CN105151268A

CN105151268A - Photovoltaic buoyancy aircraft

Info

Publication number: CN105151268A
Application number: CN201510551460.8A
Authority: CN
Inventors: 吕怀民; 吕屾
Original assignee: Individual
Current assignee: Individual
Priority date: 2015-08-27
Filing date: 2015-08-27
Publication date: 2015-12-16

Abstract

The invention relates to the technical field of aviation, high-altitude photovoltaic wind power generation, aerial houses, buoyancy platforms and other projects, in particular to a photovoltaic buoyancy aircraft. The photovoltaic buoyancy aircraft comprises the following split bodies: a buoyancy column (3), a loading body (4), a propelling system (5) and a driving or control system (6). A buoyancy body comprises the buoyancy column (3). The photovoltaic buoyancy aircraft is characterized in that a buoyancy plate (2) and a photovoltaic power generation system (10) are further included; the buoyancy plate (2) is arranged on the upper portion of the buoyancy column (3); and the photovoltaic power generation system (10) is arranged on the upper surface and the side surface of the buoyancy plate (2) or the buoyancy column (3). Due to double buoyancy of the buoyancy plate (2) and the buoyancy column (3), the self weight and flying energy consumption of the aircraft are greatly reduced. The purpose that under the condition of not consuming fuel, flying and timeless vertical taking off and landing can be carried out through solar energy is achieved. Under the action of the flexible buoyancy plate (2) and the buoyancy column (3), even though collisions, shutdown, sudden weather changes and other accidents happen in the air, people injuries or cabin crashes or cabin injuries or cabin damage cannot happen, and the photovoltaic buoyancy aircraft is quite safe and quite low in cost and photovoltaic wind power generation cost.

Description

Photovoltaic buoyancy aircraft

Technical field

The present invention relates to Aeronautics and Astronautics, air communication transport, high-altitude photovoltaic generation, high-altitude wind power generation, in the air house, air communication, aerial monitoring, field of engineering technology such as floating loading delay platform, physical culture etc., especially the field of engineering technology such as aircraft, high-altitude photovoltaic buoyancy cogeneration, aerial loading delay platform of the vertical takeoff and landing of photovoltaic power.

Background technology

There is following problem in existing aircraft.1, 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, 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.3, existing aircraft is all consumable liquid fuel, does not make full use of solar electric power.4, existing aircraft major part is all rely on airport landing, can not Vertical Free landing.5, the air mileage of the autogyro of existing vertical takeoff and landing is short, speed is slow again.6, existing aircraft is dangerous, as long as aloft have an accident, just may cause and fall.7, 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.8, existing aircraft only has as a kind of function of the vehicle, does not increase the function as aerial power house.

Technology contents

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

Content 1.

Photovoltaic buoyancy aircraft includes following split, buoyancy aid, load (4), propulsion system (5), driving or control system (6); Buoyancy aid includes buoyancy cylinder (3); The inside of its buoyancy aid, buoyancy cylinder (3) includes buoyant gas (1), and buoyant gas (1) density is lower than the gas density of the photovoltaic buoyancy aircraft external space; It is characterized in that:

Photovoltaic buoyancy aircraft also includes plate body, photovoltaic generating system (10);

Wherein plate body is arranged on the top of following wherein at least a kind of position or middle part or bottom, photovoltaic buoyancy aircraft, buoyancy aid, buoyancy cylinder (3);

Wherein photovoltaic generating system (10) includes photovoltaic cell (10.1); Its photovoltaic cell (10.1) is arranged on following wherein at least a kind of position, side surface, the upper surface of plate body, the side surface of plate body of the upper surface of buoyancy aid or buoyancy cylinder (3), buoyancy aid or buoyancy cylinder (3);

Wherein load (4) is connected with following wherein at least a kind of split, buoyancy aid, buoyancy cylinder (3), plate body;

Wherein propulsion system (5) is arranged on following wherein at least a kind of position, buoyancy aid, buoyancy cylinder (3), plate body, load (4); Propulsion system (5) includes single or multiple;

Wherein driving or control system (6) are arranged on following wherein at least a kind of position, buoyancy aid, buoyancy cylinder (3), plate body, load (4).

Skyborne photovoltaic buoyancy aircraft utilizes the main source of photovoltaic electric power as flying power of the photovoltaic generating system (10) of plate body, buoyancy cylinder (3) upper surface.Under making full use of the condition of unobstructed, the high radiated solar energy in high-altitude, carry out the photovoltaic generation at full capacity of large area plate body, buoyancy cylinder (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.Such photovoltaic buoyancy aircraft just achieves: do not needing under consume fuel condition, utilizes solar power just can carry out timeless flight, utilizes 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 2.

With parking in the air and power transmitting device of the auxiliary facility of the photovoltaic buoyancy aircraft described in content 1, it is characterized in that: it includes following split, buoyancy aid (30), aerial power transmission line (31), vertical power transmission line (32), key lock switch system (34), earth anchor (35), lightning protection system (36); It also includes following wherein at least a kind of split, aerial power transmission line (31), plug-in mechanism (33);

Wherein buoyancy aid (30) suspends in midair or supports following wherein at least a kind of parts, aerial power transmission line (31), vertical power transmission line (32); If there are many aerial power transmission lines (31), then many aerial power transmission line (31) cross connections mutually, form aerial electrical grid; Aerial power transmission line (31) includes individual layer or multilayer;

Wherein earth anchor (34) is connected with vertical power transmission line (32);

Wherein aerial power transmission line (31) and following circuit communication wherein between at least a kind of parts, vertical power transmission line (32), plug-in mechanism (33);

Wherein aerial power transmission line (31) is connected with following wherein at least a kind of parts, plug-in mechanism (33), key lock switch system (34);

Wherein plug-in mechanism (33) can with the circuit communication of the photovoltaic generating system (10) of aerial photovoltaic buoyancy aircraft or aerogenerator group system (25); Then the electric power that photovoltaic generating system (10) or aerogenerator group system (25) are produced is transported to ground;

Wherein key lock switch system (34) can be connected with the mooring of aerial photovoltaic buoyancy aircraft or fixed system (14); Then photovoltaic buoyancy aircraft mooring or be fixed on to be parked in the air and near power transmitting device, in order to plug-in mechanism (33) can with the circuit communication of the photovoltaic generating system (10) of aerial photovoltaic buoyancy aircraft or aerogenerator group system (25);

Wherein lightning protection system (36) is combined with following wherein at least a kind of parts, buoyancy aid (30), aerial power transmission line (31), vertical power transmission line (32), plug-in mechanism (33), key lock switch system (34), earth anchor (35).This lightning protection system (36) ensure that to be parked and power transmitting device, the safety of photovoltaic buoyancy aircraft when thunderstorm weather in the air, is not smashed by thunder and lightning.

Therefore, skyborne photovoltaic buoyancy aircraft utilizes to be parked and the aerial power transmission line (31) of power transmitting device, vertically power transmission line (32), plug-in mechanism (33) in the air, and the photovoltaic electric power of photovoltaic buoyancy aircraft production, wind force power are transferred to ground.So just can be avoided the self-contained power transmission line pipeline equipment of photovoltaic buoyancy aircraft, significantly reduce the deadweight of photovoltaic buoyancy aircraft.Photovoltaic buoyancy aircraft or other aerospace equipment can also be parked simultaneously.The aerial power transmission line of its multilayer (31) can park photovoltaic buoyancy aircraft or other aerospace equipment of how several times.

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

Content 3.

Photovoltaic buoyancy aircraft according to content 1, also includes following characteristics:

Plate body includes following wherein one at least, buoyancy plate body (2), lift plate body (40), sizing plate body (41); The inside of plate body includes buoyant gas (1) and constitutes buoyant buoyancy plate body (2); Buoyancy aid also includes buoyancy plate body (2);

Following wherein at least a kind of position of its buoyancy plate body (2) or buoyancy cylinder (3) is provided with photovoltaic cell (10.1), its upper surface, its side surface;

The cross sectional shape of its plate body or buoyancy plate body (2) includes following wherein one at least, wing shape, fairing shape, spindle shape, ellipsoidal shape, shuttle shape, rugby ball shape, oblong-shaped, square shape; The plane surface shape shape of plate body or buoyancy plate body (2) includes following wherein one at least, fairing shape, spindle shape, ellipsoidal shape, shuttle shape, rugby ball shape, triangle, upside-down triangle shape, oblong-shaped, square shape; Plate body or buoyancy plate body (2) include single or multiple;

The cross sectional shape of its buoyancy cylinder (3) includes following wherein one at least, wing shape, fairing shape, spindle shape, ellipsoidal shape, shuttle shape, rugby ball shape, oblong-shaped, square shape; Buoyancy cylinder (3) includes single or multiple; The utricule structure of its buoyancy cylinder (3) includes following wherein one at least, determines body main gasbag structure (3.5), determines body main gasbag+balloonet structure (3.6), variant main gasbag structure (3.7), variant main gasbag+balloonet structure structure (3.8); " variant main gasbag " version wherein among variant main gasbag structure (3.7), variant main gasbag+balloonet structure structure (3.8) adopts " variant type sky airship " version of Chinese invention people Li Xiaoyang design, its " variant type sky airship " version includes following wherein one at least, radial variant structure form (3.9), longitudinal variant structure form (3.10); Respectively for different application object and field of application; " variant type sky airship " version can make to rise to the flight of a few myriametre to tens meters altitude;

Its buoyancy aid or plate body include single or multiple, and its buoyancy plate body (2) includes single or multiple, and its buoyancy cylinder (3) includes single or multiple.

