CN104775935A - Working method of superposition pressing oxygen production rocket - Google Patents
Working method of superposition pressing oxygen production rocket Download PDFInfo
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- CN104775935A CN104775935A CN201510005171.8A CN201510005171A CN104775935A CN 104775935 A CN104775935 A CN 104775935A CN 201510005171 A CN201510005171 A CN 201510005171A CN 104775935 A CN104775935 A CN 104775935A
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- rocket
- diffusing tube
- oxygen
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Abstract
The invention relates to a working method of a superposition stamping oxygen production rocket, belonging to the technical field of aviation and aerospace. The working method of the superposition pressing oxygen production rocket is used for an aerospace plane engine, an aerospace flying vehicle engine and a guided missile. According to the working method of the superposition stamping oxygen production rocket, the rocket can take off at zero speed on the basis of jet flow vacuum working principle; compared with a rocket without superposition, the superposition pressing oxygen production rocket is capable of generating thrust which is a plurality of times higher than that generated by the rocket without superposition under the condition that the same amount of oxygen is consumed in flight, thus producing more oxygen.
Description
Technical field
Superposition punching press oxygen rocket method of work relates to and belongs to aviation and space technology field.For following sky and space plane motor and re-entry space vehicle motor.
Background technique
Although space shuttle is a a progressive step compared with nonrecoverable carrier rocket, still have such as faults frequent, many deficiencies such as somewhat expensive.And sky and space plane is different from space shuttle, its ground installation is simple, and safeguard easy to use, operating cost is low, and on common large airport, just energy horizontal take-off and landing, has the flight frequency of general course line airliner.The external form of this aircraft is similar to large-scale supersonic jet passenger plane, has the advantage of aircraft more., when aerial flight, make full use of the oxygen in air.What it can be up to a hundred time in addition reuses, and really achieves the advantage of high-effect and low expense.It is estimated, launch near earth satellite expense with its and only have 1/5 of space shuttle, and launch synchronous satellite expense and only need 1/10.Use superposition punching press oxygen rocket method of work, the rocket manufactured can enable expense be down to 1%. to make rocket be competent at just large carrying capacity, consume oxygen in-flight few, can Preparation of oxygen be also that space flight prepares in atmospheric layer, sky and space plane and re-entry space vehicle be established oneself in an unassailable position in the business competition of space on the horizon.
Summary of the invention
Superposition punching press oxygen rocket method of work is in brief: air-breathing duct 2 in head mouse flame jet drive first set jet suction means < (or, with outer suction duct 3), induction chamber 4, Laval nozzle 5, diffusing tube (a) 6>, in fuel adding point (a) 10, fuel adding point (b) 11 filling rocket fuel, light a fire in igniting place 9 or use Lavalle flame ignition, the injection power that burning produces drives the second cover jet suction means < diffusing tube (a) 6, diffusing tube b15, outer air-breathing duct (b) 16, air-breathing shouts 17> fuel adding point (c) 13, fuel adding point (d) 14 filling liquid, solid fuel and catalyzer, in Dian Chu (b) 18 igniting or the flame ignition with diffusing tube (a) 6, burn at rocket chamber, the powered rocket flight produced.
When rocket speed can meet punching press suction condition, head mouse quits work, due to high speed, the air of head-on coming is made to be stamped into interior suction duct 2, (or, with outer air-breathing duct 3) be stamped in diffusing tube (a) 6, meanwhile at fuel adding point (a) 10 and fuel adding point (b) 11 filling rocket fuel, light a fire in igniting place (a) 9, the fuel mixed with air is in diffusing tube combustion and spray in diffusing tube (b) 15, in fuel adding point (c) 13 and fuel adding point (d) 14 rocket liquid of annotating in this process, solid rocket fuel and catalyzer, be pressed into diffusing tube (b) 15 to mix, this process can produce vacuum, vacuum is through outer suction duct (b) 16, air-breathing roar 17 is by air and the suction of being stamped, meanwhile another part air is stamped in two punching press sucking pipes 19 and (opens two valves 8 on this two tubes, can to annotate before punching press sucking pipe rocket fuel) if needed, the afterbody importing diffusing tube (b) 15 sprays in rear portion rocket chamber 7, in igniting place (b) 18 or diffusing tube (a) 6 flame ignition, spray into rocket chamber burning, the thrust produced makes rocket flight.
When the stamping pressure that rocket speed produces can meet oxygen requirement, open four valves 8 of oxygen sucking pipe 20, the air be stamped through oxygen sucking pipe 20, enter oxygen generating plant 21 oxygen, oxygen after non-oxidising gas and impurity through non-oxygen discharge tube 22 (opening the valve 8 on these two pipes), enter rocket afterbody horn mouth discharge.
Accompanying drawing explanation
Fig. 1 is many interior air-breathing duct superposition punching press oxygen rocket figure, as shown in Figure 1, 4 interior air-breathing ducts 2, the inside penetrating head mouse 1 from the front of head mouse 1 passes to induction chamber 4, these four interior air-breathing ducts pass from head mouse 1 inside, the air be stamped enters diffusing tube (a) 6 through 4 interior air-breathing ducts, after adding rocket fuel igniting, at the high velocity air that diffusing tube (a) 6 burning produces, when spraying into diffusing tube (b) 15 (and Open valve 8), the vacuum of producing at this can shout 17 air intakes that will be stamped by outer air-breathing duct (b) 16 and air-breathing, burn in firing chamber 7 after adding fuel ignition burning, make rocket flight, meanwhile another part air (opens the valve 8 on these two pipes through two punching press sucking pipes 19, these two pipes can be designed to spread tubulose, as needed can to add rocket fuel at the toy trumpet mouth of pipe place of these two diffusing tubes), the air of punching press and rocket fuel are imported in the middle part of diffusing tube 15 typhon mouth, with the gas in diffusing tube 15 and fuel mix, push firing chamber 7 to burn, make rocket flight, when the stamping pressure that rocket speed produces, when can meet oxygen liquefaction oxygen condition, open two oxygen sucking pipes 20 (oxygen sucking pipe to be designed to spread tubulose, the air entered is made to enter some compression, open the valve 8 on these two pipes), the air be stamped enters oxygen generating plant 21 oxygen through oxygen sucking pipe 20, non-oxidising gas after oxygen and impurity, be discharged to rocket afterbody horn mouth through non-oxygen discharge tube 22 to discharge.
Fig. 2 is inside and outside air-breathing duct superposition punching press oxygen rocket figure, as shown in Figure 2, 4 interior air-breathing ducts 2, penetrate inside to pass (induction chamber and outer air-breathing duct fuse) from the front of head mouse 1 to outer air-breathing duct 3, the air be stamped enters diffusing tube (a) 6 through 4 interior air-breathing ducts and outer air-breathing duct 3, after adding ignited fuel, at the high velocity air that diffusing tube (a) 6 burning produces, spray into diffusing tube (b) 15 (and Open valve 8), the vacuum that this process is produced can shout 17 air intakes that will be stamped by outer air-breathing duct (b) 16 and air-breathing, adding rocket fuel is pushed in induction chamber 7, these two pipes (can be designed to spread tubulose through two punching press sucking pipes 19 by another part air, also fuel can be added at diffusing tube toy trumpet mouth of pipe place as required, open the valve 8 on these two pipes), the middle part of press-in diffusing tube (b) 15, converging with the gas in diffusing tube (b) is pressed in firing chamber 7, make rocket flight.When rocket speed can meet oxygen condition, open two valves 8 on oxygen sucking pipe 20, the air be stamped is through oxygen generating plant 21 oxygen, non-oxidising gas after oxygen and impurity, be discharged to rocket afterbody horn mouth place through non-oxidising gas discharge tube 22 (opening the valve 8 on these two pipes) and discharge.
Fig. 3 is outer air-breathing duct superposition punching press oxygen rocket figure, as shown in Figure 3, the air be stamped, diffusing tube (a) 6 is entered through outer air-breathing duct 3, at the high velocity air that diffusing tube (a) 6 burning produces after adding rocket fuel igniting, spray in diffusing tube (b) 15 (Open valve 8), the procreative vacuum of this process, vacuum is shouted 17 by outer air-breathing duct (b) 16 and air-breathing and the air be stamped and fuel is sucked, be pushed into after igniting in induction chamber 7 and burn, root pipe between two (can be designed to spread tubulose through two punching press sucking pipes 19 by the air that another part has been stamped, if needed can in these two diffusing tube toy trumpet mouth of pipe place's fuelings, open the valve 8 on these two diffusing tubes), import in the middle part of diffusing tube 15, converge with the gas in diffusing tube 15, be pushed in firing chamber 7 and burn.When rocket speed makes the pressure energy of punching press meet oxygen liquefaction condition processed, open four valves 8 on oxygen generation system, these two pipes (can be designed to spread tubulose through punching press sucking pipe 20 by the air be stamped, air is compressed further), enter oxygen generating plant 21 oxygen, non-oxidising gas after oxygen and impurity, through non-oxidising gas discharge tube 22, drain into rocket afterbody horn mouth place and discharge.
Fig. 4 is single interior air-breathing duct superposition punching press oxygen rocket figure, as shown in Figure 4, 1 interior air-breathing duct 2, inside is penetrated from head mouse 1 front dead center centre, pass to head mouse 1 afterbody centre, head mouse 1 afterbody Laval nozzle 5 (nozzle group), be located in the head mouse afterbody annular wall around interior air-breathing duct 2, the flame of Laval nozzle 5 (nozzle group) sprays and meets at a bit with funnel-like, vacuum (principle is similar to flow eddies) can be produced in funnel, air intake is compressed through interior air-breathing duct horn mouth, sprayed in diffusing tube (6) by the flame flow of Laval nozzle 5 (nozzle group), this process can produce vacuum, set the distance between intersection point and diffusing tube or position (being the important instruction producing another vacuum), the vacuum produced after injecting diffusing tube (a) 6 is second time air-breathing, this is designed with Laval nozzle effect (American engineer playing method, table tennis bat smashes by table tennis.There is this data on the net), in fuel adding point (a) 10, fuel adding point (b) 11 fueling, (or lighting a fire with Laval nozzle 5< nozzle group >) is lighted a fire in igniting place (a) 9, the rocket fuel of mixing air burns in diffusing tube (a) 6, the high velocity air produced sprays into diffusing tube (b) 15 (Open valve 8), set the gap (vacuum important indicator) between diffusing tube (a) 6 and diffusing tube (b) 15, the vacuum (in just become third time air-breathing) of producing can shout 17 by air intake through outer air-breathing duct (b) 16 and air-breathing, be pushed into firing chamber 7.When rocket flight speed can meet punching press suction condition, head mouse quits work, air shouts 17 through interior air-breathing duct 2, induction chamber 4, diffusing tube (a) 6, outer air-breathing duct (b) 16, air-breathing, diffusing tube (b) 15 and two punching press sucking pipes 19, open the valve 8 in these two systems, at each fuel adding point filling rocket fuel, in each igniting place igniting, burn in firing chamber 7.When the stamping pressure that rocket speed produces can meet oxygen condition, open all valves 8 on oxygen generation system, air, through oxygen sucking pipe 20, enters oxygen generating plant 21, non-oxidising gas after oxygen and impurity, drained into rocket afterbody jet pipe horn mouth place through non-oxygen discharge tube 22 and discharged.
Fig. 5 is air-breathing duct superposition punching press oxygen rocket figure in dendroid, as shown in Figure 5, 1 interior air-breathing duct 2 penetrates inside from head mouse 1 front dead center centre and passes to head mouse 1 afterbody centre, in addition four interior air-breathing ducts 2 are inner by penetrating head mouse 1 outside the head mouse 1 front dead center heart, and meet on Centromedian interior air-breathing duct 2 in head mouse 1 inside, on the Centromedian interior air-breathing duct 2 connected with dendritic structure, head mouse 1 afterbody Laval nozzle 5 (nozzle group), be located at the head mouse 1 afterbody annular wall around interior air-breathing duct, the flame of Laval nozzle 5 (nozzle group) sprays and meets at a bit with funnel-like, vacuum (being similar to flow eddies principle) can be produced in this process funnel and set intersection point the distance of diffusing tube or position (being the important indicator producing another vacuum), inject diffusing tube (a) 6, on be designed with Laval nozzle effect (American engineer playing method, table tennis bat smashes by table tennis.Have this data on the net), out-of-work head mouse inner cavity chamber, can play the effect of vacuum tank, can better play Lavalle effect.In fuel adding point (a) 10, fuel adding point (b) 11 filling rocket fuel, light a fire with igniting place (a) 9, fuel fuel in the typhon mouth of diffusing tube (a) 6 sprays in diffusing tube (b) 15, set gap between diffusing tube (6) and diffusing tube (b) 15 (being the important indicator of producing another vacuum) to annotate rocket fuel in fuel adding point (c) 13 fuel adding point (d) 14, vacuum is through outer air-breathing duct 16, air-breathing is shouted 17 and the air be stamped and rocket fuel to be sucked and to spray into diffusing tube 15, with place (b) 18 igniting flame ignition of diffusing tube (a) 6 (or with), rocket fuel burns in firing chamber 7.When rocket flight speed can meet punching press suction condition, head mouse quits work, air shouts 17 through interior air-breathing duct 2, induction chamber 4, diffusing tube (a) 6, outer air-breathing duct (b) 16, air-breathing, diffusing tube (b) 15 and two punching press sucking pipes 19, open the valve 8 in these two systems, at each fuel adding point filling rocket fuel, in each igniting place igniting, burn in firing chamber 7, the flame flow that burning produces makes rocket flight.When the stamping pressure that rocket speed produces can meet oxygen condition, open all valves 8 on oxygen generation system, air, through oxygen sucking pipe 20, enters oxygen generating plant 21, non-oxidising gas after oxygen and impurity, drained into rocket afterbody jet pipe horn mouth place through non-oxygen discharge tube 22 and discharged.
Fig. 6 is the thin chart of rocket part name of superposition punching press oxygen rocket.
Embodiment
Its composition of superposition punching press oxygen rocket method of work: head mouse 1, interior air-breathing duct 2 (or, with outer suction duct 3), induction chamber 4, Laval nozzle 5, diffusing tube (a) 6, firing chamber 7, valve 8, igniting place (a) 9, fuel adding point (a) 10, fuel adding point (b) 11, interior air-breathing duct horn mouth 12, fuel adding point (c) 13, fuel adding point (d) this 14, diffusing tube (b) 15, outer air-breathing duct (b) 16, air-breathing shouts 17, igniting place (b) 18, punching press sucking pipe 19, oxygen sucking pipe 20, oxygen generating plant 21, non-oxygen discharge tube 22.
The working principle of superposition punching press oxygen rocket method of work, as shown in Figure 5, 1 interior air-breathing duct 2 penetrates inside from head mouse 1 front dead center centre and passes to head mouse 1 afterbody centre, in addition four interior air-breathing ducts 2 are inner by penetrating head mouse 1 outside the head mouse 1 front dead center heart, and meet on Centromedian interior air-breathing duct 2 in head mouse 1 inside, on the Centromedian interior air-breathing duct 2 connected with dendritic structure, head mouse 1 afterbody Laval nozzle 5 (nozzle group), be located at the head mouse 1 afterbody annular wall around interior air-breathing duct, after the work of head mouse, the flame of Laval nozzle 5 (nozzle group) sprays and meets at a bit with funnel-like, vacuum (being similar to flow eddies principle) can be produced in this process funnel and set intersection point the distance of diffusing tube or position (being the important indicator producing another vacuum), inject diffusing tube (a) 6, vacuum now can produce Laval nozzle effect (American engineer playing method, table tennis bat smashes by table tennis.Have this data on the net) quit work head mouse inner cavity chamber, there is the effect of vacuum tank, what Laval nozzle effect was played is better, in fuel adding point (a) 10, fuel adding point (b) 11 filling rocket fuel, with igniting place (a) 9 light a fire (or with Laval nozzle ejection flame ignition) due to Lavalle effect, the rocket fuel of mixing air and high speed is made to spray into the typhon mouth fuel of diffusing tube (a) 6, fuel burn in the typhon mouth of diffusing tube (a) 6 produce power, spray in diffusing tube (b) 15, set gap between diffusing tube (6) and diffusing tube (b) 15 (being the important indicator producing another vacuum) to annotate rocket fuel in fuel adding point (c) 13 fuel adding point (d) 14, vacuum is through outer air-breathing duct 16, air-breathing is shouted 17 and the air be stamped and rocket fuel to be sucked and to spray into diffusing tube 15, with place (b) 18 igniting flame ignition of diffusing tube (a) 6 (or with), rocket fuel burns in firing chamber 7.When rocket flight speed can meet punching press suction condition, head mouse quits work, air is through interior air-breathing duct 2, induction chamber 4, portion of air punching press is to diffusing tube (a) 6, in this fuel adding point (a) 10, fuel adding point (b) 11 fueling, be stamped to firing chamber 7, another part air is stamped to two punching press sucking pipes 19 and (opens the valve 8 on these two pipes, punching press sucking pipe can be arranged to spread tubulose, the air entered is compressed further, as required can the suction port place fueling of these two pipes), import the middle part of diffusing tube 15, together spray into rocket fuel chamber 7 with the gas of diffusing tube 15 to burn, make rocket flight, when the stamping pressure that rocket speed produces can meet oxygen condition, open all valves 8 on oxygen generation system, air is through oxygen sucking pipe 20, enter oxygen generating plant 21, non-oxidising gas after oxygen and impurity, drained into rocket afterbody jet pipe horn mouth place through non-oxygen discharge tube 22 to discharge.
The data of " water-vapour spray vacuum pump " and < sparger >, can search out on the net.
Claims (10)
1. superpose punching press oxygen rocket method of work.It comprises head mouse 1, interior air-breathing duct 2 (or outer inhale duct 3), induction chamber 4, Laval nozzle 5, diffusing tube (a) 6, rear portion rocket chamber 7, valve 8, igniting place (a) 9, fuel adding point (a) 10, fuel adding point (b) 11, interior air-breathing duct horn mouth 12, fuel adding point (c) 13, fuel adding point (d) 14, diffusing tube (b) 15, outer air-breathing duct (b) 16, air-breathing shout 17, igniting place (b) 18, oxygen sucking pipe 20, oxygen generating plant 21, non-oxygen discharge tube 22.The superposition punching press oxygen rocket be made up of 1-22, can complete punching press air-breathing.
2. spray into diffusing tube (b) 15 at diffusing tube (a) 6 high velocity air, form vacuum and drive the 2nd inhalation methods/to annotate rocket fuel in fuel adding point (a) 13, fuel adding point (b) 14.
3. access from outer air-breathing duct 16 with head mouse Laval nozzle flame/oxygen sucking pipe 20, for diffusing tube (a) 6 is lighted a fire.
4. non-oxygen discharge tube 22 drains into rocket nozzle horn mouth place/arrange igniting place in the scope of diffusing tube (a) 6.
5. diffusing tube (a) 6 typhon mouth one end is as fuel chambers/spray into diffusing tube (b) 15 at diffusing tube (a) 6 high velocity air, forms vacuum.
6. an igniting place/mono-head mouse is set in the scope of diffusing tube (b) 15, drives a Laval nozzle 5, flame sprays into a diffusing tube (6), flame sprays into a diffusing tube (b) 15, for a rocket chamber 7 provides oxygen and fuel, flame sprays into a rocket afterbody jet pipe.
7. head mouse, drive multiple Laval nozzle 5, flame sprays into a diffusing tube (6), flame sprays into a diffusing tube (b) 15, provide oxygen and fuel for a rocket chamber 7, flame sprays into a rocket afterbody jet pipe/mono-head mouse, drives multiple Laval nozzle 5, flame sprays into multiple diffusing tube (6), flame sprays into a diffusing tube (b) 15, for a rocket chamber 7 provides oxygen and fuel, flame sprays into a rocket afterbody jet pipe.
8. head mouse, drive multiple Laval nozzle 5, flame sprays into multiple diffusing tube (6), flame sprays into multiple diffusing tube (b) 15, provide oxygen and fuel for a rocket chamber 7, flame sprays into a rocket afterbody jet pipe/mono-head mouse, drives multiple Laval nozzle 5, flame sprays into multiple diffusing tube (6), flame sprays into multiple diffusing tube (b) 15, for multiple rocket chamber 7 provides oxygen and fuel, flame sprays into a rocket afterbody jet pipe.
9. head mouse, drive multiple Laval nozzle 5, flame sprays into multiple diffusing tube (6), flame sprays into multiple diffusing tube (b) 15, provide oxygen and fuel for multiple rocket chamber 7, flame sprays in the typhon mouth that multiple rocket afterbody jet pipe collects.
10. many head mouses, drive a Laval nozzle 5, flame sprays into a diffusing tube (6), flame sprays into a diffusing tube (b) 15, provide oxygen and fuel for a rocket chamber 7, flame sprays into a rocket afterbody jet pipe/multiple head mouse, drives multiple Laval nozzle 5, flame sprays into multiple diffusing tube (6), flame sprays into multiple diffusing tube (b) 15, provide oxygen and fuel for multiple rocket chamber 7, and flame sprays in the typhon mouth that multiple rocket afterbody jet pipe collects.
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| CN201510005171.8A CN104775935A (en) | 2015-01-06 | 2015-01-06 | Working method of superposition pressing oxygen production rocket |
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| CN201510005171.8A CN104775935A (en) | 2015-01-06 | 2015-01-06 | Working method of superposition pressing oxygen production rocket |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104948346A (en) * | 2015-06-09 | 2015-09-30 | 杜善骥 | Working method of continuous detonation overlapped stamping oxygen production rocket |
| CN104963789A (en) * | 2015-07-11 | 2015-10-07 | 杜善骥 | Working method of Laval nozzle effect stamping oxygen production rocket |
| CN105041508A (en) * | 2015-07-17 | 2015-11-11 | 杜善骥 | Working method of Laval nozzle effect superposition ram oxygen production rocket |
| CN105065137A (en) * | 2015-07-19 | 2015-11-18 | 杜善骥 | Working method of Laval nozzle effect detonation superposition ram rocket |
| CN105134410A (en) * | 2015-08-09 | 2015-12-09 | 杜善骥 | Operating method of detonation superposition ram propulsion and oxygen generation rocket based on Laval nozzle effect |
| CN105201688A (en) * | 2015-09-10 | 2015-12-30 | 杜善骥 | Working method of air-breathing propulsion and oxygen generation rocket based on De Laval nozzle effect |
-
2015
- 2015-01-06 CN CN201510005171.8A patent/CN104775935A/en active Pending
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104948346A (en) * | 2015-06-09 | 2015-09-30 | 杜善骥 | Working method of continuous detonation overlapped stamping oxygen production rocket |
| CN104963789A (en) * | 2015-07-11 | 2015-10-07 | 杜善骥 | Working method of Laval nozzle effect stamping oxygen production rocket |
| CN105041508A (en) * | 2015-07-17 | 2015-11-11 | 杜善骥 | Working method of Laval nozzle effect superposition ram oxygen production rocket |
| CN105065137A (en) * | 2015-07-19 | 2015-11-18 | 杜善骥 | Working method of Laval nozzle effect detonation superposition ram rocket |
| CN105134410A (en) * | 2015-08-09 | 2015-12-09 | 杜善骥 | Operating method of detonation superposition ram propulsion and oxygen generation rocket based on Laval nozzle effect |
| CN105201688A (en) * | 2015-09-10 | 2015-12-30 | 杜善骥 | Working method of air-breathing propulsion and oxygen generation rocket based on De Laval nozzle effect |
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