CN106114097A - One can vertical take-off and landing flying car - Google Patents
One can vertical take-off and landing flying car Download PDFInfo
- Publication number
- CN106114097A CN106114097A CN201610488649.1A CN201610488649A CN106114097A CN 106114097 A CN106114097 A CN 106114097A CN 201610488649 A CN201610488649 A CN 201610488649A CN 106114097 A CN106114097 A CN 106114097A
- Authority
- CN
- China
- Prior art keywords
- lifting device
- automobile body
- vertical take
- described lifting
- flying car
- 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
- B60—VEHICLES IN GENERAL
- B60F—VEHICLES FOR USE BOTH ON RAIL AND ON ROAD; AMPHIBIOUS OR LIKE VEHICLES; CONVERTIBLE VEHICLES
- B60F5/00—Other convertible vehicles, i.e. vehicles capable of travelling in or on different media
- B60F5/02—Other convertible vehicles, i.e. vehicles capable of travelling in or on different media convertible into aircraft
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Transportation (AREA)
- Mechanical Engineering (AREA)
- Toys (AREA)
Abstract
The present invention relates to one can vertical take-off and landing flying car, it includes automobile body and the lifting device being arranged on described automobile body, its key technology is: described lifting device is two, and two described lifting devices are symmetricly set in the left and right sides of described automobile body, described lifting device is connected with described automobile body by connecting assembly, described connection assembly drives described lifting device rotate in space and tilt, it is achieved the balance of flight attitude and adjustment.Lifting device of the present invention is symmetrically arranged, and blade is oppositely oriented, and moment of torsion is offset, and makes whole system simplify, compact dimensions；The duct of lifting device can improve aeroperformance, simultaneously it can be avoided that the blade tip rotated touches people out of my cabin or thing, promotes safety；Lifting device can adjust (move forward and backward, vert, folding and unfolding) on various dimensions, it is achieved gesture stability, adapts to the different conditions requirement under mode motor, offline mode.
Description
Technical field
The present invention relates to flight instruments technical field, particularly relating to one can vertical take-off and landing flying car.
Background technology
Hovercar is a kind of can to possess certain load-carrying energy at land locomotion and the multifunctional vehicle of airflight
Power.For vertically taking off and landing flyer is compared to tradition fixed wing airplane and conventional helicopter, have the advantage that
1, for compared to tradition fixed wing airplane, it is not necessary to plane track can realize landing of taking off, have landing flexibly, times
It is engaged in adaptable feature.
2, for compared to conventional helicopter, vertically taking off and landing flyer rotor size and aircraft size are less, and have
Duct (or other form structure) protection rotor, has the advantages that safety is good, be suitable to complex environment operation.
Therefore, vertically taking off and landing flyer is at the rescue of the natural disaster such as fire rescue, earthquake, battlefield rescue, complicated landform thing
The fields such as money and personnel's delivery, convention traffic all have broad application prospects.
Domestic and international market is all without matured product at present, is limited by technology, cost, and the hovercar of normal domestic use is still in structure
Think the stage.Current technical scheme or conception mainly have fixed-wing, single rotor, many rotors to be overall plan.
There is problems in that fixed-wing scheme requires higher for landing condition；Single rotor actually by helicopter with
The combination of automobile, is limited by rotor size, and miniaturization is relatively difficult, and what additionally moment of torsion needs produced by single rotor were extra is
System is balanced the tail-rotor of helicopter (similar), and control system complexity is high, and when wing tip rotates, easily people or thing to surrounding makes
Become harm；In many rotors scheme, rotor quantity is conducive to the balance of flight attitude, but quantity increase after system complexity, cost
Also can increase accordingly, reliability reduces, and cabinet size excessive also causing cannot take into account offline mode and land locomotion pattern simultaneously
Requirement.
Summary of the invention
The technical problem to be solved is to provide one can VTOL, the small and exquisite hovercar flexibly of body.
For solving the problems referred to above, the technical solution used in the present invention is:
One can vertical take-off and landing flying car, it includes automobile body and the lifting device being arranged on described automobile body, its
Key technology is: described lifting device is two, and two described lifting devices are symmetricly set in a left side for described automobile body
Right both sides, described lifting device is connected with described automobile body by connecting assembly, and described connection assembly drives described lifting to fill
Put and rotate in space and tilt, it is achieved the balance of flight attitude and adjustment.
