CN104787333A - Electric airplane without navigation system or self contained power supply - Google Patents
Electric airplane without navigation system or self contained power supply Download PDFInfo
- Publication number
- CN104787333A CN104787333A CN201510145161.4A CN201510145161A CN104787333A CN 104787333 A CN104787333 A CN 104787333A CN 201510145161 A CN201510145161 A CN 201510145161A CN 104787333 A CN104787333 A CN 104787333A
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- wing
- speed control
- track
- cabin
- ground
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- 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
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
Abstract
The invention relates to an electric airplane without a navigation system or a self contained power supply. The electric airplane adopts the structure that a cabin is separated from wings; the cabin is connected with the wings through one or more speed control lifters which are perpendicular to the ground; the speed control lifters are inserted into a track sleeve in the manner of being perpendicular to the ground; the speed control lifters can ascend and descend along with the flying speed; the track sleeve is connected with the outer side of a low-altitude single track which is parallel to the ground through an upper track wheel and a lower track wheel; the low-altitude single track which is parallel to the ground is used for supplying power to a motor for driving propellers through sliding circuits on the speed control lifters, and is used for navigating the airplane. In addition, the electric airplane provided by the invention can take off and land down at any time through the low-altitude single track which is parallel to the ground; an electromobile can be also suspended at the bottom end of each speed control lifter, and then on-track flying of the electromobile can be achieved. The electric airplane provided by the invention is large in load, long in voyage, environment-friendly, low in noise, free of pollution, economic and practical, and is a traffic tool for environment-friendly traveling in future.
Description
[technical field] the invention relates to a kind of electric airplane, particularly a kind of not self-powered electric airplane flown on the low latitude single track being parallel to ground.
[background technology] is current, the aircraft major part of airflight all must carry driving engine, from carrying fuel, the weight of driving engine and fuel greatly reduces the capacity weight of aircraft, and the carrying amount of fuel again limit flight, and fuel also has the danger of blast, blowdown after fuel combustion also contaminated environment, and the manufacturing technology of driving engine is high-end, accurate, navigationsystem is quite complicated, above-mentioned shortcoming result in the manufacturing cost of aircraft and flight cost all very high.
For these reasons, people have invented again self-powered electric airplane, although this aircraft does not have driving engine, also not carrying fuel, have certain advantage, but the weight of the power supplys such as the storage battery carried is still too large, affects the capacity weight of aircraft, simultaneously, self-powered needs charges, and limits flight, and, the capacity weight of this aircraft is little, and practicality is very low.
Above-mentioned two kinds of aircrafts all need to take off by runway and land, and runway will take a large amount of ground on the one hand, and aircraft danger when taking off and land is maximum on the other hand, and technical requirements is the highest.
Current track traffic provides a convenient trip mode efficiently, but needs to lay straight track due to track traffic, and take ground, bridge, beat tunnel, with high content of technology, cost of investment is very high.
[summary of the invention] object of the present invention, be to provide a kind of without self-powered electric airplane, the wing without self-powered electric airplane provided is fixed-wing, also can be rotary wings.
The present invention also aims to, the landing in-orbit realizing without electrically self-powered aircraft by providing a kind of speed control lifter that can carry out controllable lift in track cover, and be under the wing of airflight or the motor of cabin before driving screw propeller by the slide circuit on this speed control lifter, cabin can be hung in the bottom of speed control lifter and also can hang electronlmobil, realize electronlmobil and fly in-orbit.
The present invention also aims to, for providing a kind of low latitude single track being parallel to ground can guiding course and power supply without self-powered electric airplane.
Last object of the present invention is, provides a kind of and is parallel to what navigate for it and power the method that the low latitude single track on ground flies without self-powered electric airplane.
