CN103496305A - Hovercar - Google Patents
Hovercar Download PDFInfo
- Publication number
- CN103496305A CN103496305A CN201310131317.4A CN201310131317A CN103496305A CN 103496305 A CN103496305 A CN 103496305A CN 201310131317 A CN201310131317 A CN 201310131317A CN 103496305 A CN103496305 A CN 103496305A
- Authority
- CN
- China
- Prior art keywords
- wing
- hovercar
- vehicle body
- rear wing
- pair
- 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
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 abstract description 15
- 238000003491 array Methods 0.000 description 9
- 241000272517 Anseriformes Species 0.000 description 6
- 238000005516 engineering process Methods 0.000 description 5
- 230000007306 turnover Effects 0.000 description 5
- 238000000034 method Methods 0.000 description 4
- 230000005855 radiation Effects 0.000 description 4
- 230000007547 defect Effects 0.000 description 3
- 230000000694 effects Effects 0.000 description 3
- 238000007667 floating Methods 0.000 description 3
- 230000006872 improvement Effects 0.000 description 3
- 230000008569 process Effects 0.000 description 3
- 230000007704 transition Effects 0.000 description 3
- 238000013459 approach Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 2
- 230000008878 coupling Effects 0.000 description 2
- 238000010168 coupling process Methods 0.000 description 2
- 238000005859 coupling reaction Methods 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 230000005484 gravity Effects 0.000 description 2
- 238000009434 installation Methods 0.000 description 2
- 238000005096 rolling process Methods 0.000 description 2
- 238000007789 sealing Methods 0.000 description 2
- 239000007921 spray Substances 0.000 description 2
- 238000005728 strengthening Methods 0.000 description 2
- 241001672694 Citrus reticulata Species 0.000 description 1
- 241000127225 Enceliopsis nudicaulis Species 0.000 description 1
- 208000001613 Gambling Diseases 0.000 description 1
- 230000006978 adaptation Effects 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 238000002485 combustion reaction Methods 0.000 description 1
- 238000011109 contamination Methods 0.000 description 1
- 230000003028 elevating effect Effects 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 239000007789 gas Substances 0.000 description 1
- 230000008676 import Effects 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 230000007246 mechanism Effects 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 238000012856 packing Methods 0.000 description 1
- 230000000087 stabilizing effect Effects 0.000 description 1
- 239000002912 waste gas Substances 0.000 description 1
Images
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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C37/00—Convertible aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/02—Aircraft characterised by the type or position of power plants
- B64D27/30—Aircraft characterised by electric power plants
- B64D27/35—Arrangements for on-board electric energy production, distribution, recovery or storage
- B64D27/353—Arrangements for on-board electric energy production, distribution, recovery or storage using solar cells
-
- 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
- Y02T10/7072—Electromobility specific charging systems or methods for batteries, ultracapacitors, supercapacitors or double-layer capacitors
-
- 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
- Y02T50/00—Aeronautics or air transport
- Y02T50/50—On board measures aiming to increase energy efficiency
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Transportation (AREA)
- Mechanical Engineering (AREA)
- Other Liquid Machine Or Engine Such As Wave Power Use (AREA)
- Motorcycle And Bicycle Frame (AREA)
Abstract
The invention discloses a hovercar with folding wings, wherein the hovercar is in a serial aerodynamic layout. The hovercar comprises a hovercar body, wheels installed on the lower portion of the hovercar body, main wings which are installed on the two sides of the hovercar body and can produce upward lift force and a propeller which is installed on the hovercar body and can produce push force. The front wings and the rear wings are all the main wings with large wing areas and long wingspans. When the wings of the hovercar are unfolded, the front wings and the rear wings constitute a longitudinal serial aerodynamic layout along the hovercar body and together produce upward lift force. When the wings of the hovercar are folded, the front wings are turned and folded to be on the two sides of the hovercar body, and the rear wings are turned and folded to be on the top of the hovercar body or the two sides of the hovercar body. The surfaces of the wings and the surface of the hovercar body are provided with large-area solar cell panels, the whole car becomes a large solar charger, and the endurance is improved. The invention further provides a hovercar vertically taking off and landing and a hovercar capable of being used in water, on land and in air on the basis of the hovercar.
Description
Technical field
The present invention relates to a kind of vehicle, especially a kind of hovercar.
Background technology
Automobile and two kinds of transportation meanss of aircraft are combined, and are long-standing ideas of the mankind.Up to the present, occur many hovercar schemes and some product material objects both at home and abroad, had various design defect more.For example Terrafugia hovercar and the More of the U.S. pause. and Taylor's hovercar can only be called the folded wing aircraft travelled on the Ke highway.The several domestic and international patents the most close with the present invention, as U.S. Patent number US6619584B11, name is called in the patent of " ROAD/AIR VEHICLE " and discloses a kind of hovercar, and Chinese Patent Application No. is CN201110047409.5, open day is on July 27th, 2011, name is called in the patent of " hovercar " and discloses a kind of hovercar, and these two kinds of hovercars have all adopted body forward structure that canard is installed, and body tail is installed the aerodynamic arrangement of main wing.In Flight Vehicle Design, canard is a kind of auxiliary wing, and its Area Ratio host wing is much smaller, only produces a small amount of lift.Above two patents all adopted canard front, main wing after layout type, the pneumatic bearing area that produces in-flight main lift still is mounted in the main wing of body tail, and this aerodynamic arrangement mode will cause the center of gravity apart from each other of the pneumatic focus of wing and hovercar, be difficult to obtain pitching during flight stable.China Patent No. is ZL200920053565.0, Granted publication day is on March 10th, 2010, name is called in the patent of " but two shrouded propeller vertical take-off and landing flying car ", but a kind of vertical take-off and landing flying car is disclosed, rely on the shrouded propeller propelling unit to realize vertical takeoff and landing and horizontal flight, but but without wing, can't long-distance flight.