Due under the effect of buoyancy plate body (2), the middle buoyant gas (1) of buoyancy cylinder (3), make photovoltaic buoyancy aircraft not only have single " lift " function of buoyancy plate body (2), also there is dual " buoyancy " function of wing shape buoyancy plate body (2), buoyancy cylinder (3).Under " lift " and " buoyancy " is added folded effect, result greatly reduces the deadweight of photovoltaic buoyancy aircraft.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 photovoltaic buoyancy aircraft also slowly can drop to ground, and crash accident can not occur.Again due to the flexible air-bag that buoyancy plate body (2), buoyancy cylinder (3) are large volumes, there occurs collision case aloft, also can not cause the injury to personnel and cabin and damage.If air bag gas leakage occurs, buoyant gas (1) has been revealed, without this accident of buoyancy, photovoltaic buoyancy aircraft just becomes aerodone, gliding parachute, glide is relied on to drop to ground.Therefore photovoltaic buoyancy aircraft is very safe, substantially there will not be personnel's casualties accident.If unmanned vehicle, its performance is better, cost performance is higher.In addition, there is air draught when wing shape, fairing shape, spindle shape, the plate body of ellipsoidal shape or buoyancy plate body (2) or buoyancy cylinder (3) can greatly reduce flight, substantially increase flying speed.In addition, multiple buoyancy plate body (2) or buoyancy cylinder (3) greatly can increase the stability of photovoltaic buoyancy aircraft when flying and reduce air draught.

Content 4.

Photovoltaic buoyancy aircraft also includes 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), just transfer from one department to another to unite (21), horizontal connector (22), vertical connections (23), oblique attaching parts (24), aerogenerator group system (25).

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

Its alighting gear (9) is used to control that photovoltaic buoyancy aircraft uses when landing ground;

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

Its balloonet (12) is for regulating the rigidity of flexible plate body (2.2), flexible buoyancy cylinder (3.2);

Its sling system (13) connects load (4) and buoyancy plate body (2), buoyancy cylinder (3), and adjusts its attitude by adjustment sling length;

Due to light, even float, so photovoltaic buoyancy aircraft must be fixed on ground by mooring or fixed system (14);

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; Avoiding problems the buoyant gas (1) when high-altitude and cubic expansion occurs, cause increase flight resistance, or damage buoyancy plate body (2), buoyancy cylinder (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 of photovoltaic buoyancy aircraft;

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

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 buoyancy plate body (2), buoyancy cylinder (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;

Its hectare transfer from one department to another system (21) can drive change buoyancy aid, load (4), propulsion system (5) direction, can before, can afterwards, can go up, can descend rotate;

Its horizontal connector (22), vertical connections (23), oblique attaching parts (24) can connect multiple buoyancy aid, plate body, buoyancy plate body (2), buoyancy cylinder (3), load (4), propulsion system (5).

Its aerogenerator group system (25) when not flying, can make full use of the powerful distinguished and admirable of high-altitude and carrying out efficiency power generation, realizing wind-force and photovoltaic cogeneration.Its wind-power electricity generation amount can exceed more than 5 times of photovoltaic power generation quantity.

Content 5.

Photovoltaic buoyancy aircraft according to content 1 or content 3, also includes following characteristics:

Buoyancy aid also includes load (4); Buoyant gas (1) is included in load (4);

Its plate body or buoyancy plate body (2) are arranged on the top of following wherein at least a kind of position or middle part or bottom, buoyancy cylinder (3), load (4); Plate body or buoyancy plate body (2) are connected with following wherein at least a kind of split, buoyancy cylinder (3), load (4), propulsion system (5), sail or control system (6); Buoyancy plate body (2) includes single or multiple;

Its buoyancy cylinder (3) is arranged on the top of following wherein at least a kind of position or middle part or bottom, plate body, buoyancy plate body (2), load (4); Buoyancy cylinder (3) is connected with following wherein at least a kind of split, plate body, buoyancy plate body (2), load (4), propulsion system (5), sails or control system (6); Buoyancy cylinder (3) includes single or multiple;

Its load (4) is arranged on the top of following wherein at least a kind of position or middle part or bottom, plate body, buoyancy plate body (2), buoyancy cylinder (3); Load (4) is connected with following wherein at least a kind of split, plate body, buoyancy plate body (2), buoyancy cylinder (3), propulsion system (5), driving or control system (6);

Wherein propulsion system (5) is arranged on the top of following wherein at least a kind of position or middle part or bottom, buoyancy aid, buoyancy cylinder (3), plate body, buoyancy plate body (2), load (4);

It is driven or control system (6) is arranged on the top of following wherein at least a kind of position or middle part or bottom, plate body, buoyancy plate body (2), buoyancy cylinder (3), load (4), propulsion system (5).

Content 6.

The buoyancy of its buoyant gas (1) is equal to and greater than the deadweight of photovoltaic buoyancy aircraft or full heavy or full weight; 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);

The anterior-posterior length of its plate body or buoyancy cylinder (3) and left and right width are than between 2: 1 to 10: 1; Flight windage can be greatly reduced like this;

Its plate body also comprises and transfers from one department to another after a little while to unite (21), and these just transfer from one department to another to unite (21) drive and change the direction of plate body, can before, can afterwards, can go up, can descend to rotate;

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

Its load (4) includes following wherein at least a kind of split, Driving control pedestal (4.1), Driving control cabin body (4.2), automatic Pilot control convenience body (4.3), aerial house (4.4);

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 comprise transfers from one department to another after a little while unite (21), just transfer from one department to another unite (21) drive change propulsion system (5) direction of propulsion, can before, can afterwards, can go up, can descend rotate advance;

It is driven or 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 7.

Photovoltaic buoyancy aircraft according to content 3, also includes following characteristics:

Its buoyancy plate body (2) includes following wherein at least a kind of split, rigidity plate body (2.1), flexible plate body (2.2), hard and soft combined plate body (2.3); Its hard and soft combined plate body (2.3) includes following wherein at least a kind of unitized construction form, rigidity plate body (2.1) and below flexible plate body (2.2) above, below rigidity plate body (2.1) and flexible plate body (2.2) above;

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

Content 8.

Photovoltaic buoyancy aircraft according to content 3 or content 4, 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; Photovoltaic generating system (10) is included, plate body, buoyancy plate body (2), buoyancy cylinder (3), load (4), vertical tail (7), tailplane (8), horizontal connector (22), vertical connections (23), oblique attaching parts (24) at the upper surface of following wherein at least a kind of split or side surface;

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 9.

Buoyancy aid also includes vertical tail (7), tailplane (8), floatage air bag (11), cooling or compression and stores gas system (15), horizontal connector (22), vertical connections (23), oblique attaching parts (24); 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), horizontal connector (22), vertical connections (23), oblique attaching parts (24);

Its vertical tail (7) or tailplane (8) are arranged on the afterbody of following wherein at least a kind of position, plate body, buoyancy plate body (2), buoyancy cylinder (3), load (4), horizontal connector (22), vertical connections (23), oblique attaching parts (24);

Under its alighting gear (9) is arranged on following wherein at least a kind of split, plate body, buoyancy plate body (2), buoyancy cylinder (3), load (4);

Its floatage air bag (11) is arranged in following wherein at least a kind of split, buoyancy plate body (2), buoyancy cylinder (3), load (4), vertical tail (7), tailplane (8), oblique attaching parts (24); Floatage air bag (11) includes following wherein one at least, buoyant balloon (11.1), buoyancy gas column (11.2); Multiple buoyancy gas column (11.2) is with following wherein at least a kind of gas column form arrangement, and longitudinal gas column form arrangement, horizontal gas column form arrange;

Its balloonet (12) is arranged in following wherein at least a kind of split, plate body, buoyancy plate body (2), buoyancy cylinder (3), load (4), vertical tail (7), tailplane (8), floatage air bag (11), horizontal connector (22), vertical connections (23), oblique attaching parts (24);

Its sling system (13) is arranged on following wherein at least a kind of split position and is connected with wherein two kinds of splits at least, plate body, buoyancy plate body (2), buoyancy cylinder (3), load (4), floatage air bag (11); Its sling system (13) includes following wherein at least a kind of parts, rope rope (13.1), manually adjustment length attitude mechanism (13.2), automatically adjustment length attitude mechanism (13.3); It is for the connection between plate body, buoyancy plate body (2), buoyancy cylinder (3), load (4), floatage air bag (11); Adjusted the attitude of plate body, buoyancy cylinder (3) by the length of sling system (13), plate body, buoyancy cylinder (3) just can be followed the tracks of and aim at sunshine;

