CN1123758A - VTOL aircraft - Google Patents

Abstract

The disk-type flying vehicle is composed of circular or oblate main body and annular wing around the main body and features vertical lift, long-distance flying capacity and use of solar energy.

Description

VTOL aircraft

The present invention relates to the high-mobility, multipurpose, wheeled vehicle aviation aircraft that a kind of energy vertical takeoff and landing is used for aviation.

In the civilized society in modern times, clothing, food, live, the elemental of behavior people daily life, and the importance of its " OK " comes to have given prominence to more, people are also more and more higher to the safety requirements of " OK "." OK " being not only the important symbol of Modern World civilization, also is the important embodiment of a national science and technology level height.Though the traffic delivery means of the world today is relatively more flourishing, as land bicycle, automobile, train are arranged, aircraft is arranged in the air, cabin ship etc. is arranged in the ocean, be more complete but it still exists serious fault: (1) purposes is more single, be subjected to the influence of place, environment more serious, above-mentioned traffic delivery means can only use in specific field basically; (2) auxiliary facilities is too much, and is costly; (3) safety rate is not high, as long as machine one et out of order, is difficult in basically in the short time and gets rid of, continue to use, and aircraft particularly, as in case et out of order aloft, the overwhelming majority can lead to fatal crass's tragedy; (4) waste land resources, destroy natural ecological environment, all need to build special circuit, bridge etc. as automobile, train, this is not only costly, also will take a large amount of soils, if this several vehicle have all been popularized in the whole world, to waste how many soils? besides aircraft, though speed is very fast, it needs broad landing site on the one hand, and is costly, as building of airport, China Guangzhou, expensive more than 200,000,000 dollar, and building time-consuming nearly 20 years of airport, the Japanese Northwest costed and how much well imagined; Be that safety rate is not high on the other hand, the traffic accident in whole world every year is the gesture of rising linearly all, next is serious to the air-polluting situation, exhaust emission as automobile, aircraft can't be handled by actv., and (5) above-mentioned traffic dynamic load tool does not all have the effective means of comprehensive development and utilization solar energy resources.Even country advanced on the Modern World has set about studying the flying body that can overcome above-mentioned deficiency, though get along with, but all be single trend, as existing V-22 " osprey " aircraft and " the going straight up to truck " that is used for military aspect of states such as autogyro and the U.S., Canada, though these carriage by air machines can vertical takeoff and landing, the speed of V-22 " osprey " machine only be 550 kilometers/time, main last voyage is lacked, capacity weight is little, and safety factor is also little.Therefore, a kind of novel air vehicle that can overcome above-mentioned defective of design is very important.

The purpose of this invention is to provide the rapid vertical takeoff and landing of a kind of energy, speed is fast, and capacity weight is big, and flying power is strong, and it is reliable to be perfectly safe, and energy comprehensive development and utilization solar energy resources, the VTOL aircraft that also can travel in the waters.

