CN105649775A

CN105649775A - System taking compressed air as force applying source, operation method for system and airplane

Info

Publication number: CN105649775A
Application number: CN201610125197.0A
Authority: CN
Inventors: 王力丰
Original assignee: Individual
Current assignee: Individual
Priority date: 2016-03-04
Filing date: 2016-03-04
Publication date: 2016-06-08
Anticipated expiration: 2036-03-04
Also published as: CN105649775B

Abstract

The invention provides a system taking compressed air as a force applying source. The system comprises a compressed air jet engine (14) which takes high-pressure and ultrahigh-pressure compressed air as a jet working medium, a compressed air production and supply device (48) for greatly producing, storing and supplying high-pressure and ultrahigh-pressure compressed air in an economic and environment-friendly manner and a controller, wherein the compressed air jet engine (14) is arranged on aviation, aerospace and navigation equipment such as airplanes, rockets, submarines, trains and the like as well as moving carriers which travel on the ground; the compressed air jet engine (14) comprises an air tank (9) used for storing the compressed air and a jet engine (16) used for generating power; the jet engine (16) comprises a primary jet engine (14) for generating thrust and a plurality of secondary jet engines for reducing air (or seawater) resistance as well as air (or seawater) sliding friction force generated in travelling of the moving carriers, so as to be beneficial for increasing the speed and saving energy, as well as increasing lifting force of wings of the airplane, so as to be beneficial for short-distance or vertical take-off, landing and the like of the airplane.

Description

Take pressurized air as system and method, the aircraft in force source

Technical field

The present invention relates to technical field of engines, special to provide a kind of take pressurized air as system and method, the aircraft in force source.

Background technology

Engine (Engine), i.e. engine, is a kind of the machine that can be converted into mechanical energy of other form, can be born in Britain, successively experienced by external combustion engine and internal combustion engine development stage. The fuel of external combustion engine in the external firing of engine, such as steamer; The fuel of oil engine burns at engine interior, such as petrol motor, diesel engine and jet engine. In fact, no matter outside or inside at engine is burnt, and the effect of burning is all produce " High Temperature High Pressure " gas in engine; Analyze the direct effect of " high temperature " and " high pressure ", insider knows, the effect of " high temperature " is mainly to raise according to the in-engine gaseous tension of thermodynamic principles, the effect of " high pressure " is then directly to do mechanical work relevant, and in engine, the height of gaseous tension determines the size of its output torque (such as steamer, petrol motor, diesel engine) or thrust (such as jet engine).

Just like steamer, petrol motor, diesel engine taking " high pressure " gas produced that burns as Power output moment of torsion, patent " economic utilization pressurized air is the system of the car power source " (patent No.: 201520365135.8 authorized, contriver: Wang Lifeng) disclose a kind of air compression power device (comprising vehicle-mounted storage tracheae and cylinder combine engine), using " high pressure " pressurized air as propulsion source output torque, for generation of driving power.

And just like jet engine taking " high pressure " gas produced that burns as Power output thrust, the present invention is intended to inquire into and exports thrust using " high pressure " pressurized air as propulsion source, it is provided that a kind of take pressurized air as the system in force source.

About prior art jet engine, there is multiple mode classification, usually can be divided into aero-jet engine and the big class of rocket engine two. Wherein aero-jet engine is at this taking turbo-jet engine (Turbojet) as representative, and this type of also can more specifically be subdivided into centrifugal-flow jet engine, axial flow turbine jet engine, turbofan engine, ram jet, pulse jet engine etc.; Rocket engine comprises chemical energy rocket engine, electric energy rocket engine, nuclear energy rocket engine, sun power rocket engine etc.; the development of current chemical energy rocket engine is comparatively ripe; use wider; namely usual rocket engine refers to chemical energy rocket engine, can be divided into liquid rocket engine and solid propellant rocket.

Wherein, 1. turbo-jet engine comprises, uptake, and air enters next structure pneumatic plant through this, 2., pneumatic plant, it is made up of stator (stator) blade and rotor (rotor) blade stagger, one pair of stator vane and spinner blade are called one-level (usually having 8-12 level), and stator is fixed in engine frame, and rotor is connected with turbine with rotor spindle, 3., combustion chamber and turbine, air enters combustion chamber and fuel oil mixed firing after pneumatic plant compresses, produce high temperature and high pressure gas expansion work, and flow through turbine and promote turbine (most modern opportunity of combat installs after-burner additional to improve engine thrust after turbine), 4., jet pipe (nozzle, or claim mouth), its convergence, convergence convergent divergent channel shape and structure determine the state of the air-flow of final discharge. liquid rocket engine is the rocket engine using liquid propellant, generally comprise 1., promote mainly injector, it it is the significant components that the chemical energy of liquid propellant (fuel and oxygenant) is transformed into propulsive force, by propellant nozzle, (fuel and oxygenant enter combustion chamber through propellant nozzle atomised jet to the composition such as combustion chamber and nozzle component, in combustion chamber mixed firing, produce high temperature and high pressure gas to discharge from nozzle component), 2., Propellant Supply system, by fuel and oxygenant tank, fuel and oxygenant pump, fuel and the composition such as oxygenant transfer line and valve, 3., enngine control system, by computer control unit and the sensor measuring each parameter of engine system, all kinds of valve and setter etc. are formed jointly, and 4., portfire (is lighted a fire when propelling agent enters combustion chamber) at once. solid propellant rocket is the rocket engine using solid propellant, by 1., medicine post, 2., combustion chamber, 3., nozzle component and 4., portfires etc. form, medicine post mixes the hollow circular cylinder made by solid propellant (fuel and oxygenant) in advance (hollow part is firing level, its cross section shape has circle, star etc.) directly load and put into storing chamber, during work, storing chamber is exactly combustion chamber, propelling agent produces high temperature and high pressure gas in this burning, nozzle component is made up of jet pipe and Thrust vector control system, portfire is usually made up of electrically-fired pipe and gunpowder box and is used for lighting medicine post. rocket engine have employed above-mentioned special structure one semi-enclosed combustion chamber connecting spray nozzle (convergent-divergent channel), such structure flows only to combustion gas outlet to jet pipe aspect, other directions are restricted, therefore, combustion gas can set up certain pressure (1��20MPa) in combustion chamber, and the outer surface pressure of nozzle exit only 0.1MPa (sea level normal atmosphere) or to be less than 0.1MPa be even zero (high-altitude is exoatmosphere even), so combustion gas is under the effect of inside and outside differential pressure, flowing to jet pipe, high-velocity jet is gone out. " High Temperature High Pressure " gas produced in above-mentioned jet engine combustion chamber, the reactive force being subject to the applying of engine combustion chamber interior walls under " high pressure " flows to jet pipe, according to newton the 3rd law, engine reactive force must be given when gas departs from engine, this reactive force is exactly the thrust of engine, and described " high pressure " pressure is more high, usual motor performance is also more good, and thrust is more big.

The self-contained propelling agent of prior art jet engine (fuel or fuel oxidizer) and the relevant facility of burning thereof, complex structure heavier to engine complete machine, restive, cost is higher, development & production difficulty is relevant greatly. the self-contained fuel oil of such as aero-jet engine, and the multistage compressor for draw air from air is arranged need to be carried as oxygenant and fuel oil reactive combustion, multistage turbine, multistage fans etc. not only increase weight but also greatly increase research and development manufacture difficulty, its difficulty reaches such degree: the Rolls-Royce limited-liability company of Jin You Britain that first-class level turbofan engine technology is grasped in the whole world is called for short sieve sieve (Rolls-RoyceGroupplc, LSE:RR), U.S. Pood and Hui Te Nipuhui (Pratt&Whitney) and General Electric's aviation (GEAviation) Deng Ji company. " father of space travel " Qi Aoer Koffsky (�� o �� o �� o �� o �� , the performance of rocket 1857-1935) is proposed to weigh with the ratio of " mass ratio " the i.e. original quality of rocket and the remaining mass of rocket at first, he calculates the mass ratio using nitric acid to add the rocket that Hydrazine propellant reaches the first cosmic velocity is 23.5, namely the rocket of gross weight 100 tons needs 96 tons of propelling agents, if adding terrestrial gravitation factor, then mass ratio will be bigger, namely mass ratio will be less to useful load with taking off. useful load is improved with the research and development of mass ratio of taking off at aerospace field, two patents " high initial speed the projectile transmitting device " (patent No.: 201420224494.7 authorized, contriver: Wang Lifeng) and " goods Rotary transport flywheel and control method thereof " (patent No.: 201110351539.8, contriver: Wang Lifeng) individually disclose a kind of high initial speed projectile transmitting device and a kind of goods Rotary transport flywheel and control method thereof, respectively can with high initial speed launch payload in flywheel high speed rotating, with the difficulty that the weight reducing useful load is brought to transport, they relate generally to the utilization of the flywheel principle outside jet engine technical field and technique means thereof. how reducing the mass ratio of rocket, or usually climb over how to improve rocket useful load and mass ratio of taking off, be one has in the industry problem to be solved always. from the data of some prior art launch vehicle useful load with mass ratio of taking off, one spot can be peeped: Israel's comet number (Shavit) useful load accounts for quality 0.7% of taking off, India's SSO (Sun Synchronous Orbit) satellite rocket (PolarSatelliteLaunchVehicle) satellite accounts for the 1% of quality of taking off, Japan's H rocket series (HLaunchVehicles) useful load accounts for quality 0.7% of taking off, U.S.'s Saturn number (Saturn) useful load accounts for the 1.6% of quality of taking off, Russia's proton number (Proton) satellite accounts for the 0.3% of quality of taking off, the useful load of China's No. five, Long March accounts for quality about 2% etc. of taking off, the ratio tangible quite high (about 98-99%) of quality of taking off shared by the facility that obvious propelling agent and burning thereof are correlated with.

And pressurized air can also produce thrust is a general knowledge out of question. in existing rocketry, pressurized air is mainly used in the cold air rail control propelling technology of one of rail control propelling technology. rail control advances that technology generally includes chemistry propelling, cold air advances, electricity propellings, nuclear propulsion, momentum conversion advance and without working medium propulsion system etc., complete three kinds of functions: gesture stability (keeps aircraft to point to the direction of setting), track keeps (maintenance aircraft run on the track specified) and Orbit Transformation (aircraft is moved to another track specified) from current track. wherein cold air propulsion system, namely the cold air rail control of one of rail control propelling technology advances technology, generally adopt pressurized gas (such as air, nitrogen, helium, carbonic acid gas etc.) as injection working medium, typical cold air propulsion system exports thrust scope 0.05N��22N usually, the thrust needed for Spacecraft Attitude Control, track maintenance and Orbit Transformation offer, moment, and cold air propulsion system adopts MEMS (MicroelectromechanicalSystem) technology to be easy to realize miniatureization of system, integrated, form micro propulsion device and along with microtronics, micromachine, the basic industry such as lightweight composite materials and Ultra-precision Turning develop rapidly can complete installation install on dividing plate, it is convenient to install and replace, and successfully it is applied to small as cold air micromass culture system, (satellite by weight > I000kg is called large satellite usually for the practice of the cold air propulsion system of micro-nano satellite and research, the satellite that weight is 500kg��1000kg is called middle satellite, the satellite that weight is I00kg��500kg is called moonlet, the satellite that weight is I0kg��I00kg is called micro-satellite, and the satellite of Ikg��I0kg is called Nano satellite, the satellite of 0.1kg��Ikg is called skin satellite, the satellite of < 0.1kg be called fly satellite). prior art cold air propulsion system, advance technology not utilize the pressurized air of a large amount of high-voltage and ultra-high to produce the demand of rocket main thrust from its functional character analysis as a kind of rail control on the one hand, also utilize, without as the main jet engine of a kind of rocket, the technology characteristic sum report that a large amount of high-voltage and ultra-high pressurized air is the source that exerts a force from prior art cold air propulsion system structure signature analysis on the other hand simultaneously.

Even if having reason it is contemplated that do not rely on self-contained oxidized burning " high temperature " generations " high pressure " gas, engine also can provide thrust taking self-contained a large amount of high-voltage and ultra-high pressurized air as spraying working medium. Wherein machine load can be laid in enough high-voltage and ultra-high pressurized air and is supplied to engine as the device of working medium, it is called for short " gas tank " at this, the storage air pipe structure function Curve guide impeller in addition of the vehicle-mounted pressurized air involved by patent " economic utilization pressurized air is the system of car power source " (patent No.: 201520365135.8, contriver: Wang Lifeng) can be used for reference; And utilize the device (as promote mainly injector: expansion chamber, jet pipe) of high-voltage and ultra-high pressurized air expansion work, the structure function Curve guide impeller in addition of injector (combustion chamber, jet pipe) can be promoted mainly with reference to conventional art liquid rocket engine. This kind, taking high-voltage and ultra-high pressurized air as the engine of working medium, provides thrust according to Newton's law (mainly the 3rd law, and the 2nd law), can be used for such as motion carriers such as aircraft, rocket, naval vessels, vehicles.