Provided by the invention without navigationsystem, without runway, can take off in-orbit at any time and land, without self-powered electric airplane, primarily of cabin, wing, screw propeller, electrical motor, tailplane, vertical tail, control system and landing shock absorber composition, its structural attitude is: cabin is separated with wing, be connected by speed control lifter between cabin with wing, cabin is suspended on speed control lifter bottom, and wing is arranged on speed control lifter top; Wai Cangtou front end, cabin is provided with the screw propeller of direct motor drive, is provided with mechanical manipulation system and electrical equipment control system in cabin; Wing afterbody is provided with vertical tail and tailplane; Speed control lifter perpendicular to ground insert track cover in, track cover be connected to by upper and lower two rail wheels be parallel to ground low latitude single track outside, track cover afterbody fixed-direction rudder is installed; Above the junction surface that outside speed control lifter and cabin, cabin is pushed up, the shock absorber that takes off is installed, below speed control lifter and wing junction surface, drop buffer is installed.
The wing of above-mentioned electric airplane is fixed-wing, is provided with the screw propeller of direct motor drive under wing, and wing afterbody is provided with elevating rudder and yaw rudder, and aerofoil surface is provided with wing flap; The wing of above-mentioned electric airplane also can be rotary wings, and rotary wings is by direct motor drive, and wing tail is provided with tailplane, and wing tail vertical beam is provided with tail-rotor.
The speed control lifter of above-mentioned electric airplane can along with the dynamic lifting of the random wing slip of speed of flying speed in track cover, the madial wall of the lateral wall of speed control lifter and track cover is provided with lifting brake equipment and the slide circuit device for motor, the speed control lifter be connected between wing and cabin is one or several; The bottom of this speed control lifter also can hang electronlmobil, and the slide circuit on speed control lifter used for electric vehicle is powered, and realizes the flight in-orbit of electronlmobil.
The present invention is also for above-mentioned electric airplane provides the low latitude single track being parallel to ground in power supply and guiding course, the formation of this single track is: this single track is the rail having rail wheel edge up and down, rail is arranged on a side of the horizontal gird of supporting track, rail and horizontal gird be degree in a vertical angle in same level, and another side of horizontal gird is arranged on the column top perpendicular to ground; The combination of multiple above-mentioned rail, horizontal gird and column forms flight track; Subsurface below track is embedded with supply line, this supply line by be laid on column and horizontal gird connection track cover and speed control lifter on slide circuit be motor.The above-mentioned horizontal gird being provided with rail also can be that symmetry is arranged on both sides, column top, forms two-way flight track.
Present invention also offers above-mentioned electric airplane and be parallel to above-mentioned the method that the low latitude single track on ground flies, this method is: switch on power, and under the combined action of screw propeller and wing, speed control lifter slides and rises in track cover, meanwhile, advance along track cross level under the control of yaw rudder; When the shock absorber on top, cabin touches track cover bottom, under the control of jacking system, wing, speed control lifter and cabin stop rising, and fly along track cross level; When aircraft needs landing, under the control of control system, flying speed slows down, and wing, speed control lifter and cabin decline, and meanwhile, lifting brake equipment and level braking device are braked jointly, land in cabin, and flight stops.
Advantageous Effects of the present invention: one, capacity weight and voyage greatly improve: because be not with driving engine and fuel, also without navigationsystem, aircraft own wt alleviates, capacity weight increases, and owing to being that ground power supply is powered, voyage does not increase by electricity restriction, simultaneously, owing to being low-latitude flying, the span and flying height can being designed to be able to the ratio utilizing ground effect, capacity weight is doubled and redoubled.
Two, environment protecting is good: because be direct motor drive flight, pollutants is zero-emission almost, because cabin is separated with wing, internal vibration little noise in cabin is low, more comfortable.
Three, safety is high: not from carrying fuel, avoids the danger of blast, without runway controlled landing in-orbit, avoids the danger of landing on runway, is parallel to the low latitude single track flight on ground, and cabin is nearer lower far from ground, and safety is higher.
Four, practicality is stronger: without navigationsystem, and without driving engine, without self-powered and without from carrying fuel, avoid the said equipment design, manufacture and install high-end, accurate and complicated technical barrier, structure is simple, and practicality is stronger.