The waste gas of internal-combustion engines vehicle discharge has caused serious atmospheric contamination.Solar power is reproducible clean energy resource, but, due to fugitiveness, the dispersiveness of solar power, it is to be difficult at present the bottleneck overcome as power that the automobile of stock size size, aircraft, boats and ships etc. directly use solar power.
In a word, above scheme and the better combination that all can't realize automobile and aircraft in kind, also can't solve the difficult problem of direct use solar power as power source.
Summary of the invention
The defect existed for above-mentioned prior art, the technical problem to be solved in the present invention is to provide a kind of hovercar, can be in conjunction with automobile and the two function of aircraft.
The technical matters that the present invention further will solve is to realize vertical takeoff and landing function or land, water and air three function of dwelling.
The technical matters that the present invention further will solve is to solve automobile, aircraft and boats and ships directly to use the problem of solar power as power source.
In order to solve the problems of the technologies described above, the technical solution adopted in the present invention is: adopted a kind of unconventional pneumatic layout---tandem wing aerodynamic arrangement in airplane design, and folded wing technology, design hovercar, realized on the basis that does not substantially increase existing family-sized car size, obtained the required larger wing area that takes off, better solved automobile and aircraft the two in conjunction with this difficult problem for a long time.Further, the present invention adopts left and right front granny rag office and Wheel lifting technology to solve the land, water and air three hovercar design challenges of dwelling.Another improvement of the present invention, utilize tandem wing layout and the engine technology that can vert has solved the vertical take-off and landing flying car design challenges.
The key distinction of tandem wing aerodynamic arrangement and canard aerodynamic arrangement is, the forward and backward wing of tandem wing aerodynamic arrangement is host wing, Main Function is to produce lift, and the canard of canard aerodynamic arrangement is auxiliary wing, Main Function be assisted control or with host wing closely pneumatic coupling to increase the lift of host wing.
The concrete solution of the present invention is: a kind of hovercar, comprise vehicle body, be installed on the wheel of body bottom section, what be installed on the vehicle body both sides can produce the host wing to raising force, and be installed on the propelling unit that can produce thrust on vehicle body, described host wing comprises a pair of front wing and a pair of rear wing, and described a pair of front wing and body forward structure both sides are flexibly connected and the energy folding and retraction, and described a pair of rear wing and body tail both sides are flexibly connected and can folding and retraction.
The wing root of described a pair of front wing is flexibly connected by the front wing frame of front wing connecting device and body forward structure both sides respectively, makes the front wing of expansion to close at the vehicle body both sides after front wing connecting device upset folds.
The wing root of described a pair of rear wing is flexibly connected by the rear wing frame of rear wing connecting device and body tail both sides respectively, makes the rear wing of expansion to close at the vehicle body both sides after rear wing connecting device upset folds.
Rear wing also has another kind of folding mode, the wing root of described a pair of rear wing is flexibly connected by rear wing connecting device and body tail both sides respectively, the inner wing of rear wing and outer wing are flexibly connected by interplane folding device, make the outer wing of the rear wing of expansion can make progress respectively upset realize after the wing doubling, then a pair of rear wing integral body forwards horizontally rotates around the rear wing connecting device of wing root separately, closes at the vehicle body top.
Further, the both sides of described vehicle body also are equipped with the rear wing strut bar be flexibly connected with vehicle body, and after this, the wing strut bar stretches out obliquely, with the inner wing of rear wing, are flexibly connected.
Further, described propelling unit is arranged on tail of body.
Further, described body forward structure a nacelle each side is installed, described propelling unit respectively is installed on each nacelle.
Further, at least one propelling unit is arranged on the front portion of vehicle body, to produce thrust vertically downward; At least one propelling unit is arranged on body tail, and to produce thrust vertically downward, when horizontal flight, the described propelling unit that is arranged on body tail verts approximately 90 °, to produce the required thrust backward of horizontal flight.
Further, upper surface and the lower surface of described a pair of front wing and a pair of rear wing are equipped with solar panel, and the surface of empennage and vehicle body is equipped with solar panel; Battery is installed on vehicle body, and described solar panel and described battery form the associating electric power system.
Further, safety air bag at the bottom of safety air bag and car is installed in escape parachute, car on this hovercar.
beneficial effect
The present invention contrasts prior art and has following beneficial effect:
1. the spacing of front wing, rear wing is large, jointly as main pneumatic bearing area, forms the tandem wing configurations, in-flight, and the mutual balance of moment that the lift of forward and backward wing produces hovercar, and front wing is little to the aerodynamic interference of rear wing;
2. after forward and backward wing-folding is packed up wing, the landing of travelling and take off on the close ，Ke highway of hovercar and family-sized car size, better in conjunction with the two function of automobile and aircraft;
3. the surface at the forward and backward wing of hovercar and each position of vehicle body is equipped with large area solar cell array, after wing launches, whole automobile becomes a large solar charger, direct radiation and the indirec radiation of sunlight have been utilized to greatest extent, self-sustaining and the green non-pollution of power self-support, duration performance is good, and the vehicle that solved stock size directly utilize the difficult problem of solar power as power;
4. another kind of improvement the of the present invention, three hovercars of dwelling have been realized waterborne travelling and the water takeoff landing; Combine automobile, aircraft and boats and ships three's function;
5. another kind of improvement of the present invention, vertical take-off and landing flying car is horizontal flight and the landing of taking off vertically at a distance, combines automobile, fixed wing aircraft, helicopter three's function;
6. complete life saving system is installed on hovercar, has solved the safety problem of family expenses aircraft.
