CN106347620A - Vacuum type buoyancy flight device based on structural mechanical design - Google Patents
Vacuum type buoyancy flight device based on structural mechanical design Download PDFInfo
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- CN106347620A CN106347620A CN201610889478.3A CN201610889478A CN106347620A CN 106347620 A CN106347620 A CN 106347620A CN 201610889478 A CN201610889478 A CN 201610889478A CN 106347620 A CN106347620 A CN 106347620A
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- vacuum
- rod member
- eyelid covering
- truss
- flight instruments
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64B—LIGHTER-THAN AIR AIRCRAFT
- B64B1/00—Lighter-than-air aircraft
- B64B1/06—Rigid airships; Semi-rigid airships
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64B—LIGHTER-THAN AIR AIRCRAFT
- B64B1/00—Lighter-than-air aircraft
- B64B1/06—Rigid airships; Semi-rigid airships
- B64B1/08—Framework construction
Abstract
Although a vacuum airship concept is already proposed for more than three centuries, vacuum airships which can be actually applied still cannot be manufactured in the field of material of human up to now. The main cause is that human cannot manufacture a light rigid material lighter than air and capable of resisting atmosphere of about 10 tons per square meter at present. A feasible vacuum type buoyancy flight device is designed by using finite element analysis software by referencing structural mechanical design, grid structure design and other mechanical designs and utilizing light weight and pressure resistance characteristics of inflation tube structures.
Description
Technical field
The invention belongs to field of aerospace technology and in particular to one kind with hydrodynamics, pneumatics, the mechanics of materials,
Structural mechanics are to instruct, the novel evacuated formula buoyancy flight instruments designed based on high-performance novel material.
Background technology
Vacuum airship (vacuum airship) is that one kind replaces hydrogen tank with Dewar vessel or helium container to provide
Dirigible in the imagination of lift.So-called " vacuum ", refers in given space, and pressure is less than 101325 Pascals (i.e.
Standard atmospheric pressure about 101kpa) gaseous state.This conception is existed by Italian francesco lana de terzi earliest
Propose within 1670, vacuum sphere is the ultimate implementation method of buoyant lift.Because 1 n/ square metre of normal atmosphere=101325.?
If that is building a vacuum airship, then every square meter will at normal atmospheric pressure for the buoyant device (vacuum chamber) of dirigible
By 10 tons about of atmospheric pressure.Although material science constantly develops in recent years, business-like, Neng Gouzhi does not also occur so far
The material of support 10 ton/square metre lightweight rigid structures.New material even with the not yet volume production such as Graphene is manufactured into reluctantly
Work(, the economic benefit that can be generated by also is far below the cost manufacturing it and being spent.Therefore, although the vision of vacuum airship is very beautiful
Good, but be all " impossible " to the primary impression of vacuum airship in the brains of most people！
List of references:
[1] Guo Peng, long-acting vacuum chamber satellite: China, patent of invention cn201510817860.9. [p]
[2] Guo Peng, intelligent cell type inflates rigid structure: China, patent of invention cn201610886675.x. [p]
[3] Weng Zhiyuan, Wang Yuangong. elastic thin shell is theoretical. Higher Education Publishing House, 1986. [m]
[4] (English) g.a. Cooley, j.d. is lucky to strangle spy. airship technology. Science Press 2008. [m]
[5] Du Zhenyong, the load-bearing capacity analysis of inflation tubular construction. master thesis. Harbin: Harbin Institute of Technology,
2008.[d]
[6] Feng Bailu, single-layer lattice shell lighting roof configuration and stress and strain model optimizing research. master thesis. China builds
Build research institute, 2015. [d]
[7] Yang Lianping, Wei Shen, Zhang Qilin. aluminium alloy space network present Research and key issue. building journal volume 34
2nd 2013 2 months phase feb.2013 vo1.34 no.2.[j]
[8] Ni Lijun, " ephemeralization " Eco-Design thought and applied research. master thesis. Shanghai Communications University, 2010
2 months [d] of year
[9] Xie Yaqi, the design of planar flexible deployable structure and expansion research. master thesis. Zhejiang University, 2013. [d]
[10] Zhang Lei, flexible membrane bar strengthens the load performance study of eyelid covering. master thesis. Harbin Institute of Technology, and 2013
[d]
[11] Wang Yiran, tether strengthens the analysis of inflatable structure load-carrying properties. master thesis. Harbin Institute of Technology, and 2013
[d]
[12] in peaceful, the load-bearing capacity analysis of inflation ring structure. master thesis. Harbin Institute of Technology, 2009 [d]
[13] Wei Jianzheng, space folding film tube inflating expanded process gas-solid coupled problem is studied. Ph.D. Dissertation. Harbin
Polytechnical university, 2008 [d]
[14] Wei Jianzheng, Mao Lina, Du Xingwen, spatial crimp folded tube ventilating control launches dynamics research. engineering mechanics,
2009, 26(1):227-232[j].