Five, good in economic efficiency: without navigationsystem, without driving engine, without self-powered and without from the advantage that these structures of carrying fuel are simple and technical risk is relatively low, aircraft cost must be made lower, more economical, be parallel to the low latitude single track on ground, do not take ground, do not build a bridge, do not beat tunnel, quantities is less than track traffic, cost is lower, electricity consumption replaces fuel oil, and price is lower, and economic benefit is better.
Six, application is wider: cabin is separated with wing, independent separately, when manufacturing and designing, is independent of each other, changeable, is applicable to the needs of main line or branch line flight; Speed control lifter bottom can hang electronlmobil, does not account for road surface again, can be used for city traffic.
The preferred embodiment of electric airplane of the present invention is described below in conjunction with accompanying drawing.
[accompanying drawing explanation] Fig. 1 is the embodiment schematic diagram of fixed-wing electric airplane of the present invention.
Fig. 2 is the embodiment schematic diagram of rotary wings electric airplane of the present invention.
Fig. 3 is the track cover of electric airplane of the present invention and the one-sided embodiment schematic diagram being parallel to the low latitude single track combination on ground.
Fig. 4 is the two-way low latitude single track embodiment schematic diagram being parallel to ground of electric airplane of the present invention flight.
Component codes in figure: cabin 11 fixed wing 12 rotary wings 13 speed control lifter 14 track overlaps 15 vertical tails 16
Tailplane 17 is parallel to low latitude single track 18 lift buffer device 19 screw propeller 20 on ground
Tail-rotor 21 electrical motor 22 horizontal gird 23 column 24 rail wheel 25
Other parts of [detailed description of the invention] wing of the present invention and cabin and formation aircraft all adopt method of designing and the design and manufacture technology manufacture of present generation aircraft.As shown in Figure 1, wing 12 is a kind of fixed-wings, and the shape of fixed-wing also can be designed to the straight wing, swept wing and delta wing etc.; As shown in Figure 2, wing 13 is rotary wings.Because wing of the present invention is separated with cabin, manufacturing and designing of wing can not affect by cabin, and wing can be designed to more favourable flight and improve the shape of lift.Cabin of the present invention wing is separated, and therefore, manufacturing and designing of cabin does not also affect by wing, can be designed to the shape of more favourable flight and raising Aircraft Load.
As shown in Figure 1, Figure 2, Figure 3 shows, speed control lifter 14 of the present invention according to the needs of Aircraft Load, should manufacture and design one or more to connect wing 12 and cabin 11; Speed control lifter 14 should use the strong on-deformable material manufacture of resistance to tension, in the slide circuit that speed control lifter 14 is powered by a sidewall of track being installed as electrical motor 22, below speed control lifter 14 and wing 12 junction surface, landing shock absorber 19 is installed, above speed control lifter 14 and junction surface, cabin 11, landing shock absorber 19 is installed.
As shown in Figure 1, Figure 2, Figure 3 shows, track cover 15 of the present invention is connected to outside that is parallel and the low latitude single track 18 on ground by upper and lower two rail wheels 25, one madial wall of track cover 15 there is the slide circuit that contact corresponding to slide circuit on speed control lifter 14, other three madial walls of track cover there is lifting brake equipment, rail wheel 25 is provided with level braking device.
As shown in Figure 1 and Figure 2, fixed wing 12 afterbody of the present invention is provided with vertical tail 16 and tailplane 17, and rotor blade 13 wing tail vertical beam is provided with tail-rotor 21; The screw propeller 20 that electrical motor 22 drives is installed in Wai Cangtou front end, cabin, installs below fixed wing 12
Have the screw propeller 20 that electrical motor 22 drives, rotary wings 13 is driven by electrical motor 22.
As shown in Figure 3, the unidirectional formation being parallel to the low latitude single track 18 on ground of the present invention is that a steel single track 18 is connected to a side of horizontal gird 23, and both degree in a vertical angle, another side of horizontal gird 23 is connected to the top of column 24.
