CN100386245C - Transportation means for marine, land and air - Google Patents
Transportation means for marine, land and air Download PDFInfo
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- CN100386245C CN100386245C CNB031076270A CN03107627A CN100386245C CN 100386245 C CN100386245 C CN 100386245C CN B031076270 A CNB031076270 A CN B031076270A CN 03107627 A CN03107627 A CN 03107627A CN 100386245 C CN100386245 C CN 100386245C
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- land
- sea
- air transport
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- cylindrical tube
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Abstract
The present invention relates to a sea, land and air traffic tool which can sail in the water, run on the land and fly in the air (vertical climbing lift, horizontal flight and hovering in the air) in a novel transportation system. The sea, land and air traffic tool comprises a rotating wing which can rotate in the center of the sea, land and air traffic tool along the opposite direction. An installation shaft is positioned at the eccentric position of the center of the rotating wing, the rotating wing is arranged in such a manner, and consequently, the orientation of the rotating wing can change the direction. A cylindrical tube body encapsulates the periphery of the maximal rotation diameter of the rotating wing, a machine body is positioned at the center part of the traffic tool, and a movable supporting rod is arranged and is connected with the cylindrical tube body and the machine body. In the sea, land and air traffic tool, the cylindrical tube body is deformed through the movement of the movable supporting rod to enter a fixed wing.
Description
Technical field
The present invention relates to a kind of new transportation vehicles, it can vertically climb, horizontal flight, hover in the air, travel on land and navigate by water in water, changes these independently functions simultaneously simple and reliablely.
Background technology
Autogiro (this paper is referred to as helicopter), the fixed-wing aircraft of (being also referred to as " VTOL ") etc. takes off vertically and lands, as having three kinds of functions, promptly vertically climb, horizontal flight and in air, spiraling, flight system, be known not only to those of ordinary skill in the art, and known by common people.Yet these aircraft have more following problems:
Helicopter of the prior art has high efficient for vertically climbing and hovering in the air, but its problem is, and is very low for the efficient of horizontal flight.In contrast, VTOL of the prior art has high efficient for horizontal flight, but it is very low for the efficient of vertically climbing and hovering in the air.In addition, these two all has important disadvantages, and promptly they can not stablize skyborne position, thus their easy overturnings, and and they are than common fixed-wing aircraft unhandy, and very easily overturning and falling.In addition, helicopter of the prior art and VTOL can not travel on the road surface of little width or fairway, and their need the same wide road surface with airstrip or the same wide fairway with big river.
Summary of the invention
The land, sea and air transport that the purpose of this invention is to provide a kind of improved reduced size, it not only can solve all independent problem, difficulty, shortcoming and the limitation of above-mentioned helicopter of the prior art and VTOL, and all vertically climb, horizontal flight, the function aspects that hovers in the air, travel on land and navigate by water in water all be the height actv., can change these independently functions simultaneously safe, simple and reliablely.
To achieve these goals, land, sea and air transport of the present invention is provided with a cylindrical tube by the periphery by propeller and has improved flight efficiency when vertically climbing and hovering in the air.When horizontal flight, by propulsion coefficient is improved at the diameter and the inclination angle of 90 degree inclination fuselages and change propeller forward.Simultaneously, the shape that closes the body of propeller changes over an elliptical cylinder wing or a linear wing from a cylinder form, with these vehicle are deformed into one with have the fixedly identical aircraft of conventional airplane shape of main wing, therefore improved the flight efficiency of horizontal flight greatly.Simultaneously, shape with large diameter cylindrical tube becomes the elliptical cylinder propeller of a minor diameter or the linear wing of a little width, even like this on a narrow lane face or fairway, these vehicle also can be along on the long diametric(al) of this elliptical cylinder propeller or along travelling or navigate by water on the linear wing longitudinal direction, thereby it can easily arrive the destination.
One aspect of the present invention is, land, sea and air transport comprises the rotation wing that the heart therein rotates in opposite direction.Installation shaft is positioned at the accentric position, center with the rotation wing, and the rotation wing so is installed, thereby the orientation of the rotation wing can turn.The periphery of the maximum rotating diameter of a cylindrical tube encapsulation rotation wing.A fuselage is positioned at the core of these vehicle.Movable pole is set connects cylindrical tube and fuselage.In this land, sea and air transport, the action by movable pole makes the cylindrical tube body deformability to enter in the fixed-wing.