The specific embodiment
Below in conjunction with accompanying drawing, specific embodiments of the present invention are further described in detail.
Fig. 1 is the schematic perspective view of hovercar of the present invention;
Fig. 2 is the wing-folding folding and unfolding principle schematic of hovercar of the present invention;
Fig. 3 is the schematic perspective view after the wing-folding of hovercar of the present invention is packed up;
Fig. 4 is the rear wing strut bar partial schematic diagram of hovercar of the present invention;
Fig. 5 is the present invention three hovercar schematic perspective view of dwelling;
Fig. 6 is that the present invention three hovercar wheel of dwelling is upwards packed up principle schematic;
Fig. 7 is vertical take-off and landing flying car of the present invention, but the tailstock is equipped with the schematic perspective view of two tilting duct driving engines;
But Fig. 8 is the schematic perspective view that vertical take-off and landing flying car of the present invention, the tailstock are equipped with a tilting duct driving engine;
Fig. 9 is the schematic perspective view that vertical take-off and landing flying car of the present invention is packed up wing;
Figure 10 is life saving system work schematic diagram of the present invention.
In figure: 1. vehicle body, 2. wheel, 3. front wing, 4. front wing connecting device, 5. front wing frame, 6. rear wing, 7. rear wing connecting device, 8. rear wing inner wing, 9. rear wing outer wing, 10. interplane folding device, 11. rear wing frame, 12. rear wing strut bar, 13. rear wing strut bar hinge, 14. vertical tail, 15. tailplane, 16. rudder face, 17. propelling unit, 18. nacelle, 19. battery, 20. solar panel, 21. floating drum, 22. but tilting duct propelling unit, 23. vertical takeoff and landing Ducted propeller, 24. upper cover plate, 25. flow deflector, 26. escape parachute, 27. safety air bag in car, 28. safety air bag at the bottom of car.
Embodiment mono-:
Referring to accompanying drawing 1, 2, this hovercar comprises vehicle body 1, front wing 3, rear wing 6, propelling unit 17, wheel 2, vertical tail 14 parts such as grade, vehicle body 1 front part sides is a pair of front wing 3 of capable of turnover folding, vehicle body 1 both sides, rear portion are two secondary rear wings 6 of capable of turnover folding, the wing root of a pair of front wing 3 is flexibly connected by front wing connecting device 4 and the front wing frame 5 of vehicle body 1 front part sides respectively, the wing root of a pair of rear wing 6 is flexibly connected by rear wing connecting device 7 and the vertical pivot of vehicle body 1 both sides, back upper place respectively, rear wing inner wing 8 is connected by interplane hinge folding device 10 with rear wing outer wing 9.The two main wing of series type aerodynamic arrangement before and after these two pairs of wings form along vehicle body 1, the common main pneumatic bearing area as producing lift.Wherein on front wing 3, rear wing 6, vertical tail 14, rudder face 16 is installed, these rudder faces 16 can be used as elevating rudder, aileron, wing flap or other controlsurfaces and use, and also mix and use.
The tailstock of hovercar is installed a propelling unit 17, and propelling unit 17 comprises driving engine and screw propeller, and driving engine can rotate or rotate by the actuator drives screw propeller by direct-driven airscrew, to produce the required power of flight.
From be usually used in strengthening aircraft controllability or produce the coupling whirlpool strengthen host wing lift small-sized auxiliary wing--canard is different, described front wing 3 and rear wing 6 are the host wing of large blade area and the long span, in the present embodiment, the span of front wing 3 is about 6 meters, chord length is about 0.8 meter, wing area is about 5 sq ms, the span of rear wing 6 is about 8 meters, chord length is about 1.1 meters, wing area is about 9 sq ms, the span chord of front like this wing 3 grows to and is equivalent to less more than 60% of rear wing 6, like this, rear two pairs of wing sizes are close, be the host wing of large blade area and the long span, and front wing 3 is connected by front wing connecting device 4 with vehicle body 1 front part sides, and collapsible folding and unfolding.
In the present embodiment, front wing connecting device 4 adopts the diaxon rotor blade fold mechanism identical with American I CON A5 aircraft, wherein the axis of first S. A. is the wing spanwise, the axis of second S. A. is perpendicular to the earth, before packing up during wing 3, the a pair of front wing 3 of horizontality first is turned to wing chord and the basic plumbness of the earth around first S. A., after second axial rotary, rotate again, finally fold and close at vehicle body 1 both sides, at this moment the spanwise of front wing 3 is basically parallel to vehicle body 1 longitudinal axis, and wing chord is substantially vertical with the earth.
Rear wing inner wing 8 and rear wing outer wing 9 are flexibly connected by interplane folding device 10, there is respectively vertical pivot vehicle body 1 both sides, back upper place, vertical pivot firmly is connected with rear wing inner wing 8 through rear wing 6 wing roots, the head of principle and U.S. variable swept back wing fighter plane F-14 is similar, wing can rotate in horizontal surface, realizes folding and retraction.
When the front wing 3 of hovercar and rear wing 6 launch flight, the common lift upwards that produces lifts flight by hovercar, at this moment the common pneumatic focus of equivalence of front wing 3 and rear wing 6 is between front wing 3 and rear wing 6, the center-of-gravity position of hovercar and the position of equivalent pneumatic focus approach and are positioned at the place ahead of the latter, wing produces a pair of balancing torque to the center of gravity of hovercar, before and after principle is similar to, two people gang up in gambling, and front and back lift layout is even like this.This hovercar can obtain enough large gross wing area after having adopted tandem wing aerodynamic arrangement, is enough to allow this hovercar take off smoothly.
