CN101823554A - Loading airplane - Google Patents
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- CN101823554A CN101823554A CN201010139371A CN201010139371A CN101823554A CN 101823554 A CN101823554 A CN 101823554A CN 201010139371 A CN201010139371 A CN 201010139371A CN 201010139371 A CN201010139371 A CN 201010139371A CN 101823554 A CN101823554 A CN 101823554A
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Abstract
The invention discloses a loading airplane, which comprises an airplane body, an engine and airplane wings extending from two sides of the airplane body. The inner spaces of the airplane wings are expended into carrying spaces; airplane wing fluid channels are arranged in the airplane wings and comprise channel inlets and channel outlets; the channel inlets are communicated with the channel outlets which are communicated with a suction inlet of the engine; the upper surface of each airplane wing is provided with at least one channel inlet; the airplane wing fluid channels are positioned in a suction force state of the engine, so that the airplane wing fluid channels are communicated with the channel inlets on the upper surface communicated therewith; and the flow speed of fluid in the airplane wing fluid channels is large than the flow speed of the fluid passing through the lower surfaces of the air plane wings in a natural state, so that a pressure difference which is enough to lift the airplane is generated between the upper surfaces and the lower surfaces of the airplane wings. The invention can generate larger lifting sources from the inside of the airplane wings, so that the airplane wings and the airplane body form the loading airplane with a larger carrying space.
Description
Technical field
The present invention relates to the aircraft field, particularly relate to load carrying airplane.
Background technology
The wing of aircraft is to get from the wing imitation of flying bird, flying bird is brandished big and thin wing, realize the flight performance that it is remarkable with minimum energy consumption, and aircraft may not brandished big and thin wing, can only be fixed on the fuselage both sides to wing, be fixed wing.Since be fixed wing, its unique function produces lift exactly.
The wing that modern theory of flight and practice all define aircraft can only be designed to greatly and approach, so that produce enough lift.That is to say the instrument that existing all aircraft wings all produce as airplane ascensional force merely.
Over 100 years, the upper and lower surface of aircraft wing is cambered surface and plane all always, and the path difference of fluid process is little between two surfaces, and the difference of pressure that can produce is also little, and the lift of Chu Xianing is little thus, and load carrying ability can be not big yet, and the aircraft energy consumption is very big.
This shows that the lift that the wing of traditional load carrying airplane produces is little, unique way increases its energy consumption exactly and realizes load carrying ability.
Summary of the invention
The technical matters that the present invention mainly solves provides a kind of can the source from the bigger lift of the inner generation of wing, make wing and fuselage form the aircraft of the load-carrying in delivery space jointly.
For solving the problems of the technologies described above, the technical scheme that the present invention adopts is: a kind of load carrying airplane is provided, comprises fuselage, driving engine, from the extended wing in fuselage both sides, described wing inner space expands to the delivery space; Comprise the wing fluid passage in the described wing, described wing fluid passage comprises feeder connection and channel outlet, described feeder connection is communicated with described channel outlet, and described channel outlet is communicated with the sucking hole of described driving engine, and described upper surface of the airfoil is provided with at least one described feeder connection; Described wing fluid passage is in the suction force state of driving engine, the upper surface feeder connection that the wing fluid passage is communicated with it communicates, flow velocity when the rate of flow of fluid in the described wing fluid passage passes through the wing lower surface greater than fluid under the state of nature makes the wing upper and lower surface produce the difference of pressure that enough rises aircraft.
Wherein, have the fuselage fluid passage in the described fuselage, fuselage upper and lower surface, front end, be provided with the fuselage introducing port on every side, described fuselage fluid passage one end is communicated with described fuselage introducing port, and the other end is communicated with the sucking hole of described driving engine.
Wherein, described upper surface of the airfoil is provided with surperficial introducing port, the controller in the described surperficial introducing port that is communicated with described wing fluid passage, at least one the venetian blind type spoiler that connects described controller, described spoiler upper surface is an arc, lower surface is the plane, or upper and lower surface is a cambered surface, fluid is accelerated through out-of-date flow velocity, the flow velocity of described introducing port is accelerated.
Wherein, described wing, fuselage comprise inner casing and shell, form described wing fluid passage and fuselage fluid passage between described inner casing and shell, and described wing fluid passage and fuselage fluid passage communicate.
