CN102490897B - Multi-driving embedded rotor manned helicopter - Google Patents
Multi-driving embedded rotor manned helicopter Download PDFInfo
- Publication number
- CN102490897B CN102490897B CN201110426789.3A CN201110426789A CN102490897B CN 102490897 B CN102490897 B CN 102490897B CN 201110426789 A CN201110426789 A CN 201110426789A CN 102490897 B CN102490897 B CN 102490897B
- Authority
- CN
- China
- Prior art keywords
- rotor
- rotating shaft
- transfer rotating
- helicopter
- driving
- 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.)
- Active
Links
Landscapes
- Toys (AREA)
- Transmission Devices (AREA)
Abstract
The invention discloses a multi-driving embedded rotor manned helicopter. The multi-driving embedded rotor manned helicopter comprises a helicopter body, wherein a control cabin is arranged on the helicopter body; multiple circular rotor mounting holes which are through from top to bottom are formed on the helicopter body; a bracket is arranged in each rotor mounting hole; a rotating shaft connected with a power transmission system is arranged on the bracket; and a rotor is mounted on the rotating shaft. The multi-driving embedded rotor manned helicopter disclosed by the invention has the following advantages that: multiple rotors are arranged on the aircraft and multi-point driving (more than two driving) mode is adopted so that the rising load of the helicopter is effectively increased, the stability and flexibility in flying are enhanced and each driving rotor is embedded (to protect the rotor). The driving position can be placed in an axis area (center of the helicopter body) of multiple driving supporting points and can be also appropriately moved backwards and forwards and from side to side according to needs.
Description
Technical field
The present invention relates to a kind of rotor manned helicopter, belong to aviation aircraft manufacturing technology field.
Background technology
At present in aviation and aircraft field, can take off vertically or the aircraft of long period hovering aloft in only have helicopter, but current helicopter rotates for offsetting rotorshaft the torsional moment producing, extend body (elongated tail) and locate the tail rotor of the anti-twisted moment of device, make body too huge, and safety factor, rising load, alerting ability and stability are all very low, limited flight range and the scope of work of helicopter.
Current " combined type autogiros " or " combined rotor aircraft " etc. are also just improved on the basis of traditional heligyro and traditional hang gliding aircraft, and advantage is outstanding, and its traditional drawback is existence still.
" 4 wheel driven moves aircraft " that can see is also just in " model plane " stage, and the one, rotor leaks outside, safe not; The 2nd, do not take the tower structure in cabin, also cannot realize occupant; The 3rd, power drive system is difficult to realize large load.
Many rotor manned helicopters especially quadrotor have been state of the art, its power drive system, rotor system, control system, maneuvering system, with and flight theory method of operating be prior art.For example the patent No. is 201010284234.5(publication No. CN101973392A, date of publication 2011.02.16) patent of invention the telescopic quadrotor of a kind of fuselage is disclosed, it for being provided with four rotors in criss-cross frame.Original many rotors comprise that the main deficiency of four its existence of rotor is, outside rotor is exposed to, lacking rotor is protected in the situation that, its scope of work is limited, and alerting ability is not high, and safety factor is little.In addition, existing quadrotor mostly is dummy vehicle, its power drive system, maneuvering system are comparatively simple, be not suitable for large-scale many rotor manneds aircraft, and the equal unexposed Power Train that the is applicable to many rotor manneds aircraft maneuvering system of unifying of existing manned craft, therefore designing a kind of many rotor manneds aircraft and developing the applicable Power Train maneuvering system of unifying still needs to pay creative work.
Summary of the invention
The object of the invention is for overcoming above-mentioned the deficiencies in the prior art, provide that a kind of hoisting force is large, flight safety, flight stable again flexibly, many drivings embedded rotor manned helicopter that scope of work is large.
For achieving the above object, the present invention adopts following technical proposals:
The embedded rotor manned helicopters that drive more, comprise fuselage, fuselage is provided with driving compartment, fuselage is provided with a plurality of upper and lower penetrating circular rotor mounting holes, in each rotor mounting hole, be equipped with support, support is provided with the rotorshaft that connects power drive system, and rotor is installed on rotorshaft.