The following wherein at least a kind of split in one end of its mooring or fixed system (14) connects, plate body, buoyancy plate body (2), buoyancy cylinder (3), load (4); Mooring or fixed system (14) other end are connected with ground;

Its cooling or compression store gas system (15) and are arranged on following wherein at least a kind of split position, buoyancy plate body (2), buoyancy cylinder (3), load (4), vertical tail (7), tailplane (8), floatage air bag (11), horizontal connector (22), vertical connections (23), oblique attaching parts (24); 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, buoyancy plate body (2), buoyancy cylinder (3), load (4), vertical tail (7), tailplane (8), floatage air bag (11), horizontal connector (22), vertical connections (23), horizontal connector (22), vertical connections (23), oblique attaching parts (24); 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, buoyancy plate body (2), buoyancy cylinder (3), load (4), vertical tail (7), tailplane (8), floatage air bag (11), inner interlayer (19), horizontal connector (22), vertical connections (23), oblique attaching parts (24); Heavily gas (20) density is equal to or higher than photovoltaic buoyancy aircraft external space density;

Its high altitude communication or monitor supervision platform device (18) are arranged on following wherein at least a kind of position, plate body, buoyancy plate body (2), buoyancy cylinder (3), load (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, buoyancy plate body (2), buoyancy cylinder (3), load (4), vertical tail (7), tailplane (8), floatage air bag (11), balloonet (12), horizontal connector (22), vertical connections (23), oblique attaching parts (24);

Its hectare transfers from one department to another system (21) 00 in following wherein at least a kind of position, plate body, buoyancy plate body (2), buoyancy cylinder (3), load (4), propulsion system (5);

Its horizontal connector (22) connects following wherein at least a kind of split, plate body, buoyancy plate body (2), buoyancy cylinder (3), load (4), propulsion system (5);

Its vertical connections (23) connects following wherein at least a kind of split, plate body, buoyancy plate body (2), buoyancy cylinder (3), load (4), propulsion system (5);

Its oblique attaching parts (24) connects following wherein at least a kind of split, plate body, buoyancy plate body (2), buoyancy cylinder (3), load (4), propulsion system (5);

Its aerogenerator group system (25) is arranged on following wherein at least a kind of position, plate body, buoyancy plate body (2), buoyancy cylinder (3), load (4); Aerogenerator group system (25) includes Luo Xuanjiang wind turbine system (25.1), electricity Dong Ji generator system (25.2), feather control system (25.3), switched system (25.4); Its feather control system (25.3) be arranged on screw propeller wind turbine system (25.1) position, this feather control system (25.3) can fly time reduce flight air draught; Switched system (25.4) can to make between aerogenerator group system (25) and motor-type propulsion system (5.1.1) can the mutual switching of practical function, conversion;

Single hull structure or multilayer shell structure version is included, plate body, buoyancy plate body (2), buoyancy cylinder (3), vertical tail (7), tailplane (8), floatage air bag (11), inner interlayer (19), horizontal connector (22), vertical connections (23), oblique attaching parts (24) in following wherein at least a kind of split;

Metallic material or rigid material or flexible material is included, plate body, buoyancy plate body (2), buoyancy cylinder (3), load (4), floatage air bag (11), vertical tail (7), tailplane (8), inner interlayer (19), horizontal connector (22), vertical connections (23), oblique attaching parts (24) in following wherein at least a kind of split; 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 10.

Photovoltaic buoyancy aircraft according to content 6, 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, buoyancy plate body (2), buoyancy cylinder (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;

Wherein motor-type propulsion system (5.1.1) include screw propeller wind turbine system (25.1), electrical motor generator system (25.2), feather control system (25.3), switched system (25.4); Its feather control system (25.3) be arranged on screw propeller wind turbine system (25.1) position, this feather control system (25.3) can fly time reduce flight air draught; Switched system (25.4) can to make between aerogenerator group system (25) and motor-type propulsion system (5.1.1) can the mutual switching of practical function, conversion.

Content 11.

Photovoltaic buoyancy aircraft according to content 7, also includes following characteristics:

The hard and soft combined plate body (2.3) of its buoyancy plate body (2) includes following wherein at least a kind of unitized construction form, outer casing is rigidity plate body (2.1) and internal layer shell is flexible plate body (2.2), and internal layer shell is rigidity plate body (2.1) and outer casing is flexible plate body (2.2); The hard and soft combination buoyancy cylinder (3.3) of its buoyancy cylinder (3) includes following wherein at least a kind of unitized construction form, outer casing is rigidity buoyancy cylinder (3.1) and internal layer shell is flexible buoyancy cylinder (3.2), and internal layer shell is rigidity buoyancy cylinder (3.1) and outer casing is flexible buoyancy cylinder (3.2).

Content 12.

Photovoltaic buoyancy aircraft according to content 9, 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 photovoltaic buoyancy aircraft external space; Multilayer shell structure substantially increase buoyancy plate body (2), buoyancy cylinder (3), load (4), vertical tail (7), tailplane (8), floatage air bag (11), inner interlayer (19), horizontal connector (22), vertical connections (23) 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.

Content 13.

Parking in the air and power transmitting device according to content 2, also includes following characteristics:

To park in the air and power transmitting device also includes following wherein at least a kind of parts, horizontal mooring guy rope (41), vertical mooring guy rope (42);

Buoyancy aid (30) can also suspend following wherein at least a kind of parts in midair, horizontal mooring guy rope (41), vertical mooring guy rope (42); Its earth anchor (34) is connected with vertical mooring guy rope (42); Its vertical mooring guy rope (42) connects following wherein at least a kind of parts, vertical power transmission line (32), key lock switch system (34); Many horizontal mooring guy rope (41) cross connections mutually, form aerial stressed gauze; Horizontal mooring guy rope (41) includes individual layer or multilayer; Wherein horizontal mooring guy rope (41) connects following wherein at least a kind of parts, aerial power transmission line (41), key lock switch system (34); Wherein plug-in mechanism (33) includes following wherein at least a kind of parts, manual plug-in mechanism (33.1), automatically plug-in mechanism (33.2); Wherein key lock switch system (34) includes following wherein at least a kind of parts, manual locking on-off system (34.1), automatically locks on-off system (34.2); The height on aerial power transmission line (41) or horizontal mooring guy rope (41) distance ground is between 300-25000 rice.Aloft, the aerial power transmission line (31) that horizontal mooring guy rope (41), vertical mooring guy rope (42) connect, vertical power transmission line (32), plug-in mechanism (33), so just can be avoided aerial power transmission line (31), vertically power transmission line (32), plug-in mechanism (33) and be subject to powerful pulling force, cause damage power transmission lines installations and facilities; Many aerial power transmission line (31) cross connections mutually, form aerial electrical grid; Aerial power transmission line (31) includes individual layer or multilayer.

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.3, make full use of buoyancy, 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.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 photovoltaic buoyancy aircraft 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, owing to taking full advantage of floating technology, photovoltaic buoyancy aircraft cost is reduced greatly, its cost quite easily extensively enters family, private daily field with intermediate vehicle.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, because therefore photovoltaic buoyancy aircraft at high-altitude prolonged stay, can create " aerial aviation " pattern that aircraft is deposited on a kind of airport aloft.11, due to can at high-altitude prolonged stay, it provide a kind of cheapness, clean, safe high-altitude service platform, such as high altitude communication platform, high-altitude monitor supervision platform, be equivalent to additionally increase New function of more than two kinds.12, due to when aircraft does not use, aircraft can be placed on high-altitude as aerial wind-force and photovoltaic cogeneration station, dual-use material.Its cogeneration benefit is very high, spends electric cost lower than 0.3 yuan/kws.13 if unmanned vehicle, and its performance is better, cost performance is higher.14, in the future propeller-parachuting can be used for physical culture, generating, floating platform, and a thing three is used.15, the life and work that the ground that " flight house " pursues the mankind moves freely is enjoyed and is improved the life and work being upgraded to freedom of the air movement and enjoy.Meanwhile, start a kind of completely newly, the living and mode of operation of airflight movement.Be equivalent to ground huge pillar industry in national economy---" real estate " industry, transfer improves and is upgraded to a huger pillar industry in national economy that is brand-new, flight movement---" the empty product in room " industry.

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 be a kind of inside be filled with buoyant gas (1), upper surface be provided with photovoltaic cell (10.1), flexible plate body (2.2) the side elevational cross-section schematic diagram of single hull structure, wherein the cross sectional shape of Fig. 1 adopts fairing shape, and wherein the cross sectional shape of Fig. 1 .1 adopts wing shape.

Fig. 2, Fig. 2 .1 be a kind of 2 inside be filled with buoyant gas (1), upper surface be provided with photovoltaic cell (10.1), flexible plate body (2.2) the side elevational cross-section schematic diagram of double-layer shell structure, be filled with heavily gas (20) between its two sheets of flexible housing; Wherein the cross sectional shape of Fig. 2 adopts fairing shape, and wherein the cross sectional shape of Fig. 2 .1 adopts wing shape.