Contrast conventional art jet engine, its spout should not closely lean on, more can not face toward motion carrier itself, because the possible ablation motion carrier of scorching hot combustion gas of its spout ejection is surperficial or at least increases the thermal fatigue of its structure, future trouble is serious, and it is not high like that from the gas temperature of pressurized air jet engine spout ejection, its high velocity air ejected can quite closely lean on, be parallel to motion carrier surface, can directly brush the upper surface of wing, it is even possible that in certain distance, certain angle scope tiltedly facing to vehicle head injection high velocity air, motion carrier is without the worry of ablation damage. and conventional art engine spray pipe only appears at motion carrier rear portion, the conventional installation position of the inferior sustainer of the wing usually owing to closely correlating with fuel combustion, and pressurized air jet engine jet pipe is possible not only to appear at motion carrier rear portion, the conventional installation position of the inferior sustainer of the wing, in fact can be arranged at almost any position in need, motion carrier periphery, high-voltage and ultra-high compressed air inlet pipe only need to be communicated to there. like this, on the one hand according to " father of hydromeehanics " Denier Bernoulli Jacob (DanielBernoulli, " air-flow or flow rate of water flow increasing 1700-1782) proposed, pressure reduce " bernoulli principle (Bernoulli'sprinciple), and Condar effect (CoandaEffect, also known as attached wall effect) etc., the jet engine jet pipe of pressurized air can be arranged on motion carrier front, body week, high velocity air is also sprayed in the positions such as the wing is front at these positions, involve the change of corresponding local aerodynamic force, gas density falls sharply, pressure drop, motion carrier motion can be produced the impact of corresponding hydromeehanics, the jet engine of these pressurized air also can be endowed except having aforementioned thrust and reduce operation resistance such as atmospheric drag and friction resistance, improve the functions such as wing lift, on the other hand pressurized air jet engine jet pipe can be arranged on spout below airframe and produces certain thrust vertically upward downwards and be beneficial to airplane short takeoff, or arrange below airframe afterbody or both sides spout forward with certain speed jet-stream wind, make the aircraft buffer deceleration in traveling, it is beneficial to short in landing. it is comprehensive, multi-functional.

Obviously, for " gas tank " of the machine load pressurized air of the jet engine of pressurized air in proposal, indispensable a kind of be that it is produced, stores, the device of supply high-voltage and ultra-high pressurized air, be called for short " pressurized air produce for device " at this, for " gas tank " of the jet engine of pressurized air is inflated. And known, the cost producing high-voltage and ultra-high pressurized air is very high, and main system transforms my heat energy because of about the 90% of the electric energy consumed in production. The structure function that the recycling of this part heat energy can use for reference the product storage device of a kind of boiler formula high pressure compressed air involved by front patent " economic utilization pressurized air is the system of car power source " (patent No.: 201520365135.8, contriver: Wang Lifeng) is improved, is designed; In addition, abbreviation " pressurized air produces for device " in improvement, design, due to as the reserves of pressurized air in " gas tank " of the jet engine of pressurized air of the motion carriers such as aircraft, pressure all much larger than with higher than the reserves of automobile mounted accumulator unit pressurized air, pressure, it is necessary to produce and store the higher high-voltage and ultra-high pressurized air of greater amount, pressure with being adapted to economy with to " gas tank " pressurization inflation of the jet engine of pressurized air; But also need to solve pressurization charging efficiency problem, such as in " pressurized air produces for device " " gas tank " pressurization inflation to the jet engine of pressurized air, the design pressure of " gas tank " is also very high, when " gas tank " that compressed air pressure in " pressurized air produces for device " drops to engine jet with pressurized air is equal, " pressurized air produces for device " also there is a large amount of unserviceable problem of high pressure compressed air. This just must a kind of " pressurized air produces for device " and " gas tank " of the jet engine of pressurized air design mutually matchingly, design becomes a system comprising " gas tank " of " pressurized air produce for device " and the jet engine of pressurized air, and a kind of take pressurized air as the system in source of exerting a force.

Summary of the invention

(1) technical problem solved

It is an object of the invention to provide a kind of can utilize to economy high-voltage and ultra-high pressurized air, using the jet engine of pressurized air as the system in the force sources such as the motion carrier propulsive force of the aviations such as aircraft, rocket, submarine, train, space flight, navigation and ground run, speed-raising and increase lift.

(2) technical scheme

For achieving the above object, the present invention provides a kind of take pressurized air as the system in force source, it is characterised in that, comprise taking high-voltage and ultra-high pressurized air as spraying the jet engine of pressurized air of working medium, pressurized air produces for device and controller;

The jet engine of described pressurized air is arranged on motion carrier; The jet engine of described pressurized air comprises gas tank and jet engine; Described gas tank is pressurized air storage vessel, comprises multiple gas storage pipe, and described gas storage pipe is for laying in and supplies the pressurized air needed for described jet engine; Described jet engine comprises main jet gas engine and the jet engine of multiple pair; Described main jet gas engine is used for the pressurized air to input from described gas storage pipe as injection working medium, and described motion carrier is granted the thrust moved forward; Multiple jet engine of described pair comprises the first secondary jet engine of the surrounding being separately positioned on described motion carrier, the jet engine of second mate, the 3rd secondary jet engine, the 4th secondary jet engine and the 5th secondary jet engine, for the pressurized air to input from described gas storage pipe as injection working medium and by with described promote mainly injection engine coordinates and to the propelling movement on described motion carrier formation target direction;

Described pressurized air produces and comprises high-voltage and ultra-high air compressor and large-sized boiler formula pressurized vessel for device; The operating pressure of described high-voltage and ultra-high air compressor is close, equal or exceed 100Mpa, under the control of described controller to the pressurization inflation of described large-sized boiler formula pressurized vessel; Described large-sized boiler formula pressurized vessel for the production of and storing compressed air, with under the control of described controller to multiple described gas storage pipe pressurization inflation;

Described controller is used for being formed by described motion carrier the propelling movement of target direction by the open and close controlling to described main jet gas engine, the first secondary jet engine, the jet engine of second mate, the 3rd secondary jet engine, the 4th secondary jet engine and the 5th secondary jet engine.

Preferably, described main jet gas engine, the first secondary jet engine, the jet engine of second mate, the 3rd secondary jet engine, the 4th secondary jet engine and the 5th secondary jet engine include the inlet pipe, expansion chamber and the De Laval noz(zle) that are made up of resistance to high pressure, lighter material;

Described inlet pipe is connected between described gas storage pipe and described expansion chamber; The surrounding of described inlet pipe is provided with inlet pipe week electric heater, and the pressurized air of all electric heaters of described inlet pipe for heating in described inlet pipe, so that the air pressure in described inlet pipe raises; The pressurized air of described storage tracheal strips is injected in described expansion chamber by the mouth of emanating of described inlet pipe;

The expansion chamber room wall of described expansion chamber is equipped with gas injects setter, described gas inject setter for regulating and controlling described inlet pipe inject the amount of setting pressure to the pressurized air in described expansion chamber so that the air pressure in described expansion chamber maintains setting pressure; The surrounding of described expansion chamber is provided with expansion chamber room wall electric heater, and for making, the pressurized air entered in described expansion chamber is pressurizeed described expansion chamber room wall electric heater by heating;

The sectional area of described De Laval noz(zle) first diminishes from front to back and becomes big again; The end of described expansion chamber and the gradually contracting portion of described De Laval noz(zle) are connected as a single entity, described expansion chamber compressed air accelerates through described De Laval noz(zle) gradually contracting portion, De Laval noz(zle) throat and De Laval noz(zle) gradually wealthy portion under stress, and final high velocity air is sprayed by De Laval noz(zle) spout.

Preferably, described first secondary jet engine is arranged on the front of the head of motion carrier, described first secondary jet engine has the profile of raindrop shape, its windward area be less than the area windward of corresponding described motion carrier head, described first secondary jet engine comprises the first inlet pipe, the first expansion chamber and the first De Laval noz(zle), also comprises a firm tubular structure, and described first secondary jet engine is fixed on the front of this motion carrier head by described firm tubular structure, described first inlet pipe is positioned within described firm tubular structure and is supported by described firm tubular structure, the end of described first expansion chamber and the gradually contracting portion of the first De Laval noz(zle) are connected as a single entity, described first De Laval noz(zle) is overall in Rafael nozzle shape structure from front to back, described first inlet pipe is stretched out to front from the head of motion carrier together with described firm tubular structure, and to the described in forward position first secondary jet engine shaft to central authorities sequentially through the first secondary jet engine spout, the first De Laval noz(zle) gradually wealthy portion, the first De Laval noz(zle) throat, described first De Laval noz(zle) gradually contracting portion and described first expansion chamber and be fixedly connected with the expansion chamber head inwall of described first expansion chamber, described expansion chamber head inwall be equipped with the first inlet pipe emanate mouth and gas injects setter, described first expansion chamber compressed air accelerates through described first De Laval noz(zle) gradually contracting portion under stress, first De Laval noz(zle) throat, finally by the gradually gap injection around motion carrier head to rear along a conical side surface between wealthy portion and the conical huge portion of firm tubular structure of described first De Laval noz(zle), the bus of described conical side surface is equivalent to the line from described first De Laval noz(zle) throat to this motion carrier head periphery, to form a cone-shaped low pressure area in this motion carrier head front, the atmospheric drag run forward for reducing this motion carrier or seawater resistance,

Described first secondary jet engine is also for granting the tractive force that described motion carrier moves forward.

Preferably, the quantity of the described jet engine of second mate is multiple, multiple described second mate's jet engine circumference is arranged at all sides of described motion carrier, described motion carrier is moved forward towards the rear injection high velocity air of described motion carrier and grants thrust by multiple described second mate jet engine spout, and the high velocity air that ejects of described second mate jet engine spout parallel and close to the surface of motion carrier, reduce the sliding-frictional resistance between when motion carrier runs forward and the external world to form one layer of low-pressure air layer around motion carrier.

Preferably, described motion carrier is provided with one or more described gas tank, and the multiple described gas storage pipe in gas tank described in each is long tubular structure, has the round shape gas storage tube wall being made up of resistance to high pressure, lighter material;

Multiple described gas storage pipe is parallel-laid into bundle arrangement, and cross section is overall in plum flower-like structure; Gas storage pipe described in each is equipped with the intake valve and vent valve that open and close separately by the control of described controller;

Around described gas storage pipe, be provided with standby electricity well heater, described standby electricity well heater for working overloadingly for some reason at the jet engine of described pressurized air, whole described gas storage pipe compressed air pressure all lower than setting lower limit time start;

One end of multiple described gas storage pipe many siphunculus of being all bullied with are connected, described in be bullied many siphunculus converge be one by tracheae; The other end of multiple described gas storage pipe all communicates with a many siphunculus of gas transmission, and multiple paths merge of the many siphunculus of described gas transmission are a pneumatic tube; Described gas storage pipe is connected with described inlet pipe by described pneumatic tube;

Described pipe of being bullied is for accepting the pressurized air pressurizeing and being filled with from described large-sized boiler formula pressurized vessel.

Preferably, for the described large-sized boiler formula pressurized vessel of the gas storage pipe pressurization inflation of described gas tank comprises large-scale flowing water water tank and some the Large Copacity tubular vessel and the collection pipes that are placed in described water tank;

Some described Large Copacity tubular vessels are divided into the comb of many group tiling shapes, and the two ends of the multiple described comb in same group are connected to a described collection pipe; Comb shape described in wherein said Large Copacity tubular vessel, has its entrance and exit; The described pipe that integrates being connected with the entrance of the Large Copacity tubular vessel in often group is as inlet end collection pipe, and the described pipe that integrates being connected with the outlet of the Large Copacity tubular vessel in often group is as exit end collection pipe; The entrance of described Large Copacity tubular vessel is provided with inlet valve, and the outlet of described Large Copacity tubular vessel is provided with outlet valve; Described inlet end collection pipe is provided with a collection tube inlet and collection tube inlet valve thereof, and described exit end collection pipe is provided with a collection pipe outlet and collection pipe outlet valve thereof;

The design volume of described Large Copacity tubular vessel and pressure are greater than and respectively higher than the design volume of described gas storage pipe and pressure; The described Large Copacity tubular vessel of part is serpentine tube, and described serpentine tube is the tubular structure of repeatedly roundabout extension in the plane that described comb tiles;

The described inlet end collection pipe on the described comb being laid in same plane, described serpentine tube and both sides thereof and exit end collection pipe form a Large Copacity tubular vessel plane; A described large-scale flowing water water tank is provided with multiple described Large Copacity tubular vessel plane, inlet end collection pipe in the described Large Copacity tubular vessel plane of many groups was connected by inlet end collection pipe communicating pipe, and share a described collection tube inlet, it is provided with collection tube inlet valve in described collection tube inlet; Exit end collection pipe in each described Large Copacity tubular vessel plane was connected by exit end collection pipe communicating pipe, and shared a described collection pipe outlet, and described collection pipe is provided with collection pipe outlet valve in exporting;

Described large-scale flowing water water tank is provided with the water-in for flowing into water coolant and the water outlet for flowing out hot water, and described water outlet is connected with the direct buried insulating pipe in central heating system;

Air compressor exhaust port and the described collection tube inlet of described high-voltage and ultra-high air compressor removably connect, for the pressurization inflation of described Large Copacity tubular vessel.

Present invention also offers a kind of aircraft, comprising as above take pressurized air as the system in force source, and wherein said first secondary jet engine is arranged on plane nose front, and the described jet engine of second mate is arranged on all sides of airframe; And the quantity of described 3rd secondary jet engine is multiple, multiple described 3rd secondary jet engine is symmetricly set on the front of the leading edge of aircraft both sides wing; The spout of described 3rd secondary jet engine is to the wing injection high velocity air at rear, and the direction of high velocity air that the spout of described 3rd secondary jet engine ejects is consistent relative to the air flow line of wing with when taking off sliding race; Described 3rd secondary jet engine is used for improving wing lift when aircraft short range or VTOL, also for granting corresponding to the thrust moved forward by described aircraft that described 3rd secondary jet engine spout jet flow stream reactive force is made a concerted effort.

