CN102267568A - Line aircraft - Google Patents
Line aircraft Download PDFInfo
- Publication number
- CN102267568A CN102267568A CN2010101930616A CN201010193061A CN102267568A CN 102267568 A CN102267568 A CN 102267568A CN 2010101930616 A CN2010101930616 A CN 2010101930616A CN 201010193061 A CN201010193061 A CN 201010193061A CN 102267568 A CN102267568 A CN 102267568A
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- China
- Prior art keywords
- aircraft
- cabin
- circuit
- line device
- flight
- 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.)
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Links
- 230000010006 flight Effects 0.000 claims abstract description 46
- 239000004020 conductor Substances 0.000 claims description 21
- 230000000694 effects Effects 0.000 claims description 7
- 230000005540 biological transmission Effects 0.000 claims description 6
- 230000003028 elevating Effects 0.000 claims description 6
- 238000004080 punching Methods 0.000 claims description 6
- 238000005276 aerator Methods 0.000 claims description 4
- 239000000725 suspension Substances 0.000 claims description 4
- 230000001105 regulatory Effects 0.000 claims description 2
- 239000007789 gas Substances 0.000 abstract description 29
- 239000002737 fuel gas Substances 0.000 abstract description 6
- 238000004642 transportation engineering Methods 0.000 abstract description 4
- 239000000567 combustion gas Substances 0.000 description 4
- 238000010276 construction Methods 0.000 description 3
- 239000012467 final product Substances 0.000 description 3
- 238000004891 communication Methods 0.000 description 2
- 239000011521 glass Substances 0.000 description 2
- 208000008425 Protein Deficiency Diseases 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000005611 electricity Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000006011 modification reaction Methods 0.000 description 1
- 239000011435 rock Substances 0.000 description 1
- 238000005096 rolling process Methods 0.000 description 1
- 239000002689 soil Substances 0.000 description 1
- 239000002912 waste gas Substances 0.000 description 1
Classifications
-
- 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
- Y02T30/00—Transportation of goods or passengers via railways, e.g. energy recovery or reducing air resistance
Abstract
The invention discloses a line aircraft which comprises an air aircraft and a line, wherein a conducting rail and a fuel gas supply pipe are laid on the line; a power supply station which is electrically connected with the conducting rail and a gas filling station for filling gas in the aircraft are arranged on the line at intervals; the aircraft is provided with an engine room, a cockpit, aerofoils, a plurality of thrust engines arranged at two sides of the engine room and a plurality of electric variable pitch propellers arranged at two sides of the engine room; a fuel gas storage tank is arranged at the bottom of the engine room; a gas filling port is arranged on the fuel gas storage tank; the gas storage tank is connected with the thrust engines through fuel gas pipes; a flight controller is arranged in the cockpit and is in controlled connection with the thrust engines and the electric variable pitch propellers; a conducting contact part which is electrically connected with the electric variable pitch propellers is also arranged on the engine room; the conducting rail is electrically contacted with the conducting contact part; and the aircraft is slidably connected to the line and operates along the line. According to the line aircraft disclosed by the invention, rail transportation is ingeniously combined with the aircraft; and the line aircraft meets the development requirement of current transportation.
Description
Technical field
The present invention relates to a kind of transportation means, particularly a kind of flight line device.
Background technology
At present, need take a large amount of land areas along with the fast development of communication, the rolling up of vehicle, the traffic pressure in city is also just big more, and the waste gas of vehicle has caused very big destruction to environment.In addition for some outlying mountain areas, wet depression, field, the desert, the lake, the location that tourist attractions etc. are with a varied topography, the difficulty of repairing the roads is made troubles to people's trip.Therefore, except that rational adjustment, must seek new traffic approach.
Summary of the invention
Technical matters to be solved by this invention is to provide a kind of flight line device that utilizes clean energy resource to the new traffic of the aerial exploitation of near-earth at existing mode of transportation deficiency, to give following new power of communication generation.