As shown in Figure 4, the present invention two-way parallel be, at the opposite side on column 24 top perpendicular to ground, horizontal gird 23 and the steel single track 18 of one group of symmetry is installed with the formation of the low latitude single track on ground.
Benly be, because electric airplane of the present invention flies in-orbit, when designing the joint of wing 12 and speed control lifter 14, the angle that wing 12 swings must be provided all around, meanwhile, wing 12 and speed control lifter 14 junction surface will provide due to collapsing length required when wing fluctuates up and down when flying.
Column 24 of the present invention, speed control lifter 14, relation when designing between flying height and the span;
Column 24 is highly equal with speed control lifter 14,
Flying height is 2 times of speed control lifter length,
If utilize ground effect to strengthen the capacity weight of aircraft, the span is approximately 2 times of flying height.
Claims (8)
1. one kind without navigationsystem, without runway, can take off in-orbit at any time and land, without self-powered electric airplane, primarily of cabin, wing, screw propeller, electrical motor, tailplane, vertical tail, control system and landing shock absorber composition, it is characterized in that: cabin is separated with wing, be connected by the speed control lifter perpendicular to ground between cabin with wing, cabin is suspended on speed control lifter bottom, and wing is arranged on speed control lifter top; Wai Cangtou front end, cabin is provided with the screw propeller of direct motor drive, is provided with mechanical manipulation system and electrical equipment control system in cabin; Wing afterbody is provided with tailplane and vertical tail; Speed control lifter perpendicular to ground insert track cover in, track cover be connected to by upper and lower two rail wheels be parallel to ground low latitude single track outside, track cover afterbody fixed-direction rudder is installed; Above the junction surface that outside speed control lifter and cabin, cabin is pushed up, the shock absorber that takes off is installed, below speed control lifter and wing junction surface, drop buffer is installed.
2. electric airplane according to claim 1, is characterized in that: wherein said wing is fixed-wing, is provided with the screw propeller of direct motor drive under wing, and wing afterbody is provided with elevating rudder and yaw rudder, and face is provided with wing flap to wing.
3. electric airplane according to claim 1, is characterized in that: wherein said wing is rotary wings, and rotary wings is by direct motor drive, and wing tail is provided with tailplane, and empennage vertical beam is provided with tail-rotor.
4. electric airplane according to claim 1, it is characterized in that: wherein said speed control lifter can along with the dynamic lifting of the random wing slip of speed of flying speed in track cover, the madial wall of the lateral wall of speed control lifter and track cover is provided with lifting brake equipment and the slide circuit device for motor, the above-mentioned speed control lifter be connected between cabin and wing is one or several.
5. electric airplane according to claim 1, is characterized in that: the bottom of wherein said speed control lifter is suspension gear, and for hanging electronlmobil, the slide circuit on speed control lifter used for electric vehicle is powered.
6. the electric airplane aiming at claim 1 is powered and guides the low latitude single track being parallel to ground in course, it is characterized in that: this single track is the rail having rail wheel edge up and down, rail is arranged on a side of the horizontal gird of supporting track, and rail and horizontal gird be degree in a vertical angle in same level; Another side of horizontal gird is arranged on column top that is vertical and ground; The combination of multiple above-mentioned rail, horizontal gird and column forms flight track; Subsurface below track is embedded with supply line, this supply line by be laid on column and horizontal gird connection track cover and speed control lifter on slide circuit be motor.
7. according to the low latitude single track being parallel to ground described in claim 6, it is characterized in that: the wherein said horizontal gird being provided with rail is that symmetry is arranged on both sides, column top, forms two-way flight track.