Description of drawings
Fig. 1 is a diagrammatic side views according to an embodiment of the land, sea and air transport of elliptical cylinder types of propellers of the present invention;
Fig. 2 is the plane sketch of the land, sea and air transport of Fig. 1;
Fig. 3 is the diagrammatic front view of the land, sea and air transport of Fig. 1;
Fig. 4 is a diagrammatic side views according to an embodiment of the land, sea and air transport of parallel double types of propellers of the present invention;
Fig. 5 is the plane sketch of the land, sea and air transport of Fig. 4; With
Fig. 6 is the diagrammatic front view of the land, sea and air transport of Fig. 4.
The specific embodiment
According to the present invention, land, sea and air transport comprises the rotation wing that the heart therein rotates in opposite direction.Installation shaft is positioned at the accentric position, center with the rotation wing, and the rotation wing so is installed, thereby the orientation of the rotation wing can turn.A cylindrical tube surrounds the periphery of the maximum rotating diameter of the rotation wing.A fuselage is positioned at the core of these vehicle.Movable pole is set connects cylindrical tube and fuselage.In this land, sea and air transport, the action by movable pole makes the cylindrical tube body deformability to enter in the fixed-wing.
Describe one embodiment of the present of invention in detail below with reference to accompanying drawing.In Fig. 1-3, be installed in main motor 2 on the fuselage 1 and 3 propulsive effort and transmitted through centrifugal clutch 4 and 5, helical wheel 6 and 7, bevel gear 8 and 9, angular wheel shaft 10 and 11 and screw propeller installation shaft 12 and 13 and arrive two contrarotation wings 14 and 15.
When two contrarotation wings 14 and 15 rotations, set up downward air draft 18, produce a hoisting force that makes progress 19 by its effect.Therefore, as the helicopter of prior art, land, sea and air transport of the present invention is floated by this hoisting force and is taken off.Simultaneously, eliminated eddy components by two contrarotation wings 14 of rotation in opposite direction and 15 eddy currents counteract effect from downward air draft 18, this screw propeller with unidirectional rotation is different.
Therefore, neither need the tail boom that prolongs backward, electricity does not need to be positioned at afterbody propeller on this tail boom tail end, although the horizontal overturning (or driftage) of these fuselages that cause for the unidirectional rotation of eliminating main screw with by the eddy current of being followed in the helicopter of prior art is absolutely necessary.Therefore, the fuselage 1 of land, sea and air transport of the present invention can be made more much smallerly and light than the length of the helicopter of prior art and big fuselage.
At this in land, sea and air transport of the present invention, supporting rod device 21 with a control screw propeller 20 always is present in the air-flow of the downward air draft 18 of being set up by this screw propeller, thereby can easily eliminate the influence of eddy current (if any) by the action of control screw propeller 20.Therefore, land, sea and air transport of the present invention also can be implemented with the single screw propeller of a unidirectional rotation.
In addition, the effect of periphery by being positioned at screw propeller 14 and 15 and the cylindrical tube 34 with a wing outline segment, the lifting amplitude of propulsive effort will be not have 1.4 times of the situation of body (seeing the P90 page or leaf of lecture notes of the Asahi aviation university on February 15th, 1964) or higher.
Therefore, the efficient of vertically climbing of land, sea and air transport of the present invention is 1.4 times of the efficient of vertically climbing of helicopter of prior art or higher, but is 1/1.4 or still less naturally for main motor 2 and 3 required propulsive efforts.
When land, sea and air transport of the present invention climbs a predetermined horizontal flight height, the aviator is with the posture of a control stalk 23 control control rotors 20 with the fuselage 1 that tilts gradually forward, up to screw propeller 14 that has horizontally rotated and 15 plane of rotation become vertical till.From now on, just the control of control stalk 23 can as the general purpose vehicle with fixed-wing of prior art, continue, thereby this land, sea and air transport can keep horizontal flight in predetermined height.
At this moment, the direction opposite with the inclination that changes fuselage 1 so receded 90 degree reaching the orientation at seat 26 in rotational pin 27 upper edges, a vertical seat for seat 25, thereby the aviator can be in a posture that is suitable for the horizontal flight direction.In land, sea and air transport of the present invention, vertical seat rotational pin 27 is centered close to a high position of center of gravity that is higher than the seat that the aviator sits, thereby seat 25 always forwards seat orientation 26 places to along with the gravity of the earth.
To be converted in the land, sea and air transport of horizontal flight at this, in screw propeller 14 and 15 rotations, they are turned to position 16 and 17 places respectively, be reduced to 31 with rotation external diameter from 30, and the inclination angle of screw propeller 16 and 17 also changes to the setting value that is used for horizontal flight from the setting value that is used for vertical flight with them.Afterwards, pole rotational line 32 shortens to a length 33, and forwarding supporting rod device 21 to position 22, thereby cylindrical tube 34 distortion enter an elliptical cylinder wing 35 (being connected the double-vane of the type on the wing tip corresponding to its wing centre section) that is used for horizontal flight.