As shown in Figure 3, when hovercar is packed up wing, a pair of front wing 3 is folding around front wing connecting device 4 upsets, with the state that the wing chordwise is approximately vertically, spanwise approximately is parallel to the car body longitudinal axis, closes at vehicle body 1 both sides locking; Rear wing outer wing 9 respectively upwards upset realize the wing doubling, rear wing 6 is whole respectively more forwards to be horizontally rotated around the vertical pivot of wing root separately, closes at vehicle body 1 top locking.
Referring to accompanying drawing 4, in order to improve the structure stress of rear wing 6, the rear wing strut bar 12 that after the both sides of vehicle body 1 also are equipped with, wing strut bar hinge 13 connects, rear wing strut bar hinge 13 can adopt spherical linkage, rear wing strut bar 12 stretches out obliquely, with wing strut bar hinge after the lower surface of rear wing inner wing 8 13, be flexibly connected, rear wing strut bar 12 can be accompanied by the folding and unfolding of rear wing 6 and activity.In rear wing 6 rotary courses, during rear wing strut bar 12 length limited, can adopt telescopic support link.
Except folded wing, the present invention also can adopt telescopic wing.
In the time of will taking off on the Dang highway, the front wing 3 of this hovercar and rear wing 4 launch, just become the aircraft of tandem wing configurations, can fly fast at a distance on the Bing highway and take off and land, simultaneously for fear of the interference in air flow of wing 6 after 3 pairs, front wing, front wing 3 can suitably adopt inverted diherdral, rear wing 6 suitably to adopt the dihedral angle in-flight, has realized the independence of aerodynamic characteristic separately.
When this hovercar is packed up wing, oad approaches the normal domestic use car, combine automobile and aircraft the two function and do not there is open defect.
Car door can be arranged on two conventional side positions.Certainly look the installation site of propelling unit 17, car door also can be arranged on vehicle body 1 front portion or rear portion.
For aircraft, lifesaving is the problem that can't avoid.Referring to accompanying drawing 10, complete life saving system is installed on this hovercar, by safety air bag 28 at the bottom of safety air bag 27 and car in escape parachute 26, car, formed.Wherein at least one escape parachute 26 is arranged on vehicle body 1 top and is connected with vehicle body 1 integral structure component; Safety air bag 27 is arranged on crew module inside in several cars, is positioned at the car body in face of cabin inner top and occupant, and the safety air bag that several can instantaneous inflation is installed at the bottom of car.When flight in case of emergency; escape parachute 26 is dished out and is opened; when emergency landing is landed; at the bottom of car, safety air bag 28 is full of immediately gas and ejects; form the air bag buffer zone of vehicle body 1 bottom, alleviate the suffered impulsive force of car body colliding surface, the safe soft landing while realizing the hovercar forced landing; in car, safety air bag 27 is opened simultaneously, protection occupant safety.
Embodiment bis-:
The present embodiment is three hovercars of dwelling, and land, water and air Combination property equilibrium, to meet the needs of living in seashore or area, rivers and lakes people.
Referring to accompanying drawing 5,6, the arranged on left and right sides of described vehicle body 1 front portion respectively is equipped with the nacelle 18 of an inclination, on each inclination nacelle 18, propelling unit 17 respectively is installed, for providing flight required pulling force.Propelling unit 17 is arranged on higher position, vehicle body 1 front portion, apart from water surface certain altitude, and obtains front wing 3 protection of front lower place, and the spray of avoiding splashing damages propelling unit 17.The moment of torsion of cancelling each other during the rotation of the screw propeller of both sides.The bottom of vehicle body 1 is the V-arrangement bottom with ramping angle, described wheel 2 adopts the wheel turnover lift technique adopted on current high speed amphibious vehicle, can allow wheel 2 bend and pack up upward, realized the stream line pattern of vehicle body 1 base profile, while navigating by water in water like this, can reduce to greatest extent resistance in water, realize that high speed waterborne takes off and land; Vehicle body 1 inside is a plurality of water-stop cabin structures, increases resistance to sinking; A pair of floating drum 21 is arranged on left and right front wing 3 belows, increases the stability of hovercar at the water surface.Certainly floating drum 21 also can be arranged on vehicle body 1 down either side, can play stabilizing efficiency equally.
While navigating by water on the water, except propelling unit 17 aerodynamic forces of the left and right sides that can use vehicle body 1 front portion advance, also the underwater scooter as waterjet propulsor one class can be installed at the bottom of car, for water sailing, advance, and spout has vector and turns to and spray function, omit rudder for ship, can realize various water sailing states.
The tailstock has two vertical tails 14 in left and right, a tailplane 15 connects the upper end of two vertical tails 14, form the Three-wing-surface layout, so both strengthened structural strength, and tailplane 15 is as an auxiliary pneumatic bearing area of hovercar, for strengthening aloft stability and road-holding property.Can certainly adopt the empennage of the other types such as vee tail.
In the present embodiment, the front wing 3 of hovercar, the upper surface of rear wing 6 and lower surface are equipped with solar panel 20, comprise described vertical tail 14, tailplane 15 and vehicle body 1 are equipped with solar panel 20 on the surface of interior a plurality of parts, more than payload space can reach tens of sq ms, the direct radiation that the solar panel 20 at the positions such as upper surface of the airfoil and vehicle body 1 top is accepted from sunshine, the solar panel 20 at wing lower surface and vehicle body 1 other positions etc. is accepted the indirec radiation flashed back the sunlight, improved the degree of utilization to solar power, wing launches rear whole automobile like this becomes a huge solar charger, solar panel can obtain at least 10 degree electric energy 20 1 daytimes, be enough to travel nearly hundred kilometers.Solve so cleverly automobile, aircraft, ship straight and scooped out the difficult problem by Driven by Solar Energy, can be in the land or the remote travelling waterborne that lack charging equipment.