Described fuselage is dish, and driving compartment is arranged on the central authorities of fuselage, can select as required size, and a plurality of rotor mounting holes are distributed on the surrounding of driving compartment.
Described rotor mounting hole is four.In each rotor mounting hole, be equipped with a rotor, form four rotor structures.The quantity of rotor also can be three, five, six ...
Described power drive system comprises driving engine, the transfer rotating shaft that is fixed on fuselage interior, and transfer rotating shaft comprises the transfer rotating shaft I that connects two relative rotorshafts and the transfer rotating shaft II and the transfer rotating shaft III that are connected respectively two other rotorshaft; Engine shaft is connected by pitch wheel with transfer rotating shaft I; Transfer rotating shaft II is all connected with transfer rotating shaft I by intermeshing cone gear with transfer rotating shaft III.(i.e. " monomotor multiple spot transfer ").
Described engine shaft is provided with gear I, and transfer rotating shaft I is provided with and gear I pitch wheel II; The middle part of described transfer rotating shaft I is provided with cone gear I, is respectively equipped with and the intermeshing cone gear II of cone gear I and cone gear III in transfer rotating shaft II and transfer rotating shaft III.
The two ends of described transfer rotating shaft I and transfer rotating shaft II are all connected with rotorshaft by intermeshing cone gear with the end of transfer rotating shaft III.
The end of the two ends of described transfer rotating shaft I and transfer rotating shaft II and transfer rotating shaft III is equipped with cone gear IV, and the lower end of rotorshaft is provided with and the intermeshing cone gear V of cone gear IV.
Described power drive system comprises the driving engine being arranged under each rotor, and engine shaft is connected with corresponding rotorshaft.(i.e. " multiple-motor individual drive ").
The described embedded rotor manned helicopter that drives also comprises the maneuvering system of controlling rotor wing rotation attitude more, and maneuvering system comprises the auto-bank unit of being located under each rotor, and the auto-bank unit under each rotor is all connected with total cycle handle; Auto-bank unit under any two relative rotors is connected with minute cycle handle; Auto-bank unit under each rotor is also connected with the collective-pitch lever of controlling rotor blade inclination angle size.
Described " a plurality of " refer to three and more than; Described power drive system is that the many rotors of multiple spot drive, refer to that three above independent point set respectively rotor and drive, and can need to select driving to count according to load or aircraft profile, single shaft rotor or diaxon heligyro that technique is more current have had breakthrough, and have reduced tail rotor.
Described each driving rotor adopts embedded mode, refers to rotor is adopted to ring protection, or increase aircraft body, rotor is arranged on to the inside of body extension.
This aircraft adopts conventional engine as propulsion source, and when a plurality of rotors adopt synchronously, and when horizontal surface rotates, at a plurality of rotors, by equilibratory hoisting force, aircraft is by the floating state of keeping certain height.About translation: when all rotors inclination angle, can realize aircraft to all directions translation (stable flat flying); When contrary inclination angle appears in " two groups " rotor of front and back configuration simultaneously, aircraft will be realized integral-rotation (will realize rotary flight if twist for a long time aircraft, this action, adopts while only making a stunt flying).About rotor inclination angle: can take popular method at present, by feathering, change rotor inclination angle, as adopted auto-bank unit (auto-bank unit is to be a kind of device of rotor blade controlled motion by the instruction transformation of the chaufeur passing over through helicopter flight maneuvering system or autopilot); Also can adopt axle head suspension type to install simultaneously, with rotating shaft and rotor, do whole full-shape and incline to putting and realize rotor disc inclination angle.About lifting: employing be popular method at present, in the situation that keeping gyroplane rotate speed certain, rely on the inclination angle that changes rotor blade to adjust the size of fuselage lift.Chaufeur can complete this operation by collective-pitch lever.When the blade inclination angle of rotor increases, aircraft rises; Otherwise aircraft declines.As need are kept certain height, rotor is kept to certain inclination angle.About safety: because adopting the embedded mode of rotor, can effectively avoid rotor to wipe awing and hang object around, improve the degree of safety that aircraft flies between groups of building and jungle, increase scope of work and used industry (can military, civilian, family expenses).About dish shape profile: adopting dish shape profile, is to increase aircraft coasting ability, improves the stability of aircraft flight.