8. the electric airplane of a claim 1 is parallel in claim 6 method that the low latitude single track on ground flies, it is characterized in that: switch on power, under the combined action of screw propeller and wing, speed control lifter slides and rises in track cover, advances under the control of yaw rudder along track cross level simultaneously; When the shock absorber on top, cabin touches the lower curtate of track cover, under the control of jacking system, wing, speed control lifter and cabin stop rising, and fly along track cross level; When aircraft needs landing, under the control of control system, flying speed slows down, and wing, speed control lifter and cabin decline, and meanwhile, lifting brake equipment and level braking device are braked jointly, and land in cabin, flight stops.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510145161.4A CN104787333B (en) | 2015-03-21 | 2015-03-21 | A kind of low latitude single track, the electric airplane for flying thereon and its flying method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510145161.4A CN104787333B (en) | 2015-03-21 | 2015-03-21 | A kind of low latitude single track, the electric airplane for flying thereon and its flying method |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN104787333A true CN104787333A (en) | 2015-07-22 |
| CN104787333B CN104787333B (en) | 2017-04-05 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510145161.4A Expired - Fee Related CN104787333B (en) | 2015-03-21 | 2015-03-21 | A kind of low latitude single track, the electric airplane for flying thereon and its flying method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN104787333B (en) |
Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3557704A (en) * | 1968-04-19 | 1971-01-26 | Tracked Hovercraft Ltd | Electro-magnetically propelled vehicle |
| DE3906727A1 (en) * | 1989-03-03 | 1990-09-06 | Hankins | Vehicle which can be moved along a rail |
| CN1113869A (en) * | 1994-05-26 | 1995-12-27 | 刘奥宇 | Cabled motor-driven air-cushion air craft |
| CN1349907A (en) * | 2000-10-24 | 2002-05-22 | 许武智 | Three similar kinds of flyer and their orbit facilities |
| CN1446729A (en) * | 2002-03-26 | 2003-10-08 | 刘毅 | Low altitude aircraft with power supplied by wired electricity |
| CN101580117A (en) * | 2008-05-15 | 2009-11-18 | 北京新漩世为科技有限公司 | Lower wing upper cabin device |
| CN201520295U (en) * | 2009-06-09 | 2010-07-07 | 叶高峰 | Rail transit system |
| US20100326311A1 (en) * | 2009-06-18 | 2010-12-30 | Simon Abner J | Air bus transportation system |
| CN201710952U (en) * | 2009-08-11 | 2011-01-19 | 渠仁书 | Suspension cable type low-altitude flight system |
| CN102267568A (en) * | 2010-06-04 | 2011-12-07 | 谭黎渊 | Line aircraft |
-
2015
- 2015-03-21 CN CN201510145161.4A patent/CN104787333B/en not_active Expired - Fee Related
Patent Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3557704A (en) * | 1968-04-19 | 1971-01-26 | Tracked Hovercraft Ltd | Electro-magnetically propelled vehicle |
| DE3906727A1 (en) * | 1989-03-03 | 1990-09-06 | Hankins | Vehicle which can be moved along a rail |
| CN1113869A (en) * | 1994-05-26 | 1995-12-27 | 刘奥宇 | Cabled motor-driven air-cushion air craft |
| CN1349907A (en) * | 2000-10-24 | 2002-05-22 | 许武智 | Three similar kinds of flyer and their orbit facilities |
| CN1446729A (en) * | 2002-03-26 | 2003-10-08 | 刘毅 | Low altitude aircraft with power supplied by wired electricity |
| CN101580117A (en) * | 2008-05-15 | 2009-11-18 | 北京新漩世为科技有限公司 | Lower wing upper cabin device |
| CN201520295U (en) * | 2009-06-09 | 2010-07-07 | 叶高峰 | Rail transit system |
| US20100326311A1 (en) * | 2009-06-18 | 2010-12-30 | Simon Abner J | Air bus transportation system |
| CN201710952U (en) * | 2009-08-11 | 2011-01-19 | 渠仁书 | Suspension cable type low-altitude flight system |
| CN102267568A (en) * | 2010-06-04 | 2011-12-07 | 谭黎渊 | Line aircraft |
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| Publication number | Publication date |
|---|---|
| CN104787333B (en) | 2017-04-05 |
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Granted publication date: 20170405 Termination date: 20180321 |