CN102490897A - Multi-driving embedded rotor manned helicopter - Google Patents
Multi-driving embedded rotor manned helicopter Download PDFInfo
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- CN102490897A CN102490897A CN2011104267893A CN201110426789A CN102490897A CN 102490897 A CN102490897 A CN 102490897A CN 2011104267893 A CN2011104267893 A CN 2011104267893A CN 201110426789 A CN201110426789 A CN 201110426789A CN 102490897 A CN102490897 A CN 102490897A
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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 the manned helicopter of a kind of rotor, belong to aviation aircraft manufacturing technology field.
Background technology
At present in aviation and aircraft field; Can take off vertically or aircraft that aloft long period hovers in have only helicopter; But current helicopter rotates the torsional moment that produces for offsetting rotorshaft, prolong the tail rotor that body (elongated tail) is located the anti-torsional moment of device, makes body too huge; And safety factor, rising load, alerting ability and stability are all very low, have limited the flight range and the scope of work of helicopter.
Present " combined type autogiros " or " combined rotor aircraft " etc. also just improve on the basis of traditional heligyro and traditional hang gliding aircraft, and advantage is outstanding, the existence that remains unchanged of its traditional drawback.
" 4 wheel driven moves aircraft " that can see also just is in " model plane " stage, and the one, rotor leaks outside, inadequately safety; The 2nd, do not take the tower structure in cabin, also can't realize the occupant; The 3rd, power drive system is difficult to realize big load.
The manned helicopter of many rotors especially four rotor crafts has been state of the art, its power drive system, rotor system, control system, maneuvering system, with and the flight theory method of operating be prior art.For example the patent No. is that the patent of invention of 201010284234.5 (publication No. CN101973392A, date of publication 2011.02.16) discloses telescopic four rotor crafts of a kind of fuselage, and it is for being provided with four rotors on the criss-cross frame.Original many rotors comprise that the main deficiency of four its existence of rotor is, outside rotor was exposed to, its scope of work was limited under lacking the situation of rotor protection, and alerting ability is not high, and safety factor is little.In addition; Mostly existing four rotor crafts are dummy vehicle; Its power drive system, maneuvering system are comparatively simple; Be not suitable for large-scale many rotors manned craft, and all unexposed Power Train that is applicable to many rotors manned craft of the existing manned craft maneuvering system of unifying, therefore design a kind of many rotors manned craft and develop the suitable Power Train maneuvering system of unifying and still need pay creative work.
Summary of the invention
The objective of the invention is for overcoming the deficiency of above-mentioned prior art, provide that a kind of hoisting force is big, flight safety, flight is promptly stable again flexibly, scope of work the is big manned helicopter of the embedded rotor of many drivings.
For realizing above-mentioned purpose, the present invention adopts following technical proposals:
The manned helicopters of embedded rotor that drive more; Comprise fuselage; Fuselage is provided with driving compartment, and fuselage is provided with a plurality of rotor mounting holes of penetrating circle up and down, is equipped with support in each rotor mounting hole; Support is provided with the rotorshaft that connects power drive system, and rotor is installed on the rotorshaft.
Said fuselage be the dish, driving compartment is arranged on the central authorities of fuselage, can select size as required, a plurality of rotor mounting holes be distributed on driving compartment around.
Said rotor mounting hole is four.Be equipped with a rotor in each rotor mounting hole, form four rotor structures.The quantity of rotor also can be three, five, six ...
Said power drive system comprises driving engine, the transfer rotating shaft that is fixed on fuselage interior, and the transfer rotating shaft comprises transfer rotating shaft I that connects two relative rotorshafts and the transfer rotating shaft II that is connected two other rotorshaft respectively and transfer rotating shaft III; Engine shaft links to each other through pitch wheel with transfer rotating shaft I; Transfer rotating shaft II all links to each other with transfer rotating shaft I through intermeshing cone gear with transfer rotating shaft III.(i.e. " monomotor multiple spot transfer ").
Said engine shaft is provided with the gear I, and transfer rotating shaft I is provided with and gear I pitch wheel II; The middle part of said transfer rotating shaft I is provided with the cone gear I, is respectively equipped with on transfer rotating shaft II and the transfer rotating shaft III and intermeshing cone gear II of cone gear I and cone gear III.
The end of the two ends of said transfer rotating shaft I and transfer rotating shaft II and transfer rotating shaft III all links to each other with rotorshaft through intermeshing cone gear.