Technical scheme of the present invention is: it is by a circle or flat a little up and down flat spherical body, and the ring air foil that is surrounded on body middle part correspondence position is formed.There are two annular snap of protruding body in order to pintle hook lock wing circle parallel to each other at described body middle part, the described following card face of going up annular snap reaches down, and the last card face of annular snap respectively has parallel to each other and big or small identical card face ball grooves more than two, between described two annular snap body inboard and greater than the distance of cabin door have two parallel to each other and be the annular ball grooves of semicircle, laterally have four pages of little cabin doors equidistantly between described two ball grooves, described cabin door is all opened in body, the control wing engine all is housed in every page of cabin door, Fuel Tank, the directed wing, the computer remote controlled system of devices such as the pressure wind wing, the outside face of cabin door (in the face of wing) can be made by the organism glass that the remote control electricity is restrainted of high strength.The gim peg mouth that a fixed wing circle is all arranged between the described adjacent cabin door, there is an osculum (gear mouth) that can pass through the miniature gears of horizontal positioned the position on the following and cabin door of described upward ball grooves, the front upper part of described body has an electrical motor, make it produce a kind of level pulling force forward, there is a round conductor hole position of drop wire slightly of described electrical motor, the communication bar that bursts at the seams is arranged under the described wire guide, have below the described antenna staff in a strip shape drive window (observation window) and the cooresponding body of described drive window driver cage is arranged, navigationsystem, communication system and full machine maneuvering system all are installed in the operator's compartment, the next radar installation that protrudes body that is equipped with of the middle separated time of described drive window, respectively there is a search lamp both sides of radar, the ring-shaped rubber loop of two connection body solar panels not of uniform size and wing cell panel is arranged below the described radar, and the last lower edge of loop all has unsealed ring shaped conductor.The radar installation of one protrusion body is arranged at the preceding bottom of described body, respectively there is a search lamp both sides of radar, (wing is above to be top in the upper back of described body, it below is the bottom, before with) empennage that the controlling aircraft horizontal direction arranged and turn to electrical motor straight line corresponding position, elevating rudder is arranged on the empennage, devices such as yaw rudder, one side of empennage has an antitorque propeller, with the straight body rear lower of described empennage, a three-bladed propeller is arranged, the described angle of rake the next slightly course rudder that is equipped with, the centre bottom of described body has an electrical motor, (or the downward jet engine of spout, as adopt this kind scheme, then need vertically to open a ventilation inlet at the top, center of body down, air compressor can be contained in the ventilation inlet of top and appropriate location between the driving engine of bottom, and adorn a Fuel Tank in the appropriate location of driving engine periphery), the slightly outstanding body of the paddle of electrical motor, what have around the electrical motor (body in part) that many groups arrange in the form of a ring provides storage battery (or electrical storage device) for oneself, around the described bottom electrical motivation, have two groups arranged side by side and every group be two landing wheel carrier (landing wheel carrier can folding and unfolding), the both sides of described bottom body, one page landing gate is respectively arranged, there is the window of many group merry-go-round arrangements the top and the bottom of described body, remove on the surface of described top body drive window, the part of annular window and other device all has the solar panel of annular arrangement.Described wing by the ring air foil circle and be fixed on the wing circle up and down two the ring wings constitute, the last lower edge of described wing circle for protrude can be with the body annular long in the wing circle annular snap of side-to-side anastomosis, on the described wing circle the last card face of annular snap and down the following card face of annular snap respectively have more than two size parallel to each other identical and block the identical wing circle card face ball grooves of face ball grooves on card face ball grooves and the following annular snap under the annular snap respectively with on the body.Described wing circle inner face has two annular wing circle ball grooves parallel and that coincide with the body ball grooves, the next slightly annular gear ring of recessed wing circle together that is equipped with of described top wing circle ball grooves, the annular ring tooth can be with the miniature gears interlock in the body to adjust the position of wing, the engine room hatchway and the gim peg mouth that have distance to equate between the described wing circle ball grooves respectively and overlap with related device in the body.Described wing is made of two ring wings up and down, described upper limb places the annular wing plate of the level under it to form by a slightly curved annular wing plate and one again, described top airfoil has the directed wing of four groups of equidistant " V " shapes, every group of directed wing is made up of two bar shaped fins, all the center line with the gim peg mouth is corresponding to divide vertical line equally in every group of directed wing, all there is the driving engine ventilation inlet of a circular arc position of the center of per two groups of directed wings and close wing circle, described ventilation inlet is all corresponding with its following driving engine, described top airfoil removes the part that the ventilation inlet and the directed wing are arranged, all device has solar panel in the form of a ring, two panel assemblies of cell panel are in the wing root position near wing circle, one annular insulation girth sheets is arranged below the two poles of the earth, the directed wing of described " V " shape can folding and unfolding by connecting rod, become the angle about 20 °-45 ° when opening with top airfoil, during gathering and top airfoil superimposed substantially.Described bottom wing places the horizontal annular wing plate under it to form by a slightly curved annular wing plate and one again, a plurality of pressure wind fins that described lower aerofoil has in the form of a ring (radial) to arrange greater than the span, the described pressure wind wing can folding and unfolding, become 10 ° to 30 ° left and right sides angles when opening with lower aerofoil, can it is superimposed in " recessed " shape mouth of lower aerofoil during gathering, around the described wing girth sheets and between the last lower wing, the driving engine that turns to about two above spouts can reach downwards is housed equidistantly, with the cooresponding bottom wing of described engine nozzle a strip arc port is arranged all, the edge of arc port is closed state, described every adjacent two with between the motivation all device a Fuel Tank and storage battery device are arranged, all there is one group of fixing support rack in the outside of described Fuel Tank, and fixing support rack is made of two stripe board and support pillar type column.The control setup of systems such as described driving engine, Fuel Tank, the directed wing, storage battery, the pressure wind wing all be contained in the cooresponding engine room hatchway of body cabin door in, be further described below in conjunction with accompanying drawing.

Description of drawings: Fig. 1 is an aircraft, and Fig. 2 is a body, and Fig. 3 is a wing, and Fig. 4 is the wing circle, and Fig. 5 is the solar cell panel assembly, and Fig. 6 replenishes figure for the body annular snap, and Fig. 7 is rubber lead figure, and Fig. 8 is engine nozzle structure and control scheme drawing.In the drawings: aircraft 6-body annular shape card of 1-aircraft, 2-body, 3-wing, 4-wing circle 5-dress solar panel replenishes Fig. 7-rubber loop 8-spout structure and control setup 9-electrical motor (driving engine) 10-lead advances hole 11-communication antenna bar, 12-drive window, 13-radar, 14-search lamp, 15-annular snap, 16-wing circle annular snap, the 17-directed wing 18,19-fixing support rack 20-pressure wind the wing 21-ventilation inlet, 22-strip arc port 23-search lamp, 24-radar, 25-circular row window 26-landing wheel carrier 27-landing gate, 28-electrical motor (driving engine) 29-navigation rudder 30-propelling unit 31-empennage 32-elevating rudder 33-yaw rudder 34-antitorque propeller 35-body ball grooves 36-gear is imported and exported 37-gim peg mouth, 38-cabin door, 39-upper limb, 40-bottom wing, 41-wing circle annular snap, 42-wing circle ball grooves, 43-wing circle annular gear ring, 44-engine room hatchway, 45-gim peg mouth, 46-hopper, 47-driving engine 48,49-wing circle card face ball grooves 50,51-solar panel 52, the positive and negative plate 54 of 53-cell panel, 55,56,72-the vertical rod of 57-body card face ball grooves, 58-inner nozzle, 59-jet pipe ball grooves, 60-outer nozzle, 61-loop, 62-slide cartridge cover, 63-slide bar, 64-miniature gears, 65-link gear mouth, 66-connecting rod, 67-spout circle, 68-ball running-on, 69-spherical bead, 70-wing girth sheets, 71-inside conductor circle

By accompanying drawing as can be known, the present invention is by body (2), and ring places the annular wing (3) at body (2) middle part to form. Described body (2) is the circular or upper flat spherical body (2) of end, there is the twice annular snap in order to pintle hook lock wing (3) parallel to each other (15) at the body middle part, the lower card face of the upper annular snap (15) of described body (2) have more than two size parallel to each other identical and with the upper circle of wing circle (4) card face ball grooves (48,49) the card face ball grooves (54 that coincide, 55), the upper card face of the lower annular snap (23) of body (2) has the card face ball grooves (56 identical and that coincide with the lower circle of wing circle (4) card face ball grooves of size parallel to each other more than two, 57), have at inboard body (2) middle part of described annular snap (15) two parallel to each other and respectively with the equidistant annular ball grooves of annular snap (15) (35) up and down, four pages of equidistant cabin doors (38) are arranged between the described ball grooves (35), described cabin door (38) is all opened in body (2), and corresponding with wing circle (4) engine opening (44), control wing engine (47) fuel tank (46) all is housed in the described cabin door (38), pressure fan (is positioned under the air inlet (21), the computer remote controlled system of the devices such as the directed wing not shown in FIG. (17) the pressure wind wing (20), all there is the gim peg mouth (37) of a fixed wing circle (4) middle of every adjacent two pages of cabin doors (38), has one can pass through the horizontal gear (in the body between the gim peg mouth (37) of described upper spheres groove (35) and body (2) front portion, not shown in FIG.) gear mouth (36). The front upper part of described body (2) is (take annular snap as object of reference, be upper on it, it is lower to lower), a motor (9) or spout engine (9) is backward arranged, make it produce a kind of level pulling force forward, the vertical lower of described motor (9) has a round conductor aperture (10) successively, a communication of stretching out the forward bar (11) that bursts at the seams is arranged under the wire guide (10), one bar shaped drive window (12) is arranged below the mast (11), be driver cage (not shown in FIG.) in the body (2) corresponding with drive window (12), a radar system (13) of protruding body (2) surface is arranged below the drive window (12), respectively there is a searchlight (14) both sides of radar (13), a radar (24) is arranged at the front bottom of described body (2) annular snap (15), respectively there is a searchlight arranged side by side (23) both sides of radar (24), there is empennage (31) upper back of body (2), the rudder (33) that elevator (32) and control aircraft (1) direction are arranged respectively on the empennage (31), one side of empennage (31) has an antitorque propeller (34), the rear lower of described body (2) and empennage (31) are in same linear position, an electronic three-bladed propeller (30) is arranged, a navigation rudder (29) is arranged below the described propeller (30), the centre bottom of described body (2) has a motor (28), (or the downward jet engine of spout, as adopt this kind scheme, then need vertically to open an air inlet at the top, center of body down, compressor can be contained in the air inlet of top and the appropriate location between the engine of bottom, and fills a fuel tank in the appropriate location of engine periphery). Described motor (28) all around (the interior part of body (2)) have in the form of a ring arrange provide storage battery or electrical storage device (not shown in FIG.) for oneself, around the described motor (28) (engine body exterior branch) have two groups parallel to each other, every group be two can folding and unfolding landing wheel carrier (26), respectively there is one page landing gate (27) described body (2) both sides, bottom, the upper and lower surface of described body (2) has the window (25) of many group annular array, in addition, the surface portion of window (25) and other device is removed on described body (2) top, can be according to the purposes device solar panel (50) of aircraft, the two poles of the earth (52 of solar panel (50) plate of rubber wire guide plate (7) and wing (3) are all used at the two poles of the earth of battery (50), 53) connect, and provide for oneself in the storage battery or confession motor (9) by what conductor aperture (10) entered body (2), (28) use. Described wing (3) by wing circle (4) and up and down two groups of annular machine fins consist of, described wing all is fixed on the wing girth sheets (70) between the wing circle annular snap (16), the up and down two ends of described wing circle (4) be twice parallel to each other and respectively with body (2) annular snap (15) up and down in the wing circle annular snap (16) of side-to-side anastomosis, on the described wing circle the lower card face of the upper card face of annular snap (16) and lower annular snap (16) respectively have more than two size parallel to each other identical and with body (2) the up and down card face ball grooves (54 of annular snap (15) up and down, 55,56,57) the circle card face ball grooves (48 that coincide, 49), wing girth sheets (70) inner face between the described wing circle annular snap (16), the wing circle ball grooves (42) parallel to each other and that coincide with the annular ball grooves of body (2) (35) in twice, there are four distances to equate and the engine opening (44) corresponding with cabin door (38) between the described twice wing circle pearl groove (42), all there is a gim peg mouth (45) corresponding with body (2) gim peg mouth (37) centre of described per two engine openings (44), between described gim peg mouth (45) and the upper limb circle ball grooves (42), there be one a little less than the wing circle annular tooth (43) of girth sheets (70) inner plane, wing circle annular tooth (43) can with gear mouth (36) in engaged gears and rotate as required to adjust the position of wing (3), the upper limb (39) of described wing (3) is made of top airfoil and the end aerofoil of upper limb (39) an arcuation annular slab and horizontal annular plate, the directed wing (17) of four groups of (every group is two) equidistant " V " shapes is arranged on the top airfoil, the directed wing (17) carries out folding and unfolding by linkage, become the angle about 10 ° to 45 ° when opening with top airfoil, during gathering and top airfoil substantially superimposed, all there is a circular arc engine air inlet (21) position of the centre of the directed wing of every two adjacent groups (17) and close wing circle (4), the following equal correspondence of each air inlet (21) the described top airfoil of an engine (47) except the directed wing (17) and air inlet (21), the solar panel (51) that multi-disc is radial arrangement also is housed, the both positive and negative polarity (52 of cell panel (51), 53) substantially near wing circle (4), a round insulation circle (not shown in FIG.) is arranged below described cell panel the two poles of the earth, [two loop shapes are identical by two rubber loop (7) for described wing cell panel (51), not of uniform size] cell panel on the same body (2) connects, described rubber loop (17) all is fixed in the appropriate location of the upper annular snap (15) of body (2), little loop places positive pole (50) and the negative pole (51) that connects respectively cell panel under the big loop (7), (370 cathetus intersects to divide vertical line and gim peg mouth in the described directed wing (17) equally, the perpendicular bisector of described air inlet (21) is all crossing with the cathetus of engine opening (44), the bottom wing (40) of described wing (3) places the horizontal annular wing plate under it to consist of by a slightly curved annular wing plate and one again, described bottom wing (40) and engine nozzle correspondence position have four equidistant strip arc ports (22), so that the spout of engine is downward, the edge of arc port (22) all is closed state, the end aerofoil of described bottom wing has the in the form of a ring pressure wind wing (20) greater than span length of (radial) arrangement of many groups, (the pressure wind wing is slightly curved), press the wind wing (2 0) can folding and unfolding by linkage, with pressing aerofoil of the corresponding end of the wind wing (20) " recessed " shape flap groove (not shown in FIG.) is arranged all, can will press the wind fin to be folded in the flap groove, when making it to draw in and end aerofoil is horizontal substantially, presses the wind wing (20) to open aerofoil at the bottom of the Shi Keyu and becomes angle about 10 ° to 30 °. (annotate: do not fill in arc port (22) scope and press the wind wing (20) sheet, reach wing girth sheets (70) all around between the described upper lower wing, the jet engine (47) that many (more than two) spouts can reach left-right rotation downwards is housed equidistantly, described engine nozzle is used the mode that secondary connects, outside the close combustion chamber is inner nozzle (58), shorter, inner nozzle (58) outer side edges is along there being a circle to be lower than the jet pipe ball grooves (59) of jet pipe (58) cheek, the arc circle of outer nozzle (60) end that is connected with inner nozzle (58) for protruding, with outer nozzle (60) dress people's inner nozzle (58), with the contact of the ball in the ball grooves (59) of the same inner nozzle of arc round edge (58) of outer nozzle (60), refill a hypotenuse annular snap, like this, outer nozzle (60) just can reach up and down as required both sides and rotates arbitrarily.

In view of the special tectonic of jet pipe and flight requirement, spout is appointed about can be up and down Meaning is rotated and according to the flight needs of aircraft, as long as spout can reach a side downwards and turn to Just move can, therefore, a kind of device (see photo) that spout rotates of controlling to be designed, Namely at the slightly outer end position place of each outer nozzle (60), each is set with the spray of a circle Pipeloop (67), jet pipe circle (67) top respectively have a ball running-on, and every adjacent two Individual jet pipe circle (67) all uses connecting rod (66) to connect, and has one section near connecting rod (66) middle part (its concrete length can be according to the spout side when making and design for spill gear mouth (65) The angle of moving and distance are more fixed), respectively there is a column vertical rod at the two ends of connecting rod (66) (72), pole tip is a spherical bead (69), the ball running-on of it can being packed into, its After have one can hold vertical rod (72) by after-opening, the wing above gear day (65) One group of hydraulic pressure or electronic slide cartridge (62,63), the lower end of slide cartridge (62,63) are respectively arranged down Have one only between pinion (64) connecting rod (66) and slide cartridge with forward and reverse rotation " U " shape device that links to each other, (guarantee that pinion is with the frequent interlock of gear mouth, again Unlikelyly affect coming off just of connecting rod (68)), like this, driving pinion (64) connects Bar (66) is mobile, and spout is thereupon mobile, driving pinion (64), and connecting rod (66) moves Moving, spout is thereupon mobile, drives slide cartridge (62,63), and nozzle exit area moves down (little In 80 ° greater than 60 ° just can), so far, the movement of spout (60) just can be according to flying The needs of row have been handled and (have been annotated: press the control system of the wind wing (20) and the directed wing (17) temporary Slightly), equal described per two of corresponding the cabin door (44) of described engine (47) A fuel tank (46) all is housed between the engine (47), described fuel tank (46) All there is one group of fixing support rack in the center line outside, and fixing support rack is by the bar shaped gripper shoe (19) and support column (18) consist of. Described rubber loop (7) is by the round rubber circle Consist of conductor (61) and wing cell panel (51) with untight ring-shaped conductor (61) A utmost point connect, inner wire (71) is connected institute with the homopolarity of body cell panel (50) State internal and external conductor (61,71) and all embed in the rubber ring (7), expose a little same the two poles of the earth Contact.

Use of the present invention and method of operating are: will make by a certain percentage and ball that size equates is fully packed in the annular ball grooves (35,42) of body (2) and wing (3), reach in the card face ball grooves (48,49) of body (2), annular snap (1 5), again wing (3) pintle hook lock is formed VTOL aircraft (1) in the annular snap (15) at body (2) middle part.Take off and to implement by following two kinds of methods.

One, start the electrical motor (28) of all driving engines (47) of wing (3) and body (2) bottom simultaneously, and make the spout (60) of driving engine (47) downward by maneuvering system, like this, the air-flow of electrical motor (28) and driving engine (47) ejection can give aircraft (1) with huge antagonistic force, simultaneously again because the constantly a large amount of people's air of inhaling of driving engine (47), therefore cause basic region of no pressure in aircraft (1) sky, for aircraft (1) provides powerful lift, after rising up into the high-altitude, utilize maneuvering system to make the spout of driving engine (47) recover former level attitude, like this, aircraft (1) can be in a kind of basic floating state, after this, start the electrical motor or the driving engine (9) of body (2) front upper part, close the electronic or driving engine (28) in bottom, close any adjacent two driving engines (47) in the wing (3) more gradually, open the directed wing (17) of a group on the separated time in two driving engines (47) that moving simultaneously, when the gim peg mouth (37) at the midperpendicalar of the directed wing (17) and body (2) rear portion when being in linear position, insert the gim peg (not shown), like this aircraft (1) just can be rapidly horizontal flight forward.After this, if two wing engines (47) that moving break down simultaneously, can immediately it be closed, and extraction gim peg, regain the directed wing (17) on the separated time wherein, during effect of inertia, stretch out miniature gears (not shown) and wing circle annular tooth (43) interlock and rotation in the body (2), the wing engine (47) of body (2) front part sides is transferred to body (2) both sides, rear portion, gim peg mouth (45) in the middle of this two driving engines (47) and the gim peg mouth (37) at body (2) rear portion are when overlapping, insert gim peg, open the directed wing (17) [driving engine (47) in separated time on], simultaneously start this two driving engines (47) gradually, like this, aircraft (1) again can be rapidly horizontal flight forward.During landing, can extract gim peg earlier out, regain the directed wing (17), start two driving engines in addition of body (2) front part sides simultaneously, when the power of all driving engines all equates, close body (2) anterior electrical motor or driving engine (9), make driving engine (47) spout downward by maneuvering system again, use the method for deceleration gradually to land again [(annotate: before landing, must emit landing wheel carrier (26), will regain landing wheel carrier (26) after taking off].

Two, open the pressure wind wing (20) under the wing (3), extract gim peg out, start one or more wing engine (47), make driving engine (47) by maneuvering system, spout (60) in the same way and with body (2) tangentially, and the antitorque propeller (34) on the startup empennage makes wing (3) high speed revolution, utilize to press the wind wing (20) to the application force of air and air-flow antagonistic force to aircraft (1), simultaneously, because the constantly a large amount of aspirated airs of driving engine (47), therefore, cause class region of no pressure and high vacuum region in aircraft (1) sky, for providing powerful lift, aircraft (1) [(takes off vertically rapidly for making aircraft (1), simultaneously can start body (2) bottom electrical motivation or driving engine (28)], after rising up into the high-altitude, close the bottom electrical motivation, allow wing (93) driving engine (47) spout recover former level attitude, close antitorque propeller, make slowly horizontal flight forward of aircraft, then, the wing engine (47) of cutting out body (2) front part sides again opens the directed wing (17) of one group of " V " shape on two driving engines (47) center line in addition that is turning round, wing circle gim peg mouth (37) under this directed wing (17) midperpendicalar is salty fashionable with the gim peg at body (2) rear portion, insert gim peg, [this sentence should ... recover former level attitude, aircraft (1) is hovered between aerial substantially)], regain landing wheel carrier (26), like this, aircraft (1) just can be rapidly horizontal flight forward.The driving engine (47) of aircraft (1) is as breaking down and landing method all can be handled with reference to method described in.In addition, (470 have damaged as aircraft (1) driving engine (47) or two driving engines before landing, can implement as follows when then landing, during landing, can be with driving engine (47) that still can normal operation, spout in the same way and with body (2) tangentially, start antitorque propeller (34), allow wing (3) high speed revolution, for safety has certain guarantee, also can start bottom electrical motivation (28) [before the wing rotation, will open and press the wind wing (30)] this moment, close the electrical motor or the driving engine (9) of body (2) front upper part again, the method landing (beginning to emit the landing wheel carrier before the landing) of using driving engine (47) and electrical motor (28) to slow down gradually then, as drop in the waters, can use the propelling unit (30) of body rear lower to make aircraft (1) continue navigation.

Above-mentioned new structure of the present invention has following function and characteristics:

One, vertical and landing takeoff rapidly, landing anywhere is not subjected to place restriction (when the landing of land the level land more bigger than aircraft must be arranged).

Two, speed is very fast, can do supersonic flight.

Three, flying power is strong, because of its wing just can be formed the unit power plant (every adjacent two is a group) that many groups make the aircraft horizontal flight by many driving engines;

Four, have a smooth flight, as safe as a house reliable, continue flight even the part wing engine damages also available other driving engine, even in the waters, also can travel;

Five, volume is big, and capacity weight is big, and anti-crosswind performance is strong;

Six, energy comprehensive development and utilization solar energy resources reduces the pollution to environment;

Seven, wide in variety, reach purposes according to actual needs, can make multiple models such as huge, large, medium and small;

Eight, this aircraft promptly can be used for civil aviaton, mass movement, also can speed be adapted as military.

Embodiment:, can need and purposes is made the aircraft of multiple this type such as huge, large, medium and small according to base is actual according to this device of accompanying drawing and said structure.Fly-dick-type vertically falls the aeronautical material that the aviation aircraft available quality is light, intensity is big and makes (based on titanium alloy material), can divide three parts to make as body, it is the top body, (concrete size can be determined in proportion according to the size of aircraft for bottom body and middle part body, the wing size reason that also Clicks here), annular snap can install behind the top wing to be installed again on the body of middle part.Now the implementing method with the main organism component of above-mentioned aircraft is summarized as follows: the front portion of top body (2) installs electrical motor (or driving engine (9) earlier, hold lead import (10) successfully, install communication antenna bar (11) and bar shaped drive window (12), again with radar 913) and the internal and external parts device of search lamp (14) good, installed the manipulation in the corresponding body of drive window (12) (2) simultaneously, navigation, communication system and operator's compartment, installed body 92 then) go up the elevating rudder (32) on the rear portion empennage (31), yaw rudder (33) and antitorque propeller (34), installing its hydraulic pressure or electric powerplant in corresponding body (2) simultaneously (does not draw among the figure, and connect with control corresponding system in the operator's compartment with conductor, then draw up annular window (25) and installed solar panel (50) and reach and wing (3) battery bonded assembly device, the cabin dividing plate and the delivery facility (reach as required in the purposes set-up diagram and do not draw) of body (2) have been refilled, middle part body (2) is with the aeronautical material making of thickness big [because of opening ball grooves (35)], hold ball grooves (35) successfully according to the size of made aircraft, cabin door (38), gim peg mouth (37) and gear mouth (36), body (2) appropriate location in gear mouth (36) installs miniature gears (not drawing among the figure), and installing hydraulic pressure or electronic gim peg in the body (2) accordingly with gim peg mouth (37), and will control and install in the wing (3) with conductor with control corresponding system connection in the operator's compartment, install the annular snap (15) of bottom, after bottom body (2) is carried out, the electrical motor (28) of device good bottom centre of elder generation and on every side provide storage battery or electrical storage device (not drawing among the figure) for oneself, body (2) rear lower paddle propelling unit (30) and course rudder (29) have been refilled, and the position installs hydraulic pressure and electric propulsion system in its corresponding body (2), install the members inside and outside body (2) such as radar (24) search lamp (23), and landing wheel carrier (26) bottom installing and the control system in the body (2) thereof, the control system of said apparatus all is connected with corresponding system in the operator's compartment, after this, refill landing gate (27) and the circular row window (25) that deposits portion's body (2) both sides.After making all parts of wing (3) (the good in proportion size of size that reaches aircraft is as required made), earlier with driving engine (47), the air compressor (not shown) connects and with after ventilation inlet (21) is connected, again driving engine (47) Fuel Tank (46) is fixed in the root between the lower wing (3), and make driving engine (47) spout corresponding good with arc port (22) respectively, install the pressure wind wing (20) and the control system thereof of the directed wing (17) and the bottom wing of upper limb, the solar panel (51) that has refilled top airfoil reaches and body (2) cell panel (50) bonded assembly the two poles of the earth (52,53), (as needs can wing root open a lead import and with wing in appropriate location dress electrical storage device, be convenient to utilize the solar energy resources of wing (3)), install subsequently and be fixed on bracing frame (18,19), after this, card face ball grooves (56 in following annular snap, 57) install ball in, and in the ball grooves of body (2), install ball in (35), again wing (3) and institute's metal elements thereof are fixed on wing girth sheets (70) around, and the control system device that wing (3) is all is in engine room hatchway (44), after respectively that aircraft (1) is above-mentioned parts are made and install well, to go up circle annular snap (16) installs, again wing (3) is installed on the following annular snap (15) of body (2), again at circle card face ball grooves (48,49) install ball in, subsequently the last annular snap (15) of body (2) is installed, after this, respectively top body (2) and bottom body and middle part body (2) are coupled together, at last with the last card face position of two rubber rings (7) device in the last annular snap (15) of body (2).What and other of the interior cabin of body (2) layer dividing plate (not shown) established to revolve (but must assemble before body (2) assembling) can be set according to the size and the purposes of aircraft (1).

Claims (5)

1, a kind of fly-dick-type aviation aircraft, a circle is arranged or go up the flat spherical body (2) of end and be surrounded on ring air foil (3) in the middle part of the body (2), it is characterized in that, described body (2) front upper part has electrical motor (9), with the cooresponding body of electrical motor (9) straight line (2) upper back empennage (31) device is arranged, elevating rudder (32) and yaw rudder (33) and antitorque propeller (34) are arranged respectively on the empennage (31), body under the cathetus of empennage (2) rear lower, propelling unit (30) and course rudder (29) are arranged respectively, electrical motor (28) and landing wheel carrier (26) are arranged at body (2) bottom, the midperpendicalar below of electrical motor (9) has lead to enter hole (10) respectively, communication antenna bar (11) and horizontal bar shaped drive window (12) and radar (13) etc., respectively there is a search lamp (14) both sides of radar (13), radar (24) is arranged at the preceding bottom of the body under the vertical line of said apparatus (2), respectively there is a search lamp (23) both sides of radar (24), respectively there is one page landing gate (27) body (2) both sides, bottom, and body (2) respectively has the window (25) of many groups annular arrangement up and down.

2, according to the vertically super aviation aircraft that falls of claim 1 described fly-dick-type, it is characterized in that, there is the annular snap (15) of twice protrusion bodies parallel to each other (2) in order to pintle hook lock wing (3) at described body (2) middle part, annular snap (15) is following up and down, last card face respectively has the identical card face ball grooves (54 of the size parallel to each other more than two, 55,56,57), two and annular snap (15) parallel annular ball grooves (35) are arranged on the body (2) between the twice annular snap (15), four pages of equidistant cabin doors (38) are arranged between the described ball grooves (35), the computer remote controlled system (not drawing among the figure) that all devices of control wing (3) are arranged in the cabin door (38), between every adjacent two pages of cabin doors (38) a gim peg mouth (37) is arranged all, described going up between ball grooves (35) and the preceding gim peg mouth (37) has a gear mouth (36) that can pass through body (2) internal pinionmw (not shown).

3, according to claim 1 described VTOL aircraft, it is characterized in that, described wing (3) is by wing circle (4) and be fixed in the inboard two groups of annular wing plates formations up and down of wing circle (4) annular snap (16), respectively there is a wing circle annular snap (16) with the interior side-to-side anastomosis of body (2) annular snap (15) at the two ends of wing circle (4), the face of card up and down of last bottom wing circle annular snap (16) respectively have size parallel to each other more than two identical and with the card face ball grooves (54 of body (2), 55,56,57) the circle card face ball grooves (48 of Wen Heing, 49) wing girth sheets (70) inner face has two wing circle ball grooves (42) parallel to each other and that coincide with body (2) ball grooves (35), article two, the engine room hatchway (44) and the gim peg mouth (45) that overlap with body (2) related device are arranged respectively between the ball grooves (42), last ball grooves (42) has the annular gear ring (43) of recessed girth sheets (70) between gim peg mouth (45), the top airfoil of described wing (3) has the directed wing (17) of many group " V " shapes, and a plurality of driving engine ventilation inlets (21) are arranged, the bottom wing bottom surface has many groups to press the flap groove (not drawing among the figure) of the wind wing (20) and respective numbers, bottom wing also has a plurality of and driving engine (47) the cooresponding strip arc port of spout (22), described driving engine (47) is fixed in the outer girth sheets (70) of engine room hatchway (44) and goes up and go up between the bottom wing, and corresponding separately a ventilation inlet (21), between every adjacent two driving engines (47) Fuel Tank (46) is arranged all, organize fixing support racks (18 more between the last bottom wing and have, 19).

According to claim 1 described institute VTOL aircraft, it is characterized in that 4, described body (2) top and wing (3) top airfoil all install solar panel (50,51).

5, according to claim 1 described VTOL aircraft, it is characterized in that the solar panel (50,51) of described body (2) and wing (3) connects by the inside and outside loop (61,71) on more than one ring-shaped rubber lead girth sheets (7) Internal and external cycle edge.

Images