CN100422044C - Solar energy buoyancy force controllable, self control balance helium gas aircraft - Google Patents
Solar energy buoyancy force controllable, self control balance helium gas aircraft Download PDFInfo
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- CN100422044C CN100422044C CNB2005100412248A CN200510041224A CN100422044C CN 100422044 C CN100422044 C CN 100422044C CN B2005100412248 A CNB2005100412248 A CN B2005100412248A CN 200510041224 A CN200510041224 A CN 200510041224A CN 100422044 C CN100422044 C CN 100422044C
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Abstract
The present invention relates to a solar energy buoyancy force controllable, self control balance helium gas aircraft provided with a buoyancy force device which uses a balloon which is lighter than air to generate buoyancy force, a propulsion device, and a manned or manned/luggage device. The buoyancy force device and a buoyancy force control device are at least provided with two groups of buoyancy force gas containers-soft balloons or balloon-rigid balloons. Different balloon groups are connected by a pipe with which a pressure pump (namely an air charging pump and an air charging and discharging valve) is connected in series. The present invention uses air charging balloons to generate buoyant force. Buoyant force gas realizes different distribution of pressure and density for the different balloon groups with the pressure function of the air charging pump, and therefore, buoyancy force is automatically controlled. The distribution of different density and pressure of buoyancy force gas among the groups of balloons is controlled and adjusted by an electronic control system or a computer program, which leads buoyancy force to be controlled and adjusted. The present invention is provided with a flight controlling airflow air pump which can realize the self control balance. Air outlet ends of the flight controlling airflow air pump are through to the periphery of a flight device through air outlet pipes and branch pipes. The present invention has the advantages of low price, little energy consumption, environmental protection and high safety.
Description
One, technical field
The present invention belongs to balloon flight device technology---dirigible technology, especially solar power controllable buoyancy, the automatic control in the aeronautical technology field helium airship that surely weighs.
Two, background technology
The enforcement the earliest of balloon flight device can be traced back to 1784, and French Robert brother's manual feed fish shape is filled taking a flight test of hydrogen HIKOUSEN.It is 2500 cubic meters that French engineer Ji Faer in 1852 has manufactured and designed air bag, promote screw propeller with steam engine is that handling of onward impulse filled the hydrogen dirigible.Afterwards, soft balloon dirigible was replaced by the rigid airship of metal, timber frame covering covering again.To 20 beginnings of the century, the dirigible technology is ripe day by day.Germany inventor Zeppelin is made significant contribution, makes the dirigible aviation become the leading trend of initial World Airways industry of 20th century.Germany De Laige dirigible airline company has only just realized from 1910 to 1914 that dirigible navigates by water the achievement of 35000 person-times of 2,140,000 kilometers, safe carrying.Germany made long 245 meters of successful Hindenburg dirigible, 41 meters of diameters in 1936, always bag volume are 230 tons of 20 ten thousand steres, gross weights, power is 4 610 kilowatts driving engine, 75 of carryings, the speed of a ship or plane reaches 130 kilometers/hour, be 200 hours cruise duration, the luxurious and equipment of inside fitting comfortable not second to " Titanic " number luxurious passenger steamer.This ship carries out 63 commercial flight altogether.In the World War I, dirigible is also extensively applied in the military affairs by various countries, and obtains outstanding effect.
Yet the termination of dirigible aircraft industry is a sign with the unexpected blast accident on fire when N.J. lands of Hindenburg airship on May 6 nineteen thirty-seven just also.But to be replaced by emerging aircraft aviation be not chance in the dirigible aviation, and its certainty is two big defectives of inflation airship at that time: the one, and body that most of dirigible is inflated is flammable explosive hydrogen; The 2nd, bulky dirigible understeer is lived, structure is not firm, is difficult to keep out the attack of storm.Particularly when civilian and military aviation were pursued the demand of high speed of a ship or plane target day by day, dirigible just can't have been competed with aircraft more mutually.
Rise and capture in the age of aircraft industry fully in the aircraft aviation, from the seventies in 20th century, inflatable vehicle---dirigible aviation begins recovery again.This is because new material technology and control technology can be improved the defective of dirigible in history on the one hand, thereby makes dirigible possess the ability of competing with the aircraft aviation in load carrying ability, shipping cost, safety; Prior underlying causes then is: world energy sources, oil shortage are serious day by day, and the aircraft aircraft industry that consumes the flood tide oil also just faces serious crisis.In case the oil exhaustion, existing all aircrafts will become a pile refuse.
Recovering inflation airship is speed of development and unhappy in decades, be far from entering in a large number civil aviation and other practical aviation fields, be because on safety, practicality, also there are some shortcomings, the motion of particularly controlling aerial all directions flexibly and comfortably is not perfect, and the energy that is consumed remains petroleum products basically.