Note: document [2] belongs to me and applied for undisclosed patent of invention, and its main contents is using Multicarity airbag structure
By more excellent mechanical property is obtained to the gas being filled with different pressure in different cavity body.Many gas in inflatable deployment structure
The mechanical characteristics that the intelligent cell type of capsule structure composition inflates rigid body are more more outstanding than traditional single-chamber body airbag structure, contribute to
The present invention is implemented.
Content of the invention
The invention discloses a kind of vacuum type buoyancy flight instruments based on structural mechanics and new material design.Specifically
Say that the present invention is with hydrodynamics, pneumatics, the mechanics of materials, structural mechanics for instructing, based on high-performance novel material
The novel evacuated formula buoyancy flight instruments designed.
Initially, I also thinks that this idea is very laughable when seeing " vacuum airship " this concept on network.Because 1
N/ square metre of normal atmosphere=101325.If that is building a vacuum airship, then the buoyant device of dirigible is (true
Empty cabin) every square meter will be by 10 tons about of atmospheric pressure at normal atmospheric pressure.Although polymer composite is strong in tension
Degree aspect has been able to meet and requires, but the air bag of the vacuum chamber of vacuum airship and conventional balloon formula dirigible has the difference of internal
Different.Conventional balloon formula dirigible typically adopts flexible air-bag, and its major function is opposing inside air bag gas pressure, and prevents lightweight
Gas escape.And vacuum chamber then needs a rigid structure to prop up to overhang a space, will interior volume gas extract out after using just
Body structure stiffness by itself resists atmospheric pressure.If according to buoyancy formula it can be calculated that vacuum type buoyancy flight instruments gross mass
Arrange gas gross mass less than it, then this vacuum type buoyancy flight instruments is obtained in that buoyancy and floats in an atmosphere.
Assume to manufacture the rigid structure of this vacuum chamber with carbon fibre composite (cfrp), for meeting it in standard atmosphere
Depressing indeformable requirement certainly will be using thick and heavy multilayer package structure.And multilayer package structure not only causes deadweight to increase,
Construction cost is lifted, and the problems such as reliability reduces, and its carrying capacity also can be greatly reduced.In essence, unless material
Leapfrog development in science, and otherwise vacuum airship is good for nothing.
Last year, I has done a feasibility study to vacuum airship.Research has been found that to be wanted with existing lightweight rigid body material
Material supports vacuum airship, unless the 1/10 of earth atmosphere pressure drop as little as previous level.For this, I devises that " long-acting vacuum chamber is defended
Star " [list of references 1], and constantly improve vacuum airship related data and reliability based on this.
Study through long-time, using the calculating of structural mechanics, finite element analyses and new material parameter, I have found one
Plant and bypass this difficult point of lightweight rigid structure, the method that vacuum chamber used by vacuum airship is manufactured with current current material.
The maximum difficult point that vacuum airship manufactures and designs is that the light vacuum cabin of standard atmosphere pressure manufactures.Light vacuum cabin
Net weight have to be lower than vacuum chamber and creates the buoyancy of vacuum environment generation that is to say, that vacuum chamber must lta from weight-average value.
Meanwhile, although traditional lightweight air dirigible airship has various deficiencies, he still belongs to a kind of matured product.Therefore, vacuum airship
Cost can not be too many beyond traditional lightweight air dirigible airship.
On the premise of meeting above-mentioned condition, I devises this flight dress of the vacuum type buoyancy based on structural mechanics
Put.
As it was noted above, the maximum problem of vacuum type buoyancy flight instruments has two.One is to need the firm of sufficient intensity
The atmospheric pressure of 10 tons about of the every square meter of body structure opposing, another is that vacuum chamber dead weight not can exceed that vacuum chamber can be generated by
Buoyancy.
At normal atmospheric pressure, air weighs about 1.293kg/ cubic meter.That is vacuum chamber includes rigid structure and takes
With thing gross weight averagely arrive vacuum chamber arrange air volume when every cubic metre average weight must lta, otherwise vacuum chamber
Cannot float.
Above-mentioned condition leads to, and rigid structure is unlikely to be current business-like any body material.Although carbon fiber
Tube material is lighter, but conducts oneself with dignity after being cured as supporting construction and be still much larger than air.Except legendary Graphene, I does not find
Any can disclosure satisfy that the rigid body manufacture requirements of vacuum airship by direct applied body material.Certainly, Graphene distance enters
The Commercialization application stage has got long long way to go, and does not consider for the time being here.
When reading document [list of references 4], lightweight pressurization tubular construction brings inspiration for me.(lightweight compression tube is also referred to as
Gas tube, film tube, space pipe, inflation beam, air-supported membrane structure, inflatable deployment structure etc.).
Vacuum chamber is exactly substantially to resist external pressure using rigid structure.As long as that is rigid structure produces
Stress is maintained an equal level with external atmospheric pressure, just can maintain vacuum chamber self space not by atmospheric compressed deformation.If added using lightweight
Pressure pipe structure is it is possible to realize resisting the mechanics effect of atmospheric pressure with atmospheric pressure.