In the distortion of this cylindrical tube, shown in Fig. 4-6, the cylindrical tube 36 of fraction type and 37 is by two straight wings that are divided into general pair of wing plane type.In the another kind distortion, a cylindrical tube is cut off a part, and extends in the mono-straight wing.Remaining reference number represent with Fig. 1-3 in the identical part of parts.
In the above-mentioned process that is deformed to the fixed-wing vehicle, the lifting of land, sea and air transport of the present invention and resistance ratios (i.e. lifting/resistance) are brought up to 10-20 (seeing the as above P80 page or leaf of the lecture notes of Asahi aviation university), although have only 3-5 at most in horizontal flight under the situation of the helicopter of prior art.Therefore, it is the lifting of helicopter and several times of resistance ratios that the lifting of land, sea and air transport of the present invention and resistance ratios are enhanced, thereby the horizontal flight efficiency ratio of land, sea and air transport of the present invention is enhanced and can flushes with the horizontal flight efficient of fixed-wing aircraft.
At this, the mechanism that is used to rotate the mechanism of the rotation wing and is used to change the inclination angle of the rotation wing can rotate and tilts to a degree that changes corresponding to the inclination angle and realize by will rotate the wing 14 and 15 with rotation wing rotating mechanism 28 and 29, wherein rotates the wing 14 and 15 and locates rotatably to be assemblied in their ends and rotate on wing installation shaft 12 and 13.The details of said mechanism is had slightly, can be easily makes up existing hydraulic pressure, pneumatic and power technology and in the scope that realizes by those of ordinary skills because it falls into.
When this land, sea and air transport climbs to the transition reverse of horizontal flight from vertical with above-mentioned, when horizontal flight is transformed into vertical decline, the elliptical cylinder wing 35 is just got back to the shape of cylindrical tube 34, the shape that the rotation wing 16 and 17 is also got back to the rotation wing 14 and 15.Then, control stalk 24 of operation rises 90 degree to reach a upwards posture of vertical flight with fuselage 1 from the horizontal flight posture.The propulsive effort of controlling main motor 2 and 3 promotes to adjust, thereby this land, sea and air transport is with the downward speed decline of a safety.If the propulsive effort of main motor is adjusted to one zero downwards during speed, just this land, sea and air transport keeps a bank position then.
In the vertical time that descends, seat 26 rotates the postures that 90 degree arrive seats 25 forward automatically at vertical seat rotational pin 27, thus the aviator can with one forwards to posture this land, sea and air transport that lands safely when observing the point that lands.
In addition, the system that adopts land, sea and air transport of the present invention is such system, wherein two contrarotation wings 14 and 15 are positioned under the center of gravity of whole vehicle framework, thereby it can keep the auto stability of flight attitude by the turning leverage of rotating part.Therefore, flight attitude no longer resembles the helicopter of prior art or the VTOL unstable, thereby the precise control device that at all no longer needs a kind of complexity, an automatic posture stabilization system for example is although it is essential in recent years helicopter or VTOL.
The example of a ground run will be described below.By after electronic walking wheel 45 lands fully down, the rotation wing 14 and 15 just enters level flight condition 16 and 17 at this land, sea and air transport, and the rotation external diameter is reduced to diameter 31 from diameter 30, and body 34 distortion enter in the elliptical cylinder wing 35.Afterwards, main motor 2 and 3 is controlled to a lower-speed state, to discharge centrifugal clutch 4 and 5.Seat 25 horizontally rotates 90 degree on a horizontal seat rotational pin 44, drive this land, sea and air transport in the face of travel direction and along target direction with walking wheel 45 and control stalk 23 to allow the aviator.For travelling on the water surface, the periphery of the bottom of this land, sea and air transport elliptical cylinder wing 35 is provided with the buoyancy aid 46 of an airbag types.As travelling on the ground, when land, sea and air transport drops to the water surface, an electric propulsion device 47 is inserted in the water, and handle the direction of control stalk 23, thereby land, sea and air transport can navigate by water along target direction with change propelling unit 47.
At this, claim 4 and 5 qualifying part are used to guarantee that land, sea and air transport of the present invention is in flight, safety when travelling and navigating by water, and as far as possible easily handle and control land, sea and air transport in making in action, thereby anyone can both handle these vehicle (although not shown also unspecified) simply.
As mentioned above, the invention provides a kind of later-model land, sea and air transport, it has not only eliminated all shortcomings of the helicopter or the VTOL of prior art, and have much a feature of not found in the helicopter of prior art or VTOL, and it can be safely and easily carry out various types of flights, ground run and the surface navigation that comprises vertical, level and orbit.The present invention has following effect.