The inside of described vehicle body 1 is equipped with battery 19, and described battery 19 is any type batteries that comprise storage battery or fuel cell, and described solar panel 20 and described battery 19 form mixed power supply system.When solar panel 20 power shortages and dull thread are taken in, can switch to the storage battery power supply pattern, or the battery-driven while also utilize solar panel 20 power supplies, in the time of can greatly extending the voyage of hovercar or boat.
In when charging, front wing 3 and rear wing 6 can self adaptation be adjusted upper and lower dihedral degree, make the sunray vertical irradiation aerofoil surface of trying one's best, and improve solar energy power generating usefulness.
Other guide is with embodiment mono-.
Embodiment tri-:
Referring to accompanying drawing 7, a close coupled type twin screw vertical takeoff and landing Ducted propeller 23 is arranged on vehicle body 1 front portion, thrust vertically downward is provided, screw propeller does not rotate vehicle body 1 is produced to moment of torsion in horizontal surface, at duct inlet, two fans and the hinged upper cover plate 24 of vehicle body 1 are set, exhausr port is provided with parallel multiple-piece flow deflector 25 arrays, and flow deflector 25 arrays and vehicle body 1 are flexibly connected.Multiple-piece flow deflector 25 arrays can carry out deflection, to realize rolling in-flight the control of attitude.During horizontal flight, flow deflector 25 arrays of the upper cover plate 24 of duct inlet and exhausr port all carry out deflection, have substantially covered the duct mouth, and sealing vehicle body 1, reduce flight resistance.
But two single screw tilting duct propelling units 22 arranged side by side of the installation of the tailstock, propeller blade hand of rotation separately is contrary, with the moment of torsion of cancelling out each other.By the state of taking off vertically during to the level flight condition transition, two propelling units 17 of the tailstock approximately 90 degree ° that can vert, to produce the required thrust backward of horizontal flight.
When aircraft takes off vertically, open upper cover plate 24 and lower guide flow 25 arrays of anterior vertical takeoff and landing Ducted propeller 23, the front and back driving engine starts simultaneously, produce downward thrust, by hovercar, lifting is liftoff gradually, at this moment before hovercar aloft opens, rear two pairs of wings, start to vert when then but two of the tailstock tilting duct propelling units 22 add high thrust, produce level thrust component backward, so hovercar obtains forward flight speed gradually, wing produce increasing lift and the most at last hovercar lift flight, upper cover plate 24 and lower guide flow 25 are closed, but two tilting duct propelling units 22 of the tailstock are tilted to approximately 90 degree °, at this moment hovercar is in level flight condition.
When by horizontal flight, during to the vertical landing status transition, carrying out above-mentioned inverse process.
Other guide is with above embodiment.
Embodiment tetra-:
Vertical take-off and landing flying car also has another kind of implementation.
Referring to accompanying drawing 8,9, the wing root of a pair of front wing 3 is flexibly connected by front wing connecting device 4 and the front wing frame 5 of vehicle body 1 front part sides respectively, makes the front wing 3 of expansion to close at vehicle body 1 both sides after front wing connecting device 4 upsets fold; The wing root of a pair of rear wing 6 is flexibly connected by rear wing connecting device 7 and the rear wing frame 11 of vehicle body 1 both sides, rear portion respectively, makes the rear wing 6 of expansion to close at vehicle body 1 both sides after rear wing connecting device 7 upsets fold.
A vertical takeoff and landing Ducted propeller 23 is arranged on vehicle body 1 front portion, and screw propeller rotates in horizontal surface, and to produce thrust vertically downward, the outlet of duct is equipped with parallel multiple-piece flow deflector 25 arrays, and flow deflector 25 arrays and vehicle body 1 are flexibly connected.Flow deflector 25 can carry out deflection, carry out water conservancy diversion to becoming a mandarin with downwash flow, reduce duct turnover air-flow resistance or have a mind to increase duct turnover air-flow resistance, the moment of torsion in the time of can offsetting anterior single screw rotation, vehicle body 1 produced, but also can suitably control flow deflector 25 deflections, to realize in-flight to rolling the control of attitude.If flow deflector 25 arrays are fixing drift angles, deflectable pneumatic rudder face 16 can also be installed below screw propeller.
But a coaxial screw propeller tilting duct fan propelling unit 22 is arranged on vehicle body 1 rear portion, in the process of verting, cause moment of torsion can to vehicle body 1 like this.The outlet of duct is equipped with parallel multiple-piece flow deflector 25 arrays equally, works effects such as adjusting vehicle body 1 attitude in the vertical takeoff and landing process.
When by the state of taking off vertically during to the level flight condition transition, approximately 90 degree ° but the tilting duct fan propelling unit 22 of the tailstock verts gradually, make screw propeller turn to produce required rear to thrust of horizontal flight at the plane internal rotation of vertical vehicle body 1 longitudinal axis, after proceeding to horizontal flight fully, but hovercar relies on the tilting duct fan propelling unit 22 of the tailstock to advance fully, and flow deflector 25 array deflection of the upper and lower import and export of the vertical takeoff and landing Ducted propeller 23 of car front portion are to substantially having covered the duct mouth, play pneumatic rectification, sealing vehicle body 1, reduce the effect of flight resistance.
Other guide is with above embodiment.
Below by reference to the accompanying drawings the specific embodiment of the present invention is described; but these explanations can not be understood to limit scope of the present invention; protection scope of the present invention is limited by the claims of enclosing, and any change on the claims in the present invention basis is all in protection scope of the present invention.
Claims (10)
1. a hovercar, comprise vehicle body, be installed on the wheel of body bottom section, what be installed on the vehicle body both sides can produce the host wing to raising force, and be installed on the propelling unit that can produce thrust on vehicle body, and it is characterized in that, described host wing comprises a pair of front wing and a pair of rear wing, described a pair of front wing and body forward structure both sides are flexibly connected and the energy folding and retraction, and described a pair of rear wing and body tail both sides are flexibly connected and can folding and retraction.