The end of the two ends of said transfer rotating shaft I and transfer rotating shaft II and transfer rotating shaft III is equipped with the cone gear IV, and the lower end of rotorshaft is provided with and the intermeshing cone gear V of cone gear IV.
Said power drive system comprises the driving engine that is installed under each rotor, and engine shaft links to each other with corresponding rotorshaft.(i.e. " multiple-motor individual drive ").
The said maneuvering system that the manned helicopter of embedded rotor also comprises control rotor rotation attitude that drives more, maneuvering system comprises the auto-bank unit of being located under each rotor, the auto-bank unit under each rotor all links to each other with total cycle handle; Auto-bank unit under any two relative rotors links to each other with a branch cycle handle; Auto-bank unit under each rotor also links to each other with the collective-pitch lever of control rotor blade inclination angle size.
Said " a plurality of " refer to three and more than; Said power drive system is that the many rotors of multiple spot drive; Be meant that three above independent point set rotor respectively and drive; And can select driving to count according to load or aircraft profile needs, single shaft rotor or diaxon heligyro that this technology is more present have had breakthrough, and have reduced tail rotor.
Said each driving rotor adopts embedded mode, is meant rotor is adopted ring protection, or increase the aircraft body, rotor is installed in the inside of body extension.
This aircraft adopts conventional engine as propulsion source, and when a plurality of rotors adopt synchronously, and when being in horizontal surface and rotating, with equilibratory hoisting force, aircraft is with the floating state of keeping certain height at a plurality of rotors.About translation: when all rotor inclination angles, can realize that aircraft is to all directions translation (stable flat flying); When " two groups " of front and back configurations when opposite inclination angle appears in rotor simultaneously, aircraft will be realized whole rotation (will realize rotary flight if twist aircraft for a long time, this action, employing when only making a stunt flying).About the rotor inclination angle: can take popular method at present; Change the rotor inclination angle through feathering and come, as adopting auto-bank unit (auto-bank unit is that the instruction transformation with chaufeur that passes over through the helicopter flight maneuvering system or autopilot is a kind of device of rotor blade controlled motion); Also can adopt simultaneously the axle head suspension type to install, do whole full-shape with rotating shaft and rotor and incline to putting and realize the rotor disc inclination angle.About going up and down: employing be popular method at present, keeping relying on the inclination angle that changes rotor blade to adjust the size of fuselage lift under the certain situation of gyroplane rotate speed.Chaufeur can be accomplished this operation through collective-pitch lever.When the increase of the blade inclination angle of rotor, aircraft rises; Otherwise aircraft descends.Keep certain height like need, the inclination angle that keeps rotor certain gets final product.About safety: because of adopting the embedded mode of rotor, object around can effectively avoiding rotor to wipe awing hanging has improved the degree of safety that aircraft flies between groups of building and jungle, has increased scope of work and has used industry (can military, civilian, family expenses).About dish shape profile: adopting dish shape profile, is to increase the aircraft coasting ability, to improve the stability of aircraft flight.
The invention has the beneficial effects as follows, drive the manned helicopter of embedded rotor more, on aircraft, adopt a plurality of rotors, the mode of Multipoint Drive (driving more than three), its advantage be flight stability, control flexibly, strong, the VTOL of load-carrying capacity etc.A plurality of rotors are symmetrically distributed in the main body four direction as the direct driving force source, and rotor is in same horizontal surface, and rotor radius, specification are all identical.And with the embedded mode (rotor is played protection) of each driving rotor employing, the safety that improves aircraft.Steering position can be placed on many axle center districts (central authorities of fuselage) that drive fulcrum, also can do suitable moving as required all around.
Description of drawings
Fig. 1 is a side elevational schematic view of the present invention;
Fig. 2 is structural representation of the present invention (" a monomotor multiple spot transfer ");
Fig. 3 is structural representation of the present invention (" a multiple-motor individual drive ");
Fig. 4 is a power transmission system structure scheme drawing of the present invention;
Fig. 5 is a rotorshaft part-structure scheme drawing of the present invention;
Fig. 6 is a maneuvering system structural representation of the present invention.
Wherein 1. fuselages, 2. driving compartment, 3. rotor mounting hole, 4. rotorshaft, 5. rotor, 6. driving engine, 7. support; 8. canopy, 9. perspective window, 10. access hatch, 11. alighting gears, 12. transfer rotating shaft I, 13. transfer rotating shaft II, 14. transfer rotating shaft III; 15. the 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 unit, 23. total cycle handles, 24. fen cycle handle, 25. collective-pitch levers, 26. power-transfer clutchs, 27. brake gears; 28. chaufeur, 29. rotor blades, 30. rotating rings not, 31. rotating rings, 32. control stalks, 33. rotation inclination angles.