Fig. 3, Fig. 3 .1 be a kind of inside be filled with buoyant gas (1), upper surface be provided with photovoltaic cell (10.1), rigidity plate body (2.1) the side elevational cross-section schematic diagram of single hull structure; Wherein the cross sectional shape of Fig. 3 adopts fairing shape, and wherein the cross sectional shape of Fig. 3 .1 adopts wing shape.。

Fig. 4, Fig. 4 .1 be a kind of inside be provided with floatage air bag (11), upper surface be provided with photovoltaic cell (10.1), rigidity plate body (2.1) the side elevational cross-section schematic diagram of single hull structure; Wherein the cross sectional shape of Fig. 4 adopts fairing shape, and wherein the cross sectional shape of Fig. 4 .1 adopts wing shape.

Fig. 5, Fig. 6 .1, Fig. 6 .2, Fig. 6 .3 is hard and soft combined plate body (2.3) the side elevational cross-section schematic diagram that 4 kinds of inside are filled with buoyant gas (1), wherein buoyancy plate body (2) the first half is the rigidity plate body (2.1) of single hull structure, wherein buoyancy plate body (2) the latter half is the flexible plate body (2.2) of two sheets of flexible housing, is filled with heavily gas (20) between two sheets of flexible housing; Wherein Fig. 5 is full of buoyant gas (1), during for landing state; Wherein Fig. 6 .1, Fig. 6 .2, Fig. 6 .1 are filled with part buoyant gas (1), and during for high-altitude flight state, the lift that flies during this shape is large; .

Fig. 7, Fig. 7 .1 be a kind of inside be filled with buoyant gas (1), upper surface be provided with photovoltaic cell (10.1), single hull structure, photovoltaic buoyancy aircraft (propeller-parachuting) the side elevational cross-section schematic diagram of flexible plate body (2.2); Wherein the cross sectional shape of Fig. 7 adopts fairing shape, and wherein the cross sectional shape of Fig. 7 .1 adopts wing shape.

Fig. 8, Fig. 8 .1 be a kind of inside be filled with buoyant gas (1), upper surface be provided with photovoltaic cell (10.1), double-layer shell structure, photovoltaic buoyancy aircraft (propeller-parachuting) the side elevational cross-section schematic diagram of flexible plate body (2.2), be filled with heavily gas (20) between its two sheets of flexible housing; Wherein the cross sectional shape of Fig. 8 adopts fairing shape, and wherein the cross sectional shape of Fig. 8 .1 adopts wing shape.

Fig. 9, Fig. 9 .1 be a kind of inside be filled with buoyant gas (1), upper surface be provided with photovoltaic cell (10.1), single hull structure, photovoltaic buoyancy aircraft (propeller-parachuting) the side elevational cross-section schematic diagram of rigidity plate body (2.1); Wherein the cross sectional shape of Fig. 9 adopts fairing shape, and wherein the cross sectional shape of Fig. 9 .1 adopts wing shape.

Figure 10, Figure 10 .1 be a kind of inside be provided with floatage air bag (11), upper surface be provided with photovoltaic cell (10.1), single hull structure, photovoltaic buoyancy aircraft (propeller-parachuting) the side elevational cross-section schematic diagram of wing shape rigidity plate body (2.1), face generalized section.

Figure 11 be a kind of inside be filled with buoyant gas (1), upper surface be provided with photovoltaic cell (10.1), photovoltaic buoyancy aircraft (propeller-parachuting) the side elevational cross-section schematic diagram of the hard and soft combined plate body of wing shape (2.3); Wherein buoyancy plate body (2) the first half is the rigidity plate body (2.1) of single hull structure, wherein buoyancy plate body (2) the latter half is the flexible plate body (2.2) of two sheets of flexible housing, is filled with heavily gas (20) between two sheets of flexible housing.

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

Figure 13 is the elevational schematic view of Figure 12.

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

Figure 15 is the elevational schematic view of Figure 14.

Figure 16 be one arrange finned body shape rigidity plate body (2.1), under have fairing shape rigidity buoyancy cylinder (3.1) to be combined into, there is the side elevational cross-section schematic diagram of the photovoltaic buoyancy aircraft of electric propulsion system (5.1), the upper surface of its rigidity plate body (2.1), rigidity buoyancy cylinder (3.1) is provided with photovoltaic cell (10.1), and the inside of its rigidity plate body (2.1), rigidity buoyancy cylinder (3.1) is filled with buoyant gas (1).

Figure 17 is the elevational schematic view of Figure 16.

Figure 18 be one arrange finned body shape rigidity buoyancy cylinder (3.1), under have the hard and soft combined plate body of fairing shape (2.3) to be combined into, there is the side elevational cross-section schematic diagram of the photovoltaic buoyancy aircraft of electric propulsion system (5.1), the upper surface of its hard and soft combined plate body (2.3), rigidity buoyancy cylinder (3.1) is provided with photovoltaic cell (10.1), and the inside of its hard and soft combined plate body (2.3), rigidity buoyancy cylinder (3.1) is filled with buoyant gas (1).

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

Figure 20 be one arrange lower finned body shape rigidity plate body (2.1), on have rigidity buoyancy cylinder (3.1) to be opened/closed to be combined into, variable-volume ellipsoidal shape floatage air bag (11) is provided with in its rigidity buoyancy cylinder (3.1) to be opened/closed, there is the side elevational cross-section schematic diagram of the photovoltaic buoyancy aircraft of electric propulsion system (5.1), the upper surface of its rigidity plate body (2.1), rigidity buoyancy cylinder (3.1) to be opened/closed is provided with photovoltaic cell (10.1), and the inside of its rigidity plate 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 wing shape rigidity plate body (2.1), system (21) is transfered from one department to another in hybrid propulsion system (5.6) setting after a little while, the side elevational cross-section schematic diagram of board-like photovoltaic buoyancy aircraft.

Figure 24 is the elevational schematic view of Figure 23.

Figure 25, Figure 26, Figure 27 are that the setting of a kind of wing shape buoyancy plate body (2) is transfered from one department to another to unite (21) after a little while, have side elevational cross-section schematic diagram, front elevational schematic, the elevational schematic view of the board-like photovoltaic buoyancy aircraft of hybrid propulsion system (5.6), its buoyancy plate body (2) inside is filled with buoyant gas (1).

Figure 28, Figure 29, Figure 30, Figure 31 be one arranged inverted triangle fairing flexible shape plate body (2.2), under have 1 fairing flexible shape buoyancy cylinder (3.2) to be combined into, have motor-type propulsion system (the side elevational cross-section schematic diagram of the photovoltaic buoyancy aircraft of 5.1.1) aerogenerator group system (25), elevational schematic view, 2 kinds of front elevational schematic.The upper surface of its flexible plate body (2.2), flexible buoyancy cylinder (3.2) is provided with photovoltaic cell (10.1), and the inside of its flexible plate body (2.2), flexible buoyancy cylinder (3.2) is filled with buoyant gas (1).In fig. 30, its load (4) and flexible buoyancy cylinder (3.2) are directly connected in one.In Figure 31, its load (4) and flexible buoyancy cylinder (3.2) are connected in one indirectly by sling system (13).

Figure 32, Figure 33, Figure 34 be one arranged the flexible plate body (2.2) of oblong-shaped, under have 2 fairing flexible shape buoyancy cylinder (3.2) to be combined into, have motor-type propulsion system (side elevational cross-section schematic diagram, elevational schematic view, the front elevational schematic of the photovoltaic buoyancy aircraft of 5.1.1) aerogenerator group system (25).The upper surface of its flexible plate body (2.2), flexible buoyancy cylinder (3.2) is provided with photovoltaic cell (10.1), and the inside of its flexible plate body (2.2), flexible buoyancy cylinder (3.2) is filled with buoyant gas (1).In Figure 34, its load (4) and flexible buoyancy cylinder (3.2) are connected in one indirectly by sling system (13).

Figure 35, Figure 36 are side elevational cross-section schematic diagram, the schematic top plan view that one arranges parking of 2 layers of Mesh air power transmission line (31) and power transmitting device in the air.

Detailed description of the invention.

Embodiment 1.From Fig. 1, Fig. 1 .1, Fig. 7, Fig. 7 .1, be a kind of inside be filled with buoyant gas (1), upper surface be provided with photovoltaic cell (10.1), the photovoltaic buoyancy aircraft (propeller-parachuting) of the flexible plate body (2.2) of single hull structure.