In order to realize the foregoing invention purpose, the technical solution adopted in the present invention is:
A kind of flight line device is characterized in that, comprising:
One aircraft, this aircraft have the cabin of taking for the passenger, with two ends, cabin bonded assembly driving compartment, are arranged on a pair of wing of both sides, cabin, are arranged on some trust engines of both sides, cabin, are arranged on the some electronic nonuniform pitch propeller of both sides, cabin; Be provided with gas storage tank in bottom, described cabin, described gas storage tank is provided with and adds gas port, described gas storage tank is connected with described trust engine by Gas Pipe, in described driving compartment, be provided with flight controller, described flight controller and described trust engine and electronic nonuniform pitch propeller control linkage; Also be provided with conductive contact member on described cabin, this conductive contact member is electrically connected with described electronic nonuniform pitch propeller;
, a circuit;
Be laid in strip conductor on the described circuit, this strip conductor and described conductive contact member electrically contact;
Be laid in gaspipe on the described circuit, the external gas station supplier of described gaspipe mouth;
The supply station that is arranged on circuit and is electrically connected with described strip conductor;
Be disposed on the gas station on the circuit, described gas station is connected with described gaspipe, and the aerator of promising carry-on gas storage tank aerating is set;
Described aircraft is slidably connected on the line and moves along described circuit.
Described trust engine is combined by ducted fan driving engine and punching engine, and it is connected on the cabin by a rotatable assembly power frame.When the circuit aircraft comes and goes operation like this, only need Rotate 180 ° to get final product.
Described electronic nonuniform pitch propeller comprises speed governing outer rotor brushless motor and the nonuniform pitch propeller that is fixed on the described speed governing outer rotor brushless motor output shaft.The effect of electronic nonuniform pitch propeller mainly is to produce additional lift, characteristics such as power-weight ratio is big, rotating speed height that it has, and it is heavy to help the minimizing machine.
Described wing is connected with the cabin by the wing rotating mechanism, and this wing rotating mechanism can be regulated the angle of attack of wing in 4 ° of scopes, to reach rational 1ift-drag ratio.
Described circuit is the suspension type circuit, and it comprises:
Somely be set up in ground column;
Be set up in the crossbeam on described each column;
With the duct type main body H-girder that some crossbeams are connected in series, described gaspipe is laid on the described duct type main body H-girder;
Be installed in some frame girders at described main body H-girder two ends;
Be connected in series the hanging beam of each frame girder, described strip conductor is arranged on the hanging beam;
Described supply station comprises inverter, the storage battery that is arranged on the crossbeam and is arranged on solar panel and aerogenerator on the crossbeam, the input end of described inverter is connected with aerogenerator with solar panel, the mouth of inverter and ground substation are incorporated into the power networks, and described storage battery is connected with ground substation and powers to strip conductor.
Nacelle top rear and front end at described aircraft is provided with conductive contact member, described conductive contact member comprises conduction hanger bracket and conductive casters, described conductive casters is suspended on described conduction hanger bracket and whole aircraft on the described strip conductor, and this conductive casters is given electronic nonuniform pitch propeller by described conduction hanger bracket and described flight controller with power transmission.
Described suspension type circuit also comprises the arched girder that is erected on the described crossbeam, and described solar panel is laid on the described arched girder.
Described conductive contact member comprises that also one hangs snare with described nacelle top bonded assembly, and this hangs snare and is connected with described conduction hanger bracket.
Described circuit is the bearing-type circuit, and it comprises:
Somely be set up in ground column;
Be set up in the crossbeam on described each column;
With the duct type main body H-girder that some crossbeams are connected in series, described gaspipe and strip conductor are laid on the described duct type main body H-girder;
Described supply station comprises and is arranged on the power supply module on the crossbeam and is arranged on solar panel and aerogenerator on the crossbeam that the input end of described power supply module is connected with civil power, solar panel and aerogenerator;
Be provided with in bottom, the cabin of described aircraft and play electric action on the one hand, play the conductive contact member of walking effect on the other hand, described conductive contact member is the pair of conductive wheel, and described conductive casters is given electronic nonuniform pitch propeller by described flight controller with power transmission.
The present invention respectively is provided with a fixed fin at described nacelle top two ends, is movably set with yaw rudder on described fixed fin, described yaw rudder and described flight controller control linkage.
Trust engine of the present invention is connected with described cabin by rotatable assembly power frame, and described rotatable assembly power frame is provided with elevating rudder, described elevating rudder and described flight controller control linkage.