The specific embodiment
Below in conjunction with accompanying drawing and embodiment the present invention is further specified.
Embodiment 1 (moving with 4 wheel driven is example, " monomotor multiple spot transfer ")
As shown in Figure 1; The manned helicopters of embedded rotor that drive more; Comprise the fuselage 1 and the fuselage outer that reaches circle of flat " dish ", 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 are placed its below; Fuselage 1 is provided with the rotor mounting holes 3 of four penetrating up and down circles, rotor mounting hole 3 be distributed on driving compartment 2 around.Be equipped with support 7 in each rotor mounting hole 3, support 7 is provided with the rotorshaft 4 that connects power drive system, is equipped with on the rotorshaft 4 to be in conplane rotor 5.Be equipped with a rotor 5 in each rotor mounting hole 3, form four rotor structures.
Said power drive system is a Multipoint Drive.A plurality of rotors, Multipoint Drive is meant to drive (can take the monomotor transfer, also can take the multiple-motor independent drive) more than two.Said each driving rotor adopts embedded mode, is meant rotor 5 is adopted ring protections, or increase the aircraft body, and rotor 5 is installed in internal body.
This aircraft (helicopter) adopts dish shape profile, is to slide remedy the sinkage that transient rises power that rotor 5 occurs reduces to cause in the direction twisting to increase aircraft, improves the stability of aircraft flight.
This machine can adopt conventional engine to drive as drive power source or high capacity high-energy battery, and through transmission shaft and gear combination, driving engine 6 outputting powers is transferred to rotorshaft 4, drives rotor 5 rotations and produces lift.Make this machine obtain more traditional single rotor and the less body extension radius of twin-rotor helicopter; Has bigger raising force, higher flying speed, better flexibility; Enlarged the flight range and effective flying power of helicopter, this machine also has more failure-free safety control.
Dish fuselage such as Fig. 3, the fuselage 1 of its flat dish shape and circular body outer, fairing ace aerodynamic principle has reduced the eddy current of body generation in-flight, increases the aircraft coasting ability, improves the degree of utilization of driving engine kinetic energy; Peculiar profile makes that also helicopter is more elegant in appearance.Central part at fuselage 1 is provided with driving compartment 2, and there is perspective canopy 8 its top, and the below is provided with perspective window 9, is convenient to chaufeur 28 and observes outside.Four rotor mounting holes 3 are evenly distributed in around the fuselage 1, and rotor mounting hole 3 middle parts are provided with erecting frame and are used to install rotor 5, and many moment fulcrum can better be guaranteed the flight stability of helicopter.Below fuselage 1, set out entry hatch 10, fuselage 1 below is provided with four with circle equidistance and retractable landing gear 11.
Said drive is meant 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 fuselage 1 inside; Power is meshed to each rotorshaft 4 transmission through gear and transmission shaft, and rotorshaft 4 drives rotors 5, and driving engine 6 energy outputs are converted into lift.
Said monomotor transfer power drive system is as shown in Figure 4; The monomotor transfer is exactly the process of monomotor power to each rotor transmission power; When driving engine 6 actings are rotated; This power will rotate thereby drive transfer rotating shaft I 12 through 16 engagements of the gear II on gear I on the engine shaft 15 and the transfer rotating shaft I 12, because of the cone gear II 18 on the cone gear I on the transfer rotating shaft I 12 17 and transfer rotating shaft II 13 and the transfer rotating shaft III 14 also is in engagement with cone gear III 19; When driving engine 6 rotates, also will drive transfer rotating shaft I 12 simultaneously and rotate.After transfer rotating shaft I 12 is rotated; The structure of rotorshaft part is 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 rotorshafts 4 rotations with 21 engagements of the cone gear V of rotorshaft 4 lower ends; Be installed in rotor 5 rotations on the rotorshaft 4, make driving engine 6 energy outputs be transferred to rotor 5 and produce the required lift of helicopter.For preventing to quit work aloft because of driving engine 6; The present invention is equipped with brake gear 27 especially in the rear end of power-transfer clutch 26; So that in helicopter decline process; The lifting airscrew rotating speed makes helicopter produce the lift of part, makes the effectively descend attitude of control helicopter of chaufeur 28, the safety when guaranteeing to land.The detailed operation principle of power-transfer clutch and brake gear: as driving engine 6 flame-outs in flight appear; Helicopter will sink, and the helicopter suspense will passively be rotated, and this moment, chaufeur separated power-transfer clutch 26; Start 27 brake gears with handle and linkage; At controlled " rotation " state, make it produce required suspense lift with control helicopter suspense rotating speed, control helicopter and in the decline process, keep stable (avoiding dish installation body image leaf equally to wave the whereabouts); Effectively the descend attitude of control helicopter is guaranteed 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 rotary system are installed on the helicopter support 7, and with front and back with about two groups of (Fig. 1 is as illustration with four rotors) each rotors to being connected.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 opposite, to offset the torsional moment that produces because of rotor 5 rotations, makes the lift of helicopter held stationary.Because of a plurality of rotors 5 (four rotors) installation is in same horizontal surface, when rotor 5 plane of rotations zero inclination angle rotated synchronously, a plurality of rotors 5 (four rotors) were with equilibratory hoisting force.