The invention has the beneficial effects as follows, drive embedded rotor manned helicopter more, on aircraft, adopt a plurality of rotors, the mode of Multipoint Drive (three above drive), its advantage is flight stability, control flexibly, load-carrying capacity is strong, vertical takeoff and landing etc.A plurality of rotors, as direct driving force source, are symmetrically distributed in main body four direction, and rotor is in same level, and rotor radius, specification are all identical.And drive rotor to adopt embedded mode (rotor is played to protection) each, improve the safety of aircraft.Steering position can be placed on many axle center districts (central authorities of fuselage) that drive fulcrum, also can do as required suitable movement all around.
Accompanying drawing explanation
Fig. 1 is side elevational schematic view of the present invention;
Fig. 2 is structural representation of the present invention (" monomotor multiple spot transfer ");
Fig. 3 is structural representation of the present invention (" multiple-motor individual drive ");
Fig. 4 is power transmission system structure schematic diagram of the present invention;
Fig. 5 is rotorshaft part-structure schematic diagram of the present invention;
Fig. 6 is maneuvering system structural representation of the present invention.
1. fuselages wherein, 2. driving compartment, 3. rotor mounting hole, 4. rotorshaft, 5. rotor, 6. driving engine, 7. support, 8. canopy, 9. window, 10. access hatch, 11. alighting gears, 12. transfer rotating shaft I, 13. transfer rotating shaft II, 14. transfer rotating shaft III, 15. gear I, 16. gear II, 17. cone gear I, 18. cone gear II, 19. cone gear III, 20. cone gear IV, 21. cone gear V, 22. auto-bank units, 23. total cycle handles, 24. minute cycle handle, 25. collective-pitch levers, 26. power-transfer clutchs, 27. brake gears, 28. chaufeurs, 29. rotor blades, 30. rotating rings not, 31. rotating rings, 32. control stalks, 33. rotation inclination angles.
The specific embodiment
Below in conjunction with drawings and Examples, the present invention is further described.
Embodiment 1(be take 4 wheel driven and is moved as example, " monomotor multiple spot transfer ")
As shown in Figure 1, the embedded rotor manned helicopters that drive more, comprise flat " dish " fuselage 1 and and circular fuselage outer, the canopy 8 that fuselage 1 middle position is provided with driving (load-carrying) cabin 2 and can has an X-rayed, driver's seat is placed its below, fuselage 1 is provided with four upper and lower penetrating circular rotor mounting holes 3, and rotor mounting hole 3 is distributed on the surrounding of driving compartment 2.In each rotor mounting hole 3, be equipped with support 7, support 7 is provided with the rotorshaft 4 that connects power drive system, is provided with and is in conplane rotor 5 on rotorshaft 4.In each rotor mounting hole 3, be equipped with a rotor 5, form four rotor structures.
Described power drive system is Multipoint Drive.A plurality of rotors, Multipoint Drive, refers to two above drivings (can take monomotor transfer, also can take multiple-motor to drive separately).Described each driving rotor adopts embedded mode, refers to rotor 5 is adopted to ring protections, or increase aircraft body, and rotor 5 is arranged on to internal body.
This aircraft (helicopter) adopts dish shape profile, and being increases aircraft to slide to make up the sinkage that transient rises power that rotor 5 occurs in direction twisting reduces to cause, and improves the stability of aircraft flight.
This machine can adopt conventional engine to drive as propulsion source or large capacity high-energy battery drives, and by transmission shaft and gear combination, driving engine 6 outputting powers is transferred to rotorshaft 4, drives rotor 5 rotations to produce lift.Make this machine obtain more traditional single rotor and the less body extension radius of twin-rotor helicopter, there is larger raising force, higher flying speed, preferably alerting ability, the flight range and the effective flying power that have expanded helicopter, this machine also has more failure-free safety control.