The present invention is provided with illuminating lamp in the front portion of described driving compartment.
The present invention combines track traffic dexterously with aircraft, improved running velocity, is fit to present development of Urban Traffic needs, can relax the traffic pressure of city and perimeter strip.。Its short construction period, saving soil help environmental protection.Be particularly suitable for outlying mountain area, wet depression, field, desert, lake, the with a varied topography and difficult location of repairing the roads such as tourist attractions; At anti-floods, earthquake can show the power that it is unique in face of the ice and snow calamity, disasteies such as mud-rock flow.Circuit aircraft of the present invention is with respect to high speed railway, express highway, and the mileage cost is minimum, and only about their 1/10th, and also construction period is also the shortest.Because when building circuit is to assemble from the preformed part of processing in advance, and construction environment is not caused any pollution.
Description of drawings
The scheme drawing that Fig. 1 moves on the line for aircraft in the embodiment of the invention 1.
Fig. 2 hangs on structure side view on the circuit for aircraft in the embodiment of the invention 1.
Fig. 3 hangs on structure front elevation on the circuit for aircraft in the embodiment of the invention 1.
Fig. 4 is the structural representation of aircraft in the embodiment of the invention 1.
Fig. 5 is the left view of Fig. 4.
Fig. 6 is the birds-eye view of Fig. 4.
The scheme drawing that Fig. 7 moves on the line for aircraft in the embodiment of the invention 2.
Fig. 8 is the structure side view of aircraft seat on circuit in the embodiment of the invention 2.
Fig. 9 is the structure birds-eye view of aircraft seat on circuit in the embodiment of the invention 2.
Figure 10 hangs on structure front elevation on the circuit for aircraft in the embodiment of the invention 2.
Figure 11 is the structural representation of aircraft in the embodiment of the invention 2.
Figure 12 is the left view of Figure 11.
Figure 13 is the birds-eye view of Figure 11.
The specific embodiment
For technological means, creation characteristic that the present invention is realized, reach purpose and effect is easy to understand, below in conjunction with concrete diagram, further set forth the present invention.
Referring to Fig. 1 to a kind of circuit aircraft shown in Figure 6, comprise aircraft 100 and circuit 200, whole circuit 200 comprises some ground columns 210 that are set up in, and has set up a crossbeam 220 between each column 210, and duct type main body H-girder 230 is connected in series all crossbeams 220.Be provided with some frame girders 240 in the compartment of terrain, two ends of duct type main body H-girder 230, hanging beam 250 is connected in series these frame girders 240, is equipped with strip conductor 260 on hanging beam 250.Strip conductor 260 is powered by the supply station that is arranged on the circuit 200.
This supply station comprises and is arranged on ground substation (not shown) and is arranged on power supply module 310, solar panel 320 and aerogenerator 330 on each crossbeam 220 that power supply module 310 comprises inverter, storage battery.The input end of inverter is connected with aerogenerator 330 with solar panel 320, and the mouth of inverter and ground substation are incorporated into the power networks, and storage battery is connected with ground substation and gives strip conductor 260 power supplies.
Putting on the shelf at crossbeam 220 is provided with an arched girder 270, and solar panel 320 is laid on the arched girder 270, can increase the area of solar panel 320 like this.
Need powerful power when considering aircraft 100 flights, present embodiment is equipped with gaspipe 340 on duct type main body H-girder 230, the input termination gas station supplier (not shown) of gaspipe 340.Be provided with some stations (not shown) on the line, be provided with the gas station (not shown) in AT STATION, gas station is connected with gaspipe and is provided with the aerator (not shown).
The aircraft 100 of this embodiment has the cabin of taking for the passenger 110, and 110 two sides are provided with glass port 111 in the cabin.The two ends in cabin 110 all are connected with driving compartment 120, after two ends are provided with driving compartment 120, no longer need to turn around during aircraft 100 shuttle flights.In driving compartment 120, be provided with the flight controller (not shown).Be provided with illuminating lamp 121 in the front of driving compartment 120, to make things convenient for Jia Shi person lookout.