2. hovercar according to claim 1, it is characterized in that, the wing root of described a pair of front wing is flexibly connected by the front wing frame of front wing connecting device and body forward structure both sides respectively, makes the front wing of expansion to close at the vehicle body both sides after front wing connecting device upset folds.
3. hovercar according to claim 2, it is characterized in that, the wing root of described a pair of rear wing is flexibly connected by the rear wing frame of rear wing connecting device and body tail both sides respectively, makes the rear wing of expansion to close at the vehicle body both sides after rear wing connecting device upset folds.
4. hovercar according to claim 2, it is characterized in that, the wing root of described a pair of rear wing is flexibly connected by rear wing connecting device and body tail both sides respectively, the inner wing of rear wing and outer wing are flexibly connected by interplane folding device, make the outer wing of the rear wing of expansion can make progress respectively upset realize after the wing doubling, then a pair of rear wing integral body forwards horizontally rotates around the rear wing connecting device of wing root separately, closes at the vehicle body top.
5. hovercar according to claim 4, is characterized in that, the both sides of described vehicle body also are equipped with the rear wing strut bar be flexibly connected with vehicle body, and after this, the wing strut bar stretches out obliquely, with the inner wing of rear wing, is flexibly connected.
6. according to the described hovercar of claim 3 or 4, it is characterized in that, described propelling unit is arranged on tail of body.
7. according to the described hovercar of claim 3 or 4, it is characterized in that, described body forward structure a nacelle each side is installed, described propelling unit respectively is installed on each nacelle.
8. according to the described hovercar of claim 3 or 4, it is characterized in that, at least one propelling unit is arranged on the front portion of vehicle body, to produce thrust vertically downward; At least one propelling unit is arranged on body tail, and to produce thrust vertically downward, when horizontal flight, the described propelling unit that is arranged on body tail verts approximately 90 °, to produce the required thrust backward of horizontal flight.
9. according to the described hovercar of claim 3 or 4, it is characterized in that, upper surface and the lower surface of described a pair of front wing and a pair of rear wing are equipped with solar panel, and the surface of empennage and vehicle body is equipped with solar panel; Battery is installed on vehicle body, and described solar panel and described battery form the associating electric power system.
10. according to the described hovercar of claim 3 or 4, it is characterized in that, safety air bag at the bottom of safety air bag and car is installed on this hovercar in escape parachute, car.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310131317.4A CN103496305A (en) | 2012-04-24 | 2013-04-16 | Hovercar |
Applications Claiming Priority (5)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2012101217859A CN102616096A (en) | 2012-04-24 | 2012-04-24 | Solar flying automobile with folding wings |
| CN201210121785.9 | 2012-04-24 | ||
| CN201210439198.4 | 2012-11-07 | ||
| CN201210439198 | 2012-11-07 | ||
| CN201310131317.4A CN103496305A (en) | 2012-04-24 | 2013-04-16 | Hovercar |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN103496305A true CN103496305A (en) | 2014-01-08 |
Family
ID=49482199
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201310131317.4A Pending CN103496305A (en) | 2012-04-24 | 2013-04-16 | Hovercar |
Country Status (2)
| Country | Link |
|---|---|
| CN (1) | CN103496305A (en) |
| WO (1) | WO2013159672A1 (en) |
Cited By (21)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2015127902A1 (en) * | 2014-02-28 | 2015-09-03 | 武汉蓝天翔航空科技有限公司 | Flying car |
| CN105329056A (en) * | 2015-11-24 | 2016-02-17 | 宁波市镇海怡福莱文化创意有限公司 | Wheel type rotor wing vehicle |
| CN106043082A (en) * | 2016-06-15 | 2016-10-26 | 陈昌志 | Flying ambulance car |
| CN107471936A (en) * | 2017-09-21 | 2017-12-15 | 张龙 | Hovercar |
| CN107651186A (en) * | 2017-08-29 | 2018-02-02 | 深圳市华力航空科技有限公司 | A kind of electric power aerodone |
| CN107757273A (en) * | 2017-09-27 | 2018-03-06 | 北京航空航天大学 | A kind of hovercar |
| CN107984992A (en) * | 2017-11-28 | 2018-05-04 | 北京航空航天大学 | It is a kind of can VTOL land and air double-used vehicle |
| CN108128453A (en) * | 2018-01-08 | 2018-06-08 | 浙江大学 | A kind of air-sea dual-purpose solar unmanned plane and its control method |
| CN108146169A (en) * | 2017-11-28 | 2018-06-12 | 北京航空航天大学 | The land and air double-used vehicle of folding after a kind of wing |
| CN108215685A (en) * | 2018-01-12 | 2018-06-29 | 赵锟乔 | A kind of multifunctional traffic means |
| CN108528162A (en) * | 2018-06-15 | 2018-09-14 | 中宇航通（北京）科技有限公司 | The telescopic empennage mechanism of hovercar and hovercar |