Dish fuselage is as Fig. 3, the fuselage 1 of its flat dish shape and circular body outer, and fairing ace meets aerodynamic principle, has reduced the eddy current that body produces in-flight, increases aircraft coasting ability, improves the degree of utilization of driving engine kinetic energy; Peculiar profile, also makes helicopter more elegant in appearance.Central part at fuselage 1 arranges driving compartment 2, and there is perspective canopy 8 its top, and below is provided with window 9, is convenient to chaufeur 28 and observes outside.Four rotor mounting holes 3 are evenly distributed in fuselage 1 surrounding, and rotor mounting hole 3 middle parts are provided with erecting frame for rotor 5 is installed, and many moment fulcrum can better be guaranteed the flight stability of helicopter.Below fuselage 1, set out entry hatch 10, fuselage 1 below arranges four with the equidistant also retractable landing gear 11 of circle.
Described drive refers to three and the driving of above rotor more.Adopt the mode of monomotor multiple spot transfer as shown in Figure 1, concrete grammar is: driving engine 6 is fixed on to fuselage 1 inside, power is meshed to each rotorshaft 4 transmissions by gear and transmission shaft, and rotorshaft 4 drives rotors 5, by driving engine 6 output Conversion of Energies, is lift.
Described monomotor transfer power drive system as shown in Figure 4, monomotor transfer is exactly that monomotor power is to the process of each rotor transmission power, when driving engine 6 actings are rotated, this power meshes the gear I by engine shaft 15 and the gear II 16 in transfer rotating shaft I 12, thereby drive 12 rotations of transfer rotating shaft I, because the cone gear I 17 in transfer rotating shaft I 12 and cone gear II 18 and cone gear III 19 in transfer rotating shaft II 13 and transfer rotating shaft III 14 are also in engagement, when driving engine 6 rotates, also will drive transfer rotating shaft I 12 to rotate simultaneously.After transfer rotating shaft I 12 is rotated, the structure of rotorshaft part as shown in Figure 5, the cone gear IV 20 of transfer rotating shaft I 12 or transfer rotating shaft II 13 or transfer rotating shaft III 14 ends drives rotorshaft 4 rotations with 21 engagements of the cone gear V of rotorshaft 4 lower ends, be arranged on rotor 5 rotations on rotorshaft 4, make driving engine 6 output Energy Transfers produce the required lift of helicopter to rotor 5.For preventing quitting work because of driving engine 6 aloft, the present invention is provided with brake gear 27 especially in the rear end of power-transfer clutch 26, so that in helicopter decline process, lifting airscrew rotating speed makes the lift of helicopter generating portion, make chaufeur 28 effectively control the descend attitude of helicopter, the safety while guaranteeing to land.The detailed operation principle of power-transfer clutch and brake gear: as there are driving engine 6 flame-outs in flight, helicopter will sink, helicopter suspense will passively be rotated, now chaufeur is by power-transfer clutch 26 separation, with handle and linkage, start 27 brake gears, to control helicopter suspense rotating speed at controlled " rotation " state, make it produce required suspense lift, control helicopter and in decline process, keep stable (avoiding dish installation body image leaf equally to wave whereabouts), effectively control the descend attitude of helicopter, guarantee safety.
The present invention adopts conventional engine to implement flight as propulsion source, as shown in Figure 1, driving engine 6 and dynamic transfer system, rotor wing rotation system are installed on helicopter support 7, and by front and back and two groups of left and right (Fig. 1 is usingd four rotors as illustration) each rotor to connection.It is identical that every group of rotor 5 turns to, but two groups of rotors 5 derotation wing each other respectively, and active direction is contrary, to offset the torsional moment producing because of rotor 5 rotations, makes the lift of helicopter held stationary.Because of tetra-rotors of a plurality of rotor 5() install in same level, when the synchronous rotary of the zero inclination angle of rotor 5 plane of rotations, tetra-rotors of a plurality of rotor 5() by equilibratory hoisting force.