110 both sides are provided with a pair of wing 130 by wing rotating mechanism (not shown) in the cabin, and the wing rotating mechanism drives wing 130 can regulate the angle of attack in 4 ° of scopes, to reach rational 1ift-drag ratio.
110 front and back end, both sides is equipped with trust engine 150 by rotatable assembly power frame 140 in the cabin, trust engine 150 is combined by ducted fan driving engine and punching engine, punching engine is simple in structure, in light weight, but can not start when having air current flow, therefore only as quickening usefulness, therefore need to be equipped with the ducted fan driving engine.After the rotatable assembly power frame 140, when the circuit aircraft comes and goes operation, only trust engine 150 Rotate 180s ° need be got final product.
110 both sides are provided with some electronic nonuniform pitch propellers 160 in the cabin, electronic nonuniform pitch propeller 160 produces additional lift, and this electronic nonuniform pitch propeller 160 comprises speed governing outer rotor brushless motor and the nonuniform pitch propeller that is fixed on the speed governing outer rotor brushless motor output shaft.The effect of electronic nonuniform pitch propeller mainly is to produce additional lift, characteristics such as power-weight ratio is big, rotating speed height that it has, and it is heavy to help the minimizing machine.
Flight controller control linkage in trust engine 150 and electronic nonuniform pitch propeller 160 and the driving compartment 120, flight controller control trust engine 150 and 160 work of electronic nonuniform pitch propeller.110 bottom is provided with the gas storage tank (not shown) in the cabin, and gas storage tank is provided with and adds gas port, with convenient filling combustion gas.Gas storage tank is connected with ducted fan driving engine in the trust engine 150 by Gas Pipe, with to ducted fan driving engine delivery of fuel gas.
The top at 110 two ends respectively is provided with one and hangs snare 170 in the cabin, on suspension snare 170, be connected with a conduction hanger bracket 180, conduction hanger bracket 180 is provided with conductive casters 190, conductive casters 190 will conduct electricity hanger bracket 180 and whole aircraft 100 and be suspended on the strip conductor 260, and this conductive casters 190 is given electronic nonuniform pitch propeller 160 by conduction hanger bracket 180 and flight controller with power transmission.
Aircraft 100 in the present embodiment adopts hang to be suspended on the circuit 100, relies on the flight of combustion gas and electric energy, flight stability, and be beneficial to environmental protection.
Embodiment 2
Referring to Fig. 7 to a kind of circuit aircraft shown in Figure 13, comprise aircraft 100 and circuit 200, whole circuit 200 comprises some ground columns 210 that are set up in, and has set up a crossbeam 220 between each column 210, and duct type main body H-girder 230 is connected in series all crossbeams 220.On duct type main body H-girder 230, be equipped with strip conductor 260.
Strip conductor 260 is powered by the supply station that is arranged on the circuit 200.This supply station comprises and is arranged on ground substation (not shown) and is arranged on power supply module 310, solar panel 320 and aerogenerator 330 on each crossbeam 220 that power supply module 310 comprises inverter, storage battery.The input end of inverter is connected with aerogenerator 330 with solar panel 320, and the mouth of inverter and ground substation are incorporated into the power networks, and storage battery is connected with ground substation and gives strip conductor 260 power supplies.
Need powerful power when considering aircraft 100 flights, present embodiment is equipped with gaspipe 340 on duct type main body H-girder 230, the input termination gas station supplier (not shown) of gaspipe 340.Be provided with some stations (not shown) on the line, be provided with the gas station (not shown) in AT STATION, gas station is connected with gaspipe and is provided with the aerator (not shown).
The aircraft 100 of this embodiment has the cabin of taking for the passenger 110, and 110 two sides are provided with glass port 111 in the cabin.The two ends in cabin 110 all are connected with driving compartment 120, after two ends are provided with driving compartment 120, no longer need to turn around during aircraft 100 shuttle flights.In driving compartment 120, be provided with the flight controller (not shown).Be provided with illuminating lamp 121 in the front of driving compartment 120, to make things convenient for Jia Shi person lookout.
110 both sides are provided with a pair of wing 130 by wing rotating mechanism (not shown) in the cabin, and the wing rotating mechanism drives wing 130 can regulate the angle of attack in 4 ° of scopes, to reach rational 1ift-drag ratio.