Preferably, described 4th secondary jet engine is arranged on the lower section of described airframe, for the back lower place of aircraft or front lower place jet-stream wind, so that described aircraft to be granted the reactive force of forward upward or back upper place; Described 5th secondary jet engine is arranged on immediately below the afterbody of described aircraft or is symmetricly set on the both sides of afterbody, for the reverse injection high velocity air in described aircraft flight direction, so that described aircraft to play the effect of buffer deceleration.

Present invention also offers the operation method of a kind of system taking pressurized air as force source, comprise the following steps:

Step one: by high-voltage and ultra-high air compressor, large-sized boiler formula pressurized vessel is carried out pressurization and inflate;

Collect tube inlet valve, all Large Copacity tubular vessel inlet valve and outlet valve in this course to open, and collect pipe outlet valve and close;

Electric motor utilizes valley electricity or the power supply not easily stored such as wind-powered electricity generation, sun power at night, by high-voltage and ultra-high air compressor through the collection tube inlet valve of air compressor exhaust port, collection tube inlet and unlatching thereof, the inlet valve of all Large Copacity tubular vessel entrance and unlatching thereof and all the outlet of Large Copacity tubular vessel and the outlet valve opened thereof to the inlet end collection pipe being arranged in large-scale flowing water water tank, all Large Copacity tubular vessel and the pressurization inflation of exit end collection pipe;

The air pressure of the gas that controller control is filled with from air compressor exhaust port and tolerance are adapted to the discharge of the hot water that water coolant and the water outlet from the inflow of large-scale flowing water water tank inlet flows out, make at inlet end collection pipe, whole Large Copacity tubular vessel and exit end collection pipe occur together in pressurized air production process the heat that produces in time cooled water-band walk, the hot water that water coolant is heated to be proper temperature flows out towards direct buried insulating pipe for central heating from water outlet in good time, until at inlet end collection pipe, still a large amount of pressurized air of normal temperature are substantially kept to reach design high pressure in whole Large Copacity tubular vessel and exit end collection pipe, store for subsequent use,

Collecting tube inlet valve, all Large Copacity tubular vessel inlet valve and outlet valve when the time comes to close, collection pipe outlet valve continues to close;

Step 2: inflated to gas tank by large-sized boiler formula pressurized vessel;

Collecting tube inlet valve and all Large Copacity tubular vessel inlet valve closedowns in this course, in whole Large Copacity tubular vessel outlet valve, only single difference is opened and all the other are closed in order, and collection pipe outlet valve is opened; Collection pipe outlet with gas storage pipe in gas tank share dock by tracheae, in gas tank each gas storage pipe intake valve only single difference open in order and all the other closedowns; What the collection pipe outlet valve of the outlet valve that controller control pressurized air is opened from a certain Large Copacity tubular vessel in an orderly manner through opening, collection pipe outlet, gas tank, gas storage pipe shared is filled with pressurized air by the gas storage pipe intake valve of tracheae and a certain unlatching to this gas storage pipe;

In the process that a Large Copacity tubular vessel is inflated to gas storage pipe one by one, air pressure declines gradually, so that it is equal to take turns to the air pressure that when inflating to certain gas storage pipe, in this Large Copacity tubular vessel, air pressure has dropped to the storage tracheal strips being bullied increases gradually afterwards, at this moment this Large Copacity tubular vessel is unable continues to this gas storage pipe gas transmission that this gas storage intraductal atmospheric pressure is not yet raised to design requirements again, controller controls each Large Copacity tubular vessel outlet valve and the opening and closing of each gas storage pipe intake valve, make the existing Large Copacity tubular vessel declined of air pressure to the low gas storage pipe inflation relatively of not yet inflation or pressure, although making to rise to some extent but the gas storage that is not yet raised to design requirements is in control the Large Copacity tubular vessel with initial high pressure or relatively high pressure inflates to it through inflation pressure,

Wherein, input gas storage pipe process at pressurized air from Large Copacity tubular vessel, for gas storage pipe internal memory air pressure, there is in rising certain intensification trend, but decline and have cooling trend for being input to its pressure of this part pressurized air storing up tracheal strips from Large Copacity tubular vessel, controller control pressurized air inputs flow, the speed of gas storage pipe from Large Copacity tubular vessel, making gas storage intraductal atmospheric pressure in this course be elevated to design requirements steadily and heat up trend and cooling trend relative equilibrium, temperature is substantially stable;

Step 3: gas tank is supplied gas to jet engine;

In jet engine working process, in gas tank, all gas storage pipe intake valves cut out, in gas tank, each gas storage pipe vent valve is only single or several unlatching in order respectively and all the other are closed; Vent valve, pneumatic tube that controller control pressurized air is opened from wherein a certain or several gas storage pipes in an orderly manner are sent into and are attached thereto the inlet pipe connect, so via being arranged on the mouth of emanating of expansion chamber head, gas injects setter and injects expansion chamber;

Inlet pipe caliber is smaller compared with gas storage pipe caliber, the all electric heaters of inlet pipe and the work of expansion chamber room wall electric heater, the pressurized air entering expansion chamber is heated by appropriateness, is kept elevated pressures, and under high pressure flow into successively the De Laval noz(zle) that is connected as a single entity with expansion chamber end gradually contracting portion, through De Laval noz(zle) throat and by De Laval noz(zle) gradually wealthy portion ejection, air-flow greatly accelerates, producing huge thrust, high velocity air also involves the change of corresponding local aerodynamic force.

(3) useful effect

The present invention provide a kind of taking pressurized air be force source system, wherein the jet engine of pressurized air to carry the high-voltage and ultra-high pressurized air of the gas tank conveying of pressurized air storage vessel as injection working medium generation power as machine, without the need to the facility that self-contained conventional art jet fuel and burning thereof are relevant, thus complete machine subtracts heavily, structure simplifies, cost is lower, is beneficial to research and development, production, control and application.

In the present invention close with operating pressure, equal or exceed 100Mpa high-voltage and ultra-high air compressor to described Large Copacity tubular vessel pressurization inflation so that high-voltage and ultra-high pressurized air provides the gas storage pipe of described gas tank for subsequent use; The electric motor of described high-voltage and ultra-high air compressor utilizes and comprises valley electricity and the wind-powered electricity generation work that not easily stores at night; A large amount of heat that 90% electric energy that a large amount of high-voltage and ultra-high pressurized air occurs together in production process in described Large Copacity tubular vessel, that be equivalent to consume transforms and the water coolant generation heat exchange flowing into described large-scale flow cistern, be heated to form hot water for central heating. Thus accomplish that production compressed air pressure height, utilization of power are economic, cleaning heat supply and energy-saving and emission-reduction simultaneously.

The described gas tank of the jet engine of pressurized air of the present invention, gas storage pipe, induction pipe, expansion chamber and De Laval noz(zle) mesohigh ultra-high voltage compressed air pressure can close, equal or exceed 100MPa, its value can be greater than the pressure (1��20MPa) of prior art rocket burning indoor fuel gas, can be main jet gas engine and higher forces is provided, thrust-weight ratio is higher, " mass ratio " is lower, is beneficial to and improves useful load and mass ratio of taking off.

Motion carrier body surface, peripheral facilities, road surface or deck will be caused ablation to damage by the scorching hot combustion gas sprayed far below conventional art jet engine due to pressurized air of the present invention jet engine spout injection high velocity air temperature, its injection high velocity air can be utilized to involve innings territory aerodynamic force change occurs, the jet engine of multiple pair can be arranged on the motion carrier fronts such as aircraft, rocket, train, submarine and all sides, for reducing described motion carrier traveling atmospheric drag or seawater resistance, sliding friction power, be conducive to speed-raising, energy-conservation; Also can be arranged on below aircraft wing front, body and tail for improving aircraft wing lift, raise airframe and make aircraft buffer deceleration, be conducive to aircraft short range/VTOL.

Accompanying drawing explanation

Fig. 1 is the schematic diagram of the structure of the jet engine of embodiment of the present invention pressurized air;

Fig. 2 is in Fig. 1I placeThe schematic perspective view of cross section stravismus;

Fig. 3 is the schematic side view of the secondary jet engine of the embodiment of the present invention first;

Fig. 4 is that in Fig. 3, II place's cross section faces enlarged diagram;

The jet engine of pressurized air that Fig. 5 is the embodiment of the present invention arranges schematic side view aboard;

Fig. 6 is that embodiment of the present invention pressurized air produces the structural representation for device;

Fig. 7 is the front elevational schematic of embodiment of the present invention Large Copacity tubular vessel plane.

Reference numeral:

1, gas storage pipe; 2, gas storage tube wall; 3, by tracheae; 4, it is bullied many siphunculus; 5, intake valve; 6, vent valve; 7, the many siphunculus of gas transmission; 8, pneumatic tube; 9, gas tank; 10, gas storage pipe first; 11, gas storage Guan Yi; 12, gas storage pipe third; 13, gas storage Guan Ding; 13a, gas storage pipe penta; 14, the jet engine of pressurized air; 15, standby electricity well heater; 16, jet engine; 17, inlet pipe; 17a, the first inlet pipe; 18, expansion chamber; 18a, the first expansion chamber; 19, De Laval noz(zle); 19a, the first De Laval noz(zle); 20, De Laval noz(zle) gradually contracting portion; 20a, the first De Laval noz(zle) gradually contracting portion; 21, De Laval noz(zle) throat; 21a, the first De Laval noz(zle) throat; 22, De Laval noz(zle) gradually wealthy portion; 22a, the first De Laval noz(zle) gradually wealthy portion; 23, De Laval noz(zle) spout; 24, high velocity air; 25, emanate mouth; 26, gas injects setter; 27, expansion chamber head; 28, expansion chamber room wall; 29, inlet pipe week electric heater; 30, expansion chamber room wall electric heater; 31, the first secondary jet engine; 32, motion carrier head; 32a, line; 33, firm tubular structure; The conical huge portion of 33a, firm tubular structure; 34, firm tubular structure and inlet pipe end; 35, mouth is emanated and gas injects setter; 37, expansion chamber head inwall; 39, the first secondary jet engine spout; 40, cone-shaped low pressure area; 41, main jet gas engine; 42, the jet engine of second mate; 43, raindrop shape profile; 44, the 3rd secondary jet engine; 45, wing upper surface; 46, the 4th secondary jet engine; 47, the 5th secondary jet engine; 48, pressurized air produces for device; 49, large-sized boiler formula pressurized vessel; 50, high-voltage and ultra-high air compressor; 51, electric motor; 52, air compressor exhaust port; 53, collection pipe; 54, large-scale flowing water water tank; 55, water-in; 56, water outlet; 57, direct buried insulating pipe; 58, water coolant; 59, hot water; 60, Large Copacity tubular vessel; 61, Large Copacity tubular vessel tube wall; 62, Large Copacity tubular vessel first; 63, Large Copacity tubular vessel second; 64, Large Copacity tubular vessel third; 65, inlet end collection pipe; 66, tube inlet is collected; 67, tube inlet valve is collected; 68, exit end collection pipe; 69, pipe outlet is collected; 70, pipe outlet valve is collected; 71, inlet end collection pipe communicating pipe; 72, exit end collection pipe communicating pipe; 73, Large Copacity tubular vessel plane; 74, comb; 75, serpentine tube; 76, Large Copacity tubular vessel entrance; 77, Large Copacity tubular vessel outlet; 78, Large Copacity tubular vessel inlet valve; 79, Large Copacity tubular vessel outlet valve.

Embodiment

Following examples are for illustration of the present invention, but are not used for limiting the scope of the invention.

In describing the invention, it is necessary to explanation, unless otherwise clearly defined and limited, term " connection " should be interpreted broadly, such as, it is possible to is be fixedly connected with, it is also possible to is removably connect, or connects integratedly; Can be directly be connected, it is also possible to be indirectly connected by intermediary; Can be electrical connection, it is also possible to be communication connection. For the ordinary skill in the art, it is possible to particular case understands above-mentioned term concrete implication in the present invention.

As shown in figs. 1-7, the present embodiment describe a kind of taking pressurized air be force source system, it is characterized in that, comprise the jet engine 14 of pressurized air taking high-voltage and ultra-high pressurized air (hereinafter referred to as pressurized air) as injection working medium, economy ground produces the device abbreviation pressurized air storing a large amount of pressurized air of supply and produces for device 48, and controller;

The jet engine 14 of described pressurized air is arranged on the motion carrier of aviation, space flight, navigation and the ground runs such as aircraft, rocket, submarine, train, and the jet engine of described pressurized air 14 comprises gas tank 9 and jet engine 16; Described gas tank 9 is pressurized air storage vessel, and it comprises some gas storage pipes 1, for laying in and supply the pressurized air needed for described jet engine 16; Described jet engine 16 comprises main jet gas engine 41 and the jet engine of multiple pair; Described main jet gas engine 41 can be arranged on aircraft tail, the inferior conventional art jet engine of wing installation position aboard, or it is arranged on the rear end of the motion carriers such as rocket, submarine, train, for the pressurized air to input from described gas tank 9 as spraying working medium, the motion carrier of above-mentioned aviation, space flight, navigation and ground run is granted the thrust moved forward; Multiple jet engine of described pair is the first secondary jet engine 31 at each position of motion carrier being arranged on aviation, space flight, navigation and the ground runs such as aircraft, rocket, submarine, train, the secondary jet engine 44 of the jet engine of second mate the 42, the 3rd, the 4th secondary jet engine 46, the 5th secondary jet engine 47, for the pressurized air to input from described gas tank 9 as spraying working medium, play the effect that the motion carriers such as auxiliary aircraft run;

Described pressurized air produces and comprises high-voltage and ultra-high air compressor 50 and large-sized boiler formula pressurized vessel 49 for device 48; The operating pressure of described high-voltage and ultra-high air compressor 50 is close, equal or exceed 100Mpa, with being used under the control of described controller to the pressurization inflation of described large-sized boiler formula pressurized vessel 49; The pressurized air produced in described large-sized boiler formula pressurized vessel 49 and store can pressurize under the control of described controller and be filled with the gas storage pipe 1 of described gas tank 9, utilizes for described major and minor jet engine;

Described controller is the automatic control system comprising computer, sensor, all kinds of valve and setter thereof, is that the system components in force source is connected taking pressurized air with described, for control described taking pressurized air be exert a force source system coordination, work in order; Wherein it is mainly used in being formed by described motion carrier the propelling movement of target direction by the open and close controlling to described main jet gas engine, the first secondary jet engine 31, the secondary jet engine 44 of the jet engine of second mate the 42, the 3rd, the 4th secondary jet engine 46 and the 5th secondary jet engine 47.