Realize flight attitude: the one, translation, a plurality of rotors 5 (four rotors) can be realized helicopter any direction translation (flat flying) when same direction inclination angle.As shown in Figure 6, when the not rotating ring 30 of chaufeur 28 through wing group cycle handle or total cycle handle 23 control rotors 5 below auto-bank units 22.Rotating ring 30 can not adjusted the rotation inclination angle 33 of rotor 5.A plurality of rotors 5 (four rotors) are controlled communication apparatus and are collected on same total cycle handle 23; Chaufeur 28 is controlled total cycle during handle 23; A plurality of rotors 5 (four rotors) will produce rotation inclination angle 33 synchronously, and body is produced equidirectional horizontal sliding power, the decision fuselage 1 flat direction that flies.The 2nd, rotate fuselage; With four rotors is example; The two groups of rotors 5 in front and back are controlled communication apparatus and are compiled respectively on two branch cycle handles 24; When chaufeur 28 was controlled through any branch cycle handle 24, " two groups " rotor 5 of front and back configuration produced inconsistent inclination angle, and helicopter fuselage will horizontally rotate (realizing tune); Simultaneously reversing sense is controlled " two groups " rotor 5, and when opposite inclination angle occurring, helicopter is with the original place fast rotational.Also can adopt the axle head suspension type to install, do whole full-shape synchronously with rotating shaft and rotor and incline to putting and realize the rotor disc inclination angle.The 3rd, go up and down: the present invention adopts popular method at present, adjusts fuselage 1 lift size through the inclination angle that changes rotor blade 29.Maneuvering system is as shown in Figure 6, and chaufeur 28 can drive control stalk 32 through collective-pitch lever 25, makes the rotating ring 31 of rotor 5 belows change rotor blade 29 inclination angles size, and when the increase of rotor blade 29 inclination angles, helicopter rises, otherwise helicopter descends.As keep certain height, rotor blade 29 keeps certain inclination angle to get final product.Controlling of 28 pairs of rotor 5 rotation attitudes of chaufeur is to implement (being placed on the below of helicopter framework) through the control system that joystick and communication means (the part communication means is a cable wire) in the driving compartment 2 are formed.Scheme two helicopter flight attitudes can also adopt the same plane that keeps rotor 5 and fuselage 1, through before and after changing or about two groups rotor 5 different rotating speed change lift, and then change the flight attitude of helicopter, accomplish the various flights of helicopter.
About safety: on the one hand; Because of adopting the embedded mode of rotor; Object around can effectively avoiding rotor 5 to wipe awing hanging and impaired has improved the degree of safety that aircraft flies between groups of building and jungle, increased 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 (moving with 4 wheel driven is example, " multiple-motor individual drive ")
As shown in Figure 2; 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 its rotor is installed on each rotorshaft 4; Each driving engine 6 directly drives rotorshaft 4, realizes that the rotor rotation produces lift.The control of driving engine 6 and rotor is implemented control (be placed on the below of helicopter framework) through the control system that joystick and communication means (the part communication means is a cable wire) are formed by chaufeur 28 in driving compartment 2.Other structure is with embodiment 1.
Claims (9)
1. drive the manned helicopter of embedded rotor one kind more; Comprise fuselage, fuselage is provided with driving compartment, it is characterized in that; Fuselage is provided with a plurality of rotor mounting holes of penetrating circle up and down; Be equipped with support in each rotor mounting hole, support is provided with the rotorshaft that connects power drive system, and rotor is installed on the rotorshaft.
2. the manned helicopter of embedded rotors that drives as claimed in claim 1 is characterized in that said fuselage be dish-shaped more, and driving compartment is arranged on the central authorities of fuselage, a plurality of rotor mounting holes be distributed on driving compartment around.
3. the manned helicopter of embedded rotor that drives as claimed in claim 2 is characterized in that said rotor mounting hole is four more.
4. like each described manned helicopters of embedded rotor that drive of claim 1-3 more; It is characterized in that; Said power drive system comprises driving engine, the transfer rotating shaft that is fixed on fuselage interior, and the transfer rotating shaft comprises transfer rotating shaft I that connects two relative rotorshafts and the transfer rotating shaft II that is connected two other rotorshaft respectively and transfer rotating shaft III; Engine shaft links to each other through pitch wheel with transfer rotating shaft I; Transfer rotating shaft II all links to each other with transfer rotating shaft I through intermeshing cone gear with transfer rotating shaft III.
5. the manned helicopter of embedded rotor that drives as claimed in claim 4 is characterized in that said engine shaft is provided with the gear I more, and transfer rotating shaft I is provided with and gear I pitch wheel II; The middle part of said transfer rotating shaft I is provided with the cone gear I, is respectively equipped with on transfer rotating shaft II and the transfer rotating shaft III and intermeshing cone gear II of cone gear I and cone gear III.
6. the manned helicopter of embedded rotor that drives as claimed in claim 4 is characterized in that the end of the two ends of said transfer rotating shaft I and transfer rotating shaft II and transfer rotating shaft III all links to each other with rotorshaft through intermeshing cone gear more.
7. the manned helicopter of embedded rotor that drives as claimed in claim 4 more; It is characterized in that; The end of the two ends of said transfer rotating shaft I and transfer rotating shaft II and transfer rotating shaft III is equipped with the cone gear IV, and the lower end of rotorshaft is provided with and the intermeshing cone gear V of cone gear IV.
8. like each described manned helicopters of embedded rotor that drive of claim 1-3, it is characterized in that said power drive system comprises the driving engine that is installed under each rotor, engine shaft links to each other with corresponding rotorshaft more.
9. like each described manned helicopters of embedded rotor that drive of claim 1-3 more; It is characterized in that; The said maneuvering system that the manned helicopter of embedded rotor also comprises control rotor rotation attitude that drives more; Maneuvering system comprises the auto-bank unit of being located under each rotor, and the auto-bank unit under each rotor all links to each other with total cycle handle; Auto-bank unit under any two relative rotors links to each other with a branch cycle handle; Auto-bank unit under each rotor also links to each other with the collective-pitch lever of control rotor blade inclination angle size.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201110426789.3A CN102490897B (en) | 2011-12-19 | 2011-12-19 | Multi-driving embedded rotor manned helicopter |
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| CN201110426789.3A CN102490897B (en) | 2011-12-19 | 2011-12-19 | Multi-driving embedded rotor manned helicopter |
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Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103171388A (en) * | 2013-03-18 | 2013-06-26 | 中国人民解放军装甲兵工程学院 | Vertical lifting land-air dual-purpose vehicle |
| 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 |
| CN104229132A (en) * | 2013-06-05 | 2014-12-24 | 倪明旺 | A transmission system of a coaxial propeller-reversing spherical aircraft |
| 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 |
| CN106628209A (en) * | 2017-01-06 | 2017-05-10 | 尚青 | Multi-axis manned 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 |
| CN107010214A (en) * | 2017-05-18 | 2017-08-04 | 阳喜英 | A kind of small-sized manned vehicle |
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| CN101559702A (en) * | 2009-03-27 | 2009-10-21 | 谢雁洲 | Tandem double-duct vertical take-off and landing land-air 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 |
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| US20060196991A1 (en) * | 2005-03-04 | 2006-09-07 | Martin Glenn N | Propulsion device |
| CN101559702A (en) * | 2009-03-27 | 2009-10-21 | 谢雁洲 | Tandem double-duct vertical take-off and landing land-air 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 |
Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103171388A (en) * | 2013-03-18 | 2013-06-26 | 中国人民解放军装甲兵工程学院 | Vertical lifting land-air dual-purpose vehicle |
| 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 |
| CN104229132A (en) * | 2013-06-05 | 2014-12-24 | 倪明旺 | A transmission system of a coaxial propeller-reversing spherical aircraft |
| 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 |
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| Publication number | Publication date |
|---|---|
| CN102490897B (en) | 2014-11-05 |
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