CN202966652U - Overpressure dish-shaped buoyancy-lifting integrated aircraft - Google Patents

Abstract

The utility model discloses an overpressure dish-shaped buoyancy-lifting integrated aircraft which comprises a boat body, a solar cell arranged on the surface of the boat body, a boat-on pushing unit is arranged on the side surface of the boat body, an equipment cabin arranged below the boat body and connected with the boat body and a cabin pushing unit arranged on the side surface of the equipment cabin. By utilization of the utility model, the problem of single buoyancy form of a conventional aircraft is solved, that is to say, floating force of an aerostat and buoyancy generated by dish-shaped configuration are combined and supplement each other, so that the aircraft is provided with a buoyancy-lifting integrated design, and the purposes that the aircraft can liftoff and finish flying in the air can be achieved.

Description

Superpressure dish buoyance lift one aircraft

Technical field

The utility model relates to the vehicle technology field, relates in particular to a kind of superpressure dish buoyance lift one aircraft that is applied to close to space vehicle.

Background technology

Aircraft is on the technological means that realizes flight at present, often take single form as main, be with wing and revolve the lift that oar produces and complete flight for it such as fixed wing aircraft, helicopter etc., the aerostatics such as dirigible are to complete flight by the buoyancy that the buoyance lift gas that fill inside produces for it, defective both is that all its lift form is single, in case its lift form lost efficacy the actv. remedial measures can't be provided, and then caused irretrievable loss.

Why prior art exists these defectives, mainly because this type of design can be satisfied the present normal operating needs of people substantially, such as aircraft is carried out flight at the height of 1 about myriametre usually, traditional airship flight is highly lower, all can realize by prior art.But for carrying out from now on the more close to space vehicle of high altitude, as 3 myriametre left and right flights highly, will there be many difficulties in prior art, only probe into up-to-date technology and just might realize, the design concept of the utility model superpressure dish buoyance lift one aircraft also just is being based on this.

The utility model content

The technical matters that (one) will solve

In view of this, main purpose of the present utility model is to provide a kind of superpressure dish buoyance lift one aircraft that is applied to close to space vehicle, to solve single this problem of conventional aircraft lift form.

(2) technical scheme

For achieving the above object, the utility model provides a kind of superpressure dish buoyance lift one aircraft, comprising: hull; Be arranged at the solar cell on hull surface; Be arranged at propulsion unit on the ship of hull side; Be arranged at the equipment compartment that is connected with hull below hull; And the equipment compartment propulsion unit that is arranged at the equipment compartment side.

In such scheme, described hull adopts the compound type configuration, and the first half is elliposoidal, and the latter half be dish, and between the first half and the latter half, employing integral forming process or seamless welding technique are connected.

In such scheme, described hull inside is provided with balloonet, and the balloonet volume reduces part and made up by the superpressure technology less than traditional dirigible balloonet volume.

In such scheme, by in described hull inside, a plurality of flexible barriers being set, auxiliary a series of load cables are realized the superpressure of this aircraft simultaneously.

In such scheme, described hull for this aircraft provides buoyancy, keeps the stagnant sky of this aircraft by the interior helium that fills.

In such scheme, described solar cell is arranged at the top surface of hull, and is connected with hull by bonding mode.

In such scheme, described solar cell is powered for this aircraft as the energy resource supply unit, and the electric energy that will produce daytime is divided into two parts, and a part is kept this aircraft and used daytime, another part is stored into the fuel cell that is installed in equipment compartment, for this aircraft night.

In such scheme, on described ship, propulsion unit is used for controlling driftage and auxiliary the advancing of aircraft, comprise the first screw propeller, the second screw propeller, triple helical oar and the quadruple screw propeller that are arranged at symmetrically the hull surrounding, and four hull propulsion electric machines and four hulls motor that verts, wherein, each screw propeller correspondence disposes a hull propulsion electric machine and hull motor that verts.

In such scheme, be connected with the rigidity mode of being connected by colligation between propulsion unit and hull on described ship.