Further, described connection assembly can in the range of limiting anterior-posterior translation, simultaneously can be around the deflection of a plurality of axis or incline
Tiltedly.
Further, described connection assembly passes through motor or hydraulic-driven.
Further, two described lifting devices can fold under the drive connecting assembly to be packed up, and reduces accounting for of space
With.
Further, described lifting device uses rotary wind type or jet-propelled lifting device.
Further, described lifting device is rotary wind type lifting device, and it includes duct and is arranged in described duct
Blade, is each provided with one group of blade, and blade steering described in two groups is contrary in each lifting device, or each described lifting fills
It is respectively provided with two groups of blades 4 in putting, and two groups of blades 4 in each lifting device turn on the contrary.
Use and have the beneficial effects that produced by technique scheme:
The present invention uses two lifting devices in left and right, and overall structure is simple, and control system is simple, it is possible to realize VTOL, rises
Fall process is less to space and site requirements, easy to use.
Two lifting device overall structure sizes of the present invention are less, decrease potential safety hazard, it is possible to narrow in running
Use in little space.
Two lifting devices can the translation of various dimensions in space, rotate and tilt, on the one hand device can be made to fly
It is in poised state during row, on the other hand can control device at flight course by the rotation of lifting device and inclination
In attitude, it is achieved VTOL, hovering with to front/rear flight.Additionally lifting device can also overall be received under mode motor
Rise, reduce space hold, to adapt to travel on existing road.
Accompanying drawing explanation
In order to be illustrated more clearly that the specific embodiment of the invention or technical scheme of the prior art, below will be to specifically
In embodiment or description of the prior art, the required accompanying drawing used is briefly described, it should be apparent that, in describing below
Accompanying drawing is some embodiments of the present invention, for those of ordinary skill in the art, before not paying creative work
Put, it is also possible to obtain other accompanying drawing according to these accompanying drawings.
Fig. 1 is the present invention structural representation in road traveling state.
Fig. 2 is the structural representation of vertical lift state of the present invention.
Fig. 3 is the structural representation of flight course state of the present invention.
Fig. 4 is the structural representation that the present invention is provided with airvane.
Wherein: 1 automobile body, 2 connection assembly, 3 ducts, 4 blades, 5 ground floor airvanes, 6 second layer airvanes.
Detailed description of the invention
For making the object, technical solutions and advantages of the present invention clearer, below in conjunction with the accompanying drawings with specific embodiment to sending out
Bright carry out clear, complete description.
One as Figure 1-3 can vertical take-off and landing flying car, it include automobile body 1 and be arranged on described automobile this
Lifting device on body 1, described lifting device is two, and two described lifting devices are symmetricly set in described automobile body 1
The left and right sides, described lifting device is connected with described automobile body 1 by connecting assembly 2, described in described connection assembly 2 drives
Lifting device rotates in space and tilts, it is achieved the balance of flight attitude and adjustment.Described lifting device employing rotary wind type, two
Individual described lifting device is driven through power transmission shaft by a set of dynamical system.If each lifting device uses one group of rotor,
Then the rotor wing rotation of two lifting devices is on the contrary, and moment of torsion is cancelled out each other.
Described lifting device includes duct 3 and the blade 4 being arranged in described duct 3, respectively arranges in each lifting device
There is one group of blade 4, and blade 4 described in two groups turns on the contrary, or each described lifting device is respectively provided with two groups of blades 4, and
Two groups of blades 4 in each lifting device turn on the contrary, then moment of torsion is just cancelled out each other inside each lifting device, it is possible to real
The balance of existing vehicle body.
Described connection assembly 2 uses by motor or hydraulically powered connection assembly, in motor or the control of hydraulic system
Under, connect assembly and drive lifting device can horizontally rotate and movable, see Fig. 2, automobile take off or land time
Waiting, the plane at the port place of duct 3 is parallel with ground level, i.e. the axis of duct 3 is vertical with ground level, when it horizontally rotates
After, as it is shown on figure 3, duct 3 port place plane is in a certain angle with ground level, lifting device produces horizontal direction to automobile
Power, it is possible to make automobile flight forward.Lifting device is movable can be adapted to centre of gravity of vehicle skew, but does not change culvert
The plane at the port place in road 3 and the corner dimension of ground level.Concrete, described connection assembly can use multi-spindle machining hands.
As it is shown in figure 1, two described lifting devices can fold under the drive connecting assembly 2 and pack up, reduce space
Take, be that automobile is travel when on road surface, it is possible to more flexible.
Hovercar of the present invention is additionally provided with attitude-adjusting system.Concrete, in the present embodiment, described attitude
Guiding mechanism includes being arranged on the ground floor airvane 5 below duct 3 and second layer airvane 6.The rudder sheet of ground floor airvane 5
Axle is installed and is parallel to the direction of advance (longitudinally mounted) of automobile, before the rudder sheet installation axle of second layer airvane 6 is perpendicular to automobile
Enter direction (being transversely mounted).
The second layer airvane 6 of the left and right sides is simultaneously when equidirectional deflects, and acquisition is bowed by aircraft (hovercar)
Face upward moment, obtain the power flown forward or backward simultaneously.When left and right sides second layer airvane 6 deflects simultaneously round about,
Aircraft will obtain yawing.When left side ground floor airvane 5 or right side ground floor airvane 5 deflect, aircraft will obtain
Rolling moment, obtains the power flown to the left or to the right simultaneously.Control the deflection angle of left and right sides airvane, direction simultaneously,
To can obtain the control moment of aircraft all directions under complicated flight environment of vehicle and attitude.
Last it is noted that above example is only in order to illustrate technical scheme, it is not intended to limit；Although
With reference to previous embodiment, the present invention is described in detail, it will be understood by those within the art that: it still may be used
So that the technical scheme described in previous embodiment to be modified, or wherein portion of techniques feature is carried out equivalent；And
These amendments or replacement, do not make the essence of appropriate technical solution depart from spirit and the model of embodiment of the present invention technical scheme
Enclose.
Claims (6)
1. can a vertical take-off and landing flying car, it includes automobile body (1) and the lifting being arranged on described automobile body (1)
Device, it is characterised in that: described lifting device is two, and two described lifting devices are symmetricly set in described automobile body
(1) the left and right sides, described lifting device is connected with described automobile body (1) by connecting assembly (2), described connection assembly
(2) described lifting device is driven to rotate in space and tilt, it is achieved the balance of flight attitude and adjustment.
One the most according to claim 1 can vertical take-off and landing flying car, it is characterised in that: described connection assembly (2) can
Anterior-posterior translation in the range of limiting, simultaneously can be around the deflection of a plurality of axis or inclination.
One the most according to claim 2 can vertical take-off and landing flying car, it is characterised in that: described connection assembly is by electricity
Machine or hydraulic-driven.
One the most according to claim 1 can vertical take-off and landing flying car, it is characterised in that: two described lifting device energy
Enough under the drive connecting assembly (2), folding is packed up, and reduces taking of space.
One the most according to claim 1 can vertical take-off and landing flying car, it is characterised in that: described lifting device uses rotation
Wing formula or jet-propelled lifting device.
One the most according to claim 1 can vertical take-off and landing flying car, it is characterised in that: described lifting device is rotor
Formula lifting device, it includes duct (3) and the blade (4) being arranged in described duct (3), respectively sets in each described lifting device
It is equipped with one group of blade (4), and described in two groups, blade (4) turns on the contrary, or each described lifting device is respectively provided with two groups of leaves
Sheet (4), and two groups of blades (4) in each lifting device turn on the contrary.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610488649.1A CN106114097A (en) | 2016-06-29 | 2016-06-29 | One can vertical take-off and landing flying car |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610488649.1A CN106114097A (en) | 2016-06-29 | 2016-06-29 | One can vertical take-off and landing flying car |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN106114097A true CN106114097A (en) | 2016-11-16 |
Family
ID=57285000
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610488649.1A Pending CN106114097A (en) | 2016-06-29 | 2016-06-29 | One can vertical take-off and landing flying car |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106114097A (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108177784A (en) * | 2017-12-14 | 2018-06-19 | 顺丰科技有限公司 | Attachment device and ducted fan and unmanned plane on power-equipment |
| AT520144A1 (en) * | 2017-06-22 | 2019-01-15 | Werner Dipl Ing Holzer | SWIVELING PROPELLER PROTECTION FRAME WITH INTEGRATED ELECTRICALLY DRIVEN PROPELLERS |
| CN109606042A (en) * | 2019-01-23 | 2019-04-12 | 南昌航空大学 | A kind of land, water and air three-purpose vehicle |
| CN112141342A (en) * | 2020-10-20 | 2020-12-29 | 叶殊钨 | Cargo aircraft with multiple rotary wings |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2790824Y (en) * | 2005-05-16 | 2006-06-28 | 沙庆军 | Liftable double-aerovane land-space dual-purpose air craft |
| WO2006066561A1 (en) * | 2004-12-23 | 2006-06-29 | Julian Kuntz | Flying device with improved maneuverability on the ground |
| US7472863B2 (en) * | 2004-07-09 | 2009-01-06 | Steve Pak | Sky hopper |
| CN101628532A (en) * | 2008-07-14 | 2010-01-20 | 陈昌志 | flying automobile |
| CN202319771U (en) * | 2011-11-07 | 2012-07-11 | 上海工程技术大学 | Air-land dual-purpose aircraft |
| US20130068876A1 (en) * | 2011-09-16 | 2013-03-21 | Bogdan Radu | Flying Vehicle |
-
2016
- 2016-06-29 CN CN201610488649.1A patent/CN106114097A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7472863B2 (en) * | 2004-07-09 | 2009-01-06 | Steve Pak | Sky hopper |
| WO2006066561A1 (en) * | 2004-12-23 | 2006-06-29 | Julian Kuntz | Flying device with improved maneuverability on the ground |
| CN2790824Y (en) * | 2005-05-16 | 2006-06-28 | 沙庆军 | Liftable double-aerovane land-space dual-purpose air craft |
| CN101628532A (en) * | 2008-07-14 | 2010-01-20 | 陈昌志 | flying automobile |
| US20130068876A1 (en) * | 2011-09-16 | 2013-03-21 | Bogdan Radu | Flying Vehicle |
| CN202319771U (en) * | 2011-11-07 | 2012-07-11 | 上海工程技术大学 | Air-land dual-purpose aircraft |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| AT520144A1 (en) * | 2017-06-22 | 2019-01-15 | Werner Dipl Ing Holzer | SWIVELING PROPELLER PROTECTION FRAME WITH INTEGRATED ELECTRICALLY DRIVEN PROPELLERS |
| CN108177784A (en) * | 2017-12-14 | 2018-06-19 | 顺丰科技有限公司 | Attachment device and ducted fan and unmanned plane on power-equipment |
| CN109606042A (en) * | 2019-01-23 | 2019-04-12 | 南昌航空大学 | A kind of land, water and air three-purpose vehicle |
| CN112141342A (en) * | 2020-10-20 | 2020-12-29 | 叶殊钨 | Cargo aircraft with multiple rotary wings |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN204452934U (en) | The double mode aircraft of rotor, fixed-wing | |
| CN205131649U (en) | Multi -axis aircraft | |
| US10005554B2 (en) | Unmanned aerial vehicle | |
| CN205916329U (en) | Coaxial double -oar unmanned vehicles | |
| KR20130026506A (en) | Personal aircraft | |
| CN105292460A (en) | Tilt-rotor based on combination of four rotor wings and fixed wing | |
| CN204660020U (en) | One is distributed independently controls multi-rotor aerocraft | |
| CN102120489A (en) | Tilt ducted unmanned aerial vehicle | |
| CN106114097A (en) | One can vertical take-off and landing flying car | |
| CN103332293A (en) | Tilting double-duct subminiature unmanned plane | |
| CN204916182U (en) | High -speed vertical take -off and landing aircraft | |
| CN104058093A (en) | Novel tiltable rotor wing vertical take-off and landing plane | |
| CN105480416A (en) | Unmanned aerial vehicle with tilted rotors | |
| CN204642152U (en) | New oil moves many rotors plant protection unmanned plane | |
| CN102490897B (en) | Multi-driving embedded rotor manned helicopter | |
| CN104590555A (en) | Electrodynamic multi-rotor helicopter | |
| CN105711827A (en) | Oil and electricity hybrid power multi-rotor aircraft | |
| CN106945829A (en) | A kind of universal hinge duct double-rotor aerobat | |
| CN108501639A (en) | A kind of hovercar | |
| CN110040248A (en) | A kind of vertically taking off and landing flyer | |
| CN204548500U (en) | A kind of can vertical takeoff and landing, hovering, flight and road driving aircraft | |
| CN106697257B (en) | A kind of tiltrotor aircraft structure | |
| CN106114852A (en) | A kind of cross-arranging type dual-culvert vertical take-off and landing Spacecraft Attitude Control | |
| CN105523182A (en) | Vertaplane with front tilting rotor wing and rear tilting rotor wing | |
| CN205418095U (en) | Many rotor crafts of oil -electricity hybrid vehicle |
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 | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20161116 |