Photovoltaic buoyancy aircraft includes propulsion system (5), drives or control system (6), load (4), sling system (13), mooring or fixed system (14); Wherein drive or control system (6), mooring or fixed system (14) not shown in FIG.;

It is characterized in that; Photovoltaic buoyancy aircraft also includes flexible plate body (2.2), photovoltaic generating system (10);

Flexible plate body (2.2) adopts single hull structure; Include buoyant gas (1) in flexible plate body (2.2), buoyant gas (1) is hydrogen or helium or ammonia, is the buoyant gas of tool; Buoyant gas (1) is arranged in flexible plate body (2.2); Wherein Fig. 1, Fig. 7 flexible plate body (2.2) cross sectional shape adopt fairing shape, wherein the cross sectional shape of the flexible plate body (2.2) of Fig. 1 .1, Fig. 7 .1 adopts wing shape; The flexible plate body (2.2) of wing shape has lift function when flying; The anterior-posterior length of flexible plate body (2.2) and left and right width are than between 2: 1 to 10: 1; Flight windage can be greatly reduced like this;

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 flexible plate 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 transfers from one department to another (21) (not shown in FIG.) of uniting after a little while, just transfer from one department to another unite (21) drive change propulsion system (5) direction of propulsion, can before, can afterwards, can go up, can descend rotate advance;

Driving or control system (6) include 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 flexible plate body (2.2) and load (4); Driving or control system (6) are arranged in load (4); Its sling system (13) includes following wherein at least a kind of parts, rope rope (13.1), manually adjustment length attitude mechanism (13.2), automatically adjustment length attitude mechanism (13.3); It is for the connection between plate body, buoyancy plate body (2), buoyancy cylinder (3), load (4), floatage air bag (11); Manually adjust the length of length attitude mechanism (13.2) or adjustment length attitude mechanism (13.3) adjustment rope rope (13.1) automatically, the attitude reaching the flexible plate body of adjustment (2.2) follows the tracks of the object of aiming at sunshine; So just can make the photovoltaic electric power that output is maximum, approximately improve the photovoltaic electric power output of 35%;

Mooring or fixed system (14) (not shown in FIG.) are stationary ropes; When not flying, long stationary rope connects load (4), and photovoltaic buoyancy aircraft is fixed on ground;

The shell of flexible plate body (2.2), sling system (13), load (4) adopts the basalt fibre of fibers and inorganic, and its cost performance is about 10 times of steel.Because basalt fibre manufacturing flexible plate body (2.2) has high tensile property, flexible plate body (2.2) volume can not increase, so the flying height of this photovoltaic buoyancy aircraft is no more than 1000 meters of height usually.

The buoyancy of this photovoltaic buoyancy aircraft is greater than deadweight, is fully loaded with.When taking off vertically, actuating motor formula propulsion system (5.1.1) and combustion engine propulsion system (5.2) simultaneously, just transfer from one department to another system (21) rotation hybrid propulsion system (5.6) and become flat shape, whole thrust is used for upward direction and advances.Enter in the air, just transfer from one department to another system (21) rotary internal combustion engine propulsion system (5.2) and become vertical shape; After this combustion engine propulsion system (5.2) is closed, because flexible plate 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 photovoltaic buoyancy aircraft, 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, unload 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 needs use photovoltaic buoyancy aircraft, adopt mode of traction or rely on automatic Pilot control system (6.2) to make photovoltaic buoyancy aircraft drop to ground, allow personnel enter photovoltaic buoyancy aircraft, again take off vertically.

Embodiment 2.From Fig. 2, Fig. 2 .1, Fig. 8, Fig. 8 .1, be a kind of inside be filled with buoyant gas (1), upper surface be provided with photovoltaic cell (10.1), the photovoltaic buoyancy aircraft (propeller-parachuting) of the flexible plate body (2.2) of double-layer shell structure.

It is characterized in that; Flexible plate 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 flexible plate 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 flexible plate body (2.2) position or load (4) position; Heavily the density of gas (20) is equal to or higher than the density of the photovoltaic buoyancy aircraft external space, adopts air as heavy gas (20);

Wherein buoyancy plate body (2) cross sectional shape of Fig. 2, Fig. 8 adopts fairing shape, wherein buoyancy plate body (the cross sectional shape employing wing shape of 2 of Fig. 2 .1, Fig. 8 .1; The flexible plate body (2.2) of wing shape has lift function when flying.All the other features are with embodiment 1.

Embodiment 3.From Fig. 3, Fig. 3 .1, Fig. 9, Fig. 9 .1, be a kind of inside be filled with buoyant gas (1), upper surface be provided with photovoltaic cell (10.1), the photovoltaic buoyancy aircraft (propeller-parachuting) of the rigidity plate body (2.1) of single hull structure.

It is characterized in that; Buoyancy plate body (2) adopts the rigidity plate body (2.1) of single hull structure.Owing to adopting the rigidity plate 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 photovoltaic buoyancy aircraft than embodiment 1, embodiment 2 from great.

Wherein buoyancy plate body (2) cross sectional shape of Fig. 3, Fig. 9 adopts fairing shape, and wherein the cross sectional shape of the buoyancy plate body (2) of Fig. 3 .1, Fig. 9 .1 adopts wing shape; The buoyancy plate body (2) of wing shape has lift function when flying.All the other features are with embodiment 1.

Embodiment 4.From Fig. 4, Fig. 4 .1, Figure 10, Figure 10 .1, it is photovoltaic buoyancy aircraft (propeller-parachuting) that a kind of inside is filled with buoyant gas (1), that be provided with constant volume floatage air bag (11) in rigidity plate body (2.1), be provided with photovoltaic cell (10.1) at upper surface.

It is characterized in that; The outside of buoyancy plate body (2) adopts the rigidity plate body (2.1) of single hull structure; Floatage air bag (11) that the inside of buoyancy plate body (2) includes the double-layer shell structure of two sheets of flexible housing, that have many constant volumes; Floatage air bag (11) adopts buoyancy gas column (11.2), and its buoyancy gas column (11.2) arranges with horizontal gas column form, sees Figure 10; When Near Ground takes off landing, the buoyancy of buoyancy gas column (11.2) 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 buoyancy gas column (11.2), the pressure increase in buoyancy gas column (11.2).Now, the buoyancy of buoyancy gas column (11.2) reduces rapidly, and propulsion system (5) rotates pushes ahead flight.During flight, the main lift relying on rigidity plate body (2.1).Owing to adopting the rigidity plate 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 photovoltaic buoyancy aircraft than embodiment 1-embodiment 3 from great.It is in Figure 10 .1, and buoyancy gas column (11.2) also can longitudinal gas column form arrangement.Wherein buoyancy plate body (2) cross sectional shape of Fig. 4 adopts fairing shape, and wherein the cross sectional shape of the buoyancy plate body (2) of Fig. 1 .1, Figure 10 adopts wing shape; The buoyancy plate body (2) of wing shape has lift function when flying.All the other features are with embodiment 1.

Embodiment 5.From Fig. 5, Fig. 6 .1, Fig. 6 .2, Fig. 6 .3, Figure 11, be a kind of inside be filled with buoyant gas (1), upper surface be provided with photovoltaic cell (10.1), the photovoltaic buoyancy aircraft (propeller-parachuting) of hard and soft combined plate body (2.3).

It is characterized in that; Buoyancy plate body (2) adopts hard and soft combined plate body (2.3); The first half of this hard and soft combined plate body (2.3) is the rigidity plate body (2.1) of single hull structure, and the lower part of this hard and soft combined plate body (2.3) is the flexible plate 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 flexible plate body (2.2); Prevent buoyant gas (1) from extracting seepage out.

Photovoltaic buoyancy aircraft also includes cooling or compression stores 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, and sees Fig. 6 .1, Fig. 6 .2, Fig. 6 .3; Doing so avoids the buoyant gas (1) when high-altitude and cubic expansion occurs, increase flight resistance, or destroy buoyancy plate body (2), buoyancy cylinder (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 can as buoyant gas (1), in order to improve the buoyancy of photovoltaic buoyancy aircraft;

Wherein Fig. 5 is that hard and soft combined plate body (2.3) is full of buoyant gas (1), presents fairing shape; Now the buoyancy of hard and soft combined plate body (2.3) is maximum, can be used for landing state; Wherein Fig. 6 .1, Fig. 6 .2, Fig. 6 .3, Figure 11 is filled with part buoyant gas (1), now the lift of hard and soft combined plate body (2.3) increases, and flight resistance reduces, and can be used for high-altitude flight state.When high-altitude flight state, the fairing shape being full of buoyant gas (1) due to hard and soft combined plate body (2.3) is very big without flight lift, again flight resistance.Therefore adopt cooling or compression storage gas system (15) buoyant gas (1) can be extracted out, compressed and liquefied, reduce volume.After hard and soft combined plate body (2.3) is become 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 combined plate 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) can as buoyant gas (1), in order to improve the buoyancy of photovoltaic buoyancy aircraft; 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 combined plate 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 combined plate 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.Be one include aerogenerator group system (25), surface is provided with the photovoltaic buoyancy aircraft (propeller-parachuting) of photovoltaic cell (10.1).