Realize flight attitude: the one, translation, tetra-rotors of a plurality of rotor 5() when same direction inclination angle, can realize helicopter any direction translation (flat flying).As shown in Figure 6, when chaufeur 28 is controlled the not rotating ring 30 of rotor 5 below auto-bank units 22 by wing group cycle handle or total cycle handle 23.Rotating ring 30 can not adjusted the rotation inclination angle 33 of rotor 5.Tetra-rotors of a plurality of rotor 5() controlling communication apparatus collects on same total cycle handle 23, chaufeur 28 is controlled total cycle during handle 23, tetra-rotors of a plurality of rotor 5() will produce synchronous rotary inclination angle 33, body will be produced to equidirectional horizontal sliding power, determine the flat direction that flies of fuselage 1.The 2nd, rotate fuselage, four rotors of take are example, the two groups of rotors 5 in front and back are controlled communication apparatus and are collected respectively on two minutes cycles handle 24, when chaufeur 28 is controlled by any one minute cycle handle 24, " two groups " rotor 5 of front and back configuration produces inconsistent inclination angles, and helicopter fuselage will horizontally rotate (realizing tune); Reversing sense is controlled " two groups " rotor 5 simultaneously, and while there is contrary inclination angle, helicopter is by original place fast rotational.Also can adopt axle head suspension type to install, with rotating shaft and rotor, do Integral synchronous full-shape and incline to putting and realize rotor disc inclination angle.The 3rd, lifting: the present invention adopts popular method at present, adjusts fuselage 1 lift size by changing the inclination angle of rotor blade 29.As shown in Figure 6, chaufeur 28 can drive control stalk 32 by collective-pitch lever 25 to maneuvering system, makes the rotating ring 31 of rotor 5 belows change rotor blade 29 inclination angle sizes, and when rotor blade 29 inclination angles increase, helicopter rises, otherwise helicopter declines.As keep certain height, rotor blade 29 keeps certain inclination angle.Controlling of 28 pairs of rotor 5 rotation attitudes of chaufeur is that the control system consisting of the interior joystick of driving compartment 2 and communication means (part communication means is cable wire) is implemented (being placed on the below of helicopter framework).Scheme two helicopter flight attitudes can also adopt the same plane that keeps rotor 5 and fuselage 1, change lift, and then change the flight attitude of helicopter by changing the different rotating speed of rotor 5 of two groups of front and back or left and right, complete the various flights of helicopter.
About safety: on the one hand, because adopting the embedded mode of rotor, can effectively avoid rotor 5 to wipe hanging around object awing and impaired, improve the degree of safety that aircraft flies between groups of building and jungle, increase scope of work and used industry (can military, civilian, family expenses).On the other hand, especially four rotors are more than 5 to adopt many rotors, even if a rotor damages, other rotor works on, and still can make this organizational security hold safe flight.
Embodiment 2(be take 4 wheel driven and is moved as example, " multiple-motor individual drive ")
As shown in Figure 2, the present embodiment adopts the mode of a plurality of driving engine individual drive, and the driving engine 6 of a smaller power is installed on each rotor support 7, and on each rotorshaft 4, its rotor is installed, each driving engine 6 directly drives rotorshaft 4, realizes rotor wing rotation and produces lift.The control of driving engine 6 and rotor, the control system consisting of joystick and communication means (part communication means is cable wire) in driving compartment 2 by chaufeur 28 implements to control (being placed on the below of helicopter framework).Other structure is with embodiment 1.
Claims (5)
1. one kind, drive embedded rotor manned helicopter more, comprise fuselage, fuselage is provided with driving compartment, it is characterized in that, fuselage is provided with a plurality of upper and lower penetrating circular rotor mounting holes, in each rotor mounting hole, is equipped with support, and support is provided with the rotorshaft that connects power drive system, rotor is installed on rotorshaft, and described power drive system is Multipoint Drive; A plurality of rotors, Multipoint Drive, described each driving rotor adopts embedded mode, refers to rotor is adopted to ring protection, or increase aircraft body, and rotor is arranged on to internal body;
Described fuselage is dish, and driving compartment is arranged on the central authorities of fuselage, and a plurality of rotor mounting holes are distributed on the surrounding of driving compartment;
The described embedded rotor manned helicopter that drives also comprises the maneuvering system of controlling rotor wing rotation attitude more, and maneuvering system comprises the auto-bank unit of being located under each rotor, and the auto-bank unit under each rotor is all connected with total cycle handle; Auto-bank unit under any two relative rotors is connected with minute cycle handle; Auto-bank unit under each rotor is also connected with the collective-pitch lever of controlling rotor blade inclination angle size;
Described power drive system comprises driving engine, the transfer rotating shaft that is fixed on fuselage interior, and transfer rotating shaft comprises the transfer rotating shaft I that connects two relative rotorshafts and the transfer rotating shaft II and the transfer rotating shaft III that are connected respectively two other rotorshaft; Engine shaft is connected by pitch wheel with transfer rotating shaft I; Transfer rotating shaft II is all connected with transfer rotating shaft I by intermeshing cone gear with transfer rotating shaft III.
