CN105000162A

CN105000162A - Aircraft with lift force and buoyancy

Info

Publication number: CN105000162A
Application number: CN201510267990.XA
Authority: CN
Inventors: 吕怀民; 吕屾
Original assignee: Individual
Current assignee: Individual
Priority date: 2015-05-18
Filing date: 2015-05-18
Publication date: 2015-10-28

Abstract

The invention provides an aircraft with lift force and buoyancy, which relates to technologiesof engineering such as aviation, photovoltaics,air consignment, air communication monitoring, sports and the like. The aircraft comprises a wing body (2), an aircraft body (3), a taking body or taking cabin body (4), a propulsion system (5), a control system (6) and other sub bodies; the aircraft is characterized by further comprising a buoyancy gas (1) and a photovoltaic power generation system (10); the density of the buoyancy gas (1) is lower than that of the air; at least one of the wing body (2), the aircraft body (3) and the taking body or taking cabin body (4) comprises the buoyancy gas (1) and the photovoltaic power generation system (10). The aircraft with the lift force and the buoyancy, provided by the invention, is advantaged in that the aircraft is provided with both single buoyancy of the wing body (2) and double buoyancy of the wing body (2) and the aircraft body (3) so that the dead-weight and flight energy consumption of the aircraft are greatly reduced; and without consuming fuels, flight as well as vertical take-off and landing can be carried out with no time limit by using solar energy. Even though the aircraft suffers accidents such as collision, stopping, abrupt meteorological change and the like in the air, injuries of personnel, crashing of the cabin and damages of the aircraft cannot occur and the craft is very safe under effects of the buoyancy, the flexible wing body (2) and the aircraft body (3). The manufacturing cost of the aircraft with the lift force and the buoyancy, provided by the invention, is extremely low.

Description

There is the aircraft of lift and buoyancy

Technical field

The present invention relates to aeronautical engineering, space engineering, photovoltaic energy engineering, air communication transportation engineering, air communication engineering, the aerial field of engineering technology such as supervision control engineering, physical culture engineering, especially the field of engineering technology such as aircraft, aerial loading delay platform of the vertical takeoff and landing of photovoltaic power.

Background technology

There is following problem in existing aircraft.1, existing aircraft all only relies on lifting flight, does not make full use of buoyancy and replaces lift, in order to reduce lift power consumption, the saving fuel energy.2, existing dirigible only relies on huge floatage air bag flight, and the flight resistance of floatage air bag is too large; It does not arrange wing, and the lift making full use of wing, to replace part buoyancy, in order to reduce the volume of floatage air bag, reaches the object reducing flight resistance; Reduce flight resistance and just decrease flight power consumption, the saving fuel energy.2, existing aircraft is all consumable liquid fuel, does not make full use of solar electric power.3, existing aircraft major part is all rely on airport landing, can not Vertical Free landing.4, the air mileage of the autogyro of existing vertical takeoff and landing is short, speed is slow again.7, existing aircraft is dangerous, as long as aloft have an accident, just may cause and fall.8, existing aircraft cost high, manipulate complexity again, limit a large amount of of it and generally use; Family, private daily field is extensively entered be not as easy like that as automobile.

Technology contents

The object of the invention is exactly to overcome above-mentioned existing shortcoming, provides a kind of aircraft having lift and buoyancy.Object of the present invention can by taking following measure to reach.

Content 1.

The aircraft of lift and buoyancy is had to comprise finned body (2), propulsion system (5), control system (6), it also includes following wherein at least a kind of split, device health (3), takes body or passenger compartment body (4); It is characterized in that:

The aircraft of lift and buoyancy is had also to include buoyant gas (1); The density of its buoyant gas (1) is lower than the gas density of the aircraft external space having lift and buoyancy, and it is the buoyant gas of tool.

Due under the effect of wing body (2), the middle buoyant gas (1) of device health (3), make the aircraft of lift and buoyancy not only have single " lift " function of finned body (2), also have dual " buoyancy " function of finned body (5), device health (3).Under " lift " and " buoyancy " is added folded effect, result greatly reduces the deadweight of the aircraft of lift and buoyancy.So both decrease flight energy consumption, making again aircraft vertical be elevated becomes possibility.In addition, owing to being provided with buoyant gas (1), even if there occurs accident (such as collide, stop, meteorological sudden change etc. accident) aloft, this has the aircraft of lift and buoyancy also slowly can drop to ground, and crash accident can not occur.Again due to the flexible air-bag that wing body (2), device health (3) are large volumes, there occurs collision case aloft, also can not cause the injury to personnel and cabin and damage.If occurred, air bag leaks gas, buoyant gas (1) has been revealed, without this accident of buoyancy, had the aircraft of lift and buoyancy just to become aerodone, gliding parachute, relies on glide to drop to ground.Therefore, there is the aircraft of lift and buoyancy very safe, substantially there will not be personnel's casualties accident.If unmanned vehicle, its performance is better, cost performance is higher.

The object of the invention can also by taking following measure to reach.

Content 2.

The aircraft having lift and buoyancy according to content 1, also includes following characteristics:

The aircraft of lift and buoyancy is had also to include photovoltaic generating system (10); Its photovoltaic generating system (10) includes photovoltaic cell (10.1).

Wing body (2), both as lift structure, again as buoyant structure, also as the face body of photovoltaic generation, is provided with 3 kinds of functions.The aircraft of lift and buoyancy is had to utilize the main source of photovoltaic electric power as flying power of the photovoltaic generating system (10) on wing body (2), device health (3).Under above-mentioned 3 kinds of advantages, under adding the condition making full use of unobstructed, the high radiated solar energy in high-altitude, carry out the photovoltaic generation at full capacity of large area wing body (2), device health (3), photovoltaic generating system (10) just can meet the propelling electricity needs of aircraft completely, or completely satisfied heating ammoniacal liquor, water, air etc. aqueous vapor becomes the vapours of high temperature, the electricity needs (its vapours, hot air can be used as buoyant gas (1)) of hot air.There is the aircraft of lift and buoyancy just to achieve like this: not needing under consume fuel condition, utilize solar power just can carry out timeless flight, utilize solar power just can carry out the vertical takeoff and landing limited without number of times.If unmanned vehicle, its performance is better, cost performance is higher.

Content 3.

Have the aircraft of lift and buoyancy also to include following wherein at least a kind of split, photovoltaic generating system (10), vertical tail (7), tailplane (8), alighting gear (9), floatage air bag (11), balloonet (12), sling system (13), mooring or fixed system (14), cooling or compression store gas system (15), electric heating system (16), air-pump inflating system (17), high altitude communication or monitor supervision platform device (18), inner interlayer (19).

Its vertical tail (7), tailplane (8) be used to control heading, height;

Its alighting gear (9) is used to control that the aircraft of lift and buoyancy uses when landing ground;

Its floatage air bag (11) is for storing buoyant gas (1);

Its balloonet (12) is for regulating the rigidity of flex-wing body (2.2), flexible device health (3.2);

Its sling system (13) is for wing body (2), device health (3), takes link between body or passenger compartment body (4);

It, due to light, even floats, so must be fixed on ground by mooring or fixed system (14) there being the aircraft of lift and buoyancy;

Its cooling or compression store gas system (15) by cooling, compression etc. method the volume-diminished of buoyant gas (1), even can be become liquid, is stored in high pressure vessel or in bomb; Doing so avoids the buoyant gas (1) when high-altitude and cubic expansion occurs, cause increase flight resistance, or damage wing body (2), device health (3) situation; When especially adopting ammonia (1.3) as buoyant gas (1), Be very effective;

Its electric heating system (16) makes full use of the unobstructed advantage in high-altitude and carries out the electric power of photovoltaic generation at full capacity to heat vapours, the hot air that ammoniacal liquor, water, air etc. aqueous vapor forms high temperature.The buoyant gas (1) that its vapours, hot air can be produced as solar electric power, in order to improve the buoyancy having the aircraft of lift and buoyancy;

Its air-pump inflating system (17) for being full of the specialized equipment of high ballast gas (20), Leakage prevention buoyant gas (1) in multilayer shell structure;

Its high altitude communication or monitor supervision platform device (18) are for the communication on ground provides high-altitude forwarding, transmission equipment platform, are the watch-dog platform that ground provides high-altitude photograph, mapping, monitoring;

Its inner interlayer (19) can be isolated into multiple cavity multiple wing body (2), device health (3) etc. these point of body component, improves their rigidity and leakage performance.There is seepage in the buoyant gas (1) of a cavity, can not cause the buoyant gas (1) of other cavity that seepage occurs, the buoyant gas (1) that also can not affect other cavity normally works, and namely the buoyancy of other cavity does not reduce.

Content 4.

In following wherein at least a kind of split, include buoyant gas (1), wing body (2), device health (3), take body or passenger compartment body (4);

Its wing body (2) is arranged on following wherein at least a kind of position, device health (3) is upper, under device health (3), in device health (3), take body or passenger compartment body (4) is upper, take body or passenger compartment body (4) under; Wing body (2) is connected with following wherein at least a kind of split, device health (3), takes body or passenger compartment body (4);

Its device health (3) is arranged on following wherein at least a kind of position, wing body (2) is upper, under wing body (2), in wing body (2), take body or passenger compartment body (4) is upper, take body or passenger compartment body (4) under; Device health (3) is connected with following wherein at least a kind of split, wing body (2), takes body or passenger compartment body (4);

It takes body or passenger compartment body (4) is arranged on following wherein at least a kind of position, on wing body (2), under wing body (2), in wing body (2), on device health (3), under device health (3), in device health (3); Take body or passenger compartment body (4) is connected with following wherein at least a kind of split, wing body (2), device health (3);

Its propulsion system (5) is arranged on following wherein at least a kind of position, wing body (2), device health (3), takes body or passenger compartment body (4);

Its control system (6) is arranged on following wherein at least a kind of position, wing body (2), device health (3), takes body or passenger compartment body (4).

Content 5.

The buoyancy of its buoyant gas (1) is equal to and greater than the deadweight of the aircraft of lift and buoyancy;

Its buoyant gas (1) includes following wherein one at least, hydrogen (1.1), helium (1.2), ammonia (1.3), aqueous vapor (1.4), hot air (1.5), fuel gas (1.6);

Its wing body (2) also comprises rotation mechanism (2.4) after a little while, and the driving of this hectare of rotation mechanism (2.4) changes the direction of wing body (2), can before, can afterwards, can go up, can descend to rotate;

Its device health (3) also includes movable upper hatchcover (3.4); Its movable upper hatchcover (3.4) can become openable cabin body device health (3) after opening; In the cabin body that this is opened, the floatage air bag (11) larger than device health (3) can be set;

It takes body or passenger compartment body (4) includes following wherein at least a kind of split, drives pedestal (4.1), driving compartment body (4.2);

Its propulsion system (5) includes following wherein one of at least kind system, electric propulsion system (5.1), combustion engine propulsion system (5.2), jet propulsion system (5.4), manual feed system (5.5), hybrid propulsion system (5.6); Its hybrid propulsion system (5.6) includes following wherein at least 2 kinds, electric propulsion system (5.1), combustion engine propulsion system (5.2), jet propulsion system (5.4), manual feed system (5.5); Wherein electric propulsion system (5.1) is connected with the circuit of photovoltaic generating system (10);

Its propulsion system (5) also comprises rotation mechanism (5.10) after a little while, hectare rotation mechanism (5.10) drive change propulsion system (5) direction of propulsion, can before, can afterwards, can go up, can descend rotate advance;

Its control system (6) includes following wherein one of at least kind system, pilot steering control system (6.1), automatic Pilot control system (6.2), mixing Ride Control System (6.3); Its mixing Ride Control System (6.3) includes pilot steering control system (6.1) and automatic Pilot control system (6.2).

Content 6.

Its wing body (2) includes following wherein at least a kind of split, rigid wings body (2.1), flex-wing body (2.2), hard and soft combination wing body (2.3); Its hard and soft combination wing body (2.3) includes following wherein at least a kind of unitized construction form, rigid wings body (2.1) and below flex-wing body (2.2) above, below rigid wings body (2.1) and flex-wing body (2.2) above;

Its device health (3) includes following wherein at least a kind of split, rigid body (3.1), flexible body (3.2), hard and soft combination health (3.3); Its hard and soft combination health (3.3) includes following wherein at least a kind of unitized construction form, rigid body (3.1) and below flexible body (3.2) above, below rigid body (3.1) and flexible body (3.2) above.

Content 7.

The aircraft having lift and buoyancy according to content 2 or content 3, also includes following characteristics:

Photovoltaic generating system (10) also includes following wherein at least a kind of parts, photovoltaic cell (10.1), load governor, storage battery, inverter; Include photovoltaic generating system (10) at the upper surface of following wherein at least a kind of split or side surface, wing body (2), device health (3), take body or passenger compartment body (4), vertical tail (7), tailplane (8);

Its photovoltaic cell (10.1) include following one or more: crystal silicon type battery, amorphous silicon type battery, film type battery, flexible thin film type battery, light-focusing type battery, multi-element compounds type battery, dye sensitization type battery, CaAs (gallium arsenide) type battery, CIGS (CIGS) type battery, CdTe (cadmium antimonide) type battery, InGaP/A type battery.

Content 8.

The aircraft having lift and buoyancy according to content 1 or content 2 or content 3, also includes following characteristics:

In following wherein at least a kind of split, also include buoyant gas (1), vertical tail (7), tailplane (8), floatage air bag (11), cooling or compression store gas system (15);

Include photovoltaic cell (10.1) at the upper surface of following wherein at least a kind of split or side surface, wing body (2), device health (3), take body or passenger compartment body (4), vertical tail (7), tailplane (8);

Its vertical tail (7) or tailplane (8) are arranged on the afterbody of following wherein at least a kind of position, wing body (2), device health (3), take body or passenger compartment body (4);

Under its alighting gear (9) is arranged on following wherein at least a kind of split, wing body (2), device health (3), take body or passenger compartment body (4);

Its floatage air bag (11) is arranged in following wherein at least a kind of split, wing body (2), device health (3), takes body or passenger compartment body (4), vertical tail (7), tailplane (8); Floatage air bag (11) arranges with following wherein at least a kind of gas column form, longitudinal gas column form, horizontal gas column form;

Its balloonet (12) is arranged in following wherein at least a kind of split, wing body (2), device health (3), takes body or passenger compartment body (4), vertical tail (7), tailplane (8), floatage air bag (11);

Its sling system (13) is arranged on following wherein at least a kind of position, wing body (2), device health (3), takes body or passenger compartment body (4), floatage air bag (11); Its sling system (13) is connected with following wherein two kinds of splits at least, wing body (2), device health (3), takes body or passenger compartment body (4), floatage air bag (11); It is for wing body (2), device health (3), takes connection between body or passenger compartment body (4), floatage air bag (11);

Its mooring or fixed system (14) are connected with following wherein at least a kind of split, wing body (2), device health (3), take body or passenger compartment body (4); Mooring or fixed system (14) are also connected with ground;

Its cooling or compression store gas system (15) and are arranged on following wherein at least a kind of split position, wing body (2), device health (3), take body or passenger compartment body (4), vertical tail (7), tailplane (8), floatage air bag (11); Cooling or compression store gas system (15) and are connected with following wherein at least a kind of split, and propulsion system (5) power connects, propulsion system (5) pipeline connects, buoyant gas (1) pipeline connects, floatage air bag (11) pipeline connects, photovoltaic generating system (10) circuit connects;

Its electric heating system (16) is arranged in following wherein at least a kind of split, wing body (2), device health (3), takes body or passenger compartment body (4), vertical tail (7), tailplane (8), floatage air bag (11); Electric heating system (16) is connected with the circuit of photovoltaic generating system (10);

Its air-pump inflating system (17) is arranged on multilayer shell locations of structures; Air-pump inflating system (17) is arranged on following wherein at least a kind of split position, wing body (2), device health (3), takes body or passenger compartment body (4), vertical tail (7), tailplane (8), floatage air bag (11), inner interlayer (19); Heavily the density of gas (20) is equal to or higher than the density of the aircraft external space of lift and buoyancy;

Its high altitude communication or monitor supervision platform device (18) are arranged on following wherein at least a kind of position, wing body (2), device health (3), take body or passenger compartment body (4);

Its inner interlayer (19) includes following wherein one at least, rigidity inner interlayer (19.1), flexible inner interlayer (19.2), hard and soft combination inner interlayer (19.3); Its hard and soft combination inner interlayer (19.3) includes rigidity inner interlayer (19.1) and flexible inner interlayer (19.2); Its inner interlayer (19) is arranged on following wherein at least a kind of position, wing body (2), device health (3), takes body or passenger compartment body (4), vertical tail (7), tailplane (8), floatage air bag (11), balloonet (12);

Its wing body (2) or device health (3) or vertical tail (7) or tailplane (8) or floatage air bag (11) or inner interlayer (19) include following wherein at least a kind of version, single hull structure, multilayer shell structure;

Its wing body (2) or device health (3) or take body or passenger compartment body (4) or floatage air bag (11) or vertical tail (7) or tailplane (8) or inner interlayer (19) and include following wherein at least a kind of material, metal, rigid material, flexible material; Especially adopt the basalt fibre of fibers and inorganic, its cost performance is about 10 times of steel, available it replace other tensile materials, and not corrosion and durability long.

Content 9.

The aircraft having lift and buoyancy according to content 5, also includes following characteristics:

Its electric propulsion system (5.1) includes following wherein one at least, motor-type propulsion system (5.1.1), electrothermic type propulsion system (5.1.2), electrostatic propulsion system (5.1.3), electromagnetic type propulsion system (5.1.4), electric laser formula propulsion system (5.1.5), electric microwave type propulsion system (5.1.6), electric chemical formula propulsion system (5.1.7); Wherein motor-type propulsion system (5.1.1) is mainly used in aviation field, and wherein electrothermic type propulsion system (5.1.2), electrostatic propulsion system (5.1.3), electromagnetic type propulsion system (5.1.4), electric laser formula propulsion system (5.1.5), electric microwave type propulsion system (5.1.6), electric chemical formula propulsion system (5.1.7) are mainly used in space industry;

The combustion engine propulsion system (5.2) of its propulsion system (5) or jet propulsion system (5.4) adopt buoyant gas (1) as fuel; Combustion engine propulsion system (5.2) or jet propulsion system (5.4) have pipeline to be connected with the buoyant gas (1) in following wherein at least a kind of split, wing body (2), device health (3), vertical tail (7), tailplane (8), floatage air bag (11); Because buoyant gas (1) is just useless after lift-off flight, lift now can replace the buoyancy of buoyant gas (1) completely.Therefore, after lift-off flight, combustion engine propulsion system (5.2) or jet propulsion system (5.4) utilize buoyant gas (1) as fuel, buoyant gas (1) is run out of, decrease the volume of buoyant gas (1), decrease flight resistance; Hydrogen (1.1) in buoyant gas (1), fuel gas (1.6) can as fuel.

Content 10.

The aircraft having lift and buoyancy according to content 6, also includes following characteristics:

The hard and soft combination wing body (2.3) of its wing body (2) includes following wherein at least a kind of unitized construction form, outer casing is rigid wings body (2.1) and internal layer shell is flex-wing body (2.2), and internal layer shell is rigid wings body (2.1) and outer casing is flex-wing body (2.2);

The hard and soft combination health (3.3) of its device health (3) includes following wherein at least a kind of unitized construction form, outer casing is rigid body (3.1) and internal layer shell is flexible body (3.2), and internal layer shell is rigid body (3.1) and outer casing is flexible body (3.2).

Content 11.

The aircraft having lift and buoyancy according to content 8, also includes following characteristics:

In multilayer shell structure, multilayer shell structure includes following wherein at least two layers, outer casing, internal layer shell; Between outer casing, internal layer shell, include heavily gas (20), or between multilayer shell, include heavily gas (20); Heavily the density of gas (20) is equal to or higher than the density of the aircraft external space of lift and buoyancy; Multilayer shell structure substantially increase wing body (2), device health (3), take body or passenger compartment body (4), vertical tail (7), tailplane (8), floatage air bag (11), inner interlayer (19) Leakage prevention gas performance (at housing or covering is impaired, damaged after), and prevent the naturally slow seepage gas performance of housing or covering;

Flexible material includes following wherein at least a kind of material, organic fiber, inorganic fibre;

Inorganic fibre includes following wherein at least a kind of material, metal fibre, igneous rock fiber, metamorphic rock fiber, sedimentary rock fiber, carbon fiber, glass fibre, ceramic-fibre; Igneous rock fiber includes following wherein at least a kind of material, acid rock fiber, intermediate rock fiber, basic rock fiber, immersion rock fiber, ejected rock fiber; Metamorphic rock fiber includes following wherein at least a kind of material, marble fiber, quartz fiber; Sedimentary rock fiber includes following wherein at least a kind of material, sandstone fiber, shale fiber, limestone fiber;

Its intermediate-felsic rock fiber includes following wherein at least a kind of material, granite fibers, liparite fiber, dacite, granodiorite, felsite, quartz porphyry, obsidian, pitchstone, perlite rock;

Wherein intermediate rock fiber includes following wherein at least a kind of material, basalt fibre, gabbro fiber, syenite, monzonite, keratophyre, diorite, quartz dioite, diorite-porphyrite, quartz diorite porphyrite, andesite, dacite, trachite;

Its mafic rocks fiber includes following wherein at least a kind of material, diorite fiber, andesite fiber, gabbro, anorthosite, diabase, peridotite, pyroxenite, kimberlite, picrite, meimechite, ophiolite.

Compared with prior art, the invention has following outstanding advantages:

1, make full use of buoyancy and replace lift, in order to reduce lift power consumption, the saving fuel energy.2, the lift making full use of wing, to replace part buoyancy, in order to reduce the volume of floatage air bag, reaches the object reducing flight resistance; Reduce flight resistance and just decrease flight power consumption, the saving fuel energy.3, make full use of the buoyancy of buoyant gas (1), achieve the Vertical Free landing of aircraft.4, that take full advantage of high-altitude, sufficient solar photovoltaic electric power fly to replace fuel, achieves without non-stop flight that is fuel, timeless, that limit without voyage, has saved fuel energy, decreased pollution.5, combine owing to making full use of buoyancy and lift, make solar photovoltaic electric power can full load for advancing flight, improve flying speed.6, owing to making full use of buoyancy and lift combination, achieve aircraft and forever can land by vertical safety; If there occurs accident (such as collide, stop, meteorological sudden change etc. accident) aloft, this has the aircraft of lift and buoyancy also slowly can drop to ground, and crash accident can not occur, very safe.7, owing to being provided with servomechanism and automatic pilot equipment, manipulation becomes very simple, also simple easier than driving a car.8, because wealth make use of floating technology, the aircraft cost of lift and buoyancy is reduced greatly, and its cost is suitable with intermediate vehicle; This achieve a large amount of of it generally to use, easily extensively enter family, private daily field.9, create a kind of cheapness, clean, safety, at a high speed, point-to-point, the green air traffic mode of the quick and brand-new whole people.10, owing to there being the aircraft of lift and buoyancy can at high-altitude prolonged stay, therefore create " aerial aviation " pattern that aircraft is deposited on a kind of airport aloft, " aerial aviation " pattern should be different from present, to deposit aircraft on airport, ground " field aerial " pattern.11, such as, due at high-altitude prolonged stay, a kind of cheapness, clean, safe high-altitude service platform can be it provided, high altitude communication platform, high-altitude monitor supervision platform, dual-use material.12, due to when aircraft does not use, aircraft can be placed on high-altitude as aerial photovoltaic plant, dual-use material.Owing to can following the tracks of daylight and blocking without cloud and mist, photovoltaic plant is electric power more than one times more multiple than ground aloft.So many photovoltaic electric powers can adopt electric wire or storage battery to be transported to ground and use.It provide a kind of cheap, efficient high-altitude power generation mode.13 if unmanned vehicle, and its performance is better, cost performance is higher.14, wherein propeller-parachuting is a kind of athletics equipment now, and in the future propeller-parachuting can be used for physical culture, generating, floating platform, and a thing three is used.

Accompanying drawing explanation

Figure notation in following accompanying drawing " " represent that "or" is looked like.Such as (1) (2), represent (1) or (2).

Fig. 1, Fig. 1 .1 is flex-wing body (2.2) the side elevational cross-section schematic diagram that a kind of inside is filled with the single hull structure of buoyant gas (1), and wherein Fig. 1 .1 is provided with photovoltaic cell (10.1) at upper surface.

Fig. 2, Fig. 2 .1 is flex-wing body (2.2) the side elevational cross-section schematic diagram that a kind of 2 inside are filled with the double-layer shell structure of buoyant gas (1), is filled with heavily gas (20) between its two sheets of flexible housing; Wherein Fig. 2 .1 is provided with photovoltaic cell (10.1) at upper surface.

Fig. 3, Fig. 3 .1 is rigid wings body (2.1) the side elevational cross-section schematic diagram that a kind of inside is filled with the single hull structure of buoyant gas (1), and wherein Fig. 3 .1 is provided with photovoltaic cell (10.1) at upper surface.

Fig. 4, Fig. 4 .1 is rigid wings body (2.1) the side elevational cross-section schematic diagram that a kind of inside is provided with the single hull structure of floatage air bag (11), is filled with heavily gas (20) between its floatage air bag (11), stiff case; Wherein Fig. 4 .1 is provided with photovoltaic cell (10.1) at upper surface.

Fig. 5, Fig. 5 .1, Fig. 6, Fig. 6 .1 is hard and soft combination wing body (2.3) the side elevational cross-section schematic diagram that a kind of inside is filled with buoyant gas (1), its wing centre section body (2) the first half is the rigid wings body (2.1) of single hull structure, its wing centre section body (2) the latter half is the flex-wing body (2.2) of two sheets of flexible housing, is filled with heavily gas (20) between two sheets of flexible housing; Wherein Fig. 5, Fig. 5 .1 be full of buoyant gas (1) for landing state time; Wherein Fig. 6, Fig. 6 .1 be filled with part buoyant gas (1) due to high-altitude flight state time, during this shape fly lift large; Wherein Fig. 5 .1, Fig. 6 .1 are provided with photovoltaic cell (10.1) at wing body (2) upper surface.

Fig. 7, Fig. 7 .1 is aircraft (propeller-parachuting) the side elevational cross-section schematic diagram having lift and buoyancy that a kind of inside is filled with the flex-wing body (2.2) of the single hull structure of buoyant gas (1); Wherein Fig. 7 .1 is provided with photovoltaic cell (10.1) at upper surface.

Fig. 8, Fig. 8 .1 is aircraft (propeller-parachuting) the side elevational cross-section schematic diagram having lift and buoyancy that a kind of inside is filled with the flex-wing body (2.2) of the double-layer shell structure of buoyant gas (1), is filled with heavily gas (20) between its two sheets of flexible housing; Wherein Fig. 8 .1 is provided with photovoltaic cell (10.1) at upper surface.

Fig. 9, Fig. 9 .1 is aircraft (propeller-parachuting) the side elevational cross-section schematic diagram having lift and buoyancy that a kind of inside is filled with the rigid wings body (2.1) of the single hull structure of buoyant gas (1); Wherein Fig. 8 .1 is provided with photovoltaic cell (10.1) at upper surface.

Figure 10 is aircraft (propeller-parachuting) the side elevational cross-section schematic diagram having lift and buoyancy that a kind of inside is provided with the rigid wings body (2.1) of the single hull structure of floatage air bag (11); Wherein can arrange or not arrange photovoltaic cell (10.1) at upper surface.

Figure 11 is aircraft (propeller-parachuting) the side elevational cross-section schematic diagram having lift and buoyancy that a kind of inside is filled with the hard and soft combination wing body (2.3) of buoyant gas (1); Its wing centre section body (2) the first half is the rigid wings body (2.1) of single hull structure, its wing centre section body (2) the latter half is the flex-wing body (2.2) of two sheets of flexible housing, is filled with heavily gas (20) between two sheets of flexible housing; Can arrange or not arrange photovoltaic cell (10.1) at wing body (2) upper surface.

Figure 12 be one arrange down rigid wings body (2.1), on have flexible body (3.2) to be combined into, there is the side elevational cross-section schematic diagram having the aircraft of lift and buoyancy of electric propulsion system (5.1), the upper surface of its rigid wings body (2.1), flexible body (3.2) is provided with photovoltaic cell (10.1), and the inside of its rigid wings body (2.1), flexible body (3.2) is filled with buoyant gas (1).

Figure 13 is the elevational schematic view of Figure 12.

Figure 14 be one arranged rigid wings body (2.1), under have flexible body (3.2) to be combined into, there is the side elevational cross-section schematic diagram having the aircraft of lift and buoyancy of hybrid propulsion system (5.6), the upper surface of its rigid wings body (2.1), flexible body (3.2) is provided with photovoltaic cell (10.1), and the inside of its rigid wings body (2.1), flexible body (3.2) is filled with buoyant gas (1).

Figure 15 is the elevational schematic view of Figure 14.

Figure 16 be one arranged rigid wings body (2.1), under have rigid body (3.1) to be combined into, there is the side elevational cross-section schematic diagram having the aircraft of lift and buoyancy of electric propulsion system (5.1), the upper surface of its rigid wings body (2.1), rigid body (3.1) is provided with photovoltaic cell (10.1), and the inside of its rigid wings body (2.1), rigid body (3.1) is filled with buoyant gas (1).

Figure 17 is the elevational schematic view of Figure 16.

Figure 18 be one arranged rigid body (3.1), under have hard and soft combination wing body (2.3) to be combined into, there is the side elevational cross-section schematic diagram having the aircraft of lift and buoyancy of electric propulsion system (5.1), the upper surface of its hard and soft combination wing body (2.3), rigid body (3.1) is provided with photovoltaic cell (10.1), and the inside of its hard and soft combination wing body (2.3), rigid body (3.1) is filled with buoyant gas (1).

Figure 19 is the schematic top plan view of Figure 18.

Figure 20 be one arrange down rigid wings body (2.1), on have rigid body to be opened/closed (3.1) to be combined into, variable-volume floatage air bag (11) is provided with in its rigid body to be opened/closed (3.1), there is the side elevational cross-section schematic diagram having the aircraft of lift and buoyancy of electric propulsion system (5.1), the upper surface of its rigid wings body (2.1), rigid body to be opened/closed (3.1) is provided with photovoltaic cell (10.1), and the inside of its rigid wings body (2.1) is filled with buoyant gas (1).

Figure 21 is the schematic top plan view of Figure 20.

Figure 22, Figure 22 .1, Figure 22 .2 be Figure 20 3 kinds of closedown activities on hatchcover (3.4), reduce and regain floatage air bag (11) state face generalized section.

Figure 23 has constant volume floatage air bag (11) under one is arranged in rigid wings body (2.1), hybrid propulsion system (5.6) arranges rotation mechanism (5.10) after a little while, the board-like side elevational cross-section schematic diagram having the aircraft of lift and buoyancy.

Figure 24 is the elevational schematic view of Figure 23.

Figure 25 is that a kind of wing body (2) arranges rotation mechanism (2.4) after a little while, have the board-like side elevational cross-section schematic diagram having the aircraft of lift and buoyancy of hybrid propulsion system (5.6), its wing body (2) inside is filled with buoyant gas (1).

Figure 26 is the front elevational schematic of Figure 25.

Figure 27 is the elevational schematic view of Figure 25.

Detailed description of the invention.

Embodiment 1.From Fig. 1, Fig. 7, it is the aircraft (propeller-parachuting) having lift and buoyancy that a kind of inside is filled with the flex-wing body (2.2) of the single hull structure of buoyant gas (1).

There is the aircraft of lift and buoyancy to include flex-wing body (2.2), propulsion system (5), control system (6), take body or passenger compartment body (4), sling system (13), mooring or fixed system (14); Wherein control system (6), mooring or fixed system (14) are not shown in FIG.;

It is characterized in that; The aircraft of lift and buoyancy is had also to include buoyant gas (1);

Buoyant gas (1) is hydrogen or helium or ammonia, is the buoyant gas of tool; Buoyant gas (1) is arranged in flex-wing body (2.2);

Propulsion system (5) is combustion engine propulsion system (5.2); Combustion engine propulsion system (5.2) includes combustion engine, screw propeller or shrouded propeller; Its propulsion system (5) also comprises rotation mechanism (5.10) (not shown in FIG.) after a little while, hectare rotation mechanism (5.10) drives the direction of propulsion changing propulsion system (5), can before, can afterwards, can go up, can descend to rotate and advance;

Control system (6) includes mixing Ride Control System (6.3) (not shown in FIG.); Its mixing Ride Control System (6.3) includes pilot steering control system (6.1) and automatic Pilot control system (6.2);

Sling system (13) connects flex-wing body (2.2) and takes body or passenger compartment body (4); Control system (6) is arranged on to be taken in body or passenger compartment body (4);

Mooring or fixed system (14) (not shown in FIG.) are stationary ropes; When not flying, long stationary rope connects takes body or passenger compartment body (4), is fixed on ground by there being the aircraft of lift and buoyancy;

Flex-wing body (2.2), sling system (13), the shell taking body or passenger compartment body (4) adopt the basalt fibre of fibers and inorganic, and its cost performance is about 10 times of steel.

This has the buoyancy of the aircraft of lift and buoyancy to be greater than deadweight, is less than full load take-off weight; Or buoyancy is greater than full load take-off weight.When taking off vertically, starting apparatus combustion engine propulsion system (5.2), hectare rotation mechanism (5.10) rotary internal combustion engine propulsion system (5.2) becomes flat shape, and whole thrust is used for upward direction and advances.Enter in the air, hectare rotation mechanism (5.10) rotary internal combustion engine propulsion system (5.2) becomes vertical shape, and whole thrust is used for forward direction and advances.Because flex-wing body (2.2) creates lift, decreases the thrust of upward direction when forward direction is flown.After this, whole thrusts of combustion engine propulsion system (5.2) just are flown at full speed for overcoming horizontal resistance.During landing, operate by reversal procedure.