As shown in Figure 1, Figure 2 with shown in Fig. 5, described jet engine 16, no matter described main jet gas engine 41 or the jet engine of each pair, includes inlet pipe 17, pressurized air expansion chamber hereinafter referred to as expansion chamber 18 and De Laval noz(zle) 19 (DeLavalnozzle), is made up of resistance to high pressure, lighter material;

Described inlet pipe 17 is connected between described gas storage pipe 1 and described expansion chamber 18, and the length of described inlet pipe 17 is relevant with the position at described expansion chamber 18 place with the described gas storage pipe 1 at its two ends with trend, relevant with each described major and minor jet engine position; Being provided with inlet pipe week electric heater 29 around described inlet pipe 17, the pressurized air in described gas storage pipe 1 injects described expansion chamber 18 by the mouth 25 of emanating of described inlet pipe 17;

In the expansion chamber room wall 28 of described expansion chamber head 27, face is equipped with pressurized air gas and is injected setter 26, described mouth 25 of emanating forms described gas to inject the primary element of setter 26, and described gas is injected setter 26 and regulated and controled in described inlet pipe 17 and injected described expansion chamber 18 by the described inlet pipe week electric heater 29 mildly heating pressurized air that thus pressure improves with certain flow; Described expansion chamber 18 is round shape, also can be spherical or annular, its volume size is to ensure that the pressurized air injecting in it from described inlet pipe 17 maintains design pressure and is as the criterion, it is provided with expansion chamber room wall electric heater 30 around described expansion chamber 18 to the pressurized air mildly heating entering described expansion chamber 18, it is beneficial to maintain compressed air pressure and at described expansion chamber 18 expansion work; Described expansion chamber 18 end and described De Laval noz(zle) are gradually connected as a single entity in contracting portion 20;

The sectional area of described De Laval noz(zle) 19 (also known as the gradually wealthy jet pipe that gradually contracts) first diminishes and then becomes big, gradually it is made up of in wealthy portion 22 Jian Suobu 20 throat 21, it is one " flow velocity enhancer ": first compressed air enters gradually contracting portion 20 under expansion chamber 18 pressure effect, follow " when fluid moves in pipe at this, little place, cross section flow velocity is big, cross section general goal flow velocity is little " principle, air-flow constantly accelerates, when arriving throat 21, flow velocity can exceed velocity of sound, and the fluid of transonic speed is no longer followed when moving, and " little place, cross section flow velocity is big, cross section general goal flow velocity is little " principle, but it is on the contrary, cross section is more big, flow velocity is more fast, speed at gradually wealthy portion 22 air-flow is accelerated to supersonic speed further, spray with pole high flow rate,

Described in the present embodiment, jet engine 16 spout injection high velocity air 24, produces huge thrust, for making described main jet gas engine 41 that the motion carrier of aviation, space flight, navigation and the ground runs such as aircraft, rocket, submarine, train is granted propulsive force, the high velocity air 24 of described jet engine 16 spout injection simultaneously involves aerodynamic force change occurs for innings territory and this gas flow temperature sprays far below conventional art jet engine scorching hot combustion gas can not to motion carrier body surface (and peripheral facilities, road surface or deck) cause ablation to damage, the first secondary jet engine 31 can be made to be arranged on aircraft, rocket, submarine, the aviations such as train, space flight, the atmospheric drag (or seawater resistance) advanced for reducing described motion carrier in motion carrier head 32 front of navigation and ground run, it is arranged on the sliding friction power of ship body and seawater when submarine ship body all sides (not shown) travels for reducing submarine with the jet engine of second mate, also the 3rd secondary jet engine 44 can be made, 4th secondary jet engine 46 and the 5th secondary jet engine 47 are separately positioned on aircraft wing front, with tail for improving aircraft wing lift below body, raise airframe and make aircraft buffer deceleration.

As shown in Fig. 3, Fig. 4 and Fig. 5, described first secondary jet engine 31 is arranged on the front of the head 32 of motion carrier, described first secondary jet engine 31 has the profile 43 of raindrop shape, its windward area be less than corresponding described motion carrier head 32 area windward, described first secondary jet engine 31 comprises the first inlet pipe 17a, the first expansion chamber 18a and the first De Laval noz(zle) 19a, also comprise a firm tubular structure 33, it is fixed on this motion carrier head 32 front by the first secondary jet engine 31 described in described firm tubular structure 33, described first inlet pipe 17a is positioned within described firm tubular structure 33, and is supported by described firm tubular structure 33, the end of described first expansion chamber 18a and the gradually contracting portion 20a of the first De Laval noz(zle) are connected as a single entity, described first De Laval noz(zle) 19a is the overall gradually contracting gradually wealthy structure in Rafael nozzle shape from front to back, described first inlet pipe 17a stretches out to front from the head 32 of motion carrier together with described firm tubular structure 33, and to the described in forward position first axial central authorities of secondary jet engine 31 sequentially through the first secondary jet engine spout 39, first De Laval noz(zle) gradually wealthy portion 22a, the first De Laval noz(zle) throat 21a, described first De Laval noz(zle) gradually contracting portion 20a and described first expansion chamber 18a, this firm tubular structure and inlet pipe end 34 are fixedly connected with described expansion chamber head inwall 37 then, the expansion chamber head inwall 37 of described first expansion chamber 18a be equipped with the first inlet pipe emanate mouth and gas injects setter 35, described first expansion chamber 18a compressed air accelerates through described first De Laval noz(zle) gradually contracting portion 20a under stress, first De Laval noz(zle) throat 21a, finally by the gradually gap injection around motion carrier head to rear along a conical side surface between wealthy portion 22a and the conical huge portion 33a of firm tubular structure of described first De Laval noz(zle), the bus of described conical side surface is equivalent to the line 32a from described first De Laval noz(zle) throat 21a to this motion carrier head 32 periphery, to form a cone-shaped low pressure area 40 in this motion carrier head 32 front, the atmospheric drag run forward for reducing this motion carrier or seawater resistance,

First secondary jet engine 31 described in the present embodiment is mainly used in reducing the atmospheric drag (or seawater resistance) that this motion carrier runs forward, this motion carrier runs forward thrust mainly from described main jet gas engine 41, the size to " traction force " that namely this motion carrier is moved forward by described first secondary jet engine 31 propulsive force forward having the reactive force of described first secondary jet engine 31 spout jet flow stream with joint efforts, described controller controls.

The quantity of the described jet engine of second mate 42 is multiple, circumference is arranged at all sides of described motion carrier, described motion carrier is moved forward towards the rear injection high velocity air of described motion carrier and grants thrust by multiple described second mate's jet engine 42 spout, and the high velocity air that ejects of described second mate's jet engine 42 spout parallel and close to the surface of motion carrier, reduce the sliding-frictional resistance between when motion carrier runs forward and the external world to form one layer of low-pressure air layer around motion carrier;

The described jet engine of second mate is arranged at submarine (not shown) body week, can have multiple, their spout closely leans on to rear and is parallel to hull surface injection high velocity air, this high velocity air covers submarine body surface, flow velocity is little to submarine body surface positive pressure greatly, and loose, volume can be blown from the seawater being close to submarine ship body, around submarine ship body, form one layer of low-pressure air layer, thus reduce when this submarine runs forward and the sliding-frictional resistance of surrounding seawater; And the jet engine of second mate described in these to rear jet flow stream to submarine travel also grant certain thrust.

Such as Fig. 1, shown in Fig. 5, described 3rd secondary jet engine 44 is arranged on aircraft wing leading edge front, symmetrical, one or more described 3rd secondary jet engine 44 can be established in every side, their spout is to the wing injection high velocity air 24 at rear, the direction of air-flow and the angle of wing chord when when the direction of its spout injection high velocity air and the angle of wing chord (leading edge of wing and the line of trailing edge) are equivalent to take off sliding race, the angle of attack (Angleofattack) of wing takes off sliding race, in other words the direction of described 3rd secondary jet engine 44 spout injection high velocity air is consistent relative to the air flow line of wing with when taking off sliding race, like this, the high velocity air of described 3rd secondary jet engine 44 spout injection increases wing upper and lower surface pressure difference (wing upper surface 45 gas velocity high pressure is low), the high velocity air of described 3rd secondary jet engine 44 spout injection also impacts the wing lower surface with certain angle of attack, and the wing upper surface 45 that the air-flow of described 3rd secondary jet engine 44 spout injection is close to protrusion flows to the downward high-speed motion of the air-flow leaving wing, therefore according to bernoulli principle, newton the 3rd law, described 3rd secondary jet engine 44 spout of Condar effect (CoandaEffect) so sprays high velocity air and has the effect improving wing lift,

The lift formula of aircraft can be expressed as usually:

Y = {C_{\frac{1}{2}}}_{y} {ρ&upsi;}^{2} S

(wherein: Y is wing lift, C_yFor lift coefficient, �� is density of air, and �� is the speed of air-flow relative to wing, and S is wing area)

At this, independent development of the present invention is a kind of, and to be applied to the simple mathematical of the short distance of aircraft or VTOL theoretical, wherein by air-flow relative to the speed �� of wing referred to as " gas speed ", aircraft uses V relative to the speed of runway referred to as " machine speed "_aRepresent, and propose a new term " gas speed machine speed ratio " accordingly, represent with B:

B=gas speed/machine speed=��/V_a

Under normal circumstances, during proximate calculation, �� V_a, usually take off and add in ski-running race when �� reaches the liftoff speed of its minimum safe (aircraft starts lift-off), B=��/V_a�� 1;

And for having the aircraft of described 3rd secondary jet engine 44, wing from described 3rd secondary jet engine 44 spout to its rear injection high velocity air flow velocity at this referred to as jet speed, be set to V_e, therefore machine speed V is equivalent to for the aircraft gas speed �� with described 3rd secondary jet engine 44_aWith jet speed V_eSum, ��=V_a+V_e;

Very high from described 3rd secondary jet engine 44 (Fig. 5) Laval nozzle 19 (with reference to figure 1) ejection air-flow velocity, velocity of sound (>=340.29m/s is reached/exceedes as above-mentioned, be equivalent to >=1225km/h), the takeoff speed of super any aircraft far away is (generally speaking, the takeoff speed of aircraft is at 200-350km/h), the aircraft just start of a race is even not yet sliding runs, and only the 3rd secondary jet engine 44 spout is to the jet speed V of the wing injection high velocity air at its rear_eGas speed �� (namely air-flow is relative to the speed of wing) formed reaches, exceedes this liftoff speed of aircraft minimum safe (aircraft starts lift-off), " gas speed machine speed ratio " B ratio (B=��/V now_a) greatly, machine speed V_aVery little, namely take off aircraft in sliding race very short distance and go up to the air, it is achieved short distance/take off vertically;

When needing short range/vertical landing, airfield approach, enters near, glides, even up, and receives " throttle " to idling ... aircraft speed (machine speed V_a) continue to reduce to wing lift be not enough to balance aircraft weight before the 3rd secondary jet engine 44 work and spray high velocity air with it to wing and maintain wing lift (with jet speed V_eMaintain gas speed ��), thus improve " gas speed machine speed ratio ", slowly can slow down above predetermined landing strip flight or be close to of aircraft hovers over aerial, and at this moment controller controls that the 3rd secondary jet engine 44 spout is jet to slow down gradually, jet fast V_eGradually falling i.e. gas speed �� gradually to fall, gradually drop to wing lift to gas speed �� and be not enough to balance aircraft weight, aircraft descends slowly and lightly and contacts to earth, and the 3rd secondary jet engine 44 stops work, and aircraft lands with its leaving velocity to slide and runs short range to stopping, and completes short range/vertical landing;

3rd secondary jet engine 44 described in the present embodiment has short range/VTOL need or open during other Special Circumstances at aircraft under the control of described controller, and it is very little to control the propulsive force that its output rating makes it that aircraft is generally executed flight forward within the specific limits; Described controller can control the propulsive force appropriateness increasing that this aircraft is executed flight forward by described 3rd secondary jet engine 44 when necessary.