2. the embedded rotor manned helicopter that drives as claimed in claim 1, is characterized in that more, and described rotor mounting hole is four.
3. the embedded rotor manned helicopter that drives as claimed in claim 1, is characterized in that more, and described engine shaft is provided with gear I, and transfer rotating shaft I is provided with and gear I pitch wheel II; The middle part of described transfer rotating shaft I is provided with cone gear I, is respectively equipped with and the intermeshing cone gear II of cone gear I and cone gear III in transfer rotating shaft II and transfer rotating shaft III.
4. the embedded rotor manned helicopter that drives as claimed in claim 1, is characterized in that more, and the two ends of described transfer rotating shaft I and transfer rotating shaft II are all connected with rotorshaft by intermeshing cone gear with the end of transfer rotating shaft III.
5. the embedded rotor manned helicopter that drives as claimed in claim 1 more, it is characterized in that, the end of the two ends of described transfer rotating shaft I and transfer rotating shaft II and transfer rotating shaft III is equipped with cone gear IV, and the lower end of rotorshaft is provided with and the intermeshing cone gear V of cone gear IV.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201110426789.3A CN102490897B (en) | 2011-12-19 | 2011-12-19 | Multi-driving embedded rotor manned helicopter |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201110426789.3A CN102490897B (en) | 2011-12-19 | 2011-12-19 | Multi-driving embedded rotor manned helicopter |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN102490897A CN102490897A (en) | 2012-06-13 |
| CN102490897B true CN102490897B (en) | 2014-11-05 |
Family
ID=46182769
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201110426789.3A Active CN102490897B (en) | 2011-12-19 | 2011-12-19 | Multi-driving embedded rotor manned helicopter |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN102490897B (en) |
Families Citing this family (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103171388B (en) * | 2013-03-18 | 2015-04-22 | 中国人民解放军装甲兵工程学院 | Vertical lifting land-air dual-purpose vehicle |
| CN104229132B (en) * | 2013-06-05 | 2018-09-25 | 吴嘉馨 | Coaxial anti-paddle spherical aircraft transmission system |
| CN103332292A (en) * | 2013-06-18 | 2013-10-02 | 南京航空航天大学 | 4+4 rotor craft respectively controlled by lift force and navigation |
| CN103708028A (en) * | 2014-01-17 | 2014-04-09 | 吴智勇 | Vertical take-off electric airplane |
| CN104743117A (en) * | 2015-03-30 | 2015-07-01 | 河南金原碟科技有限公司 | Disc-shaped manned four-rotor aircraft |
| CN106628173A (en) * | 2015-10-29 | 2017-05-10 | 马铿钧 | Four power-driven aircraft |
| CN106892081A (en) * | 2015-12-21 | 2017-06-27 | 深圳光启空间技术有限公司 | Multi-rotor aerocraft |
| CN106628209A (en) * | 2017-01-06 | 2017-05-10 | 尚青 | Multi-axis manned aircraft |
| CN107010214A (en) * | 2017-05-18 | 2017-08-04 | 阳喜英 | A kind of small-sized manned vehicle |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101559702A (en) * | 2009-03-27 | 2009-10-21 | 谢雁洲 | Longitudinal-line-type dual-culvert vertical-lifting air-ground vehicle |
| CN201932359U (en) * | 2011-01-21 | 2011-08-17 | 文杰 | Distributive power multi-rotor vertical take-off and landing aircraft |
| CN202414159U (en) * | 2011-12-19 | 2012-09-05 | 李玉杰 | Multi-drive embedded rotor manned helicopter |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| NZ538630A (en) * | 2005-03-04 | 2007-02-23 | Gnm Ltd | Propulsion device for a personal flight device with fans rotating in the same direction |