Because basalt fibre manufacturing flexible wing body (2.2) has high tensile property, flex-wing body (2.2) volume can not increase, and has the flying height of the aircraft of lift and buoyancy to be usually no more than 1000 meters of height so this.

Embodiment 2.From Fig. 2, Fig. 8, it is the aircraft (propeller-parachuting) having lift and buoyancy that a kind of inside is filled with the flex-wing body (2.2) of the double-layer shell structure of buoyant gas (1).

It is characterized in that; Flex-wing body (2.2) adopts double-layer shell structure.The air of heavily gas (20) is filled with between two sheets of flexible housing; Heavily the pressure of the air of gas (20) is greater than the pressure of flex-wing body (2.2) internal buoyance gas (1).So buoyant gas (1) seepage can not occur, greatly save the supplementary use amount of buoyant gas (1).It also includes air-pump inflating system (17), for being full of the specialized equipment of high ballast gas (20) in multilayer shell structure, Leakage prevention buoyant gas (1); Its air-pump inflating system (17) is arranged on flex-wing body (2.2) position or takes body or passenger compartment body (4) position; Heavily the density of gas (20) is equal to or higher than the density of the aircraft external space of lift and buoyancy, adopts air as heavy gas (20).

All the other features are with embodiment 1.

Embodiment 3.From Fig. 3, Fig. 9, it is the aircraft (propeller-parachuting) having lift and buoyancy that a kind of inside is filled with the rigid wings body (2.1) of the single hull structure of buoyant gas (1).

It is characterized in that; Wing body (2) adopts the rigid wings body (2.1) of single hull structure.Owing to adopting the rigid wings body (2.1) of the glass-felt plastic rigid material of the making of basalt fibre, so buoyant gas (1) seepage can not occur, greatly save the supplementary use amount of buoyant gas (1).Owing to employing rigid material, this have the aircraft of lift and buoyancy than embodiment 1, embodiment 2 from great.

All the other features are with embodiment 1.

Embodiment 4.From Fig. 4, Figure 10, that one is provided with constant volume floatage air bag (11) in rigid wings body (2.1), hybrid propulsion system (5.6) arranges rotation mechanism (5.10) after a little while, has the aircraft (propeller-parachuting) of lift and buoyancy.(in figure, depicting photovoltaic generating system (10) or photovoltaic cell (10.1)) more.

It is characterized in that; The outside of wing body (2) adopts the rigid wings body (2.1) of single hull structure; Floatage air bag (11) that the inside of wing body (2) includes the double-layer shell structure of two sheets of flexible housing, that have many constant volumes; Its floatage air bag (11) arranges with horizontal gas column form; When Near Ground takes off landing, the buoyancy of floatage air bag (11) is maximum.Rely on hybrid propulsion system (5.6) rotate on to take off landing; After entering high-altitude, due to the constancy of volume of floatage air bag (11), the pressure increase in floatage air bag (11).Now, the buoyancy of floatage air bag (11) reduces rapidly, and hybrid propulsion system (5.6) rotates pushes ahead flight.During flight, the main lift relying on rigid wings body (2.1).Owing to adopting the rigid wings body (2.1) of the glass-felt plastic rigid material of the making of basalt fibre, so buoyant gas (1) seepage can not occur, greatly save the supplementary use amount of buoyant gas (1).Owing to employing rigid material, this have the aircraft of lift and buoyancy than embodiment 1-embodiment 3 from great.

Its floatage air bag (11) also can longitudinal gas column form arrangement.

Embodiment 5.From Fig. 5, Fig. 6, Figure 11, it is the aircraft (propeller-parachuting) having lift and buoyancy that a kind of inside is filled with the hard and soft combination wing body (2.3) of buoyant gas (1).

It is characterized in that; The aircraft of lift and buoyancy is had also to include cooling or compression storage gas system (15) (not shown in FIG.), cooling or compression store gas system (15) and are connected with following wherein at least a kind of split, and propulsion system (5) power connects, propulsion system (5) pipeline connects, buoyant gas (1) pipeline connects, floatage air bag (11) pipeline connects; Cooling or compression store gas system (15) and buoyant gas (1) can be extracted out, compress and even become liquid, are stored in high pressure tank.The volume of such buoyant gas (1) just reduces; Doing so avoids the buoyant gas (1) when high-altitude and cubic expansion occurs, increase flight resistance, or destroy wing body (2), device health (3) etc. situation; In addition, several Baidu used heat of combustion engine propulsion system (5.2) is utilized buoyant gas (1) or liquid buoyant gas (1) heating can be expanded into vapours, the hot air of high temperature.Its vapours, hot air as buoyant gas (1), can have the buoyancy of the aircraft of lift and buoyancy in order to raising;

Wing body (2) adopts hard and soft combination wing body (2.3); The first half of this hard and soft combination wing body (2.3) is the rigid wings body (2.1) of single hull structure, and the lower part of this hard and soft combination wing body (2.3) is the flex-wing body (2.2) of two sheets of flexible housing; The air of high ballast gas (20) is filled with between the two sheets of flexible housing of flex-wing body (2.2); Prevent buoyant gas (1) from extracting seepage out.

Wherein Fig. 5 is that hard and soft combination wing body (2.3) is full of buoyant gas (1); Now the buoyancy of hard and soft combination wing body (2.3) is maximum, can be used for landing state; Wherein Fig. 6 is filled with part buoyant gas (1), and now the lift of hard and soft combination wing body (2.3) is maximum, and flight resistance is minimum, can be used for high-altitude flight state.When high-altitude flight state, the post shapes that hard and soft combination wing body (2.3) is full of buoyant gas (1) is very big without flight lift, again flight resistance.Buoyant gas (1) can be extracted out, compresses, liquefied so adopt cooling or compression to store gas system (15), reduce volume.After hard and soft combination wing body (2.3) is turned into wing shape, flight resistance reduces, and flight lift increases.

When landing, opening high pressure tank, buoyant gas (1) is re-entered in hard and soft combination wing body (2.3), increase buoyancy, support landing.

Such as, in the present embodiment, adopt ammonia (1.3) as buoyant gas (1), the boiling point of ammonia-33 DEG C: on ground or when being less than 3000 meters of low latitudes, can be expanded into ammonia or the heating of liquid ammoniacal liquor the ammonia (1.3) of high temperature by several Baidu used heat of combustion engine propulsion system (5.2).Its ammonia (1.3) as buoyant gas (1), can have the buoyancy of the aircraft of lift and buoyancy in order to raising; When entering high-altitude 3,000-2.5 myriametre, by cool or compress store gas system (15) rely on photovoltaic electric power can ammonia (1.3) compression and liquefaction become ammoniacal liquor, reduce volume.So just hard and soft combination wing body (2.3) is turned into the thinner wing body of Thickness Ratio, flight resistance reduces, and flight lift increases; Flying speed now can more than 500 kilometers/hour.In addition, when high-altitude 4,000-2.5 myriametre, can also the cold energy in high-altitude be inputted in hard and soft combination wing body (2.3) by cooling or compressing storage gas system (15), directly become ammoniacal liquor ammonia (1.3) is compressed and liquefied, reduce volume.Because when high-altitude 4,000-2.5 myriametre, the air themperature in high-altitude between-35 DEG C ~-70 DEG C, lower than the boiling point-33 DEG C of ammonia.

All the other features are with embodiment 1--embodiment 4.

Embodiment 6.From Fig. 1 .1, Fig. 2 .1, Fig. 3 .1, Fig. 4 .1, Fig. 5 .1, Fig. 6 .1, Fig. 7 .1, Fig. 8 .1, Fig. 9 .1, Figure 10, Figure 11, it is a kind of aircraft (propeller-parachuting) having lift and buoyancy being provided with photovoltaic cell (10.1) at wing body (2) upper surface.

It is characterized in that; The aircraft of lift and buoyancy is had also to include photovoltaic generating system (10); Photovoltaic generating system (10) includes following parts, photovoltaic cell (10.1), load governor, storage battery, inverter; Its photovoltaic cell (10.1) is arranged on the upper surface of flex-wing body (2.2);

Propulsion system (5) is electric propulsion system (5.1) or oil electric mixed dynamic propulsion system (5.6); Oil electric mixed dynamic propulsion system (5.6) includes electric propulsion system (5.1) and combustion engine propulsion system (5.2); Electric propulsion system (5.1) adopts motor-type propulsion system (5.1.1), and motor-type propulsion system (5.1.1) includes electrical motor, screw propeller or shrouded propeller; Its propulsion system (5) also comprises rotation mechanism (5.10) (not shown in FIG.) after a little while, hectare rotation mechanism (5.10) drives the direction of propulsion changing propulsion system (5), can before, can afterwards, can go up, can descend to rotate and advance;

This has the buoyancy of the aircraft of lift and buoyancy to be greater than deadweight, is less than full load take-off weight; Or buoyancy is greater than full load take-off weight.When taking off vertically, actuating motor formula propulsion system (5.1.1) and combustion engine propulsion system (5.2) simultaneously, hectare rotation mechanism (5.10) rotates hybrid propulsion system (5.6) becomes flat shape, and whole thrust is used for upward direction and advances.Enter in the air, hectare rotation mechanism (5.10) rotary internal combustion engine propulsion system (5.2) becomes vertical shape; After this combustion engine propulsion system (5.2) is closed, because flex-wing body (2.2) creates lift, decreases the thrust of upward direction when forward direction is flown.Rely on separately whole thrusts of motor-type propulsion system (5.1.1) just to come to fly at full speed for overcoming horizontal resistance later.During landing, reversal procedure operates.