Wherein, the lower surface of described wing is the plane, and the upper surface of described wing is a cambered surface, and described cambered surface upper surface of the airfoil is connected fuselage respectively with the planar wings lower surface, is connected to form triangular structure; Or the lower surface of described wing is the plane, and the upper surface of described wing is the inclined-plane, and described inclined-plane upper surface of the airfoil is connected fuselage respectively with the planar wings lower surface, is connected to form triangular structure; Or described wing and fuselage combine together, and it is parabola shaped structure that upper surface forms cross-sectional plane; Or described wing and fuselage combine together, and it is wavy shaped configuration that upper surface forms cross-sectional plane.
Wherein, comprise the empennage that connects afterbody, described fuselage and wing, empennage are made up of polyhedral a plurality of triangles, and in conjunction with forming, and low early and high after, wing also is made up of the polyhedron triangle by two triangles in its middle machine body top and the bottom.
Wherein, the length of described wing fluid passage is greater than the length of wing lower surface fluid process.
Wherein, described controller connects described surperficial introducing port, described surperficial introducing port and front end introducing port by described controller control described spoiler unlatching, close or angle changes.
Wherein, to account for the volume ratio of wing be adjustable in the delivery of the expansion in described wing space.
Wherein, the interior delivery of the delivery space of expansion and fuselage space is one-body molded in the described wing, and described aircraft outer shape is stream line pattern, polyhedron shape, ellipse, circle or semicircle.
At the big and thin defective of prior art wing, the contriver makes following exploration: also can produce bigger lift as wing is big and thick, and why must wing big and thin and can not be big and thick?
Therefore, the present invention is proposed, proposition produces the big and thick wing of bigger lift from wing or fuselage interior, portion expands to the delivery space within it, form the delivery space jointly with fuselage, almost with the condition of conventional airplane with area under, only increase the volume of wing, the carrying capacity of aircraft is multiplied.
The wing inner space is expanded, with fuselage conduct delivery space, with the inner bigger lift source that produces of wing, and wing internal extended as delivery the space, approximately identical with the conventional airplane area, but carrying capacity significantly improves, and energy consumption reduces simultaneously, makes aircraft effectively deliver the space and is multiplied.
Driving engine communicates with wing internal fluid channels and each introducing port of upper surface, in driving engine strong suction state, make the upper surface rate of flow of fluid much larger than the flow velocity of lower surface in state of nature, it is poor that upper and lower surface produces immense pressure, produce bigger lift source thus, and this lift that produces under dynamic action much larger than the lift of conventional airplane, also can be controlled the lift size by driving engine.
Further, the fuselage of aircraft, wing communicate with driving engine by the fluid passage, make overall aircraft form a big wing, and wing is big more, lift is big more, produces bigger difference of pressure between the upper and lower surface of big wing under dynamic action, produces bigger lift source thus.
Aircraft in producing the process of lift, the position of reasonable Arrangement introducing port, making longitudinally, the fluid resistance of fluid resistance, side direction and the fluid resistance of rear portion zone of negative pressure significantly reduce.
The invention has the beneficial effects as follows:
1, produce bigger lift and wing expanded to the aircraft in delivery space internally, development from now on will be far-reaching to aircraft, and it has changed the present situation of aircraft development.
1., the wing upper and lower surface is the limited difference of pressure that cambered surface and plane produce in state of nature over 100 years, also just produce limited lift, the present invention is under dynamic action, the bigger difference of pressure of Chan Shenging internally, full its internal fluid channels, expand to upper surface of the airfoil by each introducing port then, make the wing upper and lower surface bigger difference of pressure of appearance and produce bigger lift.
2., big and thin wing is changed into greatly and thickly over 100 years, is extended to the delivery space therein, forms the load-carrying space with fuselage, and the aircraft carrying capacity is significantly improved.
3., aircraft produces unique lift source and is wing and screw propeller over 100 years, the present invention is from inner bigger lift and the big and thick wing of producing of wing, make the boundary desalination between wing and the fuselage and disappear, thereby a new generation that produces bigger lift internally that produces superior performance of new generation does not have the aircraft of wing and screw propeller.