In such scheme, various instrument and equipments are installed in described equipment compartment, comprise at least fuel cell, fly to control instrument and measurement and control instrument, be used for completing various operations and control to this aircraft.

In such scheme, described equipment compartment is connected with hull by hull equipment compartment attaching parts, this hull equipment compartment attaching parts is used for guaranteeing the stability of this aircraft integral body, comprise a rigid connector and a plurality of flexible connecting member, this rigid connector is arranged on central axis between equipment compartment and hull, and these a plurality of flexible connecting members are arranged at this rigid connector surrounding.

In such scheme, described equipment compartment propulsion unit is used for controlling pitching and auxiliary the advancing of aircraft, comprise the 5th screw propeller, the 6th screw propeller, the 7th screw propeller and the 8th screw propeller that are arranged at symmetrically the equipment compartment surrounding, and four hull propulsion electric machines and four hulls motor that verts, wherein, each screw propeller correspondence disposes a hull propulsion electric machine and hull motor that verts.

In such scheme, be connected with the rigidity mode of being connected by colligation between described equipment compartment propulsion unit and equipment compartment.

(3) beneficial effect

Can find out from technique scheme, the utlity model has following beneficial effect:

1, the superpressure dish buoyance lift one aircraft that provides of the utility model, design by the aircraft new formation has solved single this problem of conventional aircraft lift form, namely by the buoyancy of aerostatics self and the lift that dish shape configuration can produce, both are in conjunction with complementing one another, make the standby buoyance lift integral type design of flying instrument, and then reach the purpose that aircraft could go up to the air and complete stagnant empty flight.

2, the superpressure dish buoyance lift one aircraft that provides of the utility model, compare with the aerostatics of routine, the lift that its buoyance lift principle of work relies on buoyancy that helium provides and self configuration to provide simultaneously, alleviated so on the one hand the dependence of aircraft for buoyancy, also given full play on the other hand the characteristics of configuration self, this is that traditional design never possesses.

3, the superpressure dish buoyance lift one aircraft that provides of the utility model, the superpressure technology is applied in the design of balloonet, the ratio that makes balloonet account for entire system by the superpressure technology reduces to some extent, so just increased to a certain extent the ratio of main gasbag, and then increasing the effective lift of system, this is improving and replenishing prior art.

4, the superpressure dish buoyance lift one aircraft that provides of the utility model completing attitude and control by being arranged on propelling unit on hull and equipment compartment aspect control, has namely changed basic control mode and the control policy of system, is a kind of new trial.

Description of drawings

Fig. 1 is the control principle schematic diagram that advances that the utility model adopts.

Fig. 2 is the structural representation of the superpressure dish buoyance lift one aircraft that provides of the utility model.

Fig. 3 is the principle schematic of superpressure dish buoyance lift one aircraft aspect the energy that the utility model provides.

Description of reference numerals:

1 solar cell, 2 hulls, 3 first screw propellers, 4 second screw propellers, 5 triple helical oars, 6 rigid connectors, 7 flexible connecting members, 8 equipment compartments, 9 the 5th screw propellers, 10 the 6th screw propellers, 11 the 7th screw propellers, 3-1 the first hull propulsion electric machine, 3-2 the first hull motor that verts, 4-1 the second hull propulsion electric machine, 4-2 the second hull motor that verts, 5-1 the 3rd hull propulsion electric machine, 5-2 the 3rd hull motor that verts, 9-1 the 5th hull propulsion electric machine, 9-2 the 5th hull motor that verts, 10-1 the 6th hull propulsion electric machine, 10-2 the 6th hull motor that verts, 11-1 the 7th hull propulsion electric machine and 11-2 the 7th hull motor that verts.

The specific embodiment

For making the purpose of this utility model, technical scheme and advantage clearer, below in conjunction with specific embodiment, and with reference to accompanying drawing, the utility model is further described.

At first, superpressure technology and flight theory that the superpressure dish buoyance lift one aircraft that provides for the utility model relates to are described in detail.

1) superpressure technology

According to desirable shape body gas equation

$\mathrm{PV}=\mathrm{nRT}=\frac{m}{M}\mathrm{RT}---\left(1.1\right)$

Suppose that dirigible cumulative volume V on stagnant outage degree remains unchanged, pressure increases,

$\mathrm{\ΔP}\·V=\frac{\mathrm{\Δm}}{M}\mathrm{RT}---\left(1.2\right)$

Wherein, M is the molal weight of helium, and Δ m is the change amount of helium weight;

Because Δ m=Δ V is ρ _{He (0)}

Substitution following formula 1.2 can get:

$\mathrm{\ΔP}=\frac{\mathrm{RT}}{\mathrm{MV}}\mathrm{\ΔV}\·{\mathrm{\ρ}}_{\mathrm{He}\left(0\right)}---\left(1.3\right)$

Here order $R_{\mathrm{He}}=\frac{R}{M}$

In 1.3 formulas

Can be reduced to:

$\frac{\mathrm{RT}}{M}=R_{\mathrm{He}}\·T---\left(1.4\right)$

Again according to 1.1 formulas $\mathrm{PV}=\frac{m}{M}\mathrm{RT}$

Can get: $P=\frac{m}{V}\·\frac{R}{M}\·T=\mathrm{\ρ}\frac{R}{M}T$

Here M presses the molal weight calculating of air, can get: P wherein _aρ _aCorresponding sustained height;

Therefore in 1.3 formulas

Abbreviation is again:

$\frac{\mathrm{RT}}{M}=R_{\mathrm{He}}\·T=R_{\mathrm{He}}\·\frac{P_a}{R_a{\mathrm{\ρ}}_a}\frac{P_a}{{\mathrm{\ρ}}_a}\·\frac{R_{\mathrm{He}}}{R_a}$ (1.5)

$=\frac{P_a}{{\mathrm{\ρ}}_a}\·\frac{{\mathrm{\ρ}}_{a0}}{{\mathrm{\ρ}}_{\mathrm{He}0}}$

After following formula 1.5 substitution 1.3 formulas, can get:

$\mathrm{\ΔP}=\frac{\mathrm{RT}}{\mathrm{MV}}\mathrm{\ΔV}\·{\mathrm{\ρ}}_{\mathrm{He}0}=\frac{\mathrm{\ΔV}}{V}\·\frac{\mathrm{RT}}{M}\·{\mathrm{\ρ}}_{\mathrm{He}0}$ (1.6)

$=\frac{\mathrm{\ΔV}}{V}\·\frac{{\mathrm{\ρ}}_{a\left(0\right)}}{{\mathrm{\ρ}}_{a\left(h\right)}}{P}_a$

Order $\mathrm{\δ}=\frac{{\mathrm{\ρ}}_{\mathrm{He}\left(h\right)}}{{\mathrm{\ρ}}_{\mathrm{He}\left(0\right)}}$

, substitution 1.6 formulas can get:

$\mathrm{\ΔP}=\frac{\mathrm{\ΔV}}{V}\·\frac{P_a}{\mathrm{\δ}}---\left(1.7\right)$

So, can get according to following formula 1.7:

$\frac{\mathrm{\ΔV}}{V}=\mathrm{\δ}\·\frac{\mathrm{\ΔP}}{P_a}---\left(1.8\right)$

Again because $\mathrm{\δ}=\frac{{\mathrm{\ρ}}_{\mathrm{He}\left(h\right)}}{{\mathrm{\ρ}}_{\mathrm{He}\left(0\right)}}=\frac{{\mathrm{\ρ}}_{a\left(h\right)}}{{\mathrm{\ρ}}_{a\left(0\right)}}$

So formula 1.8 can be changed into:

$\frac{\mathrm{\ΔV}}{V}=\frac{{\mathrm{\ρ}}_{a\left(h\right)}}{{\mathrm{\ρ}}_{a\left(0\right)}}\·\frac{\mathrm{\ΔP}}{P_a}---\left(1.9\right)$

Wherein, P _aIt is the atmospheric value on the h height

Following formula 1.9 reflects is exactly the superpressure amount that can bear on the aircraft ceiling and the corresponding relation of balloonet ratio.By this corresponding relation, can allow aircraft come corresponding reduction to the requirement of balloonet by bearing different superpressure amounts.

2) flight theory

A rises

Because aircraft is about vertical axisymmetric swivel, therefore can use for reference the releasing mode of aerostat.After the constraint of delivery system releasing to hull, aircraft goes up to the air under quiet buoyancy.Can make aircraft pass through the strong wind torrent district on top, convective zone with certain speed by the size of controlling buoyancy.

Because hull configuration characteristics cause the centre of buoyancy above center of gravity, the similar single pendulum Systems balanth of stability of aircraft, robustness is stronger, and under the wind disturbance condition, attitude of flight vehicle still can be stablized, and does not need ACTIVE CONTROL.

B is flat to fly

After arriving the ceiling, hull buoyancy and deadweight balance each other, aircraft is stabilized near the ceiling after the cycle is drifted along fluctuation gradually around the ceiling, aircraft enters and cruises or other controlled flight conditions, can control by the working in coordination of quadruplet vector propelling control device that is arranged on hull the movement that aircraft is made any direction, and it is stable to go as course, and pitch attitude stability is by certainly steady by system's barycenter countermoment.

Control program is controlled to be example to advance, and as shown in Figure 1, brief description is as follows:

The first propelling unit A1, the second propelling unit A2 produces thrust forward, is responsible for propelling;

Triple screw B1, the 4th propelling unit B2 produce the driftage controlling couple course disturbance are compensated, and are responsible for coursekeeping.

The mobile of other any directions controlled similarly.In addition, the quadruplet propelling unit that is arranged on the lower part equipment cabin can be assisted on the basis of above-mentioned quadruplet propelling unit work.

The C landing

During the aircraft landing, discharge a small amount of helium, aircraft is landed under the net weight effect, sinking speed is controlled by free air capacity.

Keep the principle of stability identical with the uphill process hull, aircraft is with the decline that holds position, and this process does not need attitude to control equally.

The D anchoring

When aircraft descends approaching anchoring place, depending on the distance of landing between point and anchoring point, start propulsion system, make aircraft near anchoring point, during near ground, draw aircraft by surface facility and enter anchored condition.

Based on above-mentioned superpressure technology and flight theory, Fig. 2 shows the structural representation of the superpressure dish buoyance lift one aircraft that the utility model provides, and this superpressure dish buoyance lift one aircraft comprises: hull 2; Be arranged at the solar cell 1 on hull surface; Be arranged at propulsion unit on the ship of hull side; Be arranged at the equipment compartment 8 that is connected with hull below hull; And the equipment compartment propulsion unit that is arranged at the equipment compartment side.

Wherein, hull 2 adopts the compound type configurations, and the first half is elliposoidal, and the latter half be dish, and between the first half and the latter half, employing integral forming process or seamless welding technique are connected.Aspect configuration, the hull of the superpressure disc-shaped flying craft that the utility model provides adopts the compound type configuration, compare with the linear hull of conventional flow, this profile has peculiar advantage, such as simple in structure, stable, larger than buoyancy, the hull skin stress is evenly distributed etc., the more important thing is that it has expected realizability.

Hull 2 inside are provided with balloonet, and the balloonet volume reduces part and made up by the superpressure technology less than traditional dirigible balloonet volume.The superpressure of this aircraft is by in described hull inside, a plurality of flexible barriers being set, auxiliary a series of load cables are realized simultaneously, namely on the one hand the some flexible barriers by being welded on hull inside (this flexible barrier is a kind of soft diaphragm, its material and hull materials similar), (this bracing cable is a kind of stay cord in some bracing cables by being bonded in the hull outside face on the other hand, material adopts Kafra fiber), be distributed in flexible barrier and bracing cable by the interior pressure of these two kinds of forms with hull, hull itself just can bear superpressure like this.

Described hull 2 for this aircraft provides buoyancy, keeps the stagnant sky of this aircraft by the interior helium that fills.

Energy aspect, as shown in Figure 3, aircraft adopts the integrated mode of solar cell and fuel cell for guaranteeing long-time stagnant sky.Solar cell can adopt flexible thin-film solar cell, and it is arranged at the top surface of hull, for example flexible thin-film solar cell is layed in the top surface of hull, and this solar cell is connected with hull by bonding mode.Solar cell is in order to convert solar energy into electrical energy, power for this aircraft as the energy resource supply unit, the electric energy that will produce daytime is divided into two parts, a part is kept this aircraft and is used daytime, another part is stored into the fuel cell that is installed in equipment compartment, for this aircraft night.

Fig. 3 describes the energy resource supply mode of superpressure dish buoyance lift one aircraft in detail, and namely the energy mainly is comprised of two parts, is respectively solar cell and hydrogen-oxygen fuel cell.Solar cell absorbs sunshine by day the time and is translated into electric energy, and a part is directly supplied with to propelling, equipment and load use by energy output unit and converting unit; Another part deposits in hydrogen-oxygen fuel cell, and hydrogen-oxygen fuel cell is converted to electric energy by chemical actions such as Xie Shui with chemical power and offers propelling, equipment and load use when do not have solar irradiation night.Solar cell and hydrogen-oxygen fuel cell just can form a circulation like this, around-the-clock aircraft power supply, warranty time Power supply.

Various instrument and equipments are installed in equipment compartment 8, comprise at least fuel cell, fly to control instrument and measurement and control instrument, be used for completing various operations and control to this aircraft.Equipment compartment 8 is connected with hull 2 by hull equipment compartment attaching parts, this hull equipment compartment attaching parts is used for guaranteeing the stability of this aircraft integral body, comprise a rigid connector 6 and a plurality of flexible connecting member 7, this rigid connector 6 is arranged on central axis between equipment compartment and hull, and these a plurality of flexible connecting members 7 are arranged at this rigid connector surrounding.Rigid connector 6 adopts titanium alloy material to make, and flexible connecting member 7 adopts Kafra fiber to make.

The control aspect, this aircraft no longer adopts the mode of traditional propelling+rudder face, but choice for use all relies on propelling, adopts special mode and strategy to complete aircraft and rises, flatly flies, lands and the control of the stages that anchors.conventional aircraft generally provides onward impulse by propelling unit, control pitching by tailplane, control driftage by vertical tail, and superpressure dish buoyance lift one aircraft no longer needs tailplane and vertical tail to control pitching and driftage, but rely on propelling unit (i.e. vert motor and the propulsion electric machine of configuration corresponding to each screw propeller) vert replace, such as the conventional aircraft tailplane to left avertence, aircraft is left-handed turning thereupon, and for superpressure dish buoyance lift one aircraft, the action here is that two propelling units on same straight line vert to both sides respectively, produce making a concerted effort left, make buoyance lift one aircraft left-handed turning, that is to say that angle of rake verting substituted the effect of empennage fully.

Specifically, this aircraft is adopting propulsion unit and equipment compartment propulsion unit on ship aspect control.Wherein, on ship, propulsion unit is used for controlling driftage and auxiliary the advancing of aircraft, comprise the first screw propeller 3, the second screw propeller 4, triple helical oar 5 and the quadruple screw propeller (not showing in Fig. 2) that are arranged at symmetrically the hull surrounding, and four hull propulsion electric machines and four hulls motor that verts, wherein, each screw propeller correspondence disposes a hull propulsion electric machine and hull motor that verts.Be connected with the rigidity mode of being connected by colligation between propulsion unit and hull on ship.The equipment compartment propulsion unit is used for controlling pitching and auxiliary the advancing of aircraft, comprise the 5th screw propeller 9, the 6th screw propeller 10, the 7th screw propeller 11 and the 8th screw propeller (not showing in Fig. 2) that are arranged at symmetrically the equipment compartment surrounding, and four hull propulsion electric machines and four hulls motor that verts, wherein, each screw propeller correspondence disposes a hull propulsion electric machine and hull motor that verts.Be connected with the rigidity mode of being connected by colligation between equipment compartment propulsion unit and equipment compartment.

In the structural representation of superpressure dish buoyance lift one aircraft shown in Figure 2, only show the first screw propeller 3, the second screw propeller 4 and triple helical oar 5, the quadruple screw propellers and be positioned at a hull side relative with the second screw propeller 4, do not show in Fig. 2.Simultaneously, in the structural representation of superpressure dish buoyance lift one aircraft shown in Figure 2, only show the 5th screw propeller 9, the 6th screw propeller 10 and the 7th screw propeller 11, the eight screw propellers and be positioned at an equipment compartment side relative with the 6th screw propeller 10, also do not show in Fig. 2.

in addition, also show in Fig. 2 and the first screw propeller 3, the second screw propeller 4, triple helical oar 5, the 5th screw propeller 9, the hull propulsion electric machine of the 6th screw propeller 10 and the corresponding configuration of the 7th screw propeller 11 and the hull motor that verts, that is: with the first hull propulsion electric machine 3-1 of the first corresponding configuration of screw propeller 3 and the first hull motor 3-2 that verts, with the second hull propulsion electric machine 4-1 of the second corresponding configuration of screw propeller 4 and the second hull motor 4-2 that verts, the 3rd hull propulsion electric machine 5-1 of configuration corresponding to triple helical oar 5 and the 3rd hull motor 5-2 that verts, with the 5th hull propulsion electric machine 9-1 of the 5th corresponding configuration of screw propeller 9 and the 5th hull motor 9-2 that verts, with the 6th hull propulsion electric machine 10-1 of the 6th corresponding configuration of screw propeller 10 and the 6th hull motor 10-2 that verts, and with the 7th hull propulsion electric machine 11-1 of the 7th corresponding configuration of screw propeller 11 and the 7th hull motor 11-2 that verts.Be positioned at a hull side relative with the second screw propeller 4 with the 4th hull propulsion electric machine of the corresponding configuration of quadruple screw propeller and the 4th hull motor that verts, do not show in Fig. 2, be positioned at an equipment compartment side relative with the 6th screw propeller 10 with the 8th hull propulsion electric machine of the 8th corresponding configuration of screw propeller and the 8th hull motor that verts, also do not show in Fig. 2.

On ship, propulsion unit and equipment compartment propulsion unit are the actuating units of controlling this aircraft, and the propulsive force by its generation guarantees the aircraft lifting, advances, turns and anchor.The quadruplet propelling unit is arranged on hull, be mainly used in controlling of aircraft, only depend on this quadruplet can realize the control of aircraft fully.The quadruplet aircraft is also arranged on equipment compartment, but function is that effect is that extra power is provided for the controlling of assisting in flying device when the hull under power.

The superpressure dish buoyance lift one aircraft that the utility model provides is as the aircraft that is lighter than air, it is mainly the relevant design that requirement is carried out for close to space vehicle, its buoyance lift principle of work mainly relies on helium to complete lift-off, be different from the traditional design part and be that it is auxiliary with self lift, the lift that namely produces by dish shape configuration itself coordinates buoyancy to complete lift-off.

In addition, on the function of balloonet, traditional lighter-than-air flight device operates to complete control and the maintenance of height fully by the inflation/deflation to balloonet, the difference to some extent of balloonet of superpressure dish buoyance lift one aircraft of the present utility model, it weakens on the function of highly controlling and keeping to some extent, weakens part and being made up by the superpressure technology, can reduce the balloonet ratio like this, corresponding increase main gasbag ratio, thus the effective lift of system increased.

In addition, aspect control, it completes attitude control by the propelling unit that is arranged on hull and equipment compartment, that is to say, whole system has changed basic control mode, substitutes rudder face by angle of rake configuration and control.

Above-described specific embodiment; the purpose of this utility model, technical scheme and beneficial effect are further described; institute is understood that; the above is only specific embodiment of the utility model; be not limited to the utility model; all within spirit of the present utility model and principle, any modification of making, be equal to replacement, improvement etc., within all should being included in protection domain of the present utility model.

Claims (13)

1. a superpressure dish buoyance lift one aircraft, is characterized in that, comprising:

Hull;

Be arranged at the solar cell on hull surface;

Be arranged at propulsion unit on the ship of hull side;

Be arranged at the equipment compartment that is connected with hull below hull; And

Be arranged at the equipment compartment propulsion unit of equipment compartment side.

2. superpressure according to claim 1 dish buoyance lift one aircraft, it is characterized in that, described hull adopts the compound type configuration, and the first half is elliposoidal, the latter half is dish, adopts integral forming process or seamless welding technique to be connected between the first half and the latter half.

3. superpressure according to claim 1 dish buoyance lift one aircraft, is characterized in that, described hull inside is provided with balloonet, and the balloonet volume reduces part and made up by the superpressure technology less than traditional dirigible balloonet volume.

4. superpressure according to claim 1 dish buoyance lift one aircraft, is characterized in that, by in described hull inside, a plurality of flexible barriers being set, auxiliary a series of load cables are realized the superpressure of this aircraft simultaneously.

5. superpressure dish buoyance lift one aircraft according to claim 1, is characterized in that, described hull for this aircraft provides buoyancy, keeps the stagnant sky of this aircraft by the interior helium that fills.

6. superpressure dish buoyance lift one aircraft according to claim 1, is characterized in that, described solar cell is arranged at the top surface of hull, and is connected with hull by bonding mode.

7. superpressure according to claim 1 dish buoyance lift one aircraft, it is characterized in that, described solar cell is powered for this aircraft as the energy resource supply unit, the electric energy that will produce daytime is divided into two parts, a part is kept this aircraft and is used daytime, another part is stored into the fuel cell that is installed in equipment compartment, for this aircraft night.

8. superpressure according to claim 1 dish buoyance lift one aircraft, it is characterized in that, on described ship, propulsion unit is used for controlling driftage and auxiliary the advancing of aircraft, comprise the first screw propeller, the second screw propeller, triple helical oar and the quadruple screw propeller that are arranged at symmetrically the hull surrounding, and four hull propulsion electric machines and four hulls motor that verts, wherein, each screw propeller correspondence disposes a hull propulsion electric machine and hull motor that verts.

9. superpressure according to claim 1 dish buoyance lift one aircraft, is characterized in that, is connected with the rigidity mode of being connected by colligation between propulsion unit and hull on described ship.

10. superpressure according to claim 1 dish buoyance lift one aircraft, it is characterized in that, various instrument and equipments are installed in described equipment compartment, comprise at least fuel cell, fly to control instrument and measurement and control instrument, be used for completing various operations and control to this aircraft.

11. superpressure dish buoyance lift one aircraft according to claim 1, it is characterized in that, described equipment compartment is connected with hull by hull equipment compartment attaching parts, this hull equipment compartment attaching parts is used for guaranteeing the stability of this aircraft integral body, comprise a rigid connector and a plurality of flexible connecting member, this rigid connector is arranged on central axis between equipment compartment and hull, and these a plurality of flexible connecting members are arranged at this rigid connector surrounding.

12. superpressure dish buoyance lift one aircraft according to claim 1, it is characterized in that, described equipment compartment propulsion unit is used for controlling pitching and auxiliary the advancing of aircraft, comprise the 5th screw propeller, the 6th screw propeller, the 7th screw propeller and the 8th screw propeller that are arranged at symmetrically the equipment compartment surrounding, and four hull propulsion electric machines and four hulls motor that verts, wherein, each screw propeller correspondence disposes a hull propulsion electric machine and hull motor that verts.

13. superpressure according to claim 1 dish buoyance lift one aircraft is characterized in that, is connected with the rigidity mode of being connected by colligation between described equipment compartment propulsion unit and equipment compartment.

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