Three, summary of the invention
Purpose of the present invention to manufacture and design exactly a kind of existing like product safer, economical, control inflatable vehicle flexibly, aviation has stronger competitive power to aircraft on practical purposes to make it: the air crash rate that makes it is far below existing aircraft aviation, the passenger and freight cost is significantly less than the aircraft air transport, also can match in excellence or beauty with the aircraft air transport on conveying efficiency, practicality; Thereby it is had ready conditions enter the civil aviation industry in a large number, and become the family expenses aircraft that spreads to the common people.The aircraft of indication of the present invention promptly be a kind of than in history, existing dirigible has the new dirigible of great technology innovation---again dirigible is called airship in the present invention.Because ship and ship are synonyms, the front adds blue sky two word tables and shows that it navigates by water in atmospheric envelope, is different from the appellation of at present popular spacecraft.
Solar power controllable buoyancy, the automatic control helium airship that surely weighs is provided with buoyant device, engine installation, manned or manned double carrying apparatus that the balloon that is lighter than air produces buoyancy; Engine installation: with electrical motor or internal-combustion engine drives screw propeller or pneumatic pump jet supersonic plane is power; Buoyant device and floatage control device: be provided with two groups of buoyancy gas containers at least---software balloon or software, hardware balloon, between the different balloon groups by plumbing connection, on pipeline, connect force lift, be inflation pump and charging and discharging valve, rely on aerating ballon to produce buoyancy, buoyancy gas is implemented in different pressures, the Density Distribution of different balloon groups under the effect of inflation pump pressure, thus automatic guidance buoyancy; The buoyant device bottom connects manned or manned double loading container, and floatage control device is utilization electronic control system or the different densities of computer program control and regulation buoyancy gas between each group balloon and the floatage control device of distribution of pressure realization; It is characterized in that: be provided with " the regulation and control flight air-flow air pump " of realizing the steady weighing apparatus of automatic control, its outlet side by vent pipe and arm lead to be distributed in orientation around the aircraft, with the air blast nozzle of adjustable tolerance valve, its inlet end leads to the admission port of opening to external world by induction tract; The automatic control that is provided with distribution that utilization electronic control system or computer program control " regulation and control flight air-flow air pump " is ejected into extraneous air-flow, the intensity device that surely weighs; Buoyancy gas container balloon is the software balloon that elastic membrane is made, and these balloons are divided into many groups, promptly main balloon A group and main balloon B group and some groups in secondary balloon; Every group of balloon group is made up of several balloons, is called for short the unit balloon, adopts the lung tubular type tracheae of similar animal lung tracheae that the unit balloon is connected to gas main; Lung tubular type tracheae and gas main have two covers, and a cover is the inflation tracheae, and another set of is the exhaust tracheae; Electrical motor in the engine installation has 3 kinds, the electrical motor of gas filed inflation pump electrical motor, promotion propeller between the promptly major and minor balloon, and promotion produces the electrical motor of the air pump of " regulation and control flight air-flow "; The space, balloon cabin that holds all balloons has flat shape, and a large tracts of land flat-top is arranged, and installs solar cell on the flat-top, establishes storage battery and small-sized internal combustion engine generator group as backup power; The all bronchi end connects with balloon, all adopts chicken intestines valve inside to connect; Every gas enters the passage of balloon, and valve inside exports in balloon; Every air-flow goes out the passage of balloon, and valve inside exports outside balloon; But the inflation pump import also has the branched pipe of a band control valve, as the pipeline of extraneous source of the gas air inlet.
The present invention allocates gas between main balloon and secondary balloon be the buoyancy gas volume that adapts for regulation and control and flight sea level elevation.Distribution, intensity that operation that the steady automatic guidance that weighs of sporting flying is utilization electronic control system or computer program propeller that the control motor drives and pneumatic pump are ejected into extraneous air-flow realize.
The present invention is that a kind of electric energy that transforms with sun the subject of knowledge and the object of knowledge is the energy of driving force motor, relies on to fill the helium balloon and produce buoyancy, can need control buoyancy, the steady weighing apparatus of auto-flare system by flight, navigates by water manned or manned double loading aircraft in atmospheric envelope;
Aircraft operation, the required electric power of driving force motor running are by the solar cell supply.Other has storage battery and small-sized internal combustion engine generator group as backup power.
" the regulation and control flight air-flow air pump " of the steady weighing apparatus of realization automatic control of the present invention is characterized in that: its outlet side by vent pipe and arm lead to be distributed in each orientation of aircraft, with the air blast nozzle of adjustable tolerance valve; Its inlet end leads to the admission port of opening to external world by induction tract.The orientation is provided with the air blast nozzle with adjustable tolerance valve around the aircraft, its outlet side by vent pipe and arm lead to be distributed in orientation around the aircraft, with the air blast nozzle of adjustable tolerance valve, its inlet end leads to the admission port of opening to external world by induction tract; The steady weighing apparatus of its automatic control is that distribution, the intensity that utilization electronic control system or computer program control " regulation and control flight air-flow air pump " are ejected into extraneous air-flow realizes.
When the electric energy that transforms with sun the subject of knowledge and the object of knowledge is the major impetus or the energy, driving force motor of the present invention, it is characterized in that: driving force motor has 3 kinds, be the electrical motor (hereinafter to be referred as main motor) of gas filed inflation pump electrical motor between the major and minor balloon group (hereinafter to be referred as the inflation electrical motor), promotion propeller, promote the electrical motor (hereinafter to be referred as the air-flow electrical motor) of the air pump of generation " regulation and control flight air-flow ".
Aircraft of the present invention, the structure that it is characterized in that it is made up of tubing framework and sheet material or film covering, and framework or the skeleton made from metal or plastics or composite material also covers covering and makes rigid airship.And to form 3 cabins combining as a whole be balloon cabin, cabin, passenger cabin, and the software balloon places in the hardware balloon cabin.
Aircraft of the present invention is characterized in that: it is equipped with the propeller that is fixed on " the skeleton shell of aircraft " or " accessory structure that is connected with airframe, shell ".
Aircraft of the present invention is characterized in that it is equiped with the computing machine and the attached control system of autonomous cruise speed system or equipped with dedicated program, but reaches the control convenience of each control valve as automatic guidance inflation electrical motor, main motor, air-flow electrical motor.
Inflation pump of the present invention is allocated gas between two groups of master's balloons be to be the regulation and control lifting, and allotment gas is the buoyancy gas volume that adapts for regulation and control and flight sea level elevation between main balloon and secondary balloon.
The effect that the present invention is increased compared to prior art is as follows:
(1) it will bring the highest air transportation of a kind of present safety.It is by dozens of or more multiple-unit balloon load-bearing, unless any pernicious air crash can not take place inclement weather.With close the writing to each other and make it can weather avoidance in weather information center.This has important attractive force in the present age of airplane crash pilosity to people.
(2) it will make the petroleum-based energy crisis that the fatal threat of aircraft industry is readily solved.Its utilization nature buoyancy greatly reduces energy consumption; It uses solar power, makes consumption of fuel drop to zero.
(3) its perfect adjustable buoyancy system, the robot control system(RCS) of the steady weighing apparatus of flight and other autonomous cruise speed system, firm light new material, make its operational flexibility, stability, safety of structure be better than in the past fill the helium dirigible.
(4) it might provide a kind of brand new aerial family expenses aircraft, might make the epoch change of family car be the family expenses airship epoch, thereby for the modern provides a kind of brand new life style, satisfy the demand that the modern upgrades day by day; And promote the development of related industry thus.
(5) its flying speed is expected to surpass automobile.It can be in overhead airport or skyscraper jack-up, falls, and need not to take the place, ground.The gap of it and the existing aircraft speed of a ship or plane, the distance that can shorten airport and origin, destination remedies.
(6) have soft air cushion at the bottom of its passenger cabin, can protect accidental situation better ground-surface damage, can also land safely and safety float on waterborne.
(7) its balloon cabin top is except that the installing solar cell, also available small part area, and double as is the occupant deck of going sightseeing; Making the occupant can obtain the impayable sky that faces of existing aerocraft experiences." deck " also can for be the occupant of safety strap " land ", go on perilous peak aloft, will bring brand new air travel mode.
(8) it also has storage battery, external power charging inlet except solar energy, can satisfy the usefulness that does not have the charging of sun lowsteaming and make a return voyage; It has small-sized internal combustion dynamotor group as backup power, has increased circuit and control system reliability.Its balloon has urgent manually relief port, but in extreme dead electricity situation also safe falling.
Generally speaking, intention of the present invention the characteristic effect painstakingly pursued be:
Embrace the happy of blue sky, the energy of cheapness, environmental protection, safety safe against all possibilities.
Four, description of drawings
Fig. 1 is an outward appearance of the present invention: among the figure, 1 is solar cell; 2 is the balloon cabin; 3 is the cabin; 4 is passenger cabin; 5 is wing; 6 is propeller; 7 is soft air cushion bag; 8 is tail cone behind the passenger cabin; 9 is tail vane.
Fig. 2 is an outward appearance front elevation of the present invention.
Fig. 3 is an outward appearance upward view of the present invention.
Fig. 4 adopts fixedly " the unit controls circuit diagram " of electronic control circuit for not adopting computer program.IC is an integrated circuit among the figure---a loop of voltage comparator (,+be its two input port, o is its mouth), U1 is transducing signal or steering instructions signal, U0 is reference signal or comparison signal, R1 is that current-limiting resistance, R2 are divider resistance, R3 is an input resistance, and C stablizes electric capacity for input, and BG is 3 utmost point pipes; JG is a solid-state relay; E+, E0 are operating power.Control unit or subsystem (complicated control unit) have: driving speed fine setting control unit, drive the speed threshold control unit, drive the direction control unit, drive and highly finely tune control unit, drive height shelves control unit, velocity-stabilization regulator system, direction are stablized regulator system, highly stable regulator system, horizontal stable regulator system, solar cell regulator system, storage battery regulator system.The principle of control unit is: when | U1|＞| U0| (the o end output high level of IC during U1＜U0=, BG has input, amplifies by BG, one or more actuating units are started in the J conducting, produce to carry out action (for example motor gear box, charge and discharge gas, select to switch).
Fig. 5 is a helium pipeline scheme drawing of the present invention.10,11,12 be respectively main gas cabin A, main gas cabin B, secondary gas cabin, but 13 be control valve, 14 is inflation pump, and 15 is the outer source of the gas supply house steward of helium.
Fig. 6 is a lung cast tracheal system scheme drawing, and 16 is gas main, and 17 is 1 grade of bronchus, and 18 is 2 grades of bronchuses, and 19 is 3 grades of bronchuses.Progression can be according to the particular case setting.Bottom bronchus (terminal bronchus) order unit balloon, 20 is the air valve that ends of the bronchial self controllable switching of the bottom, the switching that ends air valve is controlled by aircraft autonomous cruise speed system and steering instructions.Air gas sensor to finite concentration composition of air gas sensitization all is housed in each unit balloon.Control by the principle that air valve (20) opens and closes is: same group of balloon fills, exits each balloon air pressure should be even; Air admission balloon when balloon breaks, the air gas sensor (being typically exhaust gas oxygensensor) of unit balloon sends information, the terminal bronchus of this information by this balloon of automatic controlling system closed by air valve (20), by the filling of this balloon, bleed flow.
Five, the specific embodiment
Embodiments of the invention following (can contrast Figure of description 1) to accompanying drawing 6:
The buoyancy regulation and control: by the different densities between two groups of balloons, distribution of pressure is realized; Utilize setting height or rising, decline order to carry out, control by setting height or rising, decline order promptly that the work of gas filed inflation pump electrical motor, balloon charge and discharge the gas time between the major and minor balloon.Can obtain the height control information by regulative modes such as height sensor, PID.
Equally, the steady weighing apparatus of its automatic control is that the above-mentioned inclination sensor of utilization is realized by distribution, the intensity that electronic control system or computer program control " regulation and control flight air-flow air pump " are ejected into extraneous air-flow.Just use the control and regulation of electronic control system or computer program to realize " the regulation and control flight air-flow air pump " of the steady weighing apparatus of automatic control, promote regulation and control flight air-flow air pump electrical motor, produce regulation and control flight air-flow.The outlet side of regulation and control flight air-flow air pump by vent pipe and arm lead to be distributed in orientation around the aircraft, with the air blast nozzle of adjustable tolerance valve; Its inlet end leads to the admission port of opening to external world by induction tract,
The profile in balloon cabin is 30 meters of last diameters, 6 meters of following diameters, thick 5 meters inversion billiard table; Solar cell is laid on top, balloon cabin, total Maximum Power Output 50-60 kilowatt; The balloon bilge and 4 meters of last minister 5 meter, time ministers, wide 2 meters, high 1 meter cabin are connected; Go to the bottom and 4 meters of last ministers in the cabin, 3.5 meters of following ministers, and wide 2 meters, high 2 meters passenger cabin is connected.Passenger cabin is gone to the bottom along the preceding 3 meters scopes of length, and other sets up is equipped with length and width and goes to the bottom high 0.5 meter soft air cushion bag with passenger cabin.Cabin, passenger cabin two ends along its length are defined as aircraft front and back ends (implication of " preceding " " back " in this specification sheets is all consistent therewith) respectively.The joint face of the forward and backward side of top front and back ends and balloon cabin on the cabin, top and the joint face of going to the bottom on the cabin, the top is smooth surface with the joint face of going to the bottom on the passenger cabin; Wherein the forward and backward side of top front and back ends and balloon cabin bonded assembly fillet surface upper limb on the cabin extends to 10 meters sectional positions of balloon cabin diameter.In addition, on the said structure basis, cabin, passenger cabin are made 1 meter long on the taper tail (the extension fillet surface of cabin upper rear end no longer repeats to extend back) that extends back along its length more in addition; The taper tail trailing edge of cabin and passenger cabin rear end is equipped with the tail vane of capable telecommunications number control.
Balloon cabin, cabin, passenger cabin adopt the whole skeleton of carbon fibre reinforced pipe material or being made into one of aramid fiber reinforced composite tubing, as cabin, passenger cabin outer wall, surface, balloon cabin, subdivision interbody spacer adopt mylar or other high-strength membranes to make covering with the sheet material of same material.Balloon cabin top portion area is laid sheet material.Vehicle construction material is the fire-retardant fireproof material or handles through fire-retardant fireproof.
Along the cabin, the passenger cabin Width, from the cabin, the passenger cabin left and right side respectively stretches out 2 meters long wings, also by making its skeleton, shell with cabin skeleton, outer wall identical materials.The wing end links to each other through fillet surface with side, balloon cabin.Thick 0.3 meter of wing, wide 1 meter, the front and rear part of cross-sectional plane are curve and are connected (cross section becomes aircraft wing stream line pattern) with upper and lower one-tenth is smooth.Long and the cabin of wing, passenger cabin length direction are vertical, wing width longitudinal plane of symmetry alignment cabin length longitudinal plane of symmetry, wing thickness longitudinal plane of symmetry align cabin, passenger cabin interface.The elevating rudder of capable telecommunications number control all is equipped with at two wing rears.
Left and right sides wing respectively is equipped with one one of the propeller of main motor and drive thereof.Propeller is made (can be the hollow shell structure) with carbon fiber or aramid fiber composite material.Screw propeller forwardly, electrical motor and propeller thereof place among the cylinder engine room of left and right sides wing; Engine room is embedded in left and right sides wing along the long center of wing, links to each other with aerofoil surface through the smooth transition curved surface.The engine room afterbody is tapered.The skeleton of engine room, skin material are identical with wing.The screw propeller rotating diameter is 1.4 meters to 1.8 meters, and each screw propeller motor power (output) is 15 kilowatts to 20 kilowatts.Left and right engine room to left and right wing along the place ahead, rear, top, lower position and the wingtip of the wing section between the long-range end of wing with fillet surface that the balloon cabin links to each other on, but respectively be provided with the air blast nozzle (two wings, 5 orientation totally 10 wing air blast nozzles) of band control valve.But the control valve other end of left and right each air blast nozzle of wing and the regulation and control airflow line of left and right wing connect, and lead to the outlet side of " the regulation and control flight air-flow " air pump (abbreviation pneumatic pump) in the cabin after left and right regulation and control airflow line converges; The inlet end of this pneumatic pump leads to admission port by pipeline, and admission port is driveed at cabin front end, two places, rear end, but switches by control valve.
Center, top, balloon cabin; On side, forward and backward side, balloon cabin and the fillet surface that forward and backward side, cabin links to each other; But the air blast nozzle (balloon cabin top and side air blast nozzle closed 3 altogether) of a band control valve is also respectively arranged, all connect with separately regulation and control air-flow jet pipe respectively, lead to the outlet side of pneumatic pump after each jet pipe converges.Two admission ports of pneumatic pump are also made air blast nozzle, but switch air inlet or jet by the pneumatic pump control valve.The top air blast nozzle of balloon cabin is upwards jet, and the forward and backward air blast nozzle in side, balloon cabin is jet downwards.
Air-flow pump motor or engine power are 15 kilowatts to 20 kilowatts, and the outlet side of pneumatic pump also is connected with the tracheole of supplying with exchange of air in the cabin.
The balloon cabin vertically is divided into main balloon A group cabin, main balloon B group cabin and secondary balloon cabin again from top to bottom, and these 3 balloon cabin volumes respectively are 1/3rd of balloon cabin cumulative volume.
Balloon cabin cumulative volume is 24693 cubic meters:
B cabin, main balloon A cabin, secondary balloon cabin volume then are 8231 cubic meters, be taken as 8000, per 1 in these 3 balloon subdivisions is all held 27 unit balloons, their filled volume equates, behind most of balloon inflation is cube shaped, and the balloon of small part subdivision boundary vicinity can be irregularly shaped with the border.Unit airballoon cover high-strength high-elasticity low-density film material.Each balloon subdivision is interior except that being equiped with the cabin inner bracing member (serving as with tubing) that guarantees the cabin mechanical strength; Also be equiped with the balloon installation component (thinner tubing serves as with the cross section) in separating element balloon space, each unit balloon all hangs on the member of the corresponding top of space of separating.Part unit balloon has the urgent air bleeder nipple that can open manually when strict seal is urgent at ordinary times.All there is a square cross-sectional passage at each balloon subdivision center in the horizontal direction, and all passages are connected as a single entity and enter the cabin, at the passenger cabin top opening, and the space of passing through as pipeline, circuit, personnel; This passage separates with longitudinal interval again, passes through this passage (hereinafter to be referred as passage) for pipeline, circuit and personnel respectively.The door of opening in the equal directed walk between passage and each cabin, the subdivision.
Soft air cushion bag at the bottom of the passenger cabin is the soft air bag at the bottom of passenger cabin is fixed in the upper end, volume is 3 * 2 * 0.5=3 cubic meter, hold two-layer totally 8 cuboid unit air bags, they adopt and are similar to balloon group and inflation pump ways of connecting, but link to each other with pneumatic pump by lung tubular type tracheal system and house steward's control valve; Its tracheal system also is divided into appendix system, air outlet duct system, and its gas main is walked around passenger cabin afterbody interlayer and entered the cabin.
Connection between the non-integral member of Flight Vehicle Structure mainly adopts rivet to connect, and minority connects the employing Bolt Connection where necessary.The cross section of the member density of Flight Vehicle Structure, member tubing cross section, structural skin, rivet, bolt cross section are calculated definite by the aircraft load (static weight, live load, accidental distributed load) and the mechanical property of materials by engineering mechanics.The quiet gross load load of aircraft is no more than 1480 kilograms.