2, aircraft occurs over 100 years, and unique function of wing is to produce the lift source.And the wing upper and lower surface be between arc and the plane in state of nature the path difference of fluid process very little, the difference of pressure of generation is little, the lift of Xing Chenging can be not big yet thus, so conventional airplane lift is little, energy consumption is very high, carrying capacity is also little.Driving engine of the present invention communicates by a plurality of introducing ports of fluid passage and upper surface of the airfoil, under the powerful suction of driving engine, make the upper surface of the airfoil flow velocity make much larger than the flow velocity of lower surface in state of nature that immense pressure to occur between the wing upper and lower surface poor, originate and produce bigger lift, this lift source that produces is internally accelerated at the upper surface of the airfoil flow velocity by power, the lift that makes upper and lower surface produce huge difference of pressure and produce, the lift that in state of nature, produces much larger than wing over 100 years, as at dynamic action lower wing upper surface rate of flow of fluid greater than traditional wing at the flow velocity of state of nature more than one times, just produce lift greater than one times, as greater than the flow velocity of traditional wing more than 20 times, just produce greater than the lift of 20 times on traditional wing even more.This state is easy to realize by motor speed control.Meanwhile, the both sides wing is extended to the delivery space internally, makes wing not only become bigger lift source, and become the delivery space, the delivery space of aircraft is multiplied.
3, among the present invention, fuselage and wing are inner common as the delivery space, approximately be equal to the space in the fuselage after the inner space expansion of both sides wing, aircraft delivery space just is multiplied, and the area of aircraft is compared with conventional airplane almost, wing of the present invention is under dynamic action, and lift is than the big several times of conventional airplane, by appropriate design be easy to promote the to double aircraft normal flight of carrying capacity.
4, further, fuselage, wing, communicate, whole aircraft is considered as a big wing by introducing port and fluid passage and driving engine, the big more lift of wing is big more, and the wing upper and lower surface produces the immense pressure difference and produces bigger lift under dynamic action greatly.
5, aircraft of the present invention produces in the process of lift internally, the reasonable Arrangement of each introducing port imports front end, on every side fluid resistance in the fluid passage, make front fuselage and form relative zone of negative pressure on every side, spray at a high speed from the rear end then, moment is filled the rear portion zone of negative pressure, makes aircraft at front end be relative zone of negative pressure on every side, the rear portion is that the comparatively desirable fluid distribution state in powered district travels, so, having changed the fluid distribution state, fluid resistance significantly reduces.
6, wing of the present invention and fuselage form the delivery space jointly, carrying capacity is significantly improved, change the structure that wing over 100 years can only produce lift thus, produced the bigger lift of a new generation, bigger carrying capacity, speed is faster, energy consumption is lower all kinds of aircraft thus.
Description of drawings
Fig. 1 is the front schematic view of load carrying airplane embodiment one of the present invention;
Fig. 2 is the wing A-4 cross-sectional schematic of load carrying airplane embodiment one of the present invention;
Fig. 3 is the elevational schematic view of load carrying airplane embodiment one of the present invention;
Fig. 4 is the front schematic view of load carrying airplane embodiment two of the present invention;
Fig. 5 is the elevational schematic view of load carrying airplane embodiment two of the present invention;
Fig. 6 is the front schematic view of load carrying airplane embodiment three of the present invention;
Fig. 7 is the front schematic view of load carrying airplane embodiment four of the present invention;
Fig. 8 is the elevational schematic view of load carrying airplane embodiment four of the present invention;
Fig. 9 is the front schematic view of load carrying airplane embodiment five of the present invention;
The front schematic view of Figure 10 load carrying airplane embodiment six of the present invention;
The side schematic view of Figure 11 load carrying airplane embodiment six of the present invention;
Figure 12 is the front schematic view of the another kind of embodiment of embodiment six;
Figure 13 is embodiment seven elevational schematic view;
Figure 14 is that the embodiment heptalateral is looked scheme drawing;
Figure 15 is embodiment seven front schematic view.
The specific embodiment
Load carrying airplane embodiment of the present invention comprises:
Fuselage, driving engine, from the extended wing in fuselage both sides, described wing inner space expands to the delivery space;
Comprise the wing fluid passage in the described wing, described wing fluid passage comprises feeder connection and channel outlet, described feeder connection is communicated with described channel outlet, and described channel outlet is communicated with the sucking hole of described driving engine, and described upper surface of the airfoil is provided with at least one described feeder connection;
Described wing fluid passage is in the suction force state of driving engine, the upper surface feeder connection that the wing fluid passage is communicated with it communicates, flow velocity when the rate of flow of fluid in the described wing fluid passage passes through the wing lower surface greater than fluid under the state of nature makes the wing upper and lower surface produce the difference of pressure that enough rises aircraft.
Described state of nature be meant without the feeder connection of fluid passage of the present invention suck under the fluid situations, naturally at the fluid state of aircraft surfaces process.
According to foregoing invention embodiment, can extend and specifically dissolve how following embodiment:
Described wing fluid passage 4 is in the suction force state of driving engine 801,802, flow velocity when making described wing fluid passage 4 interior rate of flow of fluids pass through wing 5 lower surfaces greater than fluid under the state of nature makes wing 5 upper and lower surfaces 201,202 produce the difference of pressure that enough rises aircraft.
Described upper surface of the airfoil 201 is provided with surperficial introducing port 701, the controller 703 in the described surperficial introducing port 701 that is communicated with described wing fluid passage, at least one the venetian blind type spoiler 704 that connects described controller 703, described spoiler 704 upper surfaces are arc, lower surface is the plane, or upper and lower surface is a cambered surface, fluid is accelerated through out-of-date flow velocity, the flow velocity of described surperficial introducing port 701 is accelerated.
When aircraft flies under driving engine 801 promotes, particularly driving engine 801 extremely strong suction make wing 5 upper surfaces 201 uniform upper surface introducing port 701 and front end introducing ports 7 suck fluid high-speed on the housing in the wing fluid passage 4, make in the wing fluid passage 4 and by introducing port 7, upper surface 201 forms two-layer swiftly flowing fluid on 701 wings that communicate with it, particularly wing fluid passage 4 is interior under extremely strong suction, wing fluid passage 4 inner fluid flowing velocities are fast, the path length of process, area is big, form great difference of pressure with the flow velocity of wing lower surface 202 in state of nature, 4 inside produce very big lift in the wing fluid passage thus, fill around wing fluid passage 4, at introducing port 7 by communicating with it, 701 expand to entire upper surface 201, make wing upper and lower surface 201, form great difference of pressure between 202, produce very big lift thus, as fluid velocity faster than the flow velocity of traditional wing upper strata cambered surface more than one times, the lift that can be enhanced about more than once just, as rate of flow of fluid faster than 20 times, just improve the lift more than 20 times, in addition more.This state just is easy to realize by control driving engine 801 rotating speeds.
The wing of both sides is under the powerful suction of driving engine 801 at this moment, by introducing port 7 vertical fluid resistance is sucked the fluid passage, longitudinal resistance is reduced, upper surface introducing port 701 sucks the lateral fluid resistance in the wing fluid passage 4, the lateral fluid resistance is reduced, while is in the upper and lower surface 201 of wing 5, produce very big difference of pressure between 202, produce very big lift thus, driving engine 801 is vertical what suck then, the lateral fluid resistance, completely from the strong downwards ejection of export mouth 8, the antagonistic force of generation makes aircraft produce more high thrust and obtains bigger lift.
Aloft, folding and angle by spoiler 704 in the controller 703 control introducing ports 701 change, just can realize aircraft lifting and landing, variation such as turn to, as only opening each introducing port 701 of upper surface, very big difference of pressure appears in upper and lower surface, aircraft rises, in like manner as long as open the introducing port (Fig. 2) of the connection wing fluid passage 4 that is arranged on wing lower surface 202 in addition, aircraft descends, only open a side wing introducing port 701, aircraft turns to, and the adjusting of opening and closing introducing port and spoiler air guide angle can realize the needs that the aircraft difference in functionality changes, make aircraft more flexible, control more convenient.
At present, the aircraft load-carrying mainly is divided into two parts, the lift that wing produces, fuselage produces desired power for the enough big driving engine of delivery space requirement, but upper surface of the airfoil is cambered surface and lower surface is the plane, the path difference of both fluid processes is little, and the difference of pressure of generation is also little, and consequent naturally lift is also little.So load carrying ability is that cost realizes by driving engine with very big energy consumption mainly, among the present invention in both sides wing 5 as the load-carrying space, enlarged nearly one times loading space than conventional airplane.Under driving engine 801 powerful suctions, make between both sides wing 5 upper and lower surfaces 201,202 to produce very big difference of pressure and produce very big lift, in this state, the required energy consumption of aircraft reduces, and load carrying ability improves greatly simultaneously.