This land, sea and air transport can be with the high loading of low power vertical-lift, and can be with low power high-speed flight distance far away, thereby it has high economic benefit as the communications and transportation mechanism of a new generation.
This land, sea and air transport can be on the ground of for example runway of a narrow free time or is for example taken off on the water surface of a swimming pool or land, thereby it can be applied as in the mountain area between the place remote and that shut off oneself from society or the untapped isolated island of still unoccupied up to now Buddhist monk between communications and transportation mechanism, and can tackle with effective and efficient manner and be in question world population blast problem now.
No matter this land, sea and air transport is aspect the initial purchase expense, all be cheap aspect maintenance and the operating cost still, thereby it can both be developed further for later-model motion or the later-model application of artificial/unartificial operation in the air.
Under the situation of the accurate flying height control system that does not have complexity out of control easily, this land, sea and air transport can fly more safely with comfortable than automatic aircraft, thereby it is easy to promote the use of in worldwide, comprises developing country.
This land, sea and air transport can use in worldwide as general-duty transport establishment, it can travel on narrow lane face/fairway/navigate by water, and teleoperator is being installed or is being used under the situation of program setting system of auto-navigation system and camera head, can do the operation of various kinds and mode, and need not the operator.
Claims (5)
1. land, sea and air transport comprises: the rotation wing that rotates in opposite direction of the heart therein; Be positioned at the installation shaft with the accentric position, center of the described rotation wing, and the described rotation wing so is installed, thereby the orientation of this rotation wing can turn; The cylindrical tube of the periphery of the maximum rotating diameter of the described rotation wing of encirclement; A fuselage that is positioned at the core of the described vehicle; With movable pole be set be connected described cylindrical tube and described fuselage, wherein, the action by movable pole makes cylindrical tube be deformed into a fixed-wing.
2. by the described land, sea and air transport of claim 1, it is characterized in that: also comprise: be separately positioned on the seat center of gravity of the weight that has comprised the aircrew with under a vertical seat rotational pin and a horizontal seat rotational pin.
3. by the described land, sea and air transport of claim 1, it is characterized in that: also comprise: the land walking wheel under described cylindrical tube and/or described fuselage and a surface navigation propelling unit.
4. by the described land, sea and air transport of claim 1, it is characterized in that described fuselage and described cylindrical tube comprise: the operating control of whereabouts at a slow speed of parachute or gliding parachute type; With the hag face/water surface landing gear of an absorption impact and the buoyancy aid of an airbag types.
5. by the described land, sea and air transport of claim 1, it is characterized in that: also comprise: one in response to from the space that comprises artificial satellite, sky, ground, underground, the water surface and the fool proof drive of undersurface signal effect.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNB031076270A CN100386245C (en) | 2003-03-21 | 2003-03-21 | Transportation means for marine, land and air |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNB031076270A CN100386245C (en) | 2003-03-21 | 2003-03-21 | Transportation means for marine, land and air |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN1532116A CN1532116A (en) | 2004-09-29 |
| CN100386245C true CN100386245C (en) | 2008-05-07 |
Family
ID=34282983
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CNB031076270A Expired - Fee Related CN100386245C (en) | 2003-03-21 | 2003-03-21 | Transportation means for marine, land and air |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN100386245C (en) |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101513934B (en) * | 2009-04-08 | 2010-08-18 | 王万琼 | Aeroamphibious triphibian aircraft |
| FR3074779B1 (en) * | 2017-12-11 | 2020-10-02 | Safran Helicopter Engines | AIRCRAFT |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4009849A (en) * | 1971-03-08 | 1977-03-01 | Karl Eickmann | Fluid-stream driven aircraft |
| US4171784A (en) * | 1971-03-08 | 1979-10-23 | Karl Eickmann | Combination road and air vehicle having a lowerable chassis |
| US4173321A (en) * | 1971-03-08 | 1979-11-06 | Karl Eickmann | Vehicle for traveling in the air and on the ground equipped with hydraulically driven propellers |
-
2003
- 2003-03-21 CN CNB031076270A patent/CN100386245C/en not_active Expired - Fee Related
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4009849A (en) * | 1971-03-08 | 1977-03-01 | Karl Eickmann | Fluid-stream driven aircraft |
| US4171784A (en) * | 1971-03-08 | 1979-10-23 | Karl Eickmann | Combination road and air vehicle having a lowerable chassis |
| US4173321A (en) * | 1971-03-08 | 1979-11-06 | Karl Eickmann | Vehicle for traveling in the air and on the ground equipped with hydraulically driven propellers |
Also Published As
| Publication number | Publication date |
|---|---|
| CN1532116A (en) | 2004-09-29 |
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| C14 | Grant of patent or utility model | ||
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| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20080507 |