| CN108883827A (en) * | 2016-01-29 | 2018-11-23 | Jg创业企业有限责任公司 | Aviation automobile and correlated characteristic |
| CN108899889A (en) * | 2018-09-11 | 2018-11-27 | 东汉太阳能无人机技术有限公司 | Power supply system and aircraft |
| WO2019205186A1 (en) * | 2018-04-28 | 2019-10-31 | 深圳市元征软件开发有限公司 | Amphibious transport device |
| CN110466297A (en) * | 2018-10-25 | 2019-11-19 | 长城汽车股份有限公司 | A kind of hovercar and hovercar control method |
| CN110612253A (en) * | 2017-05-11 | 2019-12-24 | S·克莱因 | Method for converting a motor vehicle for ground and air transport, motor vehicle |
| WO2021064475A1 (en) * | 2020-01-10 | 2021-04-08 | Hazeri Majid | Vehicle with the ability to move on land, air and water |
| CN113212751A (en) * | 2021-06-11 | 2021-08-06 | 江西洪都航空工业股份有限公司 | Air-ground dual-purpose aircraft |
| CN113840742A (en) * | 2019-05-07 | 2021-12-24 | 恩福特公司 | Traveling and flying electric and hybrid VTOL vehicle |
| CN114684360A (en) * | 2022-04-08 | 2022-07-01 | 西安泽盛航空科技有限公司 | Tandem type double-duct propulsion unmanned aerial vehicle |
| WO2023177774A1 (en) * | 2022-03-17 | 2023-09-21 | Nft Inc. | Hybrid road-air vehicle |
Families Citing this family (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103692873B (en) * | 2013-12-20 | 2015-11-18 | 胡新如 | A kind of land and water hovercar |
| LT6221B (en) * | 2014-02-05 | 2015-10-26 | Uab "Globalios Technoidėjos" | Aerodynamic simulator |
| CN105711361A (en) * | 2016-04-21 | 2016-06-29 | 陈昌志 | New energy source triphibian flying car |
| CN106364269B (en) * | 2016-10-25 | 2018-12-25 | 绍兴晨唯烫印箔膜有限公司 | A kind of sea is dashed forward anti-aircraft |
| CN114212238B (en) * | 2021-12-30 | 2022-09-06 | 哈尔滨工业大学 | High-altitude long-endurance unmanned aerial vehicle with foldable telescopic wings |
| TR2021022082A2 (en) * | 2021-12-31 | 2022-01-21 | İstanbul Geli̇şi̇m Üni̇versi̇tesi̇ | VERTICAL LANDING AND TAKING FLYING CAR |
| CN115157944A (en) * | 2022-06-30 | 2022-10-11 | 中国航天空气动力技术研究院 | Solar energy range-extending electric aerocar |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1051328A (en) * | 1989-10-30 | 1991-05-15 | 孙万杰 | Light transport vehicle is adapted to the method and apparatus that travels in land, water and air |
| US20030094536A1 (en) * | 2001-10-25 | 2003-05-22 | Labiche Mitchell G. | Flyable automobile |
| DE202006017959U1 (en) * | 2006-11-23 | 2007-03-01 | Sieksmeier, Sebastian | Conversion airplane e.g. canard airplane, for use as e.g. car, has outer and inner wing parts fixed on sets of location points in body such that common centroids of parts are found remote from centroid of airplane at distances, respectively |
| CN1948034A (en) * | 2005-10-10 | 2007-04-18 | 杨福根 | Car-plane running, lifting-off or landing on road |
| US20110042507A1 (en) * | 2009-08-19 | 2011-02-24 | Seiford Sr Donald S | Convertible Vehicle For Road, Air, and Water Usage |
| DE102009060611A1 (en) * | 2009-12-28 | 2011-06-30 | Käser, Uwe, 69427 | Vehicle i.e. inflatable flight, for transportation on public road, has inflatable and/or telescopic profile segments swiveling out bearing surface and forming fully span width and profile geometry |
| US20120048989A1 (en) * | 2010-08-27 | 2012-03-01 | David John Howard Eames | Roadable aircraft |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN201941539U (en) * | 2010-12-15 | 2011-08-24 | 李广山 | Wing craft |
| CN102616096A (en) * | 2012-04-24 | 2012-08-01 | 赵辉 | Solar flying automobile with folding wings |
-
2013
- 2013-04-16 CN CN201310131317.4A patent/CN103496305A/en active Pending
- 2013-04-18 WO PCT/CN2013/074370 patent/WO2013159672A1/en active Application Filing
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1051328A (en) * | 1989-10-30 | 1991-05-15 | 孙万杰 | Light transport vehicle is adapted to the method and apparatus that travels in land, water and air |
| US20030094536A1 (en) * | 2001-10-25 | 2003-05-22 | Labiche Mitchell G. | Flyable automobile |
| CN1948034A (en) * | 2005-10-10 | 2007-04-18 | 杨福根 | Car-plane running, lifting-off or landing on road |
| DE202006017959U1 (en) * | 2006-11-23 | 2007-03-01 | Sieksmeier, Sebastian | Conversion airplane e.g. canard airplane, for use as e.g. car, has outer and inner wing parts fixed on sets of location points in body such that common centroids of parts are found remote from centroid of airplane at distances, respectively |
| US20110042507A1 (en) * | 2009-08-19 | 2011-02-24 | Seiford Sr Donald S | Convertible Vehicle For Road, Air, and Water Usage |
| DE102009060611A1 (en) * | 2009-12-28 | 2011-06-30 | Käser, Uwe, 69427 | Vehicle i.e. inflatable flight, for transportation on public road, has inflatable and/or telescopic profile segments swiveling out bearing surface and forming fully span width and profile geometry |
| US20120048989A1 (en) * | 2010-08-27 | 2012-03-01 | David John Howard Eames | Roadable aircraft |
Cited By (26)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2015127902A1 (en) * | 2014-02-28 | 2015-09-03 | 武汉蓝天翔航空科技有限公司 | Flying car |
| CN105329056A (en) * | 2015-11-24 | 2016-02-17 | 宁波市镇海怡福莱文化创意有限公司 | Wheel type rotor wing vehicle |