It is characterized in that; Photovoltaic buoyancy aircraft also includes its aerogenerator group system (25), not shown in FIG.; Aerogenerator group system (25) is arranged on following wherein at least a kind of position, plate body, buoyancy plate body (2), buoyancy cylinder (3), load (4); itsaerogenerator group system (25) includes Luo Xuanjiang wind turbine system (25.1), electricity Dong Ji generator system (25.2), feather control system (25.3), switched system (25.4); Its feather control system (25.3) be arranged on screw propeller wind turbine system (25.1) position, this feather control system (25.3) can fly time reduce flight air draught; Switched system (25.4) can to make between aerogenerator group system (25) and motor-type propulsion system (5.1.1) can the mutual switching of practical function, conversion; Or motor-type propulsion system (5.1.1) include screw propeller wind turbine system (25.1), electrical motor generator system (25.2), feather control system (25.3), switched system (25.4); Its feather control system (25.3) be arranged on screw propeller wind turbine system (25.1) position, this feather control system (25.3) can fly time reduce flight air draught; Switched system (25.4) can to make between aerogenerator group system (25) and motor-type propulsion system (5.1.1) can the mutual switching of practical function, conversion.

Due to when aircraft does not use, aircraft can be placed on high-altitude as aerial wind-force and photovoltaic cogeneration station, dual-use material.Owing to can following the tracks of daylight and blocking without cloud and mist, aerial wind-force and photovoltaic cogeneration stand in aerial electric power more than several times more multiple than ground.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, aerial wind-force and photovoltaic cogeneration pattern and Transmission Mode earthward efficiently.All the other features are with embodiment 1--embodiment 5.

Embodiment 7.From Figure 12, Figure 13, be one arrange down rigidity plate body (2.1), on have flexible buoyancy cylinder (3.2) to be combined into, have the photovoltaic buoyancy aircraft of electric propulsion system (5.1) or oil electric mixed dynamic propulsion system (5.6).

It is characterized in that; It includes rigidity plate body (2.1), flexible buoyancy cylinder (3.2), load (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 rigidity plate body (2.1), on have flexible buoyancy cylinder (3.2) to be combined into; Rigidity plate body (2.1), flexible buoyancy cylinder (3.2) upper surface are provided with photovoltaic cell (10.1);

The inside of its rigidity plate body (2.1), flexible buoyancy cylinder (3.2) is filled with buoyant gas (1); Its rigidity plate 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 buoyancy cylinder (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 flexible plate 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 load (4) position; The anterior-posterior length of rigidity plate body (2.1), flexible buoyancy cylinder (3.2) and left and right width are than between 2: 1 to 10: 1; Flight windage can be greatly reduced like this;

Its vertical tail (7), tailplane (8) are arranged on flexible buoyancy cylinder (3.2); Its balloonet (12) (not shown in FIG.) is arranged in flexible buoyancy cylinder (3.2), keeps the rigidity of flexible device buoyancy cylinder (3.2); Its mooring or fixed system (14) are connected with buoyancy plate body (2), buoyancy cylinder (3), load (4), and 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 buoyancy cylinder (3.2).

Wherein photovoltaic generating system (10) includes following parts, photovoltaic cell (10.1), load governor, storage battery, inverter; Photovoltaic cell (10.1) is included, buoyancy plate body (2), buoyancy cylinder (3), load (4), Driving control pedestal (4.1), Driving control cabin body (4.2), vertical tail (7), tailplane (8) at the upper surface of following wherein at least a kind of split or side surface.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 transfers from one department to another (21) (not shown in FIG.) of uniting after a little while, just transfer from one department to another unite (21) drive change propulsion system (5) direction of propulsion, can before, can afterwards, can go up, can descend rotate advance;

When adopting oil electric mixed dynamic propulsion system (5.6), the buoyancy of this photovoltaic buoyancy aircraft is 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), just transfers from one department to another system (21) turning motor formula propulsion system (5.1.1) and becomes flat shape, and whole thrust is used for upward direction and advances.Enter in the air, just transfer from one department to another system (21) turning motor formula propulsion system (5.1.1) and become vertical shape, whole thrust is used for forward direction and advances.Because buoyancy plate 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.Because buoyancy is greater than deadweight, this photovoltaic buoyancy aircraft swims 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 needs use photovoltaic buoyancy aircraft, adopt manpower mode or rely on automatic Pilot control system (6.2) to make photovoltaic buoyancy aircraft drop to ground, allow personnel enter photovoltaic buoyancy aircraft, again take off vertically.All the other features are with embodiment 1--embodiment 7.

Embodiment 8.From Figure 14, Figure 15, be one arranged rigidity plate body (2.1), under have flexible buoyancy cylinder (3.2) to be combined into, have the photovoltaic buoyancy aircraft of electric propulsion system (5.1) or oil electric mixed dynamic propulsion system (5.6).

It is characterized in that; It has rigidity plate body (2.1), under have flexible buoyancy cylinder (3.2) to be combined into; Rigidity plate body (2.1), flexible buoyancy cylinder (3.2) upper surface are provided with photovoltaic cell (10.1); 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 rigidity plate body (2.1), load (4) position.Its electric propulsion system (5.1) or oil electric mixed dynamic propulsion system (5.6) comprise transfers from one department to another (21) (not shown in FIG.) of uniting after a little while, just transfers from one department to another system (21) and 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, just transfer from one department to another system (21) rotation hybrid propulsion system (5.6) and become vertical shape; After this because flexible plate 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 rigidity plate body (2.1), under have rigidity buoyancy cylinder (3.1) to be combined into photovoltaic buoyancy aircraft.

It is characterized in that; It has rigidity plate body (2.1), under have rigidity buoyancy cylinder (3.1) to be combined into; Rigidity plate body (2.1), rigidity buoyancy cylinder (3.1) upper surface are provided with photovoltaic cell (10.1); 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 rigidity plate body (2.1); The inside of its rigidity plate body (2.1), rigidity buoyancy cylinder (3.1) is filled with buoyant gas (1); Cooling or compression store gas system (15) and are connected with buoyant gas (1) pipeline in rigidity plate body (2.1), rigidity buoyancy cylinder (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 rigidity buoyancy cylinder (3.1), under have hard and soft combined plate body (2.3) to be combined into photovoltaic buoyancy aircraft.

It is characterized in that; It is one arranged rigidity buoyancy cylinder (3.1), under have hard and soft combined plate body (2.3) to be combined into; Rigidity plate body (2.1), hard and soft combined plate body (2.3) upper surface are provided with photovoltaic cell (10.1); 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 the first half rigidity plate body (2.1) of hard and soft combined plate body (2.3) hard and soft combined plate body (2.3); The inside of its hard and soft combined plate body (2.3), rigidity buoyancy cylinder (3.1) is filled with buoyant gas (1); Cooling or compression store gas system (15) and are connected with buoyant gas (1) pipeline in rigidity plate body (2.1), rigidity buoyancy cylinder (3.1).Hard and soft combined plate 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 rigidity plate body (2.1), on have rigidity buoyancy cylinder (3.1) to be opened/closed to be combined into, to be provided with variable-volume floatage air bag (11) in its rigidity buoyancy cylinder (3.1) to be opened/closed, to have the photovoltaic buoyancy aircraft of electric propulsion system (5.1) or oil electric mixed dynamic propulsion system (5.6).

It is characterized in that; Rigidity plate body (2.1), hard and soft combined plate body (2.3) upper surface are provided with photovoltaic cell (10.1); Its rigidity buoyancy cylinder (3.1) is provided with hatchcover (3.4) in activity to be opened/closed, and this rigidity buoyancy cylinder (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 regain floatage air bag (11), then movable upper hatchcover (3.4) closes, and forms complete rigidity buoyancy cylinder (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 transfers from one department to another (21) (not shown in FIG.) of uniting after a little while, just transfers from one department to another system (21) and 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 .1, Figure 23, Figure 24, that one is provided with constant volume floatage air bag (11) in rigidity plate body (2.1), system (21) is transfered from one department to another in electric propulsion system (5.1) or oil electric mixed dynamic propulsion system (5.6) setting after a little while, board-like photovoltaic buoyancy aircraft.

It is characterized in that; This photovoltaic buoyancy aircraft only has buoyancy plate body (2), is board-like aircraft; Rigidity plate body (2.1) upper surface is provided with photovoltaic cell (10.1); In rigidity plate 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 electric propulsion system (5.1) or oil electric mixed dynamic propulsion system (5.6) rotate pushes ahead flight.During flight, the main lift relying on rigidity plate body (2.1).Because cooling or compression do not store gas system (15), the weight reduction of its photovoltaic buoyancy aircraft.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 the setting of a kind of buoyancy plate body (2) is transfered from one department to another unite (21) after a little while, have the board-like photovoltaic buoyancy aircraft of electric propulsion system (5.1) or oil electric mixed dynamic propulsion system (5.6), its flexible plate 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; Buoyancy plate body (2) arranges and transfers from one department to another after a little while to unite (21); When taking off landing, just transfer from one department to another system (21) rotary floating plate body (2) and upwards become vertical, be conducive to electric propulsion system (5.1) or oil electric mixed dynamic propulsion system (5.6) upwards, downwards advances, also help the area reducing and take ground simultaneously.When high-altitude flight, just transfer from one department to another (21) rotary floating plate body (2) transversely flat shape of uniting, be conducive to buoyancy plate body (2) and produce lift, replace buoyancy.All the other features are with embodiment 1-embodiment 12.

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

It is characterized in that; This buoyancy plate body (2) adopts rigidity plate body (2.1) or flexible plate body (2.2); Many constant volume floatage air bags (11) are provided with in rigidity plate body (2.1) or flexible plate body (2.2); Floatage air bag (11) includes following wherein one at least, buoyant balloon (11.1), buoyancy gas column (11.2); Multiple buoyancy gas column (11.2) is with following wherein at least a kind of gas column form arrangement, and longitudinal gas column form arrangement, horizontal gas column form arrange.All the other features are with embodiment 1-embodiment 13.

Embodiment 15.That a kind of buoyant gas (1) that adopts is as the photovoltaic buoyancy aircraft 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, buoyancy plate body (2), buoyancy cylinder (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 photovoltaic buoyancy aircraft lands, open high pressure tank, re-entering of the buoyant gas of fuel gas (1.6) (1), buoyancy plate body (2), buoyancy cylinder (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 photovoltaic buoyancy aircraft that one is provided with inner interlayer (19).

It is characterized in that; Photovoltaic buoyancy aircraft also includes inner interlayer (19) (not shown in FIG.); Inner interlayer (19) is arranged on following wherein at least a kind of position, buoyancy plate body (2), buoyancy cylinder (3), load (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 buoyancy plate body (2), buoyancy cylinder (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 photovoltaic buoyancy aircraft 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, buoyancy plate body (2), buoyancy cylinder (3), load (4).Such photovoltaic buoyancy aircraft dual-use material, both can use as aerial vehicle, can use again as the platform of aerial loading.All the other features are with embodiment 1-embodiment 16.

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

It is characterized in that; Photovoltaic buoyancy aircraft adopts ammonia (1.3) as buoyant gas (1), photovoltaic buoyancy aircraft also includes cooling or compression stores gas system (15) (not shown in FIG.), electric heating system (16), and 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 combined plate 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) can as buoyant gas (1), in order to improve the buoyancy of photovoltaic buoyancy aircraft; When entering high-altitude 3 in-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 combined plate 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 combined plate 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 Figure 28, Figure 29, Figure 30, Figure 31 be one arranged inverted triangle fairing flexible shape plate body (2.2), under have 1 fairing flexible shape buoyancy cylinder (3.2) to be combined into, have motor-type propulsion system (the photovoltaic buoyancy aircraft of 5.1.1) aerogenerator group system (25).

It is characterized in that; It comprises transfers from one department to another system (21), horizontal connector (22), vertical connections (23), oblique attaching parts (24), aerogenerator group system (25) after a little while; Its flexible plate body (2.2) adopts inverted triangle fairing shape, and flexible buoyancy cylinder (3.2) adopts inverted triangle fairing shape, and such unitized construction had both been conducive to reducing flight windage area; Be conducive to again the flight air resistance coefficient greatly reduced; Wherein Figure 30 is that load (4) is directly connected in one with flexible buoyancy cylinder (3.2); Wherein to be load (4) be connected in one by sling system (13) with flexible buoyancy cylinder (3.2) Figure 31 indirectly, because this suspension type structure is conducive to greatly improving the stability of photovoltaic buoyancy aircraft, safety, economy and rising or falling speed.Aerogenerator group system (25) is arranged on following wherein at least a kind of position, plate body, buoyancy plate body (2), buoyancy cylinder (3), load (4); Its motor-type propulsion system (5.1.1) and aerogenerator group system (25) are with one, form motor-type propulsion system (5.1.1) aerogenerator group system (25) device of coenosarc; Aerogenerator group system (25) includes Luo Xuanjiang wind turbine system (25.1), electricity Dong Ji generator system (25.2), feather control system (25.3), switched system (25.4); Its feather control system (25.3) be arranged on screw propeller wind turbine system (25.1) position, this feather control system (25.3) can fly time reduce flight air draught; Switched system (25.4) can to make between aerogenerator group system (25) and motor-type propulsion system (5.1.1) can the mutual switching of practical function, conversion;

Or motor-type propulsion system (5.1.1) include screw propeller wind turbine system (25.1), electrical motor generator system (25.2), feather control system (25.3), switched system (25.4); Its feather control system (25.3) be arranged on screw propeller wind turbine system (25.1) position, this feather control system (25.3) can fly time reduce flight air draught; Switched system (25.4) can to make between aerogenerator group system (25) and motor-type propulsion system (5.1.1) can the mutual switching of practical function, conversion.

The utricule structure of its buoyancy cylinder (3) can adopt following wherein one at least, determines body main gasbag structure (3.5), determines body main gasbag+balloonet structure (3.6), variant main gasbag structure (3.7), variant main gasbag+balloonet structure structure (3.8); " variant main gasbag " version wherein among variant main gasbag structure (3.7), variant main gasbag+balloonet structure structure (3.8) includes following wherein one at least, radial variant structure form (3.9), longitudinal variant structure form (3.10), not shown in FIG.;

Due to when aircraft does not use, aircraft can be placed on high-altitude as aerial wind-force and photovoltaic cogeneration station, dual-use material.Owing to can following the tracks of daylight and blocking without cloud and mist, aerial wind-force and photovoltaic cogeneration stand in aerial electric power more than several times more multiple than ground.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, aerial wind-force and photovoltaic cogeneration pattern and Transmission Mode earthward efficiently.All the other features are with embodiment 1--embodiment 18.

Embodiment 20.From Figure 32, Figure 33, Figure 34, be one arranged the flexible plate body (2.2) of oblong-shaped, under have 2 fairing flexible shape buoyancy cylinder (3.2) to be combined into, have motor-type propulsion system (the photovoltaic buoyancy aircraft of 5.1.1) aerogenerator group system (25).

It is characterized in that; It comprises transfers from one department to another system (21), horizontal connector (22), vertical connections (23), oblique attaching parts (24), aerogenerator group system (25) after a little while; 2 fairing flexible shape buoyancy cylinder (3.2) are combined into optimum apparatus structure build with the flexible plate body (2.2) of oblong-shaped; Such unitized construction build had both been conducive to reducing flight windage area, the flight air resistance coefficient being conducive to again greatly reducing, also helped the area that greatly increases photovoltaic cell (10.1) and improved photovoltaic generation ability; All the other features are with embodiment 19.

Embodiment 21.Be one include photovoltaic generating system (10), the photovoltaic buoyancy aircraft 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.

Embodiment 22.It is the photovoltaic buoyancy aircraft that one includes aerial house (4.4).It is characterized in that;

Its load (4) includes aerial house (4.4); All the other features are with embodiment 1--embodiment 21.Load (4) be designed to house and increase " vapor air gathering-device ", just aloft can hang up one's hat, travel, live, work.Be equivalent in " flight house ".

Embodiment 23.From Figure 35, Figure 36, be that one arranges parking and power transmitting device of 2 layers of Mesh air power transmission line (31) in the air.

It is characterized in that; It includes following split, buoyancy aid (30), aerial power transmission line (31), vertical power transmission line (32), plug-in mechanism (33), key lock switch system (34), earth anchor (35), lightning protection system (36), horizontal mooring guy rope (41), vertical mooring guy rope (42); It is characterized in that:

Buoyancy aid (30) suspends vertical mooring guy rope (42) in midair, and earth anchor (34) is connected with vertical mooring guy rope (42); Many horizontal mooring guy rope (41) cross connections mutually, form aerial stressed gauze; Horizontal mooring guy rope (41) includes 2 layers; Its aerial power transmission line (31) and following circuit communication wherein between at least a kind of parts, vertical power transmission line (32), plug-in mechanism (33); Many aerial power transmission line (31) cross connections mutually, form aerial electrical grid; Aerial power transmission line (31) includes 2 layers; Its aerial power transmission line (31) is connected with following wherein at least a kind of parts, plug-in mechanism (33), key lock switch system (34); Its plug-in mechanism (33) can with the circuit communication of the photovoltaic generating system (10) of aerial photovoltaic buoyancy aircraft or aerogenerator group system (25); Then the electric power that photovoltaic generating system (10) or aerogenerator group system (25) are produced is transported to ground; Lightning protection system (36) is combined with following wherein at least a kind of parts, buoyancy aid (30), aerial power transmission line (31), vertical power transmission line (32), plug-in mechanism (33), key lock switch system (34), earth anchor (35); Buoyancy aid (30) also can support horizontal mooring guy rope (41) in addition, forms parking and power transmitting device of single buoyancy aid (30) in the air;

Horizontal mooring guy rope (41) connects aerial power transmission line (41), key lock switch system (34).Aloft, the aerial power transmission line (31) that horizontal mooring guy rope (41), vertical mooring guy rope (42) connect, so just can be avoided aerial power transmission line (31), vertical power transmission line (32), plug-in mechanism (33) under tension, infringement power transmission lines installations and facilities.Its key lock switch system (34) can be connected with the mooring of aerial photovoltaic buoyancy aircraft or fixed system (14); Then photovoltaic buoyancy aircraft mooring or be fixed on to be parked in the air and near power transmitting device, in order to plug-in mechanism (33) can with the circuit communication of the photovoltaic generating system (10) of aerial photovoltaic buoyancy aircraft or aerogenerator group system (25).

Skyborne photovoltaic buoyancy aircraft utilizes to be parked and the aerial power transmission line (31) of power transmitting device, vertically power transmission line (32), plug-in mechanism (33) in the air, and the photovoltaic electric power of photovoltaic buoyancy aircraft production, wind force power are transferred to ground.So just can be avoided the self-contained power transmission line pipeline equipment of photovoltaic buoyancy aircraft, significantly reduce the deadweight of photovoltaic buoyancy aircraft.Photovoltaic buoyancy aircraft or other aerospace equipment can also be parked simultaneously.The aerial power transmission line of its multilayer (31) can park photovoltaic buoyancy aircraft or other aerospace equipment of how several times.

Claims

1. photovoltaic buoyancy aircraft includes following split, buoyancy aid, load (4), propulsion system (5), driving or control system (6); Buoyancy aid includes buoyancy cylinder (3); The inside of its buoyancy aid, buoyancy cylinder (3) includes buoyant gas (1), and buoyant gas (1) density is lower than the gas density of the photovoltaic buoyancy aircraft external space; It is characterized in that:

Wherein photovoltaic generating system (10) includes photovoltaic cell (10.1); Photovoltaic cell (10.1) is arranged on following wherein at least a kind of position, side surface, the upper surface of plate body, the side surface of plate body of the upper surface of buoyancy aid or buoyancy cylinder (3), buoyancy aid or buoyancy cylinder (3);

2. with the parking in the air and power transmitting device of the auxiliary facility of photovoltaic buoyancy aircraft according to claim 1, it is characterized in that: it includes following split, buoyancy aid (30), aerial power transmission line (31), vertical power transmission line (32), key lock switch system (34), earth anchor (35), lightning protection system (36); It also includes following wherein at least a kind of split, aerial power transmission line (31), plug-in mechanism (33);

Wherein buoyancy aid (30) suspends in midair or supports following wherein at least a kind of parts, aerial power transmission line (31), vertical power transmission line (32);

Wherein aerial power transmission line (31) and following circuit communication wherein between at least a kind of parts, vertical power transmission line (32), plug-in mechanism (33); If there are many aerial power transmission lines (31), then many aerial power transmission line (31) cross connections mutually, form aerial electrical grid; Aerial power transmission line (31) includes individual layer or multilayer;

Wherein plug-in mechanism (33) can with the circuit communication of the photovoltaic generating system (10) of aerial photovoltaic buoyancy aircraft or aerogenerator group system (25);

Wherein key lock switch system (34) can be connected with the mooring of aerial photovoltaic buoyancy aircraft or fixed system (14);

Wherein lightning protection system (36) is combined with following wherein at least a kind of parts, buoyancy aid (30), aerial power transmission line (31), vertical power transmission line (32), plug-in mechanism (33), key lock switch system (34), earth anchor (35).

3. photovoltaic buoyancy aircraft according to claim 1; It is characterized in that:

The cross sectional shape of its buoyancy cylinder (3) includes following wherein one at least, wing shape, fairing shape, spindle shape, ellipsoidal shape, shuttle shape, rugby ball shape, oblong-shaped, square shape, leafy shape; Buoyancy cylinder (3) includes single or multiple; The utricule structure of its buoyancy cylinder (3) includes following wherein one at least, determines body main gasbag structure (3.5), determines body main gasbag+balloonet structure (3.6), variant main gasbag structure (3.7), variant main gasbag+balloonet structure structure (3.8); " variant main gasbag " version wherein among variant main gasbag structure (3.7), variant main gasbag+balloonet structure structure (3.8) includes following wherein one at least, radial variant structure form (3.9), longitudinal variant structure form (3.10);

Its buoyancy aid includes single or multiple, and its plate body or buoyancy plate body (2) include single or multiple, and its buoyancy cylinder (3) includes single or multiple.

4. photovoltaic buoyancy aircraft according to claim 1; It is characterized in that:

5. according to claim 1 or photovoltaic buoyancy aircraft according to claim 3; It is characterized in that:

Buoyancy aid also includes load (4); Buoyant gas (1) is included in load (4);

Its plate body or buoyancy plate body (2) are arranged on the top of following wherein at least a kind of position or middle part or bottom, buoyancy cylinder (3), load (4); Plate body or buoyancy plate body (2) are connected with following wherein at least a kind of split, buoyancy cylinder (3), load (4), propulsion system (5), sail or control system (6); Plate body or buoyancy plate body (2) include single or multiple;

6. photovoltaic buoyancy aircraft according to claim 1; It is characterized in that:

The anterior-posterior length of its plate body or buoyancy cylinder (3) and left and right width are than between 2: 1 to 10: 1;

Its plate body also comprise transfer from one department to another after a little while unite (21);

Its buoyancy cylinder (3) also includes movable upper hatchcover (3.4);

Its propulsion system (5) also comprises to be transfered from one department to another to unite (21) after a little while;

7. photovoltaic buoyancy aircraft according to claim 3; It is characterized in that:

Its plate body or buoyancy plate body (2) include following wherein at least a kind of split, rigidity plate body (2.1), flexible plate body (2.2), hard and soft combined plate body (2.3); Its hard and soft combined plate body (2.3) includes following wherein at least a kind of unitized construction form, rigidity plate body (2.1) and below flexible plate body (2.2) above, below rigidity plate body (2.1) and flexible plate body (2.2) above;

8. according to claim 3 or photovoltaic buoyancy aircraft according to claim 4; It is characterized in that:

Photovoltaic generating system (10) also includes following wherein at least a kind of parts, load governor, storage battery, inverter; Photovoltaic generating system (10) is included, plate body, buoyancy plate body (2), buoyancy cylinder (3), load (4), vertical tail (7), tailplane (8), horizontal connector (22), vertical connections (23), oblique attaching parts (24), oblique attaching parts (24) at the upper surface of following wherein at least a kind of split or side surface;

9. according to claim 3 or photovoltaic buoyancy aircraft according to claim 4; 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, plate body, buoyancy plate body (2), buoyancy cylinder (3), load (4);

Its balloonet (12) is arranged in following wherein at least a kind of split, buoyancy plate body (2), buoyancy cylinder (3), load (4), vertical tail (7), tailplane (8), floatage air bag (11), horizontal connector (22), vertical connections (23), oblique attaching parts (24);

Its sling system (13) is arranged on following wherein at least a kind of split position and is connected with wherein two kinds of splits at least, plate body, buoyancy plate body (2), buoyancy cylinder (3), load (4), floatage air bag (11); Its sling system (13) includes following wherein at least a kind of parts, rope rope (13.1), manually adjustment length attitude mechanism (13.2), automatically adjustment length attitude mechanism (13.3);

Its electric heating system (16) is arranged in following wherein at least a kind of split, buoyancy plate body (2), buoyancy cylinder (3), load (4), vertical tail (7), tailplane (8), floatage air bag (11), horizontal connector (22), vertical connections (23), oblique attaching parts (24); 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, buoyancy plate body (2), buoyancy cylinder (3), load (4), vertical tail (7), tailplane (8), floatage air bag (11), inner interlayer (19), horizontal connector (22), vertical connections (23), oblique attaching parts (24); Heavily the density of gas (20) is equal to or higher than the density of the photovoltaic buoyancy aircraft external space;

Its hectare transfers from one department to another system (21) and is arranged on following wherein at least a kind of position, plate body, buoyancy plate body (2), buoyancy cylinder (3), load (4), propulsion system (5);

Its vertical connections (24) connects following wherein at least a kind of split, plate body, buoyancy plate body (2), buoyancy cylinder (3), load (4), propulsion system (5);

Its aerogenerator group system (25) is arranged on following wherein at least a kind of position, plate body, buoyancy plate body (2), buoyancy cylinder (3), load (4); Aerogenerator group system (25) includes Luo Xuanjiang wind turbine system (25.1), electricity Dong Ji generator system (25.2), feather control system (25.3), switched system (25.4); Its feather control system (25.3) be arranged on screw propeller wind turbine system (25.1) position;

Metallic material or rigid material or flexible material is included, plate body, buoyancy plate body (2), buoyancy cylinder (3), load (4), floatage air bag (11), vertical tail (7), tailplane (8), inner interlayer (19), horizontal connector (22), vertical connections (23), oblique attaching parts (24) in following wherein at least a kind of split.

10. photovoltaic buoyancy aircraft according to claim 6; It is characterized in that:

Its electric propulsion system (5.1) includes following wherein one at least, motor-type propulsion system (51.1), 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, buoyancy plate body (2), buoyancy cylinder (3), vertical tail (7), tailplane (8), floatage air bag (11);

Wherein motor-type propulsion system (5.1.1) include screw propeller wind turbine system (25.1), electrical motor generator system (25.2), feather control system (25.3), switched system (25.4); Its feather control system (25.3) be arranged on screw propeller wind turbine system (25.1) position.