This shows that conventional airplane is to be cost to enlarge the airframe wing and to improve the driving engine energy consumption, and the present invention expands as the delivery space in wing inside, and to improve lift, increasing part power is to assist the purpose that realizes increasing load-carrying.
Opportunity of combat can make speed improve by this structure, and carrying capacity improves, than the easier vertical takeoff and landing of existing aircraft.
When the both sides wing down and fuselage tail rear engine 801,803 when working, produce huge suction, make big upper surface of the airfoil 201 suck the fluid passage to fluid high-speed by wing and each introducing port 7,701 of fuselage upper surface, upper surface 201 is at dynamic regime, produce very big difference of pressure with lower surface 202 at the flow velocity of state of nature, so produce very big lift.In this state, do not need too big power just can promote the aircraft vertical lift, three driving engines 801,803 form the strong scorching hot fluid (the tail rear engine is downward with the vectoring technology spout) that sprays of triangle downwards and are easy to make the aircraft vertical lift, reduce energy consumption than the whole dependence powered of conventional airplane.
Not too big as aircraft, wing both sides driving engine 801 just can promote the aircraft vertical lift.
Another embodiment removes driving engine 801 and wing bottom flow passage under the wing of both sides, establishes the last fluid passage on the fuselage, and driving engine 803 air suctiton inlets communicate with last fluid passage with big upper surface of the airfoil 201 each introducing port that fuselage and wing form.Wing is the wing (not drawing) of conventional airplane, under the effect of driving engine strong suction, makes big wing upper and lower surface produce great difference of pressure and produce lift.
Among the present invention, the length of described wing fluid passage 4 can be greater than the length of wing lower surface 202 fluid processes.
Embodiment 5, as shown in Figure 9, are not both wing upper strata, both sides housing 201 with embodiment 1 and intersect the formation triangle at back, and the stability of aircraft improves greatly.Driving engine 801 has 2 introducing ports, top introducing port 706, front end introducing port 705, wherein the wing fluid passage 4 in top introducing port 706 and the wing 5 communicates, the same front end with conventional airplane of front end introducing port 705 is an admission port, introducing port 705 and 706 can open as required or close or the aspirated volume size control, when closing introducing port 705, open top introducing port 706 and wing fluid passage 4 and each introducing port 7,701 communicate, strong suction makes the rate of flow of fluid of upper surface 201 much larger than the flow velocity of lower surface 202 in state of nature, form very big difference of pressure thus and produce bigger lift, by the control of driving engine 801 rotating speed speeds, thereby can control the lift situation of aircraft as required.Can close top introducing port 706 aloft, open front end introducing port 705, with regard to as the driving engine of conventional airplane, or operation conversely; Partly open introducing port 705,706 simultaneously also, driving engine 801 can suck the fluid of sense of motion, also can suck upper surface of the airfoil 201 lip-deep fluids, control by top introducing port 706 suction quantity, thereby the lift size of control wing 5, same principle, driving engine 802 also can be by this setting.
Embodiment 6, as Figure 10, shown in Figure 11, be not both with embodiment 4, the aircraft front shape is semicircle, the side is similar to train, might as well be called monorail train, if above embodiment also can see the vestige of traditional wing, so monorail train is not because there is wing to be different from existing aircraft so, monorail train delivery space increases introducing port 7 greatly, 701 and around the fluid passage 4 around the fuselage, communicate with fuselage afterbody driving engine 801, fluid passage 4 between shell 2 and the inner casing 3 around fuselage around, in driving engine 801 powerful suction force state, produce the immense pressure difference between the surface, aircraft top and the bottom and produce bigger lift.
Another embodiment, as Figure 11, shown in Figure 12, this machine upper surface is the waveform that cambered surface forms, and both sides are arc, and the bottom is the plane, does not have the bottom flow passage.This shows that type aircraft can be Any shape, the more suitable flight of streamline contour is travelled certainly.
Embodiment 7, as Figure 13,14, shown in 15, fuselage 1 and wing 5, empennage 502 is made up of polyhedral a plurality of triangles, its middle machine body top and the bottom by 2 triangles in conjunction with forming, and it is low early and high after, wing 5 also is made up of the polyhedron triangle, the stability of aircraft improves greatly, make also simple simultaneously, the shell 2 of fuselage 1 and wing 5 and inner casing 3, between be fluid passage 4, with front end introducing port 7, the introducing port of the first half of shell and wing 5 inboard at least one introducing port 701 and 3 driving engines 801 in rear portion communicates all around, the air nozzle of driving engine 801 communicates with export mouth 8, delivery space 501, inside on fuselage 1 inside and the wing 5 increases the aircraft carrying capacity greatly, the fluid passage 4 of fuselage 1 and wing 5 communicates with driving engine 801 simultaneously, making whole airplane skin 2 housings is the upper surface 201 of fuselage 1 first half and wing 5 inboards, lower surface 202 with the base plane housing and the wing outside, the big wing that forms, the area of big wing is much larger than traditional wing, wing 5 is big more, the difference of pressure that upper and lower surface produces is big more, and lift is big more.
When aircraft travels, driving engine 801 produces huge suction fluid is sucked fluid in the fluid passage 4 from front end introducing port 7 casing-upper halfs and wing 5 at least one introducing port 701 of interior both sides, make near the fluid the introducing port suck fast, so that be distributed on the shell 2 near each introducing port, form the mobile fast fluid of case surface last layer and be inhaled into each introducing port, fluid is in the huge suction force state of driving engine, the path length of the internal fluid channels of process, area is big, speed is fast, air pressure is low, form the inside and outside two-layer fluid that flows fast on upper surface of outer cover 201 and in the fluid passage, produce very big difference of pressure with the flow velocity of lower surface 202 in state of nature in the base plane housing and the wing outside, produce very big lift thus, the huge lift that under dynamic action, produces in this fluid passage internally, in the fluid passage in full half one aboard, expand to again communicate with it rationally be distributed on each introducing port 701 on the skin, make the rate of flow of fluid that flows fast on the case surface be equal to the flow velocity in the fluid passage, inside and outside two-layer flow velocity is the flow velocity in state of nature faster than the base plane and the wing outside far, it is big more that both flow velocitys differ, the lift that aircraft produces is big more, and load carrying ability is just big more simultaneously.Compare with conventional airplane, lift improves, and load carrying ability improves, and energy consumption reduces simultaneously.
In addition, this machine shell is made of polyhedron shape entirely, except that stability, the load carrying ability of aircraft improves greatly, also can weaken radar returns.
Among the present invention, the delivery space of expansion can be one-body molded with delivery space in the fuselage in the described wing, and described aircraft outer shape is stream line pattern, polyhedron shape, ellipse, circle or semicircle.
The above only is embodiments of the invention; be not so limit claim of the present invention; every equivalent structure or equivalent flow process conversion that utilizes specification sheets of the present invention and accompanying drawing content to be done; or directly or indirectly be used in other relevant technical fields, all in like manner be included in the scope of patent protection of the present invention.
Claims (10)
1. load carrying airplane comprises fuselage, driving engine, from the extended wing in fuselage both sides, it is characterized in that:
Described wing inner space expands to the delivery space;
Comprise the wing fluid passage in the described wing, described wing fluid passage comprises feeder connection and channel outlet, described feeder connection is communicated with described channel outlet, and described channel outlet is communicated with the sucking hole of described driving engine, and described upper surface of the airfoil is provided with at least one described feeder connection;
Described wing fluid passage is in the suction force state of driving engine, the upper surface feeder connection that the wing fluid passage is communicated with it communicates, flow velocity when the rate of flow of fluid in the described wing fluid passage passes through the wing lower surface greater than fluid under the state of nature makes the wing upper and lower surface produce the difference of pressure that enough rises aircraft.
2. load carrying airplane according to claim 1 is characterized in that:
Have the fuselage fluid passage in the described fuselage, fuselage upper and lower surface, front end, be provided with the fuselage introducing port on every side, described fuselage fluid passage one end is communicated with described fuselage introducing port, and the other end is communicated with the sucking hole of described driving engine.
3. load carrying airplane according to claim 2 is characterized in that:
Described upper surface of the airfoil is provided with surperficial introducing port, the controller in the described surperficial introducing port that is communicated with described wing fluid passage, at least one the venetian blind type spoiler that connects described controller, described spoiler upper surface is an arc, lower surface is the plane, or upper and lower surface is a cambered surface, fluid is accelerated through out-of-date flow velocity, the flow velocity of described introducing port is accelerated.
4. load carrying airplane according to claim 3 is characterized in that:
Described wing, fuselage comprise inner casing and shell, form described wing fluid passage and fuselage fluid passage between described inner casing and shell, and described wing fluid passage and fuselage fluid passage communicate.
5. according to each described load carrying airplane of claim 1 to 4, it is characterized in that:
The lower surface of described wing is the plane, and the upper surface of described wing is a cambered surface, and described cambered surface upper surface of the airfoil is connected fuselage respectively with the planar wings lower surface, is connected to form triangular structure; Or
The lower surface of described wing is the plane, and the upper surface of described wing is the inclined-plane, and described inclined-plane upper surface of the airfoil is connected fuselage respectively with the planar wings lower surface, is connected to form triangular structure; Or
Described wing and fuselage combine together, and it is parabola shaped structure that upper surface forms cross-sectional plane; Or
Described wing and fuselage combine together, and it is wavy shaped configuration that upper surface forms cross-sectional plane.
6. according to each described load carrying airplane of claim 1 to 4, it is characterized in that:
Comprise the empennage that connects afterbody, described fuselage and wing, empennage are made up of polyhedral a plurality of triangles, and in conjunction with forming, and low early and high after, wing also is made up of the polyhedron triangle by two triangles in its middle machine body top and the bottom.
7. according to each described load carrying airplane of claim 1 to 5, it is characterized in that:
The length of described wing fluid passage is greater than the length of wing lower surface fluid process.
8. load carrying airplane according to claim 3 is characterized in that:
Described controller connects described surperficial introducing port, described surperficial introducing port and front end introducing port by described controller control described spoiler unlatching, close or angle changes.
9. load carrying airplane according to claim 1 is characterized in that: the volume ratio that the expansion delivery space in the described wing accounts for wing is adjustable.
10. load carrying airplane according to claim 1 is characterized in that: the interior delivery of the delivery space of expansion and fuselage space is one-body molded in the described wing, and described aircraft outer shape is stream line pattern, polyhedron shape, ellipse, circle or semicircle.
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| CN201010139371A CN101823554A (en) | 2010-03-29 | 2010-03-29 | Loading airplane |
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| CN201010139371A CN101823554A (en) | 2010-03-29 | 2010-03-29 | Loading airplane |
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| CN101941522A (en) * | 2010-09-13 | 2011-01-12 | 朱晓义 | Flying device |
| CN103612742A (en) * | 2013-11-27 | 2014-03-05 | 中国航空工业集团公司西安飞机设计研究所 | Wavy flying-wing aircraft pressure chamber |
| CN104554734A (en) * | 2014-12-31 | 2015-04-29 | 陈俞任 | Jet-propelled helicopter |
| WO2018196810A1 (en) * | 2017-04-26 | 2018-11-01 | 朱晓义 | Aircraft gaining greater propulsion and lift from fluid continuity |
| CN110606186A (en) * | 2019-09-12 | 2019-12-24 | 青岛度丘新能源技术有限公司 | Integrated frame light aircraft |
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| CN101224790A (en) * | 2008-01-25 | 2008-07-23 | 朱晓义 | Aerocraft equipped with airstream channel |
| CN101229822A (en) * | 2008-02-04 | 2008-07-30 | 朱晓义 | Moving device |
| CN101618724A (en) * | 2009-07-27 | 2010-01-06 | 朱晓义 | Train |
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| CN101941522B (en) * | 2010-09-13 | 2013-07-17 | 朱晓义 | Flying device |
| CN103612742A (en) * | 2013-11-27 | 2014-03-05 | 中国航空工业集团公司西安飞机设计研究所 | Wavy flying-wing aircraft pressure chamber |
| CN103612742B (en) * | 2013-11-27 | 2016-04-13 | 中国航空工业集团公司西安飞机设计研究所 | A kind of waveform flying wing aircraft pressurized module |
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| WO2018196810A1 (en) * | 2017-04-26 | 2018-11-01 | 朱晓义 | Aircraft gaining greater propulsion and lift from fluid continuity |
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| US11858617B2 (en) | 2017-04-26 | 2024-01-02 | Xiaoyi Zhu | Propeller-driven helicopter or airplane |
| CN110606186A (en) * | 2019-09-12 | 2019-12-24 | 青岛度丘新能源技术有限公司 | Integrated frame light aircraft |
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