110 front and back end, both sides is equipped with trust engine 150 by rotatable assembly power frame 140 in the cabin, trust engine 150 is combined by ducted fan driving engine and punching engine, punching engine is simple in structure, in light weight, but can not start when having air current flow, therefore only as quickening usefulness, therefore need to be equipped with the ducted fan driving engine.After the rotatable assembly power frame 140, when the circuit aircraft comes and goes operation, only trust engine 150 Rotate 180s ° need be got final product.
110 both sides are provided with some electronic nonuniform pitch propellers 160 in the cabin, electronic nonuniform pitch propeller 160 produces additional lift, and this electronic nonuniform pitch propeller 160 comprises speed governing outer rotor brushless motor and the nonuniform pitch propeller that is fixed on the speed governing outer rotor brushless motor output shaft.The effect of electronic nonuniform pitch propeller mainly is to produce additional lift, characteristics such as power-weight ratio is big, rotating speed height that it has, and it is heavy to help the minimizing machine.
Flight controller control linkage in trust engine 150 and electronic nonuniform pitch propeller 160 and the driving compartment 120, flight controller control trust engine 150 and 160 work of electronic nonuniform pitch propeller.110 bottom is provided with the gas storage tank (not shown) in the cabin, and gas storage tank is provided with and adds gas port, with convenient filling combustion gas.Gas storage tank is connected with ducted fan driving engine in the trust engine 150 by Gas Pipe, with to ducted fan driving engine delivery of fuel gas.
The pair of conductive that plays on the one hand electric action, plays the walking effect on the other hand that respectively is provided with at two ends, 110 bottom is taken turns 170a in the cabin, and conductive casters 170a is supported on whole aircraft 100 on the circuit 100.Conductive casters 170a gives lifting propeller 160 by flight controller with power transmission.
Two ends, 100 top respectively are provided with a fixed fin 112 in the cabin, are movably set with yaw rudder 113 on fixed fin 112, yaw rudder 113 and flight controller control linkage.Rotatable assembly power frame 140 is provided with elevating rudder 141, elevating rudder 141 and flight controller control linkage.
Aircraft 100 in the present embodiment adopts bearing mode to be carried on the circuit 100, relies on the flight of combustion gas and electric energy, flight stability, and be beneficial to environmental protection.
More than show and described groundwork of the present invention and principal character and advantage of the present invention.The technical personnel of the industry should be understood; the present invention is not restricted to the described embodiments; that describes in the foregoing description and the specification sheets just illustrates principle of the present invention; without departing from the spirit and scope of the present invention; the present invention also has various changes and modifications, and these changes and improvements all fall in the claimed scope of the invention.The claimed scope of the present invention is defined by appending claims and equivalent thereof.
Claims (11)
1. a flight line device is characterized in that, comprising:
One aircraft, this aircraft have the cabin of taking for the passenger, with two ends, cabin bonded assembly driving compartment, are arranged on a pair of wing of both sides, cabin, are arranged on some trust engines of both sides, cabin, are arranged on the some electronic nonuniform pitch propeller of both sides, cabin; Be provided with gas storage tank in bottom, described cabin, described gas storage tank is provided with and adds gas port, described gas storage tank is connected with described trust engine by Gas Pipe, in described driving compartment, be provided with flight controller, described flight controller and described trust engine and electronic nonuniform pitch propeller control linkage; Also be provided with conductive contact member on described cabin, this conductive contact member is electrically connected with described electronic nonuniform pitch propeller;
, a circuit;
Be laid in strip conductor on the described circuit, this strip conductor and described conductive contact member electrically contact;
Be laid in gaspipe on the described circuit, the external gas station supplier of described gaspipe mouth;
The supply station that is arranged on circuit and is electrically connected with described strip conductor;
Be disposed on the gas station on the circuit, described gas station is connected with described gaspipe, and the aerator of promising carry-on gas storage tank aerating is set;
Described aircraft is slidably connected on the line and moves along described circuit.
