensor 13, and goods hook 16 is arranged at bottom.
Annular seal space 11 thin wire and carbon fiber bar do keel shoe, and outside keel shoe, on set, thin film is made, at collection
The both direction up and down of middle deck 12 is each fixes an annular seal space 11, forms Inflatable fuselage.Collection middle deck 12 is outside to be moved with four
Power apparatus connects.
The present invention, on the basis of existing rotor wing unmanned aerial vehicle, designs Inflatable fuselage, and this fuselage is generally to close
One or several spherical sealed, the rotor support of unmanned plane becomes to organically combine with inflator figure, and the construction features of fuselage will not
Aerodynamic characteristics when affecting rotor rotational, fuselage is designed to upper and lower two spherical sealed chambeies, respectively in upper and lower, middle
Position be the place that two spherical sealed chambeies connect, therefore have bigger space for placing collection middle deck 12, due in centre
Space is left in position, and the aerostatic buoyancy driven when blade rotates will not be affected by fuselage.When flight, fill owing to adding
Mechanism of qi body, fills hydrogen or helium in fuselage with, and fuselage can produce buoyancy upwards, thus alleviates the load of motor；To machine
The volume size of body is controlled, and the buoyancy that fuselage produces is less than the weight that unmanned plane is overall, in order to unmanned during flight downwards
The controllability of machine.
Claims (2)
1. inflation rotor wing unmanned aerial vehicle, it is characterised in that at least one spherical sealed chamber (11) is connected with collection middle deck (12), and formation can
Inflatable body fuselage, is mounted with to fly to control module, remote control module, battery, electricity mode transfer block in collection middle deck (12), collection middle deck (12) is outside
Being connected with power set, power set are made up of brushless electric machine (14), blade (15), and Inflatable back has position height
Sensor (13), bottom has goods to link up with (16), and the buoyancy that fuselage produces is less than the weight that unmanned plane is overall.
Inflation rotor wing unmanned aerial vehicle the most according to claim 1, it is characterised in that described annular seal space (11) thin wire and carbon
Fiber rod does keel shoe, and outside keel shoe, on set, thin film is made, and the both direction up and down at collection middle deck (12) is each fixing
One annular seal space (11), forms Inflatable fuselage, and collection middle deck (12) is outside to be connected with four power set.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610764396.6A CN106167091A (en) | 2016-08-31 | 2016-08-31 | Inflation rotor wing unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610764396.6A CN106167091A (en) | 2016-08-31 | 2016-08-31 | Inflation rotor wing unmanned aerial vehicle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN106167091A true CN106167091A (en) | 2016-11-30 |
Family
ID=57376843
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610764396.6A Pending CN106167091A (en) | 2016-08-31 | 2016-08-31 | Inflation rotor wing unmanned aerial vehicle |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106167091A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| TWI641532B (en) * | 2017-09-05 | 2018-11-21 | 朝陽科技大學 | UAV and its flying method and driving device |
| WO2019135802A1 (en) * | 2018-01-05 | 2019-07-11 | Raytheon Company | Flight vehicle with drone and lift-producing balloon |
| WO2021006837A1 (en) * | 2019-07-09 | 2021-01-14 | Karako Cem | A carrying apparatus |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103274042A (en) * | 2013-05-10 | 2013-09-04 | 华南农业大学 | Suspension-type helicopter |
| WO2014207732A1 (en) * | 2013-06-28 | 2014-12-31 | Paolo Bellezza Quater | A multi-rotor aircraft |
| CN105035299A (en) * | 2015-06-29 | 2015-11-11 | 长安大学 | Cruise and suspension aircraft and flight control method thereof |
| CN204822096U (en) * | 2015-06-10 | 2015-12-02 | 刘亚敏 | Unmanned aircraft |
| CN205087138U (en) * | 2015-10-22 | 2016-03-16 | 深圳光启合众科技有限公司 | Multi -rotor aircraft |
-
2016
- 2016-08-31 CN CN201610764396.6A patent/CN106167091A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103274042A (en) * | 2013-05-10 | 2013-09-04 | 华南农业大学 | Suspension-type helicopter |
| WO2014207732A1 (en) * | 2013-06-28 | 2014-12-31 | Paolo Bellezza Quater | A multi-rotor aircraft |
| CN204822096U (en) * | 2015-06-10 | 2015-12-02 | 刘亚敏 | Unmanned aircraft |
| CN105035299A (en) * | 2015-06-29 | 2015-11-11 | 长安大学 | Cruise and suspension aircraft and flight control method thereof |
| CN205087138U (en) * | 2015-10-22 | 2016-03-16 | 深圳光启合众科技有限公司 | Multi -rotor aircraft |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| TWI641532B (en) * | 2017-09-05 | 2018-11-21 | 朝陽科技大學 | UAV and its flying method and driving device |
| WO2019135802A1 (en) * | 2018-01-05 | 2019-07-11 | Raytheon Company | Flight vehicle with drone and lift-producing balloon |
| US11352134B2 (en) | 2018-01-05 | 2022-06-07 | Raytheon Company | Flight vehicle with drone and lift-producing protrusion |
| WO2021006837A1 (en) * | 2019-07-09 | 2021-01-14 | Karako Cem | A carrying apparatus |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20161130 |
|
| RJ01 | Rejection of invention patent application after publication |