Because buoyancy is greater than deadweight, this has the aircraft (propeller-parachuting) of lift and buoyancy when manned, can load more storage battery and swim in and go in the air to use as high-altitude photo-voltaic power generation station.Its photovoltaic generating system (10) works on, and provides electric power to storage battery.After storage battery is full of electric power, photovoltaic generating system (10) continues to provide electric power earthward, is equivalent to an aerial micro generation station.Or ground of landing back, unloads the storage battery that storage battery is full of electric power, then the storage battery changing unregulated power into get back to go in the air continue charging.When needing use to have the aircraft of lift and buoyancy, adopt mode of traction or rely on automatic Pilot control system (6.2) to make the aircraft of lift and buoyancy drop to ground, allow personnel be with the aircraft of lift and buoyancy, again take off vertically.

All the other features are with embodiment 1--embodiment 5.

Embodiment 7.From Figure 12, Figure 13, be one arrange down rigid wings body (2.1), on have flexible body (3.2) to be combined into, have the aircraft having lift and buoyancy of electric propulsion system (5.1).(in figure, depicting photovoltaic generating system (10) or photovoltaic cell (10.1)) more.

It is characterized in that; It includes rigid wings body (2.1), flexible body (3.2), takes body or passenger compartment body (4), electric propulsion system (5.1), photovoltaic generating system (10), vertical tail (7), tailplane (8), alighting gear (9), floatage air bag (11), balloonet (12), mooring or fixed system (14), air-pump inflating system (17);

Have under it rigid wings body (2.1), on have flexible body (3.2) to be combined into;

The inside of its rigid wings body (2.1), flexible body (3.2) is filled with buoyant gas (1); Its rigid wings body (2.1) is single hull structure, adopts the glass-felt plastic rigid material of the making of basalt fibre, so buoyant gas (1) seepage can not occur; Its flexible body (3.2) adopts double-layer shell structure; The air of heavily gas (20) is filled with between two sheets of flexible housing; Heavily the pressure of the air of gas (20) is greater than the pressure of flex-wing body (2.2) internal buoyance gas (1).So buoyant gas (1) seepage can not occur, greatly save the supplementary use amount of buoyant gas (1); Electric propulsion system (5.1) is arranged on takes body or passenger compartment body (4) position;

Its vertical tail (7), tailplane (8) are arranged on flexible body (3.2); Its balloonet (12) (not shown in FIG.) is arranged in flexible body (3.2), keeps the rigidity of flexible device health (3.2); Its mooring or fixed system (14) and wing body (2), device health (3), take body or passenger compartment body (4) is connected, mooring or fixed system (14) are also connected with ground; Its air-pump inflating system (17) is for being full of the specialized equipment of high ballast gas (20), Leakage prevention buoyant gas (1) in the double-layer shell structure to flexible body (3.2).

All the other features are with embodiment 1--embodiment 6.

Embodiment 8.From Figure 14, Figure 15, be one arranged rigid wings body (2.1), under have flexible body (3.2) to be combined into, have the aircraft having lift and buoyancy of hybrid propulsion system (5.6).(in figure, depicting photovoltaic generating system (10) or photovoltaic cell (10.1)) more.

It is characterized in that; It has rigid wings body (2.1), under have flexible body (3.2) to be combined into; It also includes hybrid propulsion system (5.6), cooling or compression and stores gas system (15) (not shown in FIG.); Its hybrid propulsion system (5.6) is arranged on rigid wings body (2.1), takes body or passenger compartment body (4) position.

Its hybrid propulsion system (5.6) comprises rotation mechanism (5.10) (not shown in FIG.) after a little while, and hectare rotation mechanism (5.10) drives the direction of propulsion changing hybrid propulsion system (5.6); Hybrid propulsion system (5.6) rotates becomes flat shape, and whole thrust is used for upward direction and advances.Enter in the air, hectare rotation mechanism (5.10) rotates hybrid propulsion system (5.6) becomes vertical shape; After this because flex-wing body (2.2) creates lift, decreases the thrust of upward direction when forward direction is flown.Whole thrusts of later hybrid propulsion system (5.6) just are flown at full speed for overcoming horizontal resistance.

Cooling or compression store gas system (15) feature with embodiment 4; All the other features are with embodiment 1--embodiment 7.

Embodiment 9.From Figure 16, Figure 17, be one arrange rigid wings body (2.1), under have rigid body (3.1) to be combined into the aircraft having lift and buoyancy.(in figure, depicting photovoltaic generating system (10) or photovoltaic cell (10.1)) more.

It is characterized in that; It has rigid wings body (2.1), under have rigid body (3.1) to be combined into; It includes hybrid propulsion system (5.6), cooling or compression and stores gas system (15) (not shown in FIG.); Its propulsion system (5) is arranged on rigid wings body (2.1); The inside of its rigid wings body (2.1), rigid body (3.1) is filled with buoyant gas (1); Cooling or compression store gas system (15) and are connected with buoyant gas (1) pipeline in rigid wings body (2.1), rigid body (3.1);

Cooling or compression store gas system (15) feature with embodiment 5; All the other features are with embodiment 1--embodiment 8.

Embodiment 10.From Figure 18, Figure 19, be one arrange rigid body (3.1), under have hard and soft combination wing body (2.3) to be combined into the aircraft having lift and buoyancy.(in figure, depicting photovoltaic generating system (10) or photovoltaic cell (10.1)) more.

It is characterized in that; It is one arranged rigid body (3.1), under have hard and soft combination wing body (2.3) to be combined into, it include hybrid propulsion system (5.6), cooling or compression store gas system (15) (not shown in FIG.); Its propulsion system (5) is arranged on the first half rigid wings body (2.1) of hard and soft combination wing body (2.3) hard and soft combination wing body (2.3); The inside of its hard and soft combination wing body (2.3), rigid body (3.1) is filled with buoyant gas (1); Cooling or compression store gas system (15) and are connected with buoyant gas (1) pipeline in rigid wings body (2.1), rigid body (3.1).

Hard and soft combination wing body (2.3), cooling or compression store gas system (15) feature with embodiment 5, embodiment 9; All the other features are with embodiment 1--embodiment 9.

Embodiment 11.From Figure 20, Figure 21, Figure 22, Figure 22 .1, Figure 22 .2, be one arrange down rigid wings body (2.1), on have rigid body to be opened/closed (3.1) to be combined into, to be provided with variable-volume floatage air bag (11) in its rigid body to be opened/closed (3.1), to have the aircraft having lift and buoyancy of electric propulsion system (5.1).(in figure, depicting photovoltaic generating system (10) or photovoltaic cell (10.1)) more.

It is characterized in that; Its rigid body (3.1) is provided with hatchcover (3.4) in activity to be opened/closed, and this rigid body (3.1) is also provided with variable-volume floatage air bag (11); Cooling or compression store gas system (15) (not shown in FIG.) and are connected with the circuit of photovoltaic generating system (10); Cooling or compression store gas system (15) and are also connected with floatage air bag (11) pipeline; Cooling or compression store gas system (15) even can become liquid buoyant gas (1) extraction in floatage air bag (11), compression, is stored in high pressure tank; Wherein Figure 22, Figure 22 .1, Figure 22 .2 represents, the volume of buoyant gas (1) is reducing, and regains floatage air bag (11), and then movable upper hatchcover (3.4) closes, and forms complete rigid body (3.1).Therefore, just greatly reduce flight resistance when high-speed flight, effectively improve flying speed; When taking off landing, opening high pressure tank, buoyant gas (1) being re-entered in floatage air bag (11), makes buoyancy maximum, increase buoyancy support is taken off landing.

Its propulsion system (5) comprises rotation mechanism (5.10) (not shown in FIG.) after a little while, and hectare rotation mechanism (5.10) drives the direction of propulsion changing propulsion system (5).

Cooling or compression store gas system (15) feature with embodiment 5; All the other features are with embodiment 1--embodiment 10.

Embodiment 12.From Fig. 4, Figure 23, Figure 24, that one is provided with constant volume floatage air bag (11) in rigid wings body (2.1), hybrid propulsion system (5.6) arranges rotation mechanism (5.10) after a little while, the board-like aircraft having lift and buoyancy.(in figure, depicting photovoltaic generating system (10) or photovoltaic cell (10.1)) more.

It is characterized in that; This has an aircraft finned body (2) of lift and buoyancy, is board-like aircraft; In rigid wings body (2.1), be provided with many constant volume floatage air bags (11), its floatage air bag (11) arranges with horizontal gas column form; When Near Ground takes off landing, the buoyancy of floatage air bag (11) is maximum.Rely on hybrid propulsion system (5.6) rotate on to take off landing; After entering high-altitude, due to the constancy of volume of floatage air bag (11), the pressure increase in floatage air bag (11).Now, the buoyancy of floatage air bag (11) reduces rapidly, and hybrid propulsion system (5.6) rotates pushes ahead flight.During flight, the main lift relying on rigid wings body (2.1).Because cooling or compression do not store gas system (15), it has the weight reduction of the aircraft of lift and buoyancy.

Its floatage air bag (11) also can longitudinal gas column form arrangement.

All the other features are with embodiment 1--embodiment 11.

Embodiment 13.From Figure 25, Figure 26, Figure 27, that a kind of wing body (2) arranges rotation mechanism (2.4) after a little while, have the board-like aircraft having lift and buoyancy of hybrid propulsion system (5.6), its flex-wing body (2.2) inside is filled with buoyant gas (1).(in figure, depicting photovoltaic generating system (10) or photovoltaic cell (10.1)) more.

It is characterized in that; Wing body (2) arranges rotation mechanism (2.4) after a little while; When taking off landing, hectare rotation mechanism (2.4) rotary wings body (2) upwards becomes vertically, is conducive to hybrid propulsion system (5.6) and upwards, downwards advances, and also helps the area reducing and take ground simultaneously.When high-altitude flight, hectare rotation mechanism (2.4) rotary wings body (2) transversely flat shape, is conducive to wing body (2) and produces lift, replace buoyancy.

All the other features are with embodiment 1--embodiment 12.

Embodiment 14.It is a kind of aircraft (propeller-parachuting) having lift and buoyancy being provided with constant volume floatage air bag (11) in wing body (2).

It is characterized in that; This wing body (2) adopts rigid wings body (2.1) or flex-wing body (2.2); Many constant volume floatage air bags (11) are provided with in rigid wings body (2.1) or flex-wing body (2.2);

All the other features are with embodiment 1--embodiment 13.

Embodiment 15.That a kind of buoyant gas (1) that adopts is as the aircraft having lift and buoyancy of propulsion system (5) fuel.

It is characterized in that; It also includes the high pressure tank of the buoyant gas (1) storing fuel gas (1.6); Its combustion engine propulsion system (5.2) or jet propulsion system (5.4) are connected by the buoyant gas (1) of pipeline with the fuel gas (1.6) in following wherein at least a kind of split, wing body (2), device health (3), vertical tail (7), tailplane (8), floatage air bag (11); Because the buoyant gas (1) of fuel gas (1.6) is just useless after lift-off flight, lift now can replace the buoyancy of the buoyant gas (1) of fuel gas (1.6) completely.Therefore, after lift-off flight, combustion engine propulsion system (5.2) or jet propulsion system (5.4) utilize the buoyant gas (1) of fuel gas (1.6) as fuel, the buoyant gas of fuel gas (1.6) (1) is run out of, decrease the volume of the buoyant gas (1) of fuel gas (1.6), decrease flight resistance; The buoyant gas (1) of hydrogen (1.1) etc. fuel gas (1.6) can as fuel.

When there being the aircraft landing of lift and buoyancy, open high pressure tank, re-entering of the buoyant gas of fuel gas (1.6) (1), wing body (2), device health (3), vertical tail (7), tailplane (8), floatage air bag (11); Add buoyancy, be conducive to vertical landing.

All the other features are with embodiment 1-embodiment 14.

Embodiment 16.It is the aircraft having lift and buoyancy that one is provided with inner interlayer (19).

It is characterized in that; The aircraft of lift and buoyancy is had also to include inner interlayer (19) (not shown in FIG.); Inner interlayer (19) is arranged on following wherein at least a kind of position, wing body (2), device health (3), takes body or passenger compartment body (4), vertical tail (7), tailplane (8), floatage air bag (11), balloonet (12); Its inner interlayer (19) includes following wherein one at least, rigidity inner interlayer (19.1), flexible inner interlayer (19.2), hard and soft combination inner interlayer (19.3); Its hard and soft combination inner interlayer (19.3) includes rigidity inner interlayer (19.1) and flexible inner interlayer (19.2).Its inner interlayer (19) can be isolated into multiple cavity multiple wing body (2), device health (3) etc. these point of body component, improves their rigidity and leakage performance.There is seepage in the buoyant gas (1) of a cavity, can not cause the buoyant gas (1) of other cavity that seepage occurs, the buoyant gas (1) that also can not affect other cavity normally works, and namely the buoyancy of other cavity does not reduce.

All the other features with all the other features with embodiment 1-embodiment 15.

Embodiment 17.It is the aircraft having lift and buoyancy that one is provided with high altitude communication or monitor supervision platform device (18).

It is characterized in that; It also includes high altitude communication or monitor supervision platform device (18) (not shown in FIG.); Its high altitude communication or monitor supervision platform device (18) are arranged on following wherein at least a kind of position, wing body (2), device health (3), take body or passenger compartment body (4).There is the aircraft dual-use material of lift and buoyancy like this, both can use as aerial vehicle, can use as the platform of aerial loading again.

All the other features are with embodiment 1-embodiment 16.

Embodiment 18.That a kind of ammonia (1.3) that adopts is as the aircraft having lift and buoyancy of buoyant gas (1).

It is characterized in that; The aircraft of lift and buoyancy is had to adopt ammonia (1.3) as buoyant gas (1), have the aircraft of lift and buoyancy also to include cooling or compression storage gas system (15) (not shown in FIG.), electric heating system (16), this cooling or compression store gas system (15), electric heating system (16) is connected with the circuit of photovoltaic generating system (10); Cooling or compression store gas system (15) and are also connected with the buoyant gas (1) in hard and soft combination wing body (2.3) or floatage air bag (11) pipeline;

Cooling or compression store gas system (15) feature with embodiment 5; All the other features are with embodiment 1--embodiment 17.

Adopt ammonia (1.3) as buoyant gas (1), the boiling point of ammonia-33 DEG C: on ground or when being less than 3000 meters of low latitudes, relies on photovoltaic electric power ammonia or the heating of liquid ammoniacal liquor can be expanded into the ammonia (1.3) of high temperature by electric heating system (16).Its ammonia (1.3) as buoyant gas (1), can have the buoyancy of the aircraft of lift and buoyancy in order to raising; When entering high-altitude 3,000-2.5 myriametre, by cool or compress store gas system (15) rely on photovoltaic electric power can ammonia (1.3) compression and liquefaction become ammoniacal liquor, reduce volume.So just hard and soft combination wing body (2.3) is turned into the thinner wing body of Thickness Ratio, flight resistance reduces, and flight lift increases; Flying speed now can more than 500 kilometers/hour.In addition, when high-altitude 4,000-2.5 myriametre, can also the cold energy in high-altitude be inputted in hard and soft combination wing body (2.3) by cooling or compressing storage gas system (15), directly become ammoniacal liquor ammonia (1.3) is compressed and liquefied, reduce volume.Because when high-altitude 4,000-2.5 myriametre, the air themperature in high-altitude between-35 DEG C ~-70 DEG C, lower than the boiling point-33 DEG C of ammonia.

Embodiment 19.From Fig. 1 .1, Fig. 2 .1, Fig. 3; 1, Fig. 4 .1, Fig. 5 .1, Fig. 6 .1, Fig. 7 .1, Fig. 8 .1, Fig. 9 .1, and Figure 10--Figure 27 is known, be one include photovoltaic generating system (10), the aircraft having lift and buoyancy of buoyant gas (1).