-
2011
- 2011-12-19 CN CN201110426789.3A patent/CN102490897B/en active Active
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101559702A (en) * | 2009-03-27 | 2009-10-21 | 谢雁洲 | Longitudinal-line-type dual-culvert vertical-lifting air-ground vehicle |
| CN201932359U (en) * | 2011-01-21 | 2011-08-17 | 文杰 | Distributive power multi-rotor vertical take-off and landing aircraft |
| CN202414159U (en) * | 2011-12-19 | 2012-09-05 | 李玉杰 | Multi-drive embedded rotor manned helicopter |
Also Published As
| Publication number | Publication date |
|---|---|
| CN102490897A (en) | 2012-06-13 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN102490897B (en) | Multi-driving embedded rotor manned helicopter | |
| CN106927030B (en) | Oil-electricity hybrid power multi-rotor aircraft and flight control method thereof | |
| CN101837195B (en) | Model airplane with vertical takeoff and landing | |
| CN102133926B (en) | Tailstock type vertical take-off and landing unmanned aerial vehicle | |
| CN201729271U (en) | Twin-propeller vertical duct controlled tiltrotor aircraft | |
| CN106585976A (en) | Aircraft layout of tilt rotors/lift fan during high-speed long endurance | |
| CN103979104B (en) | One can variant X-type wing vertical landing minute vehicle | |
| CN205916329U (en) | Coaxial double -oar unmanned vehicles | |
| CN101643116A (en) | Tiltrotor controlled by double-propeller vertical duct | |
| CN201712787U (en) | Electric tilt rotor unmanned aircraft | |
| CN113753229B (en) | Foldable fixed-wing four-rotor composite unmanned aerial vehicle and control method thereof | |
| CN105292460A (en) | Tilt-rotor based on combination of four rotor wings and fixed wing | |
| CN107662702B (en) | Hybrid power double-coaxial same-side reverse tilting rotor aircraft | |
| CN104590555A (en) | Electrodynamic multi-rotor helicopter | |
| CN102085912A (en) | Dishing magnetic suspension ring-wing aircraft | |
| CN101879945A (en) | Electric tilting rotor wing unmanned aerial vehicle | |
| RU2521090C1 (en) | High-speed turboelectric helicopter | |
| CN106628162A (en) | Composite unmanned aerial vehicle | |
| CN204197290U (en) | A kind of novel tiltrotor aircraft | |
| CN104590535A (en) | Propelling device for airship power device | |
| CN205661659U (en) | Electronic multiaxis rotor unmanned aerial vehicle system of verting | |
| CN107352029A (en) | A kind of electronic multiaxis tilting rotor wing unmanned aerial vehicle system | |
| RU146302U1 (en) | SPEED COMBINED HELICOPTER | |
| CN205554576U (en) | Multiaxis screw and rotor combination flight lift arrangement | |
| CN201744174U (en) | Model airplane vertically taking off and landing |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| ASS | Succession or assignment of patent right |
Owner name: LI MIN Free format text: FORMER OWNER: LI YUJIE Effective date: 20140926 Owner name: LI YUJIE Effective date: 20140926 |
|
| C41 | Transfer of patent application or patent right or utility model | ||
| COR | Change of bibliographic data |
Free format text: CORRECT: ADDRESS; FROM: 250002 JINAN, SHANDONG PROVINCE TO: 250004 JINAN, SHANDONG PROVINCE |
|
| TA01 | Transfer of patent application right |
Effective date of registration: 20140926 Address after: 250004, No. 35, building 10, No. 27 Xin Nan Road, Shizhong District, Shandong, Ji'nan, 201 Applicant after: Li Min Applicant after: Li Yujie Address before: 250002, Lantian District, South Second Ring Road, Shandong, Ji'nan 3-1-502 Applicant before: Li Yujie |
|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant |