CN205418125U - Multi -functional aircraft of long flight time of heavy load for operation - Google Patents
Multi -functional aircraft of long flight time of heavy load for operation Download PDFInfo
- Publication number
- CN205418125U CN205418125U CN201620233451.4U CN201620233451U CN205418125U CN 205418125 U CN205418125 U CN 205418125U CN 201620233451 U CN201620233451 U CN 201620233451U CN 205418125 U CN205418125 U CN 205418125U
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- China
- Prior art keywords
- rotor
- rotor assemblies
- motor
- wing
- electromotor
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T10/00—Road transport of goods or passengers
- Y02T10/60—Other road transportation technologies with climate change mitigation effect
- Y02T10/62—Hybrid vehicles
Abstract
The utility model discloses a multi -functional aircraft of long flight time of heavy load for operation, including oil -electricity hybrid vehicle part, vert pivot part and fuselage wing structure part, the oil -electricity hybrid vehicle part is located inside the fuselage. The engine rating drive the generator electricity generation, the generator drives each motor, the output voltage of power control unit through detecting the generator, feed back to the engine through the negative feedback, make the output of engine adjustable according to different work condition and load, and then the output voltage who makes the generator is adjustable according to operating mode and load, preceding pivot motor drives the axle rotation of walking around of leaning forward through preceding turbine, and then drive first rotor subassembly, vert in the time of second rotor subassembly, the cooperation of verting in the front and back can realize verting of aircraft. The utility model discloses a serial -type hybrid has the long advantage of time of endurance for the aircraft provides power, in addition, being connected of vert pivot and rotor part can make the aircraft vert, realizes VTOL and level flight in a flexible way.
Description
Technical field
This utility model relates to aircraft field, is specifically related to multifunction aircraft during a kind of operation heavy load length boat.
Background technology
Existing pure Electric aircraft uses the energy needed for pure electric energy supply aircraft, and its lithium battery energy storage battery is little, causes the flight time short, and if desired hours underway is long, it is necessary to a large amount of batteries, battery weight can be caused excessive, cause bearing capacity to decline.Patrol and examine at military affairs, plant protection, electric inspection process, oil and gas pipes, police, geological prospecting, forest fire protection, the field such as ocean remote sensing, cruising time, the requirement of payload the two basic technical indicator to aircraft are high, and existing pure electronic unmanned vehicle does not clearly reach requirement.
Traditional aircraft can not occur verting forward or backward, if wanting to realize when realizing horizontal balance verting, two the rotor rotating speeds being so in front fuselage to reduce, and be in two rotor rotating speeds of back body and to increase, so owing to front and back end rotor rotating speed is different, it is poor to produce lift, fuselage can be made to produce pitching, but flying to produce between vertical lifting before so having to make aircraft level influences each other.
Utility model content
For solving the problems referred to above, multifunction aircraft when this utility model provides a kind of operation heavy load length boat, use tandem oil electricity to be mixed into aircraft and power is provided, there is long-endurance advantage；Additionally, vert, rotating shaft and the connection of rotor component, can make aircraft vert, realize VTOL and horizontal flight flexibly.
For achieving the above object, the technical scheme that this utility model is taked is:
nullMultifunction aircraft when a kind of operation is navigated by heavy load length，Including oil electric mixed dynamic parts、Vert rotating axis component and fuselage wing structure parts，Described oil electric mixed dynamic parts include electromotor、Electromotor、Output control device、First rotor motor、Second rotor motor、3rd rotor motor、4th rotor motor、Front rotary shaft motor and rear rotating shaft electric motor，Driven by engine electrical power generators，Output control device is by detecting the output voltage of electromotor，Electromotor is fed back to by negative feedback，The output making electromotor is adjustable according to different operating modes and load，And then make the output voltage of electromotor according to operating mode and load adjustable，Electromotor passes through power line and the first rotor motor、Second rotor motor、3rd rotor motor、4th rotor motor、Front rotary shaft motor is connected with rear rotating shaft electric motor，Output control device and electromotor、Electromotor is connected，The described rotating axis component that verts includes front turbine、Rear turbine、Lean forward and walk around axle and hypsokinesis is walked around axle，Described fuselage wing structure parts include fuselage、First fixes wing、Second fixes wing、3rd fixes wing、4th fixes wing、First rotor assemblies、Second rotor assemblies、3rd rotor assemblies and the 4th rotor assemblies，Fore-body lateral symmetry is provided with first and fixes wing、Second fixes wing，Fuselage afterbody lateral symmetry is provided with the 3rd and fixes wing、4th fixes wing，Lean forward the walk around two ends of axle are symmetrically installed with the first rotor assemblies by pin、Second rotor assemblies，Pin provides support force，Rotor is rotatable around pin，First rotor assemblies、Second rotor assemblies is arranged in first and fixes wing、Second front middle part fixing wing，Front rotary shaft motor is connected with the axle of walking around of leaning forward by front turbine，And then drive the first rotor assemblies、Vert while second rotor assemblies，Hypsokinesis axle two ends of walking around are symmetrically installed with the 3rd rotor assemblies by pin、4th rotor assemblies，Pin provides support force，Rotor is rotatable around pin，3rd rotor assemblies、4th rotor assemblies is arranged in the 3rd and fixes wing、4th front middle part fixing wing，Rear rotating shaft electric motor is connected by rear turbine axle of walking around with hypsokinesis，And then drive the 3rd rotor assemblies、Vert while 4th rotor assemblies，Cooperating of front and back verting can realize verting of aircraft.
Preferably, described electromotor uses piston-mode motor, driven by engine electrical power generators, and electromotor electricity provides aircraft vertical landing and the active force of horizontal flight for each electric machine rotation, motor.
Preferably, described waist is provided with rotor drive device, and rotor drive device is by drive rod respectively by the first rotor assemblies and the second rotor assemblies, and the 3rd rotor assemblies and the 4th rotor assemblies couple together, it is achieved DCB Specimen synchronous axial system.
Preferably, the 3rd fixing wing, the 4th size fixing wing is all higher than first and fixes wing, the second size fixing wing, the 3rd rotor assemblies, the size of the 4th rotor assemblies are all higher than the first rotor assemblies, the size of the second rotor assemblies.
This utility model has the advantages that
1) piston-mode motor is used can to play fuel-efficient effect；
2) using tandem oil electric mixed dynamic, engine rotation drives electrical power generators, electromotor output electric energy to supply each motor, and motor flies the active force with VTOL before providing aircraft level；
3) by output control device according to load and regulating working conditions engine speed and generator output voltage, and then allow motor speed with load and climatic conditioning；
4) rotating axis component two ends of verting are used to connect the structure of two rotor components, the rotation of rotating shaft of making to vert can drive verting of two ends rotor component simultaneously, the cooperation front and back verted, aircraft can be made to vert, such that it is able to make the cruising time of aircraft and bearing capacity increase, and the mobility of aircraft and motility also improve, easily realize taking off vertically, land, hover, horizontal flight.
Accompanying drawing explanation
Multifunction aircraft overall structure schematic diagram when Fig. 1 is this utility model embodiment one operation heavy load length boat
Fig. 2 is the rotating shaft schematic diagram that verts in this utility model embodiment.
In figure, 1-the first rotor assemblies, 2-the first rotor motor, 3-first fixes wing；4-the 3rd rotor assemblies, 5-the 3rd rotor motor, 6-the 3rd fixes wing, 7-fuselage wing structure parts, 8-fuselage, rotating shaft electric motor after 9-, turbine after 10-, 11-hypsokinesis is walked around axle, and 12-the 4th fixes wing, 13-the 4th rotor assemblies, 14-the 4th rotor motor, 15-electromotor, 16-oil electric mixed dynamic parts, 17-electromotor, 18-output control device, 19-second fixes wing, 20-the second rotor assemblies, 21-the second rotor motor, 22-front rotary shaft motor, 23-verts rotating axis component, turbine before 24-, and 25-leans forward axle of walking around.
Detailed description of the invention
In order to make the purpose of this utility model and advantage clearer, below in conjunction with embodiment, this utility model is further elaborated.Should be appreciated that specific embodiment described herein, only in order to explain this utility model, is not used to limit this utility model.
nullAs described in Fig. 1-2，Multifunction aircraft when this utility model embodiment provides a kind of operation heavy load length boat，Including oil electric mixed dynamic parts 16、Vert rotating axis component 23 and fuselage wing structure parts 7，It is characterized in that，Described oil electric mixed dynamic parts 16 include electromotor 17、Electromotor 15、Output control device 18、First rotor motor 2、Second rotor motor 21、3rd rotor motor 5、4th rotor motor 14、Front rotary shaft motor 22 and rear rotating shaft electric motor 9，Electromotor 17 drives electromotor 15 to generate electricity，Output control device 18 is by detecting the output voltage of electromotor 15，Electromotor 17 is fed back to by negative feedback，The output making electromotor 17 is adjustable according to different operating modes and load，And then make the output voltage of electromotor 15 according to operating mode and load adjustable，Electromotor 15 is by power line and the first rotor motor 2、Second rotor motor 21、3rd rotor motor 5、4th rotor motor 14、Front rotary shaft motor 22 is connected with rear rotating shaft electric motor 9，Output control device 18 and electromotor 17、Electromotor 15 is connected，The described rotating axis component 23 that verts includes front turbine 24、Rear turbine 10、Lean forward and walk around axle 25 and hypsokinesis is walked around axle 11，Described fuselage wing structure parts 7 include fuselage 8、First fixes wing 3、Second fixes wing 19、3rd fixes wing 6、4th fixes wing 12、First rotor assemblies 1、Second rotor assemblies 20、3rd rotor assemblies 4 and the 4th rotor assemblies 13，Fuselage 8 front part sides is symmetrically installed with first and fixes wing 3、Second fixes wing 19，Fuselage 8 rear portion lateral symmetry is provided with the 3rd and fixes wing 6、4th fixes wing 12，Lean forward the walk around two ends of axle 25 are symmetrically installed with the first rotor assemblies 1 by pin、Second rotor assemblies 20，Pin provides support force，Rotor is rotatable around pin，First rotor assemblies 1、Second rotor assemblies 20 is arranged in first and fixes wing 3、Second front middle part fixing wing 19，Front rotary shaft motor 22 is connected with the axle 25 of walking around of leaning forward by front turbine 24，And then drive the first rotor assemblies 1、Vert while second rotor assemblies 20，Hypsokinesis axle 11 two ends of walking around are symmetrically installed with the 3rd rotor assemblies 4 by pin、4th rotor assemblies 13，Pin provides support force，Rotor is rotatable around pin，3rd rotor assemblies 4、4th rotor assemblies 13 is arranged in the 3rd and fixes wing 6、4th front middle part fixing wing 12，Rear rotating shaft electric motor 9 is connected by rear turbine 10 axle 11 of walking around with hypsokinesis，And then drive the 3rd rotor assemblies 4、Vert while 4th rotor assemblies 13，Cooperating of front and back verting can realize verting of aircraft.
Described electromotor 17 uses piston-mode motor, fuel-efficient；The electrically coupled in series output of oil: electromotor 17 rotates and drives electromotor 15 to generate electricity, electromotor 15 drives each motor, output control device 18 is by detecting the output voltage of electromotor 15, electromotor 17 is fed back to by negative feedback, the output making electromotor 17 is adjustable according to different operating modes and load, and then makes the output voltage of electromotor 15 according to operating mode and load adjustable.
Being provided with rotor drive device in the middle part of described fuselage 8, rotor drive device is by drive rod respectively by the first rotor assemblies 1 and the second rotor assemblies 20, and the 3rd rotor assemblies 4 and the 4th rotor assemblies 13 couple together, it is achieved DCB Specimen synchronous axial system.
3rd fixes wing the 6, the 4th size fixing wing 12 is all higher than first and fixes wing 3, the second size fixing wing 19, the size of the 3rd rotor assemblies the 4, the 4th rotor assemblies 13 is all higher than the size of first rotor assemblies the 1, second rotor assemblies 20, can avoid producing between before and after's rotor aerodynamic interference.
Originally it is embodied as oil electric mixed dynamic parts 16 and is positioned at fuselage interior.Described electromotor 17 rotates and drives electromotor 15 to generate electricity, electromotor 15 drives each motor, output control device 18 is by detecting the output voltage of electromotor 15, electromotor 17 is fed back to by negative feedback, the output making electromotor 17 is adjustable according to different operating modes and load, and then make the output voltage of electromotor 15 according to operating mode and load adjustable, front rotary shaft motor 22 drives the axle 25 of walking around of leaning forward to rotate by front turbine 24, and then vert while driving first, second rotor assemblies 1,20, the cooperation front and back verted can realize verting of aircraft.
Originally being embodied as having two kinds of patterns of taking off, during VTOL, first rotor assemblies the 1, second rotor assemblies the 20, the 3rd rotor assemblies 4 and the 4th rotor assemblies 13 direction are the most upward；During horizontal flight, the first rotor assemblies 1 and the second rotor assemblies 20, the 3rd rotor assemblies 4 and the 4th rotor assemblies 13 direction are all towards heading.
The above is only preferred implementation of the present utility model; it should be pointed out that, for those skilled in the art, on the premise of without departing from this utility model principle; can also make some improvements and modifications, these improvements and modifications also should be regarded as protection domain of the present utility model.
Claims (4)
- null1. multifunction aircraft when an operation is navigated by heavy load length，Including oil electric mixed dynamic parts (16)、Vert rotating axis component (23) and fuselage wing structure parts (7)，It is characterized in that，Described oil electric mixed dynamic parts (16) include electromotor (17)、Electromotor (15)、Output control device (18)、First rotor motor (2)、Second rotor motor (21)、3rd rotor motor (5)、4th rotor motor (14)、Front rotary shaft motor (22) and rear rotating shaft electric motor (9)，Electromotor (17) drives electromotor (15) generating，Electromotor (15) passes through power line and the first rotor motor (2)、Second rotor motor (21)、3rd rotor motor (5)、4th rotor motor (14)、Front rotary shaft motor (22) is connected with rear rotating shaft electric motor (9)，Output control device (18) and electromotor (17)、Electromotor (15) is connected，The described rotating axis component that verts (23) includes front turbine (24)、Rear turbine (10)、Lean forward and walk around axle (25) and hypsokinesis is walked around axle (11)，Described fuselage wing structure parts (7) includes fuselage (8)、First fixes wing (3)、Second fixes wing (19)、3rd fixes wing (6)、4th fixes wing (12)、First rotor assemblies (1)、Second rotor assemblies (20)、3rd rotor assemblies (4) and the 4th rotor assemblies (13)，Fuselage (8) front part sides is symmetrically installed with first and fixes wing (3)、Second fixes wing (19)，Fuselage (8) rear portion lateral symmetry is provided with the 3rd and fixes wing (6)、4th fixes wing (12)，Lean forward the walk around two ends of axle (25) are symmetrically installed with the first rotor assemblies (1) by pin、Second rotor assemblies (20)，First rotor assemblies (1)、Second rotor assemblies (20) is arranged in first and fixes wing (3)、Second front middle part fixing wing (19)，Front rotary shaft motor (22) is connected with the axle (25) of walking around of leaning forward by front turbine (24)，Hypsokinesis axle (11) two ends of walking around are symmetrically installed with the 3rd rotor assemblies (4) by pin、4th rotor assemblies (13)，3rd rotor assemblies (4)、4th rotor assemblies (13) is arranged in the 3rd and fixes wing (6)、4th front middle part fixing wing (12)，Rear rotating shaft electric motor (9) is connected by rear turbine (10) axle (11) of walking around with hypsokinesis.
- Multifunction aircraft during a kind of operation heavy load length boat the most according to claim 1, it is characterized in that, described electromotor (17) uses piston-mode motor, electromotor (17) drives electromotor (15) generating, electromotor (15) electricity provides aircraft vertical landing and the active force of horizontal flight for each electric machine rotation, motor.
- Multifunction aircraft during a kind of operation heavy load length boat the most according to claim 1, it is characterized in that, described fuselage (8) middle part is provided with rotor drive device, rotor drive device passes through drive rod respectively by the first rotor assemblies (1) and the second rotor assemblies (20), 3rd rotor assemblies (4) and the 4th rotor assemblies (13) couple together, it is achieved DCB Specimen synchronous axial system.
- Multifunction aircraft during a kind of operation heavy load length boat the most according to claim 1, it is characterized in that, 3rd fix wing (6), the 4th size fixing wing (12) is all higher than first and fixes wing (3), the second size fixing wing (19), and the 3rd rotor assemblies (4), the size of the 4th rotor assemblies (13) are all higher than the first rotor assemblies (1), the size of the second rotor assemblies (20).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620233451.4U CN205418125U (en) | 2016-03-18 | 2016-03-18 | Multi -functional aircraft of long flight time of heavy load for operation |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620233451.4U CN205418125U (en) | 2016-03-18 | 2016-03-18 | Multi -functional aircraft of long flight time of heavy load for operation |
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| Publication Number | Publication Date |
|---|---|
| CN205418125U true CN205418125U (en) | 2016-08-03 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201620233451.4U Expired - Fee Related CN205418125U (en) | 2016-03-18 | 2016-03-18 | Multi -functional aircraft of long flight time of heavy load for operation |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105752345A (en) * | 2016-03-18 | 2016-07-13 | 西安交通大学 | Large load long duration multifunctional aircraft for operation |
| CN109641656A (en) * | 2016-09-08 | 2019-04-16 | 通用电气公司 | Tilting rotor propulsion system for aircraft |
| CN109641657A (en) * | 2016-09-08 | 2019-04-16 | 通用电气公司 | Tilting rotor propulsion system for aircraft |
-
2016
- 2016-03-18 CN CN201620233451.4U patent/CN205418125U/en not_active Expired - Fee Related
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105752345A (en) * | 2016-03-18 | 2016-07-13 | 西安交通大学 | Large load long duration multifunctional aircraft for operation |
| CN105752345B (en) * | 2016-03-18 | 2019-03-22 | 西安交通大学 | A kind of long endurance multifunction aircraft of operation heavy load |
| CN109641656A (en) * | 2016-09-08 | 2019-04-16 | 通用电气公司 | Tilting rotor propulsion system for aircraft |
| CN109641657A (en) * | 2016-09-08 | 2019-04-16 | 通用电气公司 | Tilting rotor propulsion system for aircraft |
| CN109641657B (en) * | 2016-09-08 | 2022-08-16 | 通用电气公司 | Tiltrotor propulsion system for aircraft |
| US11673661B2 (en) | 2016-09-08 | 2023-06-13 | General Electric Company | Tiltrotor propulsion system for an aircraft |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| 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: 20160803 Termination date: 20170318 |
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| CF01 | Termination of patent right due to non-payment of annual fee |