2. flight line device as claimed in claim 1 is characterized in that described circuit is the suspension type circuit, and it comprises:
Somely be set up in ground column;
Be set up in the crossbeam on described each column;
With the duct type main body H-girder that some crossbeams are connected in series, described gaspipe is laid on the described duct type main body H-girder;
Be installed in some frame girders at described main body H-girder two ends;
Be connected in series the hanging beam of each frame girder, described strip conductor is arranged on the hanging beam.
3. flight line device as claimed in claim 1 is characterized in that described circuit is the bearing-type circuit, and it comprises:
Somely be set up in ground column;
Be set up in the crossbeam on described each column;
With the duct type main body H-girder that some crossbeams are connected in series, described gaspipe and strip conductor are laid on the described duct type main body H-girder.
4. as the described flight line device of each claim of claim 1 to 3, it is characterized in that described trust engine is combined by ducted fan driving engine and punching engine, it is connected on the cabin by a rotatable assembly power frame.
5. as the described flight line device of each claim of claim 1 to 3, it is characterized in that described electronic nonuniform pitch propeller comprises speed governing outer rotor brushless motor and the nonuniform pitch propeller that is fixed on the described speed governing outer rotor brushless motor output shaft.
6. as the described flight line device of each claim of claim 1 to 3, it is characterized in that described wing is connected with the cabin by the wing rotating mechanism, this wing rotating mechanism can be regulated the angle of attack of wing in 4 ° of scopes, to reach rational 1ift-drag ratio.
7. as the described flight line device of each claim of claim 1 to 3, it is characterized in that, described supply station comprises inverter, the storage battery that is arranged on the crossbeam and is arranged on solar panel and aerogenerator on the crossbeam, the input end of described inverter is connected with aerogenerator with solar panel, the mouth of inverter and ground substation are incorporated into the power networks, and described storage battery is connected with ground substation and powers to strip conductor.
8. flight line device as claimed in claim 2, it is characterized in that, nacelle top rear and front end at described aircraft is provided with conductive contact member, described conductive contact member comprises conduction hanger bracket and conductive casters, described conductive casters is suspended on described conduction hanger bracket and whole aircraft on the described strip conductor, and this conductive casters is given electronic nonuniform pitch propeller by described conduction hanger bracket and described flight controller with power transmission.
9. flight line device as claimed in claim 3, it is characterized in that, be provided with in bottom, the cabin of described aircraft and play electric action on the one hand, play the conductive contact member of walking effect on the other hand, described conductive contact member is the pair of conductive wheel, and described conductive casters is given electronic nonuniform pitch propeller by described flight controller with power transmission.
10. flight line device as claimed in claim 3 is characterized in that, respectively is provided with a fixed fin at described nacelle top two ends, is movably set with yaw rudder on described fixed fin, described yaw rudder and described flight controller control linkage.
11. flight line device as claimed in claim 4 is characterized in that, described rotatable assembly power frame is provided with elevating rudder, described elevating rudder and described flight controller control linkage.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2010101930616A CN102267568A (en) | 2010-06-04 | 2010-06-04 | Line aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2010101930616A CN102267568A (en) | 2010-06-04 | 2010-06-04 | Line aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN102267568A true CN102267568A (en) | 2011-12-07 |
Family
ID=45050063
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2010101930616A Pending CN102267568A (en) | 2010-06-04 | 2010-06-04 | Line aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN102267568A (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104787333A (en) * | 2015-03-21 | 2015-07-22 | 王文平 | Electric airplane without navigation system or self contained power supply |
| CN105235687A (en) * | 2015-10-30 | 2016-01-13 | 佛山市神风航空科技有限公司 | Pneumatic rail transportation tool |
| CN106184749A (en) * | 2016-09-21 | 2016-12-07 | 苏州机甲龙机械科技有限公司 | A kind of rail mounted aircraft and conduit thereof run system |
| CN111301441A (en) * | 2019-12-31 | 2020-06-19 | 张帅 | Three-dimensional layered space buoyancy traffic system above urban highway |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN104787333A (en) * | 2015-03-21 | 2015-07-22 | 王文平 | Electric airplane without navigation system or self contained power supply |
| CN104787333B (en) * | 2015-03-21 | 2017-04-05 | 王文平 | A kind of low latitude single track, the electric airplane for flying thereon and its flying method |
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Application publication date: 20111207 |