But the deck of balloon cabin top double as for going sightseeing for the occupant, deck flange has remote-controlled automatic lifting guard rail rod, the mounting deck person all be furnished with safety strap be fixed in " deck ".
Major equipment has pneumatic pump in the cabin, inflation pump, air valve, battery pack, control housing equipment, communication facilities, computing machine, air conditioner.The inflation pump motor power (output) is 1 kilowatt to 3 kilowatts.The battery pack capacity is 30 kilowatt hour to 50 kilowatt hours, and weight is no more than 120 kg.2 branch bronchuses air inlet that use in refrigeration system pneumatic pump plumbing system is drawn and giving vent to anger.
Aircraft of the present invention is also equipped following sensing equipment: front and back, left and right horizontal inclination sensor (representative type adopts communicating pipe liquid level relay), flying speed and direction sensor, several acceleration pick-ups (stress alternation that adopts stress sensitive material degree of will speed up to produce is an electric signal), several are apart from floor level or apart from all directions adjacent barrier rang sensor (adopting laser ranging or supersonic range finder), (air velocity transducer is contained in wingtip and balloon cabin connecting section for several ambient pressures and air velocity transducer, the cabin front end, tail ends etc. are located), several environment electrostatic transducers, the electromechanical appliance state sensor, several outdoor scene camera audioheads.Height sensor, representative type adopts pressure sensor (altimeter) also is provided with GPS and electronic chart in addition.
The passenger cabin front portion is an operator seat, the pilot control basic equipment is bearing circle (lifting, press down controlling aircraft rising, descending motion on the bearing circle), set its come-up and navigation height by altimeter, general navigation is a 1000-3000 rice highly, has on the control panel: a plurality of control keys, speed handwheel (switching use) more, instrument and footbrake device, several panel display screens, video heads, microphone, loud speaker; Computer keyboard, the mouse that can extract out are arranged in the control panel drawer.
Article are used non-metallic elastic material as far as possible in the passenger cabin.Passenger cabin internal volume (not comprising the taper tail) is for long 2.5 meters, and is wide 1.8 meters, high 1.8 meters.3 row's seats are set along its length.But the front row is operator seat and both sides turnup type seat.But middle row is passenger-seat and turnup type seat; Back row is the seat that crouches, and the seat bottom of crouching is apparatus storage boxs such as food, water, water halter, aloft work clothes.In row's back of seat identical with front side plate structure under the chair, all can stir and be backrest (be with and to dig seat corresponding, the prolongation backrest of can open, packing up), side plate, bed board, middle row's seat also can move whole front and back.The left and right wall in cabin has can dig desktop.Passenger cabin sealing connects in the air conditioner, deflation hole is at passenger cabin top front and back ends opening.Back row crouches has the door of gate open to passenger cabin tapered tail branch space after the seat, can enter sanitary accomodation in the passenger cabin taper tail space (long 1 meter, high 1.8 meters, widely be contracted to zero by 2 meters) by door, and the sanitary accomodation toilet is directly to airborne release.The door and the toilet of sanitary accomodation should be respectively at the two ends of Width.Standby small-sized internal combustion engine generator (about 1 kilowatt to 3 kilowatts of capacity), fuel tank penetrate passenger cabin tail cone space from tail cone space, cabin, and oil inlet is at passenger cabin tail cone bottom (width center) opening; Extraneous source of the gas induction tract, extraneous charge power supply and feedwater are also at this interface.Passenger cabin also has rope ladder.
The aircraft of present embodiment adopts the computing machine of equipped with dedicated application software to control (but the standby again cover of electrical equipment is without straight control system of computing machine), actr adopts the multi-stage solid stage relay, is connected with own coding device (integrated circuit), decoder (integrated circuit), channel between solid-state relay and the Computer I/O interface.The terminal solid-state relay is controlled each electrical motor, but each electronic control valve, the servo micromotor of each assisted control.Various sensor signals adopt message handler, and the information-processing circuit that analog information is become digital signal becomes digital signal, behind the encoded again device coding, enter Computer I/O interface.Coder, decoder, message handler, solid-state relay are all in control housing.Height by altimeter (being typically weather gauge) and operating and setting is made comparisons, thereby controls the liter of airship or fall by the barometric distribution (during come-up gas is put to the free expansion balloon, otherwise pressurizeed in the pressure spheroid) of controlling balloon.
Aircraft of the present invention is equipped with radio remote controller, and driver behavior is carried out at any position that remote controller can replace riding manipulation equipment to make chaufeur be in aircraft.
It is as follows with the automatically controlled basic control system that the present invention drives control:
(1) speed control:, be transformed to the speed-regulating instruction (quicken, slow down, stop) of main motor by the flying speed instruction (or pre-set programs) of chaufeur and the flying speed information of sensor.
(2) direction control:, be transformed to the tail vane movement instruction by the heading instruction (or pre-set programs) of chaufeur and the heading information of sensor.
(3) craspedodrome automatic control:, be transformed to the difference speed-regulating instruction (realizing stable rectilinear flight) of left and right main motor by the acceleration information of sensor
(4) highly control:, but be transformed to the starting order of inflation electrical motor and the open and close instruction of corresponding control valve by the flying height instruction (or pre-set programs) of chaufeur and the flying height information of sensor.
(5) steadily automatic control:, but be transformed to the starting order of pneumatic pump and open and close instruction (realization smooth flight) and the diving rudder movement instruction of corresponding control valve by flight inclination information, the wind speed information of sensor.
(6) dodge (be divided into again and dodge, brake) automatic control: by sensor apart from the obstacle information (comprising ground) and the safety distance information of adjusting, but be transformed to the switch order of main motor, pneumatic pump, inflation priming of pump speed-regulating instruction and corresponding control valve, promptly to the reasonable modify instruction of original kinematic velocity, direction.When steering instructions and electrical equipment directly control instruction with dodge instruction when inconsistent the control system mechanism guarantee to obey the latter.
(7) electrical equipment electric current, voltage, heat protection, and other safety guard-safeguard autonomous cruise speed systems.
(8) the automatic flicon of driverless operation:
When no steering instructions, automatically the steering instructions channel is switched to the automated flight information equipment (also being a kind of message handler) of adjusting, at this moment aircraft by former line direction, speed, the highly automatic control of flying and keep straight on, the smooth flight automatic control, dodge automatic control.If direction, speed, highly drift about, dual mode is arranged then: elimination is drifted about, and follows drift.
Present embodiment is applicable to carrying 4 to 5 people (passenger-cargo gross weight is no more than 300 kilograms), and the flight height above sea level is below 3000 meters.
The present invention can also have other embodiment, as: increase overall dimensions and power, increase carrying capacity; Increase by 1,2 of secondary balloon subdivision of isometric(al) and secondary balloon group numbers, make flying height increase to 7000 meters, about 10 kms.Also can reduce overall dimension, power is made individual lift device.In order to increase safety, also safety air bag can be set in the passenger cabin.The present invention can also have the embodiment of other appearance and modeling that adopts different and previous embodiment appearance and modeling.The appearance and modeling of all embodiment of the present invention is carried out certain adjustment after also should calculating, test by aerodynamics.
Employing fuel oil of the present invention is the energy, and adopting combustion engine is that driving engine and embodiment are as described below:
Gas cabin diameter is 20 meters, highly is 5 meters, and all the other sizes are with the embodiment of aforementioned employing solar power.A small amount of solar cell is laid in the gas cabin.Storage battery surpasses 20 kilograms, 10 kilowatt hours.The driving engine of left and right screw propeller (propelling motor) mostly is 20-30 horsepower 4 stroke IC engines, one one of the personal electric generator of their each tractions.The inflation pump engine is the 3-5 kilowatt motor.Pneumatic pump is its engine by the airscrew engine double as, and by its turnover gas of automatic control Air Valve Control, when need not with air-flow regulation and control flight, this air pump is given vent to anger and led to screw propeller over against the wing rear.All the other structures are identical with aforementioned solar power embodiment.It always carries high above 900 kilograms, and carrying goods is no more than 200 kilograms, carrying 2-3 people.
Claims (4)
1. solar power controllable buoyancy, the automatic control helium airship that surely weighs is provided with buoyant device, engine installation, manned or manned double carrying apparatus that the balloon that is lighter than air produces buoyancy; Engine installation: with electrical motor or internal-combustion engine drives screw propeller or pneumatic pump jet supersonic plane is power; Buoyant device and floatage control device: be provided with two groups of buoyancy gas containers at least---software balloon or software, hardware balloon, between the different balloon groups by plumbing connection, on pipeline, connect force lift, be inflation pump and charging and discharging valve, rely on aerating ballon to produce buoyancy, buoyancy gas is implemented in different pressures, the Density Distribution of different balloon groups under the effect of inflation pump pressure, thus automatic guidance buoyancy; The buoyant device bottom connects manned or manned double loading container, and floatage control device is utilization electronic control system or the different densities of computer program control and regulation buoyancy gas between each group balloon and the floatage control device of distribution of pressure realization; It is characterized in that: be provided with " the regulation and control flight air-flow air pump " of realizing the steady weighing apparatus of automatic control, its outlet side by vent pipe and arm lead to be distributed in orientation around the aircraft, with the air blast nozzle of adjustable tolerance valve, its inlet end leads to the admission port of opening to external world by induction tract; The automatic control that is provided with distribution that utilization electronic control system or computer program control " regulation and control flight air-flow air pump " is ejected into extraneous air-flow, the intensity device that surely weighs; Buoyancy gas container balloon is the software balloon that elastic membrane is made, and these balloons are divided into many groups, promptly main balloon A group and main balloon B group and some groups in secondary balloon; Every group of balloon group is made up of several balloons, is called for short the unit balloon, adopts the lung tubular type tracheae of similar animal lung tracheae that the unit balloon is connected to gas main; Lung tubular type tracheae and gas main have two covers, and a cover is the inflation tracheae, and another set of is the exhaust tracheae; Electrical motor in the engine installation has 3 kinds, the electrical motor of gas filed inflation pump electrical motor, promotion propeller between the promptly major and minor balloon, and promotion produces the electrical motor of the air pump of " regulation and control flight air-flow "; The space, balloon cabin that holds all balloons has flat shape, and a large tracts of land flat-top is arranged, and installs solar cell on the flat-top, establishes storage battery and small-sized internal combustion engine generator group as backup power; The all bronchi end connects with balloon, all adopts chicken intestines valve inside to connect; Every gas enters the passage of balloon, and valve inside exports in balloon; Every air-flow goes out the passage of balloon, and valve inside exports outside balloon; But the inflation pump import also has the branched pipe of a band control valve, as the pipeline of extraneous source of the gas air inlet.
2. by the described solar power controllable buoyancy of claim 1, the automatic control helium airship that surely weighs, it is characterized in that: in each unit balloon the air gas sensor is housed all; The terminal bronchus that each unit balloon links to each other all has the air valve that ends of self controllable switching, and the switching that ends air valve is controlled by aircraft autonomous cruise speed system and steering instructions.
3. by the described solar power controllable buoyancy of claim 1, the automatic control helium airship that surely weighs, it is characterized in that its structure is made up of tubing framework and sheet material or film covering, and to form 3 cabins combining as a whole be balloon cabin, cabin, passenger cabin, and the software balloon places in the balloon cabin; Aircraft skin has anti-static coating.
4. by the described solar power controllable buoyancy of claim 1, the automatic control helium airship that surely weighs, it is characterized in that being equipped with the skeleton shell that is fixed on aircraft or with accessory structure that the airframe shell is connected on propeller.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNB2005100412248A CN100422044C (en) | 2005-07-28 | 2005-07-28 | Solar energy buoyancy force controllable, self control balance helium gas aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNB2005100412248A CN100422044C (en) | 2005-07-28 | 2005-07-28 | Solar energy buoyancy force controllable, self control balance helium gas aircraft |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN1765699A CN1765699A (en) | 2006-05-03 |
| CN100422044C true CN100422044C (en) | 2008-10-01 |
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Families Citing this family (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2480804A (en) * | 2010-05-25 | 2011-12-07 | New Create Ltd | Controllable buoyant system |
| CN102541065A (en) * | 2010-12-20 | 2012-07-04 | 西安韦德沃德航空科技有限公司 | High-accuracy low-height control method and system for aircraft |
| CN104913418A (en) * | 2015-06-19 | 2015-09-16 | 陈春灵 | Balloon purifier used in air |
| CN104906929A (en) * | 2015-06-19 | 2015-09-16 | 陈春灵 | Aviationhazepurifier |
| CN105667754B (en) * | 2015-12-31 | 2018-01-30 | 上海交通大学 | Dirigible valve flow optimal control method |
| CN107914861A (en) * | 2017-10-11 | 2018-04-17 | 舒林勇 | Go straight up to electrical propulsion vehicle |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6119983A (en) * | 1999-04-28 | 2000-09-19 | Provitola; Anthony Italo | Airship/spacecraft |
| US6354535B1 (en) * | 1998-12-11 | 2002-03-12 | Southwest Research Institute | Autonomous stratospheric airship |
| US20030146345A1 (en) * | 2001-05-11 | 2003-08-07 | Daihachi Ogawa | Airship |
| FR2836449A1 (en) * | 2002-02-26 | 2003-08-29 | Pateras Pescara De Castellucci | Airship has envelope containing variable volume chambers filled with lighter-than-air gas and adjustable by actuator to form ballast |
| US6739549B2 (en) * | 2000-05-12 | 2004-05-25 | Aerospace Adour Technology | Dirigible balloon rigidified by helium tanks |
-
2005
- 2005-07-28 CN CNB2005100412248A patent/CN100422044C/en not_active Expired - Fee Related
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6354535B1 (en) * | 1998-12-11 | 2002-03-12 | Southwest Research Institute | Autonomous stratospheric airship |
| US6119983A (en) * | 1999-04-28 | 2000-09-19 | Provitola; Anthony Italo | Airship/spacecraft |
| US6739549B2 (en) * | 2000-05-12 | 2004-05-25 | Aerospace Adour Technology | Dirigible balloon rigidified by helium tanks |
| US20030146345A1 (en) * | 2001-05-11 | 2003-08-07 | Daihachi Ogawa | Airship |
| FR2836449A1 (en) * | 2002-02-26 | 2003-08-29 | Pateras Pescara De Castellucci | Airship has envelope containing variable volume chambers filled with lighter-than-air gas and adjustable by actuator to form ballast |
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| CN1765699A (en) | 2006-05-03 |
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