Current composite development is extremely swift and violent, and structural strength creates peak repeatly.Taking pbo material as a example, its tensile strength >=
5.8gpa, modulus 280gpa, heat resisting temperature reaches 600 DEG C, and his density only has 1.56g/ cubic centimetre.
Note: 1 normal atmosphere=9.8mpa, 1gpa=1000mpa.
Manufacture vacuum equipment material requested and be in fact not as in the most people imagination so difficulty.1 normal atmosphere is substantially
Be equivalent to the pressure of 10 tons of every square meter, sound a very big numeral, but careful calculate after can find that what is not in fact
The problem that can not possibly solve., the material that it adopts is poly terephthalic acid second two taking common Coke bottle in daily life as a example
Alcohol ester.One qualified Coke bottle can bear 10 normal atmospheres that is to say, that our Coke bottle materials of all seeing daily
The every square meter of matter can bear 100 tons of pressure.And the various composite compressive resistances of being capable of industrialized production now are far super poly-
Ethylene glycol terephthalate, therefore commercialization manufacture vacuum airship problem of materials to material science and technology of today be no longer
Bottleneck.
Lightweight compression tube is prepared using polymer composite, its intensity can meet vacuum chamber rigid structure intensity completely
Demand.In finite element modelling experiment, only needing to 3 normal atmospheres inside lightweight compression tube, can to resist extraneous standard big
Pressure produced by air pressure.As shown in figure 1, vacuum type buoyancy flight instruments vacuum chamber structural representation.
If using simple lightweight pressurization tubular construction in order to resist external atmosphere pressure, the deadweight after the inflation of lightweight compression tube
It is possible to maintain an equal level with external atmosphere pressure.Therefore simple lightweight pressurization tubular construction can not bring too big buoyancy for vacuum chamber.With
When, lightweight compression tube is once occur leakage to be likely to cause devastating consequence to vacuum type buoyancy flight instruments.Therefore, I sets
Count [list of references 2] intellectuality cell type inflation rigid structure.
Traditional single-chamber gas tube is replaced with intelligent cell type inflation rigid structure, is obtained in that more preferably mechanical property
Energy.Meanwhile, if the safety of vacuum type buoyancy flight instruments can be lifted further using multi-cavity structure.As shown in figure 1,
Inflate the vacuum chamber support system of rigid structure composition using intelligent cell type.(inflatable structure described in literary composition all can be using biography
System inflatable structure or intelligent cell type inflation rigid structure or both combinations, do not affect present invention power from different modes
Belong to).
Inflatable structure as described in document [5], the axial compression buckling load of especially inflation tubular construction can pass through finite element
Calculate gas tube axially compressive strength.It is computed, gas tube axially compressive strength is more than radial direction compressive resistance and shearing
Intensity.Meanwhile, ambient air is more than to the pressure producing on eyelid covering with the spatial mesh structure intensity that inflatable structure is made for rod member
By force.If substituted into after intelligent cell type inflates rigid structure data additionally it is possible to improve the structural strength of space lattice further.
And the deadweight of this spatial mesh structure is far below traditional rigid structure.
If summary situation is filled it can be calculated that being manufactured with inflatable structure (intelligent cell type inflation rigid structure)
Gas formula spatial mesh structure truss, and with this inflation truss support stressed-skin construction, you can obtain a light overpressure resistant vacuum chamber.
The light overpressure resistant vacuum chamber manufacturing in this way have from heavy and light, can resist outside the feature such as suppress, be to manufacture vacuum type to float
The ideal material of power flight instruments.
Vacuum type buoyancy flight instruments is mainly by vacuum chamber 1, energy resource system 2, dynamical system 3, load system 4, monitoring system
System 5, control system 6, communication system 7, automatic repair system 8 form.Wherein vacuum chamber is mainly by eyelid covering 9, truss 10, vacuum pump
11 compositions.Truss 10 is main to be made up of rod member 12, inflation rod member 13, drawstring 14.
Vacuum chamber 1 is the core of vacuum type buoyancy flight instruments, and it is mainly characterized by using eyelid covering 9, truss 10, vacuum pump
11 one lightweight rigid space structure of composition.Vacuum type buoyancy is made to fly after extracting the gas in vacuum chamber 1 out using vacuum pump 11
Deadweight lta put by luggage, then obtains buoyancy in atmospheric environment.Can have in vacuum type buoyancy flight instruments one or
More than one vacuum chamber 1.
Energy resource system 2 is the energy resource system assembly of vacuum type buoyancy flight instruments.Including energy supply system, the energy
Stocking system and energy consumption system three part.Energy supply system includes solar battery group, wind power generating set, internal combustion engine
Generating set, fuel cell unit, nuclear power generation unit etc. can provide the device of energy supply.Energy storage system includes electricity
The energy storage devices such as pond group, accumulator battery, energy accumulation device for fly wheel, compression air energy-storing apparatus.Energy consumption system is floated for vacuum type
All energy consumption system assemblies needed for power flight instruments.Either the energy resource consumption of the various equipment of flight instruments itself is still
The energy resource consumption of other equipments of load all belongs to energy consumption system.
Dynamical system 3 is the dynamical system assembly that vacuum type buoyancy flight instruments moves in an atmosphere.Vacuum type buoyancy flies
Luggage is put to be needed to carry out to advance in flight course, the action such as retreat, rise, declining, turning to is required to dynamical system and is driven
Dynamic.In order to obtain preferable driving force, can be using the electromotor of the electromotor of propeller driving or injection engine driving.Send out
Motivation can be fixing or rotated freely by cardan shaft driving.Vacuum type buoyancy flight instruments substantially situation with
Traditional dirigible is suitable.Therefore, dynamical system 3 can directly quote the dynamical system design of conventional aircraft.
Load system 4 is the load system assembly including gondola.The essence of vacuum type buoyancy flight instruments is to utilize
The buoyancy of vacuum chamber 1 carries weight floating, and its basic load mode is structure for pod.Gondola is connected with vacuum chamber, in gondola
Interior place load or directly load is fixed on inside and outside vacuum chamber, or truss structure is connected with vacuum chamber 1, after will load
It is fixed on truss structure.Vacuum type buoyancy flight instruments substantially situation is suitable with traditional dirigible.Therefore, load system 4 is permissible
Load system with reference to traditional floating type aircraft.
Monitoring system 5 is the general designation of various monitoring devices on vacuum type buoyancy flight instruments.Monitoring system 5 can be by optics
Multiple detecting devices such as detector, pressure detector, hygrosensor, ultrasonic detector, electromagnetic wave detector, electronic compass
Composition, whether its major function is healthy for monitoring each system of whole vacuum type buoyancy flight instruments at any time, and will monitor number
It is analyzed according to being real-time transmitted to control system 6.It is internal and outer that monitoring system 5 can monitor vacuum type buoyancy flight instruments simultaneously
All information in portion.
Control system 6 is a kind of intelligent control system, is the control axis of vacuum type buoyancy flight instruments.Control system
6 utilize computer or manual type to the vacuum chamber 1 of vacuum type buoyancy flight instruments, energy resource system 2, dynamical system 3, load
Its in system 4, monitoring system 5, communication system 7, automatic repair system 8, vacuum pump 11 or vacuum type buoyancy flight instruments
He is controlled equipment.
Communication system 7 is the communication backbone of vacuum type buoyancy flight instruments.The communication of vacuum type buoyancy flight instruments is divided into
Intercommunication and PERCOM peripheral communication.Wherein intercommunication is mainly vacuum chamber 1, energy resource system 2, dynamical system 3, load system 4, prison
Communication between examining system 5, control system 6, communication system 7, automatic repair system 8, vacuum pump 11 and vacuum type buoyancy fly
Communication of entrained occupant etc. put by luggage.Depending on correspondence with foreign country is then according to vacuum type buoyancy flight instruments specific works situation.Logical
The communication network of letter system composition can be wire communication or radio communication.
Automatically repair system 8 is the dress that using automation equipment, vacuum type buoyancy flight instruments simply can be repaired
Put.In the present invention, the groundwork mode of automatic repair system 8 is can be moved freely in gas pipeline using robot
Characteristic, when monitoring system 5 unusual circumstance, to control automatic repair system 8 to go to using communication system 7 different for control system 6
Reason condition location, is processed according to practical situation.Automatically repair system 8 teleoperator process abnormal conditions can be by counting
Calculation machine automatically controls and completes it is also possible to be completed by manually carrying out hand control.Automatically repair system 8 sharpest edges are to run
If it find that air bag local leakage can go to location of leak to carry out eyelid covering repairing by robot in journey.
Eyelid covering 9 can be single thin film structure it is also possible to the composite construction that is made up of several air bags.As [list of references
2] described, the inflated type rigid structure of many airbag structure compositions can assume specific mechanics effect.By several airbag structures
Atmospheric pressure dispersion outside eyelid covering can be turned to and cancel out each other using domes with type arched structure by the eyelid covering 9 of composition,
So that eyelid covering 9 can resist external atmosphere pressure.In order to obtain enough rigidity, truss can be disposed in air bag, also can be in gas
Truss is disposed outside capsule.Supplement air bag stress intensity itself using truss, disclosure satisfy that vacuum chamber 1 resists the requirement of external atmosphere pressure
(Fig. 2, Fig. 3, Fig. 4, Fig. 5).
Truss 10 is main to be made up of rod member 12, inflation rod member 13, drawstring 14.In the present invention, the Main Function of truss 10
It is the mechanical support that sufficient intensity is provided for eyelid covering 9.In order to resist external atmosphere pressure, lightweight is formed by eyelid covering 9 and truss 10 firm
Body case.Truss 10 may be mounted at eyelid covering 9 inside it is also possible to be arranged on outside eyelid covering 9.Using rod member 12, inflation rod member 13,
The stereochemical structure of drawstring 14 composition has preferable mechanical property and relatively light quality, is the ideal complement of eyelid covering 9.In order to
Reduce the weight of truss 10 as far as possible, can be using the three-dimensional sphere truss of network composition.For example with " fowler spherical structure "
The truss of composition is exactly a kind of ideal lattice supporting framework.[list of references 6,7,8] in the present invention, truss structure can
To adopt spherical structure, it would however also be possible to employ other structures.
The major function of vacuum pump 11 is to provide malleation or negative for vacuum chamber 1, eyelid covering 9, inflation rod member 13 or other air bags
Pressure supply.In the present invention, it is possible to use vacuum pump 11 provides negative pressure, vacuum chamber 1 air pressure inside is reduced, then makes vacuum chamber
Obtain buoyancy.Can also be eyelid covering 9 using vacuum pump 11, inflation rod member 13 or other air bags provide malleation inflate so as to have
Certain mechanical strength.In the present invention, vacuum pump 11 can be one or multiple stage.The mode of operation of vacuum pump 11
Can be for work independently can also associated working.
Rod member 12 is made up of various lightweight rigid structures.Although inflation rod member 13 disclosure satisfy that in most cases rigid body knot
The mechanical requirements of structure, but be not excluded for some in particular cases still needing conventional lightweight rigid structure.Tied by these lightweight rigid bodies
The rod member 12 of structure composition is the important supplement to whole vacuum type buoyancy flight instruments.
Inflation rod member 13 is by the lightweight rigid structure of gas tube structure composition.Inflation rod member 13 can be by Conventional pneumatic pipe
Composition is it is also possible to be made up of intelligent cell type inflation rigid structure [list of references 2].Being mainly characterized by of inflation rod member 13 is light
Matter is pressure rigid structure, as described in document, [list of references 5,12,13,14] gas tube has lighter deadweight, and in axial force
Aspect has excellent performance.Inflate filling of the described many airbag structure compositions of rigid structure [list of references 2] using intelligent cell type
Gas rod member 13 has the mechanical property more more excellent than traditional single-chamber bromhidrosis capsule, can meet inflation rod member 13 completely for vacuum chamber
The demand of 1 opposing external atmosphere pressure.
Drawstring 14 is the important component part of vacuum type buoyancy flight instruments.As described in document [list of references 10,11], draw
Rope structure can play to air bag stress and greatly supplement, and contribute to steering, decomposition or the concentration of stress.In the present invention, draw
Rope 14 can be rope form, can also be netted.Drawstring 14 can be integrated it is also possible to individualism with eyelid covering, air bag.Drawstring 14 can
To be arranged on vacuum chamber inside it is also possible to be arranged on outside vacuum chamber.
It is noted that the volume of vacuum chamber can not be too low during design vacuum type buoyancy flight instruments.As shown in Fig. 6 form,
When spherical structure diameter is less than 6 meters, the ratio of volume and surface area is area > volume, and spherical structure with diameter greater than 6 meters when face
Long-pending < volume.During a diameter of 6 meters of spherical vacuum cabin, the ratio of surface area and volume is 1:1.In the present invention, lattice support structure
It is substantially identical to surface with rounded structures to amass.When spherical vacuum cabin is with diameter greater than 6 meters, spherical structure volume ratio will be more than table
Area.Larger volume can arrange more air, is that vacuum type buoyancy flight instruments brings more buoyancy.
With the continuous development of materialogy, following material may be more outstanding.True using high-strength material manufacture
Empty cabin can select arbitrary structures to be not necessarily limited to spherical.The guiding theory of the present invention is to resist air pressure using air pressure, selects
Other structures vacuum chamber does not affect ownership of the present invention.
Brief description:
In accompanying drawing, corresponding numeral is: eyelid covering 9, truss 10, air bag 15, normal atmospheric environment 16, vacuum environment 17.
Fig. 1 is vacuum type buoyancy flight instruments overall structure diagram.Wherein eyelid covering 9, air bag 15, truss 10 are integrated into
Integrally.
Fig. 2 is structural representation after single airbag structure and its inflation.Figure middle body is regional area enlarged diagram,
Arrow represents air pressure stress direction.When air bag internal gas pressure is more than external environment condition, air bag can tend to spherical in shape.When two air bags
When interfering, the stress of contact surface can interact.Other region cyst walls as air bag extend to the limit, and stress can be converted into
Pulling force to airbag wall.As long as tension intensity would not produce further deformation or tear less than airbag wall tensile strength.Cause
This, airbag wall tensile strength > air bag internal gas pressure > and adjacent cells contact surface deformable stress when, air bag internal stress is concentrated in adjacent
Balloon contacts face.
Fig. 3 is internal force schematic diagram detailed annotation (locally) after many air bags parallel construction and its inflation.The air bag eyelid covering of this kind of pattern
Based on [document 2] intellectuality cell type inflation rigid structure design, using the interaction force opposing air between multi-layer airbag
Pressure.This kind of stressed-skin construction is characterized as that inner side air bag pressure is more than outside air bag pressure, and air bag is domed under gas pressure, helps
Turn in external atmospheric pressure and cancel out each other.This kind of structure is applied to super large structure for vacuum cabin, and it has higher rigidity.
Fig. 4 is state when eyelid covering 9 is entirely pneumatic.Now eyelid covering 9 is intrinsic pressure roughly the same with external environment atmospheric pressure,
Suitably eyelid covering 9 is manufactured under this kind of state or overhauled.
Fig. 5 is eyelid covering 9 shown in Fig. 4 completely into the situation after working condition.Now, external atmosphere pressure is normal atmosphere
(natural atmosphere environment).Composition eyelid covering 9 air bag in be filled with gases at high pressure, the active force of the contact surface between air bag and air bag it
With more than air bag outside atmosphere pressure pressure.The pressure that external atmosphere pressure produces can be turned by the now substantially spherical structure of air bag
Marry adjacent area.As long as both make a concerted effort just to meet vacuum cabin structure to opposing air pressure ring less than airbag wall tensile strength
The requirement in border.Note: in accompanying drawing, multi-layer airbag structure composition eyelid covering 9 is based only on a kind of scheme of principle of the invention design, according to
The aircraft of the different patterns of the principle design of vacuum type buoyancy flight instruments can be using different eyelid coverings and inflation truss
Compound mode.Change air bag arrangement mode or airbag structure does not affect ownership of the present invention.
Fig. 6 is the ratio table between spherical vacuum cabin surface area and volume.
Specific embodiment:
Taking vacuum cabin structure shown in Fig. 5 as a example:
Known standard atmosphere is depressed 1 cubic metre of air and is weighed about as 1.29 kilograms
Taking the spherical vacuum cabin of 10 meters of a diameter as a example:
The spherical vacuum cabin girth of 10 meters of diameter is about 31.4 meters
Surface area is about 314.16 square metres
Volume is about 523.6 cubic metres
Calculate eyelid covering air bag volume first
If to be 10cm(macromolecular material airbag wall very thin extremely light for eyelid covering balloon thickness it has not been convenient to independent calculated weight.Therefore will weigh
Amount is attached in balloon thickness, that is, set balloon thickness 15cm)
1 square meter eyelid covering volume is about 1*1*0.15=0.15 cubic meter
3 times of 1.29 kilograms * 0.15 cubic metre=0.5805 kilogram of atmospheric pressure * (being filled with eyelid covering every square meter net weight after 3 times of atmospheric pressure)
182 kilograms of 10 meters of spherical vacuum cabin 314.16*0.5805 kilogram of ≈ of surface area of diameter
After being filled with 3 times of atmospheric pressure, eyelid covering gross dry weight is about 182 kilograms
10 meters of spherical vacuum nacelle of known diameter are amassed and are about 523.6 cubic metres, standard atmosphere depress 1 cubic metre of air weigh about for
1.29 kilogram.675 kilograms of buoyancy 523.6*1.29 ≈ can be calculated
675-182=493 kilogram.
Thus can calculate, 10 meters of vacuum chambers of diameter still can have 493 kilograms of buoyancy after excluding stressed-skin construction deadweight.
Most of aircraft movement requirements can be met completely.
Note 1: because vacuum chamber own vol is less, eyelid covering air bag is intrinsic pressure can be using (construction weight is relatively compared with low internal pressure
Low).When vacuum nacelle amasss larger, (such as 100 meters of diameter), in order to resist vacuum chamber deadweight, needs in membrane inflatable tube
Pressure is strengthened and is increased internal truss frame.
Note 2: when below 6 meters of small size vacuum cabin diameter is used in experiment, spherome surface amasss and is more than volume, thus true below 6 meters of diameter
Empty cabin design structure and algorithm are different from more than 6 meters structures, and details are with reference to Fig. 6.
Note 3: if gas-filled film tubular construction be obtained in that using intelligent cell type inflation rigid structure [document 2] higher
Mechanical property, and conduct oneself with dignity without significantly rising.Concrete numerical value needs to calculate according to actual product.
Industrial applicibility:
The history of floating type aircraft is very long, but floating type aircraft in the past adopts light gas to fill as buoyancy mostly
The driving core put.The light gas that main flow buoyancy aircraft adopts in the world mainly have hydrogen and helium, but all exist huge
Defect.Although hydrogen produce conveniently, with low cost, there is inflammable and explosive danger.World today's most countries have been prohibited
Only hydrogen is used for inflated type lighter-than-air flight device.Helium is the light gas used by lightweight aircraft of main flow in the world at present, but
Helium belongs to non-renewable resources.Once if applying it is also possible that extensive development helium aircraft arises that one on a small quantity
The embarrassed shape that gas difficulty is asked.
The present invention designs truly feasible vacuum type buoyancy flight instruments based on current commercialization material.His is excellent
Gesture is not need specific light gas, as long as needing the area of lift-off by vacuum type buoyancy flight instruments after the completion of building
Interior evacuating air can float.
Can be with large-scale application to transport field using the vacuum type buoyancy flight instruments that current material produces.Vacuum type
Buoyancy flight instruments is not restricted by landform, and energy amount transport goods and materials, and landing is without airport etc hardware facility.
Claims (10)
1. a kind of vacuum type buoyancy flight instruments, it is characterized by design lightweight rigid body truss structure with structural mechanics, with macromolecule
Material is eyelid covering, with gas tube for supporting, makes a kind of light overpressure resistant vacuum equipment, will be true for this light overpressure resistant using vacuum pump
The buoyancy being obtained after empty device extracting vacuum is more than vacuum equipment net weight, and this vacuum equipment can obtain floating under atmospheric environment
Power carries out a liter flight of wafing.
2. vacuum type buoyancy flight instruments as claimed in claim 1 is by vacuum chamber 1, energy resource system 2, dynamical system 3, load system
System 4, monitoring system 5, control system 6, communication system 7, automatic repair system 8 form, and wherein vacuum chamber is mainly by eyelid covering 9, purlin
Frame 10, vacuum pump 11 form, and truss 10 is main to be made up of rod member 12, inflation rod member 13, drawstring 14.
3. vacuum chamber 1 as claimed in claim 2 is the core of vacuum type buoyancy flight instruments, its be mainly characterized by using eyelid covering 9,
Truss 10, vacuum pump 11 form a lightweight rigid structure, adjust the air pressure in vacuum chamber 1 using vacuum pump 11, work as vacuum type
During the air quality that the deadweight total amount of buoyancy flight instruments arranges less than vacuum chamber, vacuum type buoyancy flight instruments obtains on buoyancy
Floating, one or more vacuum chamber 1 can be disposed in vacuum type buoyancy flight instruments.
4. dynamical system 3 as claimed in claim 2 is the dynamical system assembly that vacuum type buoyancy flight instruments moves in an atmosphere,
In order to obtain preferable power, can be using the electromotor of the electromotor of propeller driving or injection engine driving, electromotor
Can be fixing or rotated freely by cardan shaft driving, dynamical system 3 can quote traditional floating type aircraft
Dynamical system design.
5. load system 4 as claimed in claim 2 is vacuum type buoyancy flight instruments load system assembly, and it is mainly characterized by profit
Carry the system of all kinds of load devices with vacuum chamber 1 for core, load system 4 can be gondola or be dragged by drawstring 14
The arbitrary load device draging.
6. repair system 8 is using automation equipment, vacuum type buoyancy flight instruments can be entered automatically as claimed in claim 2
The simple device repaired of row, in the present invention, the groundwork mode of automatic repair system 8 is can be in gas transmission using robot
The characteristic teleoperator moving freely in pipeline processes abnormal conditions, and this process can be automatically controlled by a computer and complete,
Can also be completed by manually carrying out hand control.
7. eyelid covering 9 as claimed in claim 2 can be single thin film structure it is also possible to the composite junction that is made up of several air bags
Structure, the eyelid covering 9 being made up of several airbag structures can be with type arched structure, using domes by the atmospheric pressure outside eyelid covering
Dispersion turns to and cancels out each other, so that eyelid covering 9 can resist external atmosphere pressure, in order to obtain enough rigid body intensity, can be in gas
Intracapsular arrangement truss, also can dispose truss outside air bag, supplement air bag stress intensity itself using truss.
8. truss 10 as claimed in claim 2 is main is made up of rod member 12, inflation rod member 13, drawstring 14, using rod member 12, inflation
Rod member 13, the stereochemical structure truss 10 of drawstring 14 composition have preferable mechanical property and relatively light quality, can be to illiteracy
Skin 9 is pressure, and rigid structure plays great enhancing, and the truss 10 using rod member 12, inflation rod member 13, drawstring 14 composition can be pacified
It is contained in inside or outside eyelid covering 9, assist eyelid covering 9 opposing external atmosphere pressure.
9. the major function of vacuum pump 11 as claimed in claim 2 is for vacuum chamber 1, eyelid covering 9, inflation rod member 13 or other air bags
Malleation or negative pressure supply are provided；In the present invention, it is possible to use vacuum pump 11 provides negative pressure, vacuum chamber 1 air pressure inside is reduced,
Then make vacuum chamber obtain buoyancy it is also possible to using vacuum pump 11 be eyelid covering 9, inflation rod member 13 or other air bags provide malleation fill
Gas is so as to have certain mechanical strength；In the present invention, vacuum pump 11 can also be able to be multiple stage for one, vacuum pump 11
Mode of operation can be for work independently can also associated working.
10. inflation rod member 13 as claimed in claim 2 is common inflation tubular construction or intelligent cell type inflation rigid structure
[cn201610886675.x], it is mainly characterized by making rod member using lightweight inflation tubular construction, using its lightweight feature
The truss 10 of auxiliary vacuum type buoyancy flight instruments supports eyelid covering 9 opposing external atmosphere pressure, and inflation rod member 13 can install air bag
Outside is it is also possible to be arranged on inside air bag.
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| CN201610889478.3A CN106347620A (en) | 2016-10-12 | 2016-10-12 | Vacuum type buoyancy flight device based on structural mechanical design |
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| CN201610889478.3A CN106347620A (en) | 2016-10-12 | 2016-10-12 | Vacuum type buoyancy flight device based on structural mechanical design |
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Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107031809A (en) * | 2017-04-25 | 2017-08-11 | 哈尔滨工业大学 | A kind of Hengsheng dead-wood material unit for floating island |
| CN107054609A (en) * | 2017-04-25 | 2017-08-18 | 哈尔滨工业大学 | Modularization stratosphere floating island |
| CN108182308A (en) * | 2017-12-19 | 2018-06-19 | 北京空间机电研究所 | A kind of Inflatable re-entry vehicle structural dynamical model method and system for considering non-linear effects |
| CN109204770A (en) * | 2017-06-30 | 2019-01-15 | 东莞前沿技术研究院 | The patch system and method for repairing and mending of aerostatics utricule |
| IT201900017183A1 (en) * | 2019-09-25 | 2021-03-25 | Di Priero Ludovico Umberto Turinetti | Hollow body in which to apply the vacuum and configured to be a floating body of an aircraft. |
| US20220177106A1 (en) * | 2019-04-05 | 2022-06-09 | Silvano PASCUCCI | Airship with rigid supporting structure |
| DE202022000839U1 (en) | 2022-04-02 | 2023-07-10 | Julian Jain | Load transfer system, redundancy system and functional system for an aerostatic buoyancy device |
| GB2623016A (en) * | 2021-06-20 | 2024-04-03 | Norouzi Ramin | Reconfiguring vertical takeoff and landing aircraft |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1376617A (en) * | 2001-03-22 | 2002-10-30 | 高松 | Manned craft |
| CN1398757A (en) * | 2002-07-25 | 2003-02-26 | 欧绪凡 | Air vehicle lighter than air without working gas |
| US20080128434A1 (en) * | 2006-12-05 | 2008-06-05 | Sean Anderson Barton | Light-weight vacuum chamber and appalications thereof |
| CN105383677A (en) * | 2015-11-24 | 2016-03-09 | 郭鹏 | Long-acting vacuum chamber satellite |
| CN105644762A (en) * | 2016-01-19 | 2016-06-08 | 北京航空航天大学 | Novel stratospheric airship |
| CN206297721U (en) * | 2016-10-12 | 2017-07-04 | 郭鹏 | A kind of vacuum type buoyancy flight instruments based on structural mechanics design |
-
2016
- 2016-10-12 CN CN201610889478.3A patent/CN106347620A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1376617A (en) * | 2001-03-22 | 2002-10-30 | 高松 | Manned craft |
| CN1398757A (en) * | 2002-07-25 | 2003-02-26 | 欧绪凡 | Air vehicle lighter than air without working gas |
| US20080128434A1 (en) * | 2006-12-05 | 2008-06-05 | Sean Anderson Barton | Light-weight vacuum chamber and appalications thereof |
| CN105383677A (en) * | 2015-11-24 | 2016-03-09 | 郭鹏 | Long-acting vacuum chamber satellite |
| CN105644762A (en) * | 2016-01-19 | 2016-06-08 | 北京航空航天大学 | Novel stratospheric airship |
| CN206297721U (en) * | 2016-10-12 | 2017-07-04 | 郭鹏 | A kind of vacuum type buoyancy flight instruments based on structural mechanics design |
Cited By (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107031809A (en) * | 2017-04-25 | 2017-08-11 | 哈尔滨工业大学 | A kind of Hengsheng dead-wood material unit for floating island |
| CN107054609A (en) * | 2017-04-25 | 2017-08-18 | 哈尔滨工业大学 | Modularization stratosphere floating island |
| CN107054609B (en) * | 2017-04-25 | 2019-06-04 | 哈尔滨工业大学 | Modularization stratosphere floating island |
| CN107031809B (en) * | 2017-04-25 | 2019-09-24 | 哈尔滨工业大学 | A kind of Hengsheng dead-wood material unit for floating island |
| CN109204770A (en) * | 2017-06-30 | 2019-01-15 | 东莞前沿技术研究院 | The patch system and method for repairing and mending of aerostatics utricule |
| CN109204770B (en) * | 2017-06-30 | 2024-02-23 | 深圳光启空间技术有限公司 | Repairing system and repairing method for aerostat capsule |
| CN108182308A (en) * | 2017-12-19 | 2018-06-19 | 北京空间机电研究所 | A kind of Inflatable re-entry vehicle structural dynamical model method and system for considering non-linear effects |
| CN108182308B (en) * | 2017-12-19 | 2021-07-13 | 北京空间机电研究所 | Inflatable reentry vehicle structure dynamics analysis method and system considering nonlinear influence |
| US20220177106A1 (en) * | 2019-04-05 | 2022-06-09 | Silvano PASCUCCI | Airship with rigid supporting structure |
| IT201900017183A1 (en) * | 2019-09-25 | 2021-03-25 | Di Priero Ludovico Umberto Turinetti | Hollow body in which to apply the vacuum and configured to be a floating body of an aircraft. |
| GB2623016A (en) * | 2021-06-20 | 2024-04-03 | Norouzi Ramin | Reconfiguring vertical takeoff and landing aircraft |
| DE202022000839U1 (en) | 2022-04-02 | 2023-07-10 | Julian Jain | Load transfer system, redundancy system and functional system for an aerostatic buoyancy device |
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