| CN108883827A (en) * | 2016-01-29 | 2018-11-23 | Jg创业企业有限责任公司 | Aviation automobile and correlated characteristic |
| US11420739B2 (en) | 2016-01-29 | 2022-08-23 | JG Entrepreneurial Enterprises LLC | Aeronautical car and associated features |
| US10787256B2 (en) | 2016-01-29 | 2020-09-29 | Lta Corporation | Aeronautical car and associated features |
| EP3408173A4 (en) * | 2016-01-29 | 2019-11-20 | JG Entrepreneurial Enterprises LLC | Aeronautical car and associated features |
| US11713115B2 (en) | 2016-01-29 | 2023-08-01 | JG Entrepreneurial Enterprises LLC | Aeronautical car and associated features |
| CN106043082A (en) * | 2016-06-15 | 2016-10-26 | 陈昌志 | Flying ambulance car |
| CN110612253A (en) * | 2017-05-11 | 2019-12-24 | S·克莱因 | Method for converting a motor vehicle for ground and air transport, motor vehicle |
| CN107651186A (en) * | 2017-08-29 | 2018-02-02 | 深圳市华力航空科技有限公司 | A kind of electric power aerodone |
| CN107471936A (en) * | 2017-09-21 | 2017-12-15 | 张龙 | Hovercar |
| CN107757273A (en) * | 2017-09-27 | 2018-03-06 | 北京航空航天大学 | A kind of hovercar |
| CN108146169A (en) * | 2017-11-28 | 2018-06-12 | 北京航空航天大学 | The land and air double-used vehicle of folding after a kind of wing |
| CN107984992A (en) * | 2017-11-28 | 2018-05-04 | 北京航空航天大学 | It is a kind of can VTOL land and air double-used vehicle |
| CN108146169B (en) * | 2017-11-28 | 2021-06-29 | 北京航空航天大学 | Wing rear-folding type air-ground dual-purpose carrier |
| CN108128453A (en) * | 2018-01-08 | 2018-06-08 | 浙江大学 | A kind of air-sea dual-purpose solar unmanned plane and its control method |
| CN108215685A (en) * | 2018-01-12 | 2018-06-29 | 赵锟乔 | A kind of multifunctional traffic means |
| WO2019205186A1 (en) * | 2018-04-28 | 2019-10-31 | 深圳市元征软件开发有限公司 | Amphibious transport device |
| CN108528162A (en) * | 2018-06-15 | 2018-09-14 | 中宇航通（北京）科技有限公司 | The telescopic empennage mechanism of hovercar and hovercar |
| CN108899889A (en) * | 2018-09-11 | 2018-11-27 | 东汉太阳能无人机技术有限公司 | Power supply system and aircraft |
| CN110466297A (en) * | 2018-10-25 | 2019-11-19 | 长城汽车股份有限公司 | A kind of hovercar and hovercar control method |
| CN113840742A (en) * | 2019-05-07 | 2021-12-24 | 恩福特公司 | Traveling and flying electric and hybrid VTOL vehicle |
| WO2021064475A1 (en) * | 2020-01-10 | 2021-04-08 | Hazeri Majid | Vehicle with the ability to move on land, air and water |
| CN113212751A (en) * | 2021-06-11 | 2021-08-06 | 江西洪都航空工业股份有限公司 | Air-ground dual-purpose aircraft |
| WO2023177774A1 (en) * | 2022-03-17 | 2023-09-21 | Nft Inc. | Hybrid road-air vehicle |
| CN114684360A (en) * | 2022-04-08 | 2022-07-01 | 西安泽盛航空科技有限公司 | Tandem type double-duct propulsion unmanned aerial vehicle |
Also Published As
| Publication number | Publication date |
|---|---|
| WO2013159672A1 (en) | 2013-10-31 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN103496305A (en) | Hovercar | |
| CN109849604B (en) | Folding rotor triphibian aircraft | |
| CN203528804U (en) | Large-size rescue amphibious aircraft | |
| US20150048215A1 (en) | Efficient control and stall prevention in advanced configuration aircraft | |
| CN102616096A (en) | Solar flying automobile with folding wings | |
| CN108045575B (en) | Short-distance take-off vertical landing aircraft | |
| CN107089328A (en) | Hybrid power tail sitting posture VTOL long endurance unmanned aircraft and its flight control method | |
| CN102785776A (en) | Fixed-wing one-man flight vehicle capable of vertically taking off and landing | |
| CN206984354U (en) | A kind of aircraft | |
| RU2521090C1 (en) | High-speed turboelectric helicopter | |
| CN105564633A (en) | Wing flap lift enhancement type joined-wing airplane with approximately horizontal rotation propellers | |
| CN104973234A (en) | Aircraft using distributed electric ducted fan flap lift-rising system | |
| CN104276281A (en) | One-man flight vehicle | |
| CN115709623B (en) | Amphibious migration detection unmanned aerial vehicle powered by solar energy and working method | |
| CN201023656Y (en) | Ground effect aircraft | |
| CN201525255U (en) | Gyroplane landing ship capable of driving on land and water | |
| CN107176297A (en) | A kind of aircraft | |
| CN110901906A (en) | Ground effect rotor craft and flight mode switching method | |
| CN110282117A (en) | A kind of city VTOL aircraft having wing-folding storage function | |
| CN106081099A (en) | Airborne vehicle fixed-wing and use many gyroplanes and the fixed wing airplane of this fixed-wing | |
| CN205203366U (en) | Approximate level is rotated propeller wing flap lift -rising and is connected wing aircraft | |
| CN107021208A (en) | The tail sitting posture VUAV and control method of a kind of utilization duct | |
| CN201010045Y (en) | Ground-effect aircraft | |
| CN106167096A (en) | Modified model level of approximation rotates propeller wing flap lift-rising and connects wing aircraft | |
| CN209776067U (en) | Folding rotor triphibian aircraft |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C02 | Deemed withdrawal of patent application after publication (patent law 2001) | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20140108 |