As shown in Figure 1, shown in Figure 5, described 4th secondary jet engine 46 is arranged on its spout below airframe ablation road surface or deck can not grant the reactive force of forward upward or back upper place to the aircraft back lower place or front lower place jet-stream wind to aircraft, and described 5th secondary jet engine 47 is arranged on immediately below aircraft afterbody or tail zygomorphy the distributes jet effect that aircraft flight has certain buffer deceleration in its spout reversible flight direction;

4th secondary jet engine 46 spout described in when being necessary in the aircraft short range/process that takes off vertically, to the reactive force of airframe back lower place jet-stream wind to the certain forward upward of aircraft, assists described 3rd secondary jet engine 44 to work to shorten further to take off and sliding run distance;

Against flying, direction is jet makes aircraft slow down to 5th secondary jet engine 47 spout described in when being necessary in aircraft short range/vertical landing process, and described 4th secondary jet engine 46 spout to airframe front lower place jet-stream wind to the certain reactive force rearwardly and upwardly of aircraft, coordinating described 3rd secondary jet engine 44 to work to assist further, aircraft is slow above predetermined landing strip flies or hover, shorten aircraft landing cunning race distance;

4th secondary jet engine 46, the 5th secondary jet engine 47 described in the present embodiment have at aircraft under the control of described controller to be opened when short range/VTOL needs or other Special Circumstances, and their output rating is limited to cooperation, assist described 3rd secondary jet engine 44 to complete aircraft short range/VTOL.

As shown in Figure 1, Figure 2, shown in Fig. 3 and Fig. 5, the motion carrier of aviation, space flight, navigation and the ground runs such as aircraft, rocket, submarine, train can be arranged and the one or more described gas tank 9 that described major and minor jet engine mates mutually; Multiple described gas storage pipe 1 in gas tank 9 described in each is long tubular structure, its round shape gas storage tube wall 2 is made up of resistance to high pressure, lighter material, and its caliber is less than the internal diameter of the identical capacity of conventional art with the compressed air reservoir of pressure therefore it can deposit the higher pressurized air of pressure by pipe in identical material situation;

Multiple described gas storage pipe 1 can arrange by front and back parallel longitudinal one-tenth bundle, if its cross section is plum blossom shape, is called plum blossom pipe or is referred to as several holes plum blossom pipe more accurately, such as seven apertures in the human head plum blossom pipe; Wherein gas storage pipe 1 described in each respectively has its intake valve 5 and vent valve 6 to have a gas storage unit that can open and close separately of one's own; Namely multiple described gas storage pipe 1 is equivalent to multiple gas storage unit, and they can be called gas storage pipe first 10, gas storage pipe second 11, gas storage pipe the third 12, gas storage pipe fourth 13, holder pipe penta 13a according to sequence ... their caliber, length are relevant with design pressure, the capacity of described gas tank 9;

It is provided with standby electricity well heater 15 around described gas storage pipe 1, described standby electricity well heater 15 does not start usually, work overloadingly for some reason at the jet engine 14 of described pressurized air, whole described gas storage pipe 1 compressed air pressure all lower than a certain setting lower limit certain in emergency circumstances, described well heater for subsequent use 15 is emergency start in good time, heat described gas storage pipe 1, its pipe compressed air is raised by pressure while of heat temperature raising, now described inlet pipe week electric heater 29, described expansion chamber room wall electric heater 30 is also emergent improves Heating temperature, export from described gas storage pipe 1 to maintain, the pressurized air injecting described expansion chamber 18 through described inlet pipe 17 keeps certain temperature and pressure, the power of the jet engine 14 of described pressurized air is maintained within for some time,

Described gas storage pipe 1 also can with the space of the framework of the motion carrier at its place, tendency, or bending spiraling draw close together, or nature of taking advantage of a situation stretches, and described gas storage pipe 1 is arranged on close to the position at jet engine 16 place mated with its phase in the conceived case, as with as described in the 3rd jet engine 44 phase mate as described in gas storage pipe 1 can be arranged on the space among aircraft wing;

Multiple described gas storage pipe 1 shares one by tracheae 3, namely the front of their respective intake valves 5 many siphunculus 4 of being bullied with respectively communicate, described many siphunculus 4 of being bullied converge be one by tracheae 3, such as seven intake valves 5 of above-mentioned seven apertures in the human head plum blossom pipe just communicate with seven pipes in eight siphunculus, this eight siphunculus vacant pipe be that this seven apertures in the human head plum blossom pipe shares by tracheae 3; A pneumatic tube 8 is shared with the multiple described gas storage pipe 1 of reason, namely their respective vent valves 6 communicate with a many siphunculus 7 of gas transmission respectively, it is a pneumatic tube 8 that the many siphunculus 7 of described gas transmission converge, such as seven vent valves 6 of above-mentioned seven apertures in the human head plum blossom pipe just communicate with seven pipes in another eight siphunculus, this eight siphunculus vacant pipe be this seven apertures in the human head plum blossom pipe share pneumatic tube 8;

Wherein, described gas tank 9 can with a described jet engine 16, described main jet gas engine 41 or secondary jet engine, mate air feed mutually, and at this moment the inlet pipe 17 of pneumatic tube 8 engine 16 jet with this that each gas storage pipe 1 in this gas tank 9 shares directly is connected; Described gas tank 9 also can with multiple described jet engine 16, described main jet gas engine 41 or secondary jet engine, mating air feed mutually, the pneumatic tube 8 that at this moment each gas storage pipe in this gas tank 91 shares can bifurcated be that the inlet pipe 17 of the multiple described jet engine 16 that multiple pipeline mates with above-mentioned phase again is connected respectively;

What in described gas tank 9, multiple described gas storage pipe 1 shared is subject to tracheae 3 for accepting the pressurized air pressurizeing and being filled with from described large-sized boiler formula pressurized vessel 49.

As shown in Figure 6,7, for the described large-sized boiler formula pressurized vessel 49 of the gas storage pipe 1 pressurization inflation of described gas tank 9 comprises large-scale flowing water water tank 54 and some the Large Copacity tubular vessels 60 being placed in described water tank; Described Large Copacity tubular vessel 60 is tubular, its tube wall 61 is made by resistance to high pressure, lighter material, its caliber is less than the internal diameter of the conventional art compressed air reservoir of identical capacity and pressure, and in identical material situation, it can tolerate higher pressurized air relative to holding pressure;

In described large-scale flowing water water tank 54, multiple described Large Copacity tubular vessel 60 is laid into comb 74, their two ends are connected with collection pipe 53, every root comb 74 i.e. each Large Copacity tubular vessel 60 has its entrance 76 and outlet 77 and inlet valve 78 thereof and outlet valve 79, the collection pipe being connected with their entrance is called inlet end collection pipe 65, the collection pipe being connected with their outlet is called exit end collection pipe 68, described inlet end collection pipe 65 and exit end collection pipe 68 are respectively equipped with a collection tube inlet 66 and collection pipe outlet 69, and it is respectively equipped with corresponding collection tube inlet valve 67 and collection pipe outlet valve 70 at described collection tube inlet 66 and collection pipe outlet 69,

Wherein single described Large Copacity tubular vessel 60 design volume and pressure equalization is not greater than and higher than the design volume of single described gas storage pipe 1 and pressure, when the capacity of a certain described comb 74 is not enough to meet design requirement, high pressure is born and should not select to expand caliber to expand capacity owing to must ensure that tube wall is competent, when needing the design requirements being reached dilatation by extension tube, this comb can be substituted it is arranged between described inlet end collection pipe 65 and exit end collection pipe 68 by serpentine tube 75 1 kinds repeatedly roundabout pipe in the plane that described comb 74 tiles, described serpentine tube 75 is also with the entrance at its two ends, inlet valve and outlet, outlet valve is connected with described inlet end collection pipe 65 and exit end collection pipe 68 respectively,

It is laid in inlet end collection pipe 65 and exit end collection pipe 68 described in the described comb 74 of a plane, described serpentine tube 75 and both sides thereof and forms a Large Copacity tubular vessel plane 73; A described large-scale flowing water water tank 54 can be provided with multiple described Large Copacity tubular vessel plane 73, wherein the inlet end collection pipe 65 in each described Large Copacity tubular vessel plane 73 is connected by inlet end collection pipe communicating pipe 71 mutually, and shares a described collection tube inlet 66 and corresponding collection tube inlet valve 67 thereof; Exit end collection pipe 68 in each described Large Copacity tubular vessel plane 73 is connected by exit end collection pipe communicating pipe 72 mutually, and shares a described collection pipe outlet 69 and corresponding collection pipe outlet valve 70 thereof;

Wherein, comb 74 described in every root or serpentine tube 75 are equivalent to the relatively independent pressurized air of a Large Copacity tubular vessel 60 that is one and produce storage unit, when there are many described combs 74 and/or serpentine tube 75 namely is equivalent to have multiple described Large Copacity tubular vessel 60, they can be called Large Copacity tubular vessel first 62 according to sequence, Large Copacity tubular vessel second 63, Large Copacity tubular vessel the third 64 ... multiple described Large Copacity tubular vessel 60 can also arrange by other forms in described large-scale flowing water water tank 54, as in round tube type water tank, they can be connected and are arranged between the inlet end collection pipe of volution and exit end collection pipe,

Described large-scale flowing water water tank 54 is provided with water-in 55 so that water coolant 58 flows into, with water outlet 56 so that direct-buried thermal insulation pipe 57 is connected with central heating system under hot water 59 flows out earthing;

The air compressor exhaust port 52 of described high-voltage and ultra-high air compressor 50 can be flexibly connected with described collection tube inlet 66, the electric motor 51 of described high-voltage and ultra-high air compressor 50 utilize electric energy comprise night low ebb and not easily store wind-powered electricity generation work, by described collection tube inlet 66 to each described Large Copacity tubular vessel 60 pressurization inflation; There is heat exchange with the water coolant 58 flowing into described large-scale flowing water water tank 54 in a large amount of heat occurred together in generation process in a large amount of pressurized air Large Copacity tubular vessel 60 described in these, described water coolant 58 flows out after being heated to form hot water 59 and imports direct buried insulating pipe 57 for central heating; The a large amount of pressurized air produced in Large Copacity tubular vessel 60 described in these can be stored in wherein, and described collection pipe outlet 69 can be filled with pressurized air with being flexibly connected by tracheae 3 of the gas storage pipe 1 in described gas tank 9 to the described gas storage pipe 1 in described gas tank 9 when needed;

Described large-sized boiler formula pressurized vessel 49 can be arranged on ground, underground, on large ship, vehicle is truck such as, on train and on large-scale carrier, wherein it is arranged on vehicle, described large-sized boiler formula pressurized vessel 49 on large-scale carrier is in lifting or can water in emptying described large-scale flowing water water tank 54 before starting, outside the protecting sheathing that large-scale flowing water water tank 54 casing described in removal replaces a kind of compact light weight covers in described Large Copacity tubular vessel 60, it is called tubular vessel freight container (not shown), it is convenient to transport, for being arranged on aircraft, rocket, train, the described gas storage pipe 1 of the described gas tank 9 of the jet engine of described pressurized air 14 on the motion carriers such as submarine is inflated,

Wherein, described tubular vessel freight container is set and makes it as the aerial filling machine of one on large-scale carrier, other can be equipped with the jet engine of pressurized air 14 and implement aerial aerating as the aircraft of the machine of being bullied; Described aerial filling machine machine carries the outlet of the described collection pipe in described tubular vessel freight container 69 and leans out to square tube type after machine and end can tapered sleeve in umbrella shape, described machine head of being bullied is equipped with telescopic be bullied inserting tube (not shown) its continue by tracheae 3 phase with the described of gas storage pipe 1 in described gas tank 9 on this machine, it is bullied after machine and filling machine two machine " junction ", inserting tube of being bullied described in treating is connected with the tapered sleeve of described umbrella shape and automatically locks, gas circuit is connected automatically, complete " docking ", aerial filling machine starts the machine of being bullied aerial " aerating ", then two machines " dismission ".

As shown in Fig. 3, Fig. 5, the jet engine 14 of described pressurized air can be arranged on the motion carrier of aviation, space flight, navigation and the ground runs such as aircraft, rocket, submarine, train;

Wherein aboard, described main jet gas engine 41 and described first secondary jet engine 31, the secondary jet engine 44 of the jet engine of second mate the 42, the 3rd, the 4th secondary jet engine 46, the 5th secondary jet engine 47 can choice for use or use with the collocation of certain conventional art engine: 1., described first secondary jet engine 31, the jet engine 42 of described second mate for reducing aircraft flight atmospheric drag and with the sliding friction power of air, be conducive to airplane accelerating, energy-conservation; 2., the 3rd secondary jet engine 44, the 4th secondary jet engine 46 can be used for aircraft short range/take off vertically, the 3rd secondary jet engine 44, the 4th secondary jet engine 46, the 5th secondary jet engine 47 can be used for aircraft short range/vertical landing; 3rd secondary jet engine 44, the 4th secondary jet engine 46, the 5th secondary jet engine 47 before aircraft wing, under fuselage, the above-mentioned functions position such as tail is fixedly installed, or movable setting, namely these engines at ordinary times and are converged in wing and/or fuselage to reduce expose movable parts during flight, only reach above-mentioned functions position when there being aircraft short range/VTOL to need and start; 3., have and aerial aerating when needing, can be carried out; 4. work overloadingly, for some reason when making described gas storage pipe 1 compressed air pressure lower and can start well heater 15 for subsequent use, within for some time, maintain the power of the jet engine 14 of described pressurized air; 5., if desired, as when as described in main jet gas engine 41 fault time, the 3rd secondary jet engine 44 power can be strengthened and maintain one section of flight; 6., in emergency circumstances the 3rd secondary jet engine 44, the 4th secondary jet engine 46, the 5th secondary jet engine 47 cooperatively interact and make the safe short range/vertical landing of aircraft in a certain spacious region; 7. and described main jet gas engine 41 and described first secondary jet engine 31, the secondary jet engine 44 of the described jet engine of second mate the 42, the 3rd all described aircraft can be moved forward and grant thrust;

Described main jet gas engine 41 and described first secondary jet engine 31, the described jet engine of second mate can be arranged on rocket, described main jet gas engine 41 expansion chamber 18 compressed air design pressure can remarkable >=20MPa, higher than rocket burning indoor fuel gas top pressure, and structure is simple, light, be conducive to reducing " mass ratio " of rocket; Described first secondary jet engine 31, the described jet engine of second mate are conducive to reducing rocket and fly atmospheric drag and the sliding friction power with air before atmospheric layer, make rocket speed-raising, energy-conservation; And described rocket all can be moved forward and grant thrust by described main jet gas engine and described first secondary jet engine 31, the described jet engine of second mate;

Collocation selected by described main jet gas engine 41 and described first secondary jet engine 31, the jet engine of second mate or they and certain conventional art engine, is configurable on submarine; Described first secondary jet engine 31, for blowing loose, volume from hindering seawater in submarine head front, forms a cone-shaped low pressure area 40 (even vacuum zone) in submarine head front; The described jet engine of second mate for blow loose, volume from the seawater being close to submarine ship body, one layer of low-pressure air layer is formed around submarine ship body, make the submarine in the seawater high pressure of script depths just like travelling in low-pressure air, be conducive to reducing the sliding friction power of seawater resistance and ship body and seawater, make submarine speed-raising, energy-conservation, and quiet; Described submarine all can be moved forward and grant thrust by described main jet gas engine and described first secondary jet engine 31, the described jet engine of second mate;

Collocation selected by described main jet gas engine 41, described first secondary jet engine 31, the jet engine of second mate or they and certain conventional art engine, is configurable on train, described first secondary jet engine 31, for forming a cone-shaped low pressure area 40 (even vacuum zone) in described train head front, is conducive to reducing atmospheric drag, makes train speed raising, energy-conservation, multiple described second mate jet engine spout, towards the rear injection high velocity air of described train (not shown), forms one layer of low-pressure air layer around described train body and reduces when described train runs forward and the sliding-frictional resistance of air, wherein, both sides are had to the train of the outstanding structure of aerofoil profile shape, multiple described jet engine of second mate is arranged on the front of the outstanding structure of described aerofoil profile shape, and described aerofoil profile shape outstanding body structure surface injection high velocity air is comprised to train body surface, rear, although the upper surface of the outstanding structure of described aerofoil profile shape is streamlined projection but the very slight lift produced to the outstanding structure of this aerofoil profile shape of its distance outstanding to both sides is not enough to described train to lifting in the air, but alleviate described train to the positive pressure of track because high velocity air brushes the lift in the outstanding body structure surface generation of described aerofoil profile shape, thus reduce the rolling resistance power of wheel and track in the advance of described train, be conducive to described train energy-saving, speed-raising, and described train is all moved forward and grants thrust by described main jet gas engine, the first secondary jet engine 31, the jet engine of second mate, and the above-mentioned described 5th secondary jet engine for aircraft afterbody can be set at described last vehicle of train, it can be used for described train deceleration, parking to described train driving direction reverse jet.

The system that the present embodiment a kind of take pressurized air as force source has following advantage:

1) namely turn into for without combustion engine, avoiding and relevant side effect and the puzzlement of burning from oil engine from conventional art jet engine to the jet engine 14 of pressurized air of the present invention

1. avoid self-contained fuel and the relevant facility of burning thereof, make that complete machine subtracts heavily, structure simplifies, cost is lower, be beneficial to research and development, productions, control and apply.

2. the technical barrier relevant to combustion high temperature is avoided:

Conventional art jet fuel can reach about 3500K (��5800 ��F) in combustion chambers burn temperature, often exceed the fusing point (graphite and tungsten except) of jet pipe and combustor material, it is necessary to guarantee that these materials can not burn, melt or seethe with excitement, combustion chamber is under certain hoop stress, due to high-temperature work environment so that it is the tensile strength of structured material significantly reduces, and also makes its design pressure that may bear be subject to a definite limitation, also need to adopt cooling system to prevent material overheated, (room wall has ablator to the conventional type of cooling as ablation cooling, can constantly absorb heat and come off), radiation cooling (making room wall reach white heat state with radiations heat energy), sink type cools (by one propelling agent, normally liquid hydrogen, fall down along room wall), re-generatively cooled (propelling agent first flows through the cooling jacket in the wall of room before combustion), (propellant jet device is by special arrangement for Water-Curta in Cooling, so that the fuel gas temperature around the wall of room reduces), (room wall is soaked film cooling by liquid propellant, liquid evaporation endothermic makes it cooling), Sweat coolling (special shape of film cooling) etc., make engine structure complicated unavoidably, weightening finish ... these difficult problems of conventional art jet engine are relevant to combustion high temperature, and they and the jet engine 14 of pressurized air of the present invention do not hinder.

3. owing to no longer spraying high-temperature fuel gas, replace the high velocity air that injection temperature is relatively quite low, ablation will be caused to damage motion carrier, therefore the present invention can utilize each pair jet engine spout injection high velocity air to involve an innings territory aerodynamic force change, it is achieved reduce air (or seawater) resistance and with air (or seawater) sliding-frictional resistance, improve the functions such as wing lift.

2) produce for high-voltage and ultra-high pressurized air economy, environmental protection

Conventional art jet engine (containing aero-jet engine, rocket engine) combustion fuel produces high temperature and high pressure gas expansion work, thus produce three main problems: resource consumption, environmental pollution, greenhouse gas emission, wherein aircraft and rocket operating altitude height, the oxynitride of generation more easily damages the ozone layer. With the jet engine 14 actuation movement carrier of pressurized air of the present invention, comprise aircraft, rocket, submarine, train etc., taking high-voltage and ultra-high pressurized air as power, zero release and nothing very resource consumption when their aviations, space flight, navigation, ground run;

Even if discharge when investigating initial production high-voltage and ultra-high pressurized air and cost: the air compressor of high-voltage and ultra-high described in the present invention 50 (operating pressure close, equal or exceed 100Mpa) can utilize night valley electricity or the electric energy not easily stored such as wind-powered electricity generation, sun power described pressurized air produced pressurize inflation for device 48; And a large amount of heat energy that high-voltage and ultra-high air occurs together in production process in described large-sized boiler formula pressurized vessel (49) (being equivalent to 90% electric energy consumed) can be used for central heating by centralized recovery.

Therefore to the present invention be that the system in force source is analyzed from whole efficiency (Theoverallefficiency) taking pressurized air, also pretty economical, inexpensive, energy-conservation, environment assessment is good.

3) pressurized air of the present invention jet engine 14 expansion chamber 18 pressure height, thrust is big, safety, sealing are good

1., pressure height, thrust are big

Insider knows, conventional art jet engine is if rocket combustion chamber operational pressure is between 1--20MPa, and pressure is more high, and usual performance is also more good, and thrust is relatively also bigger.

And along with modern age pressurized vessel, pneumatic transmission element and Materials science development, ultra-high voltage pressurized air machine exports pressure and reaches > 100MPa, ultra-high voltage (code name U) container p >=100MPa in pressurized vessel, far above 20MPa;

In addition in the present invention, Large Copacity tubular vessel 60 and gas storage pipe 1 are long tubular structure, their caliber is all less than the internal diameter of the conventional art high pressure compressed air gas-holder of identical capacity, pressure, in identical material situation, it can tolerate higher pressurized air relative to holding pressure, the pressure formula that one of its basis can be able to be born see pipe in the mechanics of materials

P=(2* ��/S* ��)/D

(wherein: P is pressure, �� is tensile strength, and S is safety coefficient, and �� is wall thickness, and D is tube outer diameter)

And, in the present invention, high-voltage and ultra-high pressurized air is injected expansion chamber 18 way also by inlet pipe week electric heater 29 and expansion chamber room wall electric heater 30 mildly heating from gas storage pipe 1 by inlet pipe 17, is also conducive to its expansion work, obtains higher thrust.

2., safety

Pressurized vessel has formulated safety standard (Safetycodes) as the industry of a kind of maturation, safety standard limits 40% that legal operating pressure (thelegalworkingpressure) is less than the parting pressure (therupturepressure) of accumulator unit, safety coefficient be 2.5 (that is the ratio of ultimate stress and permissible stress is 2.5), security is reliable;

For another example the common feature of the pneumatic transmission taking pressurized air as working medium is clearly set forth by university textbook: pneumatic transmission action is rapid, reaction is fast, working environment adaptability is strong, particularly safe and reliable work under the bad working environments such as the big temperature difference, dust inflammable and explosive, many, vibration, has fire prevention, the advantage such as explosion-proof, energy-conservation, efficient, pollution-free;

Along with progress in materials science, pressurized vessel is often made up of the carbon fiber of resistance to high pressure, light weight, carbon fiber is fragility, even if can divide under super big pressure, but any shell fragment can not be caused, only there will be housing " fragmentation " at the most, situation that pressurized air spills, the unsafe condition that fragment and high pressure gas flash would not occur, security is also relatively better.

3., sealing is good

As for seal aspect, along with pneumatic transmission technology progress valve packing technique is also more reliable, insider knows a contrast, and the speed that pressurized air accumulator unit loses heart is also lower than the speed that its electricity is automatically slowly exhausted by store battery along with time lengthening in non-electric situation.

4) reduce motion carrier run resistance, speed-raising, energy-conservation; Improve aircraft wing lift, it is beneficial to short range/VTOL

These advantages and the present invention are taking the high-voltage and ultra-high pressurized air high-temperature fuel gas that non-burning produces as force source, and described Laval nozzle 19 can be utilized to spray, and aerodynamic force that high velocity air 24 produces around motion carrier according to bernoulli principle changes relevant.

The Laval nozzle that Swede Gustaf De Laval (GustavdeLaval) invents, is acknowledged as " flow velocity enhancer ", and widespread use is as the jet pipe of rocket engine; Laval nozzle is as described in existing above, also played the effect of " flow velocity enhancer ", make to spray high velocity air 24 from described jet engine 16 spout in the present invention;

According to the Bernoulli's theorem (Bernoulli'sprinciple) that " father of hydromeehanics " Denier Bernoulli Jacob (DanielBernoulli) proposes, state with Bernoulli equation:

\frac{1}{2} {ρv}^{2} + ρ g h + p = c o n s t a n t

(in formula, p is the pressure suffered by fluid, and v is velocity of flow, and �� is fluid density, and g is universal gravity constant, and h is this place height)

Namely a fluid system, such as air-flow, in current, flow velocity is more fast, and the pressure that fluid produces is more little, and substantially fluid density reduces simultaneously.

Have about this, the first secondary jet engine 39, the jet engine of second mate and the 3rd secondary jet engine 44 done concise and to the point supplementing:

I, about the first secondary jet engine 39

As above-mentioned when the first secondary jet engine spout 39 is at certain distance, certain angle scope tiltedly injection high velocity air 24 around motion carrier head 32, a cone-shaped low pressure area 40 is formed in motion carrier head 32 front, it is to motion carrier head 32 without very resistance, and now motion carrier forefront is raindrop shape expansion chamber 36. Formula according to atmospheric drag:

F = \frac{1}{2} {CρSV}^{2}

(in formula, C is atmospheric drag coefficient, and �� is density of air, S object area windward, and V is the speed of relative movement of object and air)

Analyzing raindrop shape expansion chamber 36 accordingly and met atmospheric drag: 1. atmospheric drag coefficient (dragcoefficient), also known as air resistance coefficient, the shape of raindrop shape expansion chamber 36 belongs to the minimum person of air resistance coefficient; 2. the area windward of raindrop shape expansion chamber 36 may diminish to only motion carrier head 32 windward area 1/tens even several mono-percent; 3. be subject to the elastic force of air by compressing relevant for atmospheric drag and the air before mobile operationally its, and the outer surface of cone-shaped low pressure area 40 and conical side surface are the high velocity air 24 from the first secondary jet engine 31 injection after raindrop shape expansion chamber 36, flow velocity is extremely high, usually far above the movement velocity of motion carrier, not only the air in raindrop shape expansion chamber (36) front can not be compressed to some extent, flow to rear on the contrary by along the air being with " pullling " front thereupon, density of air declines, and is conducive to motion carrier to move ahead.

Known, motion carrier moves square being directly proportional of the atmospheric drag that is subject to and speed in atmosphere; When having report speed to reach 400��600 meters/second, the cube to speed is directly proportional by atmospheric drag, and when speed is higher, atmospheric drag can be directly proportional to the high power of speed. So for day by day aerospace (before flying atmospheric layer) aircraft at a high speed how to reduce atmospheric drag be one can not ignore problem, high-speed aircraft and rocket are considered application the first secondary jet engine 31 is especially meaningful.

II, about the jet engine of second mate

When an object is on the surface of another object during relative movement, the power of the obstruction relative movement being subject to, is sliding friction power, and sliding friction power heel pressure is directly proportional, and is also exactly the vertical of another body surface be directly proportional with an object. Specifically, when submarine is in the seawater relative to seawater movement, being subject to the sliding friction power hindering its relative movement that submarine ship body surface is granted by seawater, this kind of sliding friction power follows the pressure of seawater to be directly proportional, and is also exactly the positive pressure on submarine ship body surface be directly proportional with seawater. Can sliding friction power formulae express:

F=�� F_N

(wherein: F is sliding friction power, F_NFor positive pressure, �� is dynamic friction factor)

Therefore when the jet engine spout of second mate quite closely leans on, is parallel to submarine (not shown) ship body surface to rear injection high velocity air, this high velocity air covers submarine body surface, flow velocity is little to submarine body surface positive pressure greatly, and can blow loose, volume from the seawater being close to submarine ship body, around submarine ship body, form one layer of low-pressure air layer, thus reduce when this submarine runs forward and the sliding-frictional resistance of surrounding seawater; And the jet engine of second mate described in these to rear jet flow stream to submarine travel also grant certain thrust.

III, about the 3rd secondary jet engine (44)

The seventies in last century, the U.S. and USSR (Union of Soviet Socialist Republics) are successively each releases a kind of aircraft with wing engine, is experimental Boeing YC-14 (being cancelled for various reasons) and amp-72 (�� respectively_{�ߧ��ߧ��}��_��-72), the jet flow of their engines directly brushed the upper surface of wing, accelerated wing upper surface air-flow, increased lift, to realize STOL. This kind of technology (is referred to as �� below_��-72 technology) difference technology feature is as follows compared with the 3rd secondary jet engine 44 of the present invention:

�٧�_��The combustion gas that-72 engines produce taking fuel combustion is as power (belonging to oil engine), and the secondary jet engine 44 of the present invention the 3rd take pressurized air as power (belonging to " without combustion engine ");

�ڧ�_��The high-temperature fuel gas of-72 engines injections can cause the thermal fatigue (required by wing material too high, cost is too expensive) of aerofoil surface ablation to a certain degree and structure, and the present invention the 3rd secondary jet engine (44) jet-stream wind can not cause body ablation to damage;

�ۧ�_��-72 engines are arranged on above wing, and the secondary jet engine 44 of the present invention the 3rd is arranged on wing leading edge front;

�ܧ�_HThe effect of wing lift is mainly produced at wing upper surface by-72 engines, and wing lift effect is not only that wing upper surface also acts on the wing lower surface with certain angle of attack by the secondary jet engine 44 of the present invention the 3rd, and efficiency is higher;

�ݧ�_��The wing engine of-72 that is the main puopulsion engine of aircraft need to continue work (cruise not need to increase when rising and can not shut down and its combustion gas continues to blow at wing upper surface), and the secondary jet engine 44 of the present invention the 3rd only works (aircraft separately has main puopulsion engine) in short-term when needs increase and rise;

�ާ�_��-72 voyages limited (maximum commercial transport voyage 800km), the secondary jet engine of the present invention the 3rd (44) is unrelated with voyage (aircraft separately has main puopulsion engine) under normal conditions;

�ߧ�_��" the gas speed machine speed ratio " of-72 aircrafts continues at a relatively stable numerical value substantially, " the gas speed machine speed ratio " of the aircraft with the secondary jet engine 44 of the present invention the 3rd can raise when taking off, land (when the 3rd secondary jet engine 44 works), and other times are as usual.

The present embodiment describes the operation method of a kind of system taking pressurized air as force source, comprises the following steps:

Step one: by high-voltage and ultra-high air compressor 50, large-sized boiler formula pressurized vessel 49 is carried out pressurization and inflate;

Collect tube inlet valve 67, all Large Copacity tubular vessel inlet valve 78 and outlet valve 79 in this course to open, and collect pipe outlet valve 70 and close;

Electric motor 51 utilizes valley electricity or the power supply not easily stored such as wind-powered electricity generation, sun power at night, by high-voltage and ultra-high air compressor 50 through air compressor exhaust port 52, collection tube inlet 66 and the valve 67 opened, all Large Copacity tubular vessel entrance 76 and the valve 78 opened thereof and all Large Copacity tubular vessel outlet 77 and the valve 79 opened thereof to the inlet end collection pipe 65 being arranged in large-scale flowing water water tank 54, all Large Copacity tubular vessel 60 and the pressurization inflation of exit end collection pipe 68;

The air pressure of the gas that controller control is filled with from air compressor exhaust port 52 and tolerance are adapted to the discharge of the hot water 59 that water coolant 58 and the water outlet 56 from the inflow of large-scale flowing water water tank 54 water-in 55 flows out, make at inlet end collection pipe 65, whole Large Copacity tubular vessel 60 and exit end collection pipe 68 occur together in pressurized air production process the heat that produces in time cooled water 58 take away, the hot water 59 that water coolant 58 is heated to be proper temperature flows out towards direct buried insulating pipe 57 for central heating from water outlet 56 in good time, until at inlet end collection pipe 65, still a large amount of pressurized air of normal temperature are substantially kept to reach design high pressure in whole Large Copacity tubular vessel 60 and exit end collection pipe 68, store for subsequent use,

Collecting tube inlet valve 67, all Large Copacity tubular vessel inlet valve 78 and outlet valve 79 when the time comes to close, collection pipe outlet valve 70 continues to close;

Step 2: inflated to gas tank 9 by large-sized boiler formula pressurized vessel 49;

Collection tube inlet valve 67 and whole Large Copacity tubular vessel inlet valve 78 are closed in this course, and in whole Large Copacity tubular vessel outlet valve 79, only single difference is opened and all the other are closed in order, and collection pipe outlet valve 70 is opened, collection pipe outlet 69 is docked by tracheae 3 with what gas storage pipe in gas tank 91 shared, and in gas tank 9, gas storage pipe 1 intake valve 5 single difference are opened and all the other are closed in order, the collection pipe outlet valve 70 of the outlet valve 79 that controller control pressurized air is opened from a certain Large Copacity tubular vessel 60 in an orderly manner through opening, collection pipe outlet 69, what in gas tank 9, gas storage pipe 1 shared is filled with pressurized air by tracheae 3 and a certain the gas storage pipe intake valve 5 opened to this gas storage pipe 1 ... such as, pressurized air inputs gas storage pipe first 10 from Large Copacity tubular vessel first 62, when being full of the pressurized air reaching design requirements pressure in gas storage pipe first 10, gas storage pipe first 10 intake valve 5 cuts out, then gas storage pipe second 11 intake valve 5 is opened, pressurized air inputs gas storage pipe second 11 from Large Copacity tubular vessel first 62

In the process that a Large Copacity tubular vessel 60 is inflated to gas storage pipe 1 one by one, air pressure declines gradually, so that taking turns to when inflating to certain gas storage pipe 1 air pressure in this Large Copacity tubular vessel 60 afterwards has dropped to equal with the air pressure increased gradually in the gas storage pipe 1 being bullied, at this moment this Large Copacity tubular vessel 60 is unable continues to this gas storage pipe 1 gas transmission air pressure in this gas storage pipe 1 again and is not yet raised to design requirements, such as this kind of situation occurs in Large Copacity tubular vessel first 62 in the gas transmission process of gas storage pipe the third 12, both air pressure one fall one liter when reaching equal, in gas storage pipe the third 12 air pressure be not yet raised to design requirements and in Large Copacity tubular vessel first 62 air pressure dropped to the unable gas storage pipe the third 12 continuing to be elevated to air pressure certain value again of certain value and continued gas transmission, at this moment controller control gas storage pipe the third 12 intake valve 5 cuts out, gas storage pipe fourth 13 intake valve 5, single orderly opening and closing in succession such as gas storage pipe penta 13a intake valve 5 grade, the pressurized air making air pressure in Large Copacity tubular vessel first 62 also have certain overbottom pressure is emptied to the relatively low gas storage pipe fourth 13 of air pressure successively, gas storage pipe penta 13a ... then Large Copacity tubular vessel first 62 outlet valve 79 is closed, Large Copacity tubular vessel second 63 outlet valve 79 is opened, simultaneously gas storage pipe the third 12 intake valve 5 is opened again, the Large Copacity tubular vessel second 63 making to have " original " high pressure reaches design requirements to making the air pressure being elevated to certain value before in it continue rising with the relatively low gas storage pipe of its reduced pressure the third 12 inflation, then gas storage pipe the third 12 intake valve 5 cuts out, and then gas storage pipe fourth 13 intake valve 5 is opened

Wherein, input gas storage pipe 1 process at pressurized air from Large Copacity tubular vessel 60, for gas storage pipe 1 internal memory air pressure, there is in rising certain intensification trend, but its pressure of this part pressurized air being input in gas storage pipe 1 from Large Copacity tubular vessel 60 is declined and have cooling trend, controller control pressurized air inputs flow, the speed of gas storage pipe 1 from Large Copacity tubular vessel 60, make in this course in gas storage pipe 1 air pressure be elevated to design requirements steadily and heat up trend and cooling trend relative equilibrium, temperature is substantially stable;

Step 3: gas tank 9 is supplied gas to jet engine 16;

In jet engine 19 working process, in gas tank 9, all gas storage pipe 1 intake valves 5 cut out, and in gas tank 9, single or several of each gas storage pipe 1 vent valve 6 is opened and all the other are closed respectively in order; Vent valve 6, pneumatic tube 8 that controller control pressurized air is opened from wherein a certain or several gas storage pipes 1 in an orderly manner are sent into and are attached thereto the inlet pipe 17 connect, so via being arranged on the mouth 25 of emanating of expansion chamber head 27, gas injects setter 26 and injects expansion chamber 18;

Inlet pipe 17 caliber is smaller compared with gas storage pipe 1 caliber, the all electric heaters 29 of inlet pipe and expansion chamber room wall well heater 30 work, the pressurized air entering expansion chamber 18 is heated by appropriateness, is kept elevated pressures, and under high pressure flow into the De Laval noz(zle) being connected as a single entity with expansion chamber 18 end and gradually gradually spray in wealthy portion 22 by De Laval noz(zle) through De Laval noz(zle) throat 21 in contracting portion 20, air-flow greatly accelerates, producing huge thrust, high velocity air 24 also involves the change of corresponding local aerodynamic force.

The above is only the preferred embodiment of the present invention; it is noted that for those skilled in the art, under the prerequisite not departing from the technology of the present invention principle; can also making some improvement and replacement, these improve and replace and also should be considered as protection scope of the present invention.

Claims

1. one kind take pressurized air as the system in force source, it is characterised in that, comprise taking high-voltage and ultra-high pressurized air as spraying the jet engine of the pressurized air (14) of working medium, pressurized air produces for device (48) and controller;

The jet engine of described pressurized air (14) is arranged on motion carrier; The jet engine of described pressurized air (14) comprises gas tank (9) and jet engine (16); Described gas tank (9) is pressurized air storage vessel, comprises multiple gas storage pipe (1), and described gas storage pipe (1) is for deposit and supplies the pressurized air needed for described jet engine (16); Described jet engine (16) comprises main jet gas engine (41) and the jet engine of multiple pair; Described motion carrier as spraying working medium, is granted the thrust moved forward for the pressurized air to input from described gas storage pipe (1) by described main jet gas engine (41); Multiple jet engine of described pair comprises the first secondary jet engine (31) of the surrounding being separately positioned on described motion carrier, the jet engine of second mate (42), the 3rd secondary jet engine (44), the 4th secondary jet engine (46) and the 5th secondary jet engine (47), for the pressurized air to input from described gas storage pipe (1) as injection working medium and by with described promote mainly injection engine coordinates and to the propelling movement on described motion carrier formation target direction;

Described pressurized air produces and comprises high-voltage and ultra-high air compressor (50) and large-sized boiler formula pressurized vessel (49) for device (48); The operating pressure of described high-voltage and ultra-high air compressor (50) is close, equal or exceed 100Mpa, under the control of described controller to the pressurization inflation of described large-sized boiler formula pressurized vessel (49); Described large-sized boiler formula pressurized vessel (49) for the production of and storing compressed air, with under the control of described controller to multiple described gas storage pipe (1) pressurization inflation;

Described controller is used for being formed by described motion carrier the propelling movement of target direction by the open and close controlling to described main jet gas engine (41), the first secondary jet engine (31), the jet engine of second mate (42), the 3rd secondary jet engine (44), the 4th secondary jet engine (46) and the 5th secondary jet engine (47).

2. according to claim 1 taking pressurized air be force source system, it is characterized in that, described main jet gas engine (41), the first secondary jet engine (31), the jet engine of second mate (42), the 3rd secondary jet engine (44), the 4th secondary jet engine (46) and the 5th secondary jet engine (47) include the inlet pipe (17), expansion chamber (18) and the De Laval noz(zle) (19) that are made up of resistance to high pressure, lighter material;

Described inlet pipe (17) is connected between described gas storage pipe (1) and described expansion chamber (18); The surrounding of described inlet pipe (17) is provided with inlet pipe week electric heater (29), the pressurized air of described inlet pipe week electric heater (29) for heating in described inlet pipe (17), so that the air pressure in described inlet pipe (17) raises; Pressurized air in described gas storage pipe (1) is injected in described expansion chamber (18) by the mouth of emanating (25) of described inlet pipe (17);

Expansion chamber room wall (28) of described expansion chamber (18) is equipped with gas and is injected setter (26), described gas inject setter (26) for regulating and controlling described inlet pipe (17) inject the amount of setting pressure to the pressurized air in described expansion chamber (18) so that the air pressure in described expansion chamber (18) maintains setting pressure; The surrounding of described expansion chamber (18) is provided with expansion chamber room wall electric heater (30), and for making, the pressurized air entered in described expansion chamber (18) is pressurizeed described expansion chamber room wall electric heater (30) by heating;

The sectional area of described De Laval noz(zle) (19) first diminishes from front to back and becomes big again; The end of described expansion chamber (18) and the gradually contracting portion (20) of described De Laval noz(zle) are connected as a single entity, described expansion chamber (18) compressed air accelerates through described De Laval noz(zle) gradually contracting portion (20), De Laval noz(zle) throat (21) and De Laval noz(zle) gradually wealthy portion (22) under stress, and final high velocity air (24) is sprayed by De Laval noz(zle) spout (23).

3. according to claim 2 taking pressurized air be force source system, it is characterised in that, described first secondary jet engine (31) is arranged on the front of the head (32) of motion carrier, described first secondary jet engine (31) has the profile (43) of raindrop shape, its windward area be less than the area windward of corresponding described motion carrier head (32), described first secondary jet engine (31) comprises the first inlet pipe (17a), the first expansion chamber (18a) and the first De Laval noz(zle) (19a), also comprising a firm tubular structure (33), described first secondary jet engine (31) is fixed on the front of this motion carrier head (32) by described firm tubular structure (33), described first inlet pipe (17a) is positioned within described firm tubular structure (33) and is supported by described firm tubular structure (33), the end of described first expansion chamber (18a) and the gradually contracting portion (20a) of the first De Laval noz(zle) are connected as a single entity, described first De Laval noz(zle) (19a) is overall in Rafael nozzle shape structure from front to back, described first inlet pipe (17a) is stretched out to front from the head (32) of motion carrier together with described firm tubular structure (33), and to the described in forward position first axial central authorities of secondary jet engine (31) sequentially through the first secondary jet engine spout (39), the first De Laval noz(zle) gradually wealthy portion (22a), the first De Laval noz(zle) throat (21a), described first De Laval noz(zle) gradually contracting portion (20a) and described first expansion chamber (18a) and expansion chamber head inwall (37) with described first expansion chamber (18a) is fixedly connected with, described expansion chamber head inwall (37) be equipped with the first inlet pipe emanate mouth and gas injects setter (35), described first expansion chamber (18a) compressed air accelerates through described first De Laval noz(zle) gradually contracting portion (20a) under stress, first De Laval noz(zle) throat (21a), finally by the gap being positioned between the conical huge portion (33a) of described first De Laval noz(zle) gradually wealthy portion (22a) and firm tubular structure to rear along a conical side surface to surrounding's injection of motion carrier head, the bus of described conical side surface is equivalent to the line (32a) from described first De Laval noz(zle) throat (21a) to this motion carrier head (32) periphery, to form a cone-shaped low pressure area (40) in this motion carrier head (32) front, the atmospheric drag run forward for reducing this motion carrier or seawater resistance,

Described first secondary jet engine (31) is also for granting the tractive force that described motion carrier moves forward.

4. according to claim 3 taking pressurized air be force source system, it is characterized in that, the quantity of the jet engine of described second mate (42) is multiple, multiple described second mate jet engine (42) circumference is arranged at all sides of described motion carrier, described motion carrier is moved forward towards the rear injection high velocity air of described motion carrier and grants thrust by multiple described second mate jet engine (42) spout, and the high velocity air that ejects of described second mate jet engine (42) spout parallel and close to the surface of motion carrier, the sliding-frictional resistance between when motion carrier runs forward and the external world is reduced to form one layer of low-pressure air layer around motion carrier.

5. according to claim 1 taking pressurized air be force source system, it is characterized in that, described motion carrier is provided with one or more described gas tank (9), multiple described gas storage pipe (1) in gas tank described in each (9) is long tubular structure, has round shape gas storage tube wall (2) being made up of resistance to high pressure, lighter material;

Multiple described gas storage pipe (1) is parallel-laid into bundle arrangement, and cross section is overall in plum flower-like structure; Gas storage pipe (1) described in each is equipped with the intake valve (5) and vent valve (6) that open and close separately by the control of described controller;

Around described gas storage pipe (1), be provided with standby electricity well heater (15), described standby electricity well heater (15) for working overloadingly for some reason at the jet engine of described pressurized air (14), whole described gas storage pipe (1) compressed air pressure all lower than setting lower limit time start;

One end of multiple described gas storage pipe (1) many siphunculus (4) of being all bullied with are connected, described in be bullied many siphunculus (4) converge be one by tracheae (3); The other end of multiple described gas storage pipe (1) all communicates with the many siphunculus of a gas transmission (7), and multiple paths merge of the many siphunculus of described gas transmission (7) are a pneumatic tube (8); Described gas storage pipe (1) is connected with described inlet pipe (17) by described pneumatic tube (8);

The described pressurized air pressurizeing and being filled with for acceptance from described large-sized boiler formula pressurized vessel (49) by tracheae (3).

6. according to claim 1 taking pressurized air be force source system, it is characterized in that, for described large-sized boiler formula pressurized vessel (49) of gas storage pipe (1) the pressurization inflation of described gas tank (9) comprises large-scale flowing water water tank (54) and some the Large Copacity tubular vessel (60) and collection pipe (53) that are placed in described water tank;

Some described Large Copacity tubular vessels (60) are divided into the comb (74) of many group tiling shapes, described collection pipe (53) is positioned at the both sides of the often comb (74) of group tiling shape, described Large Copacity tubular vessel (60) two ends in described comb (74) shape are provided with entrance (76) and outlet (77), the described pipe (53) that integrates being connected with Large Copacity tubular vessel entrance (76) in often group is as inlet end collection pipe (65), the described pipe (53) that integrates being connected with Large Copacity tubular vessel outlet (77) in often group is as exit end collection pipe (68), the entrance (76) of described Large Copacity tubular vessel (60) is provided with inlet valve (78), and the outlet (77) of described Large Copacity tubular vessel (60) is provided with outlet valve (79), described inlet end collection pipe (65) is provided with collection tube inlet (66) and collection tube inlet valve (67) thereof, and described exit end collection pipe (68) is provided with collection pipe outlet (69) and collection pipe outlet valve (70) thereof,

The design volume of described Large Copacity tubular vessel (60) and pressure is greater than respectively and higher than the design volume of described gas storage pipe (1) and pressure; The described Large Copacity tubular vessel (60) of part is serpentine tube (75), and described serpentine tube (75) is the tubular structure of repeatedly roundabout extension in the plane that described comb (74) tiles;

The described comb (74) being laid in same plane and described inlet end collection pipe (65) on both sides thereof and exit end collection pipe (68) form Large Copacity tubular vessel plane (73); A described large-scale flowing water water tank (54) is provided with multiple described Large Copacity tubular vessel plane (73), inlet end collection pipe (65) in described Large Copacity tubular vessel plane (73) of many groups is connected by inlet end collection pipe communicating pipe (71), and share a described collection tube inlet (66), it is provided with collection tube inlet valve (67) in described collection tube inlet (66); Exit end collection pipe (68) in each described Large Copacity tubular vessel plane (73) is connected by exit end collection pipe communicating pipe (72), and share described collection pipe outlet (69), it is provided with collection pipe outlet valve (70) in described collection pipe outlet (69);

Described large-scale flowing water water tank (54) is provided with the water-in for flowing into water coolant (58) (55) and the water outlet (56) for flowing out hot water (59), and described water outlet (56) is connected with the direct buried insulating pipe (57) in central heating system;

The air compressor exhaust port (52) of described high-voltage and ultra-high air compressor (50) and described collection tube inlet (66) removably connect, for the pressurization inflation of described Large Copacity tubular vessel (60).

7. an aircraft, it is characterized in that, comprise as described in item as arbitrary in claim 1 to 6 taking pressurized air be force source system, wherein said first secondary jet engine (31) is arranged on plane nose front, and the jet engine of described second mate (42) is arranged on all sides of airframe; And the quantity of described 3rd secondary jet engine (44) is multiple, multiple described 3rd secondary jet engine (44) is symmetricly set on the front of the leading edge of aircraft both sides wing; The spout of described 3rd secondary jet engine (44) is to wing injection high velocity air (24) at rear, and the direction of high velocity air that the spout of described 3rd secondary jet engine (44) ejects is consistent relative to the air flow line of wing with when taking off sliding race; Described 3rd secondary jet engine (44) for when aircraft short range or VTOL improve wing lift, also for granting corresponding to the thrust that described aircraft is moved forward that described 3rd secondary jet engine (44) spout jet flow stream reactive force is made a concerted effort.

8. aircraft according to claim 7, it is characterized in that, described 4th secondary jet engine (46) is arranged on the lower section of described airframe, for the back lower place of aircraft or front lower place jet-stream wind, so that described aircraft to be granted the reactive force of forward upward or back upper place; Described 5th secondary jet engine (47) is arranged on immediately below the afterbody of described aircraft or is symmetricly set on the both sides of afterbody, for the reverse injection high velocity air in described aircraft flight direction, so that described aircraft to play the effect of buffer deceleration.

9. one kind take pressurized air as the operation method of the system in force source, it is characterised in that, comprise the following steps:

Step one: by high-voltage and ultra-high air compressor (50), large-sized boiler formula pressurized vessel (49) is carried out pressurization and inflate;

Collect tube inlet valve (67), all Large Copacity tubular vessel inlet valve (78) and outlet valve (79) in this course to open, and collect pipe outlet valve (70) and close;

Electric motor (51) utilizes valley electricity or wind-powered electricity generation at night, the power supply that sun power etc. are not easily stored, by high-voltage and ultra-high air compressor (50) through air compressor exhaust port (52), collection tube inlet (66) and collection tube inlet valve (67) opened thereof, whole Large Copacity tubular vessel entrance (76) and the inlet valve (78) opened thereof, and the outlet valve (79) of all Large Copacity tubular vessel outlet (77) and unlatching thereof is to inlet end collection pipe (65) being arranged in large-scale flowing water water tank (54), whole Large Copacity tubular vessel (60) and exit end collection pipe (68) pressurization inflation,

The discharge of the hot water (59) that the air pressure of the gas that controller control is filled with from air compressor exhaust port (52) and tolerance are adapted to the water coolant (58) that flows into from large-scale flowing water water tank (54) water-in (55) and water outlet (56) flows out, make at inlet end collection pipe (65), whole Large Copacity tubular vessel (60) and exit end collection pipe (68) occur together in pressurized air production process the heat that produces in time cooled water (58) take away, the hot water (59) that water coolant (58) is heated to be proper temperature flows out towards direct buried insulating pipe (57) for central heating from water outlet (56) in good time, until at inlet end collection pipe (65), still a large amount of pressurized air of normal temperature are substantially kept to reach design high pressure in whole Large Copacity tubular vessel (60) and exit end collection pipe (68), store for subsequent use,

Collecting tube inlet valve (67), all Large Copacity tubular vessel inlet valve (78) and outlet valve (79) when the time comes to close, collection pipe outlet valve (70) continues to close;

Step 2: inflated to gas tank (9) by large-sized boiler formula pressurized vessel (49);

Collect tube inlet valve (67) and all Large Copacity tubular vessel inlet valve (78) closedowns in this course, in whole Large Copacity tubular vessel outlet valve (79), only single difference is opened and all the other are closed in order, and collection pipe outlet valve (70) is opened; What collection pipe outlet (69) and gas storage pipe (1) in gas tank (9) shared docks by tracheae (3), in gas tank (9) each gas storage pipe (1) intake valve (5) only single difference open in order and all the other closedowns; What outlet valve (79) gas storage pipe (1) through collection pipe outlet valve (70), collection pipe outlet (69), gas tank (9) of unlatching that controller control pressurized air is opened from a certain Large Copacity tubular vessel (60) in an orderly manner shared is filled with pressurized air by tracheae (3) and a certain individual gas storage pipe intake valve (5) opened to this gas storage pipe (1);

Decline gradually to air pressure in the process that gas storage pipe (1) is inflated one by one a Large Copacity tubular vessel (60), so that taking turns to this Large Copacity tubular vessel (60) interior air pressure when inflating to certain gas storage pipe (1) afterwards has dropped to equal with the air pressure increased gradually in the gas storage pipe (1) being bullied, at this moment this Large Copacity tubular vessel (60) is unable continues to this gas storage pipe (1) gas transmission that this gas storage pipe (1) interior air pressure is not yet raised to design requirements again, controller controls the opening and closing of each Large Copacity tubular vessel outlet valve (79) and each gas storage pipe (1) intake valve (5), make the existing Large Copacity tubular vessel (60) declined of air pressure to low gas storage pipe (1) inflation relatively of not yet inflation or pressure, although making to rise to some extent but the gas storage pipe (1) that is not yet raised to design requirements obtains having the Large Copacity tubular vessel (60) of initial high pressure or relatively high pressure to its inflation through inflation pressure,

Wherein, input gas storage pipe (1) process at pressurized air from Large Copacity tubular vessel (60), for gas storage pipe (1) internal memory air pressure, there is in rising certain intensification trend, but its pressure of this part pressurized air being input in gas storage pipe (1) from Large Copacity tubular vessel (60) is declined and have cooling trend, controller control pressurized air inputs the flow of gas storage pipe (1) from Large Copacity tubular vessel (60), speed, gas storage pipe (1) interior air pressure in this course is made to be elevated to design requirements steadily and heat up trend and cooling trend relative equilibrium, temperature is substantially stable,

Step 3: gas tank (9) is supplied gas to jet engine (16);

In jet engine (16) working process, in gas tank (9), all gas storage pipes (1) intake valve (5) are closed, in gas tank (9), each gas storage pipe (1) vent valve (6) is only single or several unlatching in order respectively and all the other are closed; Vent valve (6), pneumatic tube (8) that controller control pressurized air is opened from wherein a certain or several gas storage pipes (1) in an orderly manner are sent into and are attached thereto the inlet pipe (17) connect, so via being arranged on the mouth of emanating (25) of expansion chamber head (27), gas injects setter (26) and injects expansion chamber (18);

Relatively gas storage pipe (1) caliber is smaller for inlet pipe (17) caliber, inlet pipe week electric heater (29) and expansion chamber room wall electric heater (30) work, the pressurized air entering expansion chamber (18) is heated by appropriateness, keep elevated pressures, and under high pressure flow into De Laval noz(zle) gradually contracting portion (20) being connected as a single entity with expansion chamber (18) end successively, through De Laval noz(zle) throat (21) and by De Laval noz(zle) gradually wealthy portion (22) ejection, air-flow greatly accelerates, produce huge thrust, high velocity air (24) also involves the change of corresponding local aerodynamic force.