It is characterized in that; The aircraft of lift and buoyancy is had also to include photovoltaic generating system (10), electric propulsion system (5.1);

Wherein photovoltaic generating system (10) includes following parts, photovoltaic cell (10.1), load governor, storage battery, inverter; Include photovoltaic cell (10.1) at the upper surface of following wherein at least a kind of split or side surface, wing body (2), device health (3), take body or passenger compartment body (4), drive pedestal (4.1), driving compartment body (4.2), vertical tail (7), tailplane (8);

Propulsion system (5) is electric propulsion system (5.1) or oil electric mixed dynamic propulsion system (5.6); When adopting oil electric mixed dynamic propulsion system (5.6), oil electric mixed dynamic propulsion system (5.6) includes electric propulsion system (5.1) and combustion engine propulsion system (5.2); Electric propulsion system (5.1) adopts motor-type propulsion system (5.1.1), and motor-type propulsion system (5.1.1) includes electrical motor, screw propeller or shrouded propeller; Its propulsion system (5) also comprises rotation mechanism (5.10) (not shown in FIG.) after a little while, hectare rotation mechanism (5.10) drives the direction of propulsion changing propulsion system (5), can before, can afterwards, can go up, can descend to rotate and advance;

When adopting oil electric mixed dynamic propulsion system (5.6), this has the buoyancy of the aircraft of lift and buoyancy to be greater than deadweight, is less than full load take-off weight; Or buoyancy is greater than full load take-off weight.When taking off vertically, actuating motor formula propulsion system (5.1.1), hectare rotation mechanism (5.10) turning motor formula propulsion system (5.1.1) becomes flat shape, and whole thrust is used for upward direction and advances.Enter in the air, hectare rotation mechanism (5.10) turning motor formula propulsion system (5.1.1) becomes vertical shape, and whole thrust is used for forward direction and advances.Because wing body (2) creates lift, decreases the thrust of upward direction when forward direction is flown.After this, whole thrusts of motor-type propulsion system (5.1.1) just are flown at full speed for overcoming horizontal resistance.During landing, operate by reversal procedure.

When adopting oil electric mixed dynamic propulsion system (5.6), this has the buoyancy of the aircraft of lift and buoyancy to be greater than deadweight, is less than full load take-off weight.When taking off vertically, actuating motor formula propulsion system (5.1.1) and combustion engine propulsion system (5.2) simultaneously, hectare rotation mechanism (5.10) rotates hybrid propulsion system (5.6) upward direction and advances.Enter in the air, hectare rotation mechanism (5.10) rotates hybrid propulsion system (5.6) forward direction and advances.After this, combustion engine propulsion system (5.2) is closed, because flex-wing body (2.2) creates lift, decreases the thrust of upward direction when forward direction is flown.After, rely on separately the thrust of motor-type propulsion system (5.1.1) just can fly at full speed.During landing, reversal procedure operates.

Because buoyancy is greater than deadweight, this has the aircraft of lift and buoyancy to swim in when not using in the air.Its photovoltaic generating system (10) works on, and provides electric power to storage battery.After storage battery is full of electric power, photovoltaic generating system (10) continues to provide electric power earthward, is equivalent to an aerial micro generation station.When needing use to have the aircraft of lift and buoyancy, adopt manpower mode or rely on automatic Pilot control system (6.2) to make the aircraft of lift and buoyancy drop to ground, allow personnel be with the aircraft of lift and buoyancy, again take off vertically.

All the other features are with embodiment 1--embodiment 18.

Embodiment 20.Be that one is provided with electric heating system (16), buoyant gas (1) adopts the aircraft having lift and buoyancy of vapours, hot air.

It is characterized in that; It includes electric heating system (16) (not shown in FIG.), electric heating system (16) is arranged in following wherein at least a kind of split, wing body (2), device health (3), takes body or passenger compartment body (4), vertical tail (7), tailplane (8), floatage air bag (11); Its electric heating system (16), cooling or compression store gas system (15) and are connected with photovoltaic generating system (10) circuit; Photovoltaic generating system (10) can make full use of the unobstructed advantage in high-altitude and carry out photovoltaic generation at full capacity.Use this electric power can meet heating water completely, ammoniacal liquor, air are expanded into high temperature vapours, hot air.Its vapours, hot air can as the buoyant gas (1) of wing body (2), device health (3), vertical tail (7), tailplane (8), floatage air bag (11) inside; The buoyant gas (1) that its vapours, hot air can be produced as solar electric power, in order to improve the buoyancy having the aircraft of lift and buoyancy, the saving fuel energy.

The feature of photovoltaic generating system (10) is with embodiment 19, and all the other features are with embodiment 1--embodiment 19.

Embodiment 21.Be one include photovoltaic generating system (10), the aircraft having lift and buoyancy of buoyant gas (1).

It is characterized in that; Motor-type propulsion system (5.1.1) adopts electric propulsion system (5.1) pattern of two electric power of " electric power of the electric power+relay storage battery of photovoltaic generating system (10) ".Owing to adopting the electric power of single photovoltaic generating system (10) not enough, high speed flight for a long time can not be reached by powerful propulsion aircraft, so adopt electric propulsion system (5.1) pattern of two electric power of " electric power of the electric power+relay storage battery of photovoltaic generating system (10) " to strengthen increase flight thrust and flying speed.When existing battery power exhausts, relay storage battery that more renew after aircraft is dropped to ground, that be full of electric power continues flight.In future, the storage battery being full of electric power, as conventional replacing commodity selling, is equivalent to change LPG cyoinders business method.

Electric propulsion system (5.1) pattern of two electric power of this " electric power of the electric power+relay storage battery of photovoltaic generating system (10) ", can ensure that aircraft all uses electric power, at full throttle fly full stroke.

All the other features are with embodiment 1--embodiment 20.

Claims

1. there is the aircraft of lift and buoyancy to comprise finned body (2), propulsion system (5), control system (6), it also includes following wherein at least a kind of split, device health (3), takes body or passenger compartment body (4); It is characterized in that:

The aircraft of lift and buoyancy is had also to include buoyant gas (1); The density of its buoyant gas (1) is lower than the gas density of the aircraft external space having lift and buoyancy.

2. the aircraft having lift and buoyancy according to claim 1; It is characterized in that:

3. the aircraft having lift and buoyancy according to claim 1; It is characterized in that:

Have the aircraft of lift and buoyancy also to include following wherein at least a kind of split, vertical tail (7), tailplane (8), alighting gear (9), floatage air bag (11), balloonet (12), sling system (13), mooring or fixed system (14), cooling or compression store gas system (15), electric heating system (16), air-pump inflating system (17), high altitude communication or monitor supervision platform device (18), inner interlayer (19).

4. the aircraft having lift and buoyancy according to claim 1; It is characterized in that:

5. the aircraft having lift and buoyancy according to claim 1; It is characterized in that:

Its wing body (2) also comprises rotation mechanism (2.4) after a little while;

Its device health (3) also includes movable upper hatchcover (3.4);

Its propulsion system (5) also comprises rotation mechanism (5.10) after a little while;

6. the aircraft having lift and buoyancy according to claim 1; It is characterized in that:

7. according to claim 2 or the aircraft having lift and buoyancy according to claim 3; It is characterized in that:

Photovoltaic generating system (10) also includes following wherein at least a kind of parts, load governor, storage battery, inverter; Include photovoltaic generating system (10) at the upper surface of following wherein at least a kind of split or side surface, wing body (2), device health (3), take body or passenger compartment body (4), vertical tail (7), tailplane (8);

8. according to claim 1 or claim 2 or the aircraft having lift and buoyancy according to claim 3; It is characterized in that:

Its vertical tail (7) or tailplane (8) are arranged on the afterbody of following wherein at least a kind of position, wing body (2), device health (3), take body or passenger compartment body (4); Its vertical tail (7) or tailplane (8) also include buoyant gas (1);

Its mooring or fixed system (14) are connected with wing body (2) or device health (3);

Its wing body (2) or device health (3) or take body or passenger compartment body (4) or floatage air bag (11) or vertical tail (7) or tailplane (8) or inner interlayer (19) and include following wherein at least a kind of material, metal, rigid material, flexible material.

9. the aircraft having lift and buoyancy according to claim 5; It is characterized in that:

Its electric propulsion system (5.1) includes following wherein one at least, motor-type propulsion system (5.1.1), electrothermic type propulsion system (5.1.2), electrostatic propulsion system (5.1.3), electromagnetic type propulsion system (5.1.4), electric laser formula propulsion system (5.1.5), electric microwave type propulsion system (5.1.6), electric chemical formula propulsion system (5.1.7);

The combustion engine propulsion system (5.2) of its propulsion system (5) or jet propulsion system (5.4) adopt buoyant gas (1) as fuel; Combustion engine propulsion system (5.2) or jet propulsion system (5.4) have pipeline to be connected with the buoyant gas (1) in following wherein at least a kind of split, wing body (2), device health (3), vertical tail (7), tailplane (8), floatage air bag (11).

10. the aircraft having lift and buoyancy according to claim 6; It is characterized in that: