CN104727978A - Working method of superimposed ram rocket - Google Patents
Working method of superimposed ram rocket Download PDFInfo
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- CN104727978A CN104727978A CN201510005184.5A CN201510005184A CN104727978A CN 104727978 A CN104727978 A CN 104727978A CN 201510005184 A CN201510005184 A CN 201510005184A CN 104727978 A CN104727978 A CN 104727978A
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- rocket
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- ram
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Abstract
The invention discloses a working method of a superimposed ram rocket and relates to the technical field of aviation and aviation. The working method of the superimposed ram rocket is applied to aerospace plane engines, aerospace vehicle engines and missiles. The working method of the superimposed ram rocket is achieved according to a jet flow vacuum working principle, after a head small rocket drives a jet flow gas suction device to generate first gas suction, fuel is mixed and ignition is carried out, power generated by combustion drives the other set of jet flow gas suction device, fuel is added again, and stronger power is generated after combustion to drive the rocket to fly. Due to the fact that the head small rocket is a traditional rocket, combustion needs liquid oxygen and rocket fuel, and the head small rocket can take off at a zero speed. When the speed of the rocket meets a ram condition, the rocket enters a ram flying condition, and the thrust generated by the superimposed ram rocket is much bigger than that of a ram rocket without superposition by consuming oxygen of the same amount.
Description
Technical field
Superposition ram 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.Superpose the method for huge rocket secondary suction, rocket is enable to be competent at just large transport flight weight in endoatmosphere and in atmospheric layer, to consume less oxygen, empty sky flies and re-entry space vehicle is established oneself in an unassailable position in the business competition of space on the horizon, and in order to this target, we should effort.
Summary of the invention
Superposition ram rocket method of work is in brief: head mouse 1 to start in rear flame jet drive first set jet suction means < air-breathing duct 2 (or, with outer suction duct 3, induction chamber 4, Laval nozzle 5, diffusing tube (a) 6 is called first set jet suction means >, in fuel adding point (a) 10, fuel adding point (b) 11 filling rocket fuel, light a fire in igniting place 9, burn at diffusing tube (a) 6 after fuel mixes with air, jet suction means < diffusing tube (a) 6 is overlapped in the injection motivational drive second produced, diffusing tube (b1) 5, outer air-breathing duct (b) 16, air-breathing is shouted 17 and is called the second cover jet suction means > fuel adding point (c) 13, fuel adding point (d) 14 filling liquid, solid fuel and catalyzer, light a fire at Dian Chu (b) 18, burn at rocket chamber, the powered rocket flight produced.
When rocket flight 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 (a) 3 and outer air-breathing duct (b) 16, 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, meanwhile at fuel adding point (c) 13 and fuel adding point (d) 14 filling rocket liquid, 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 shouts 17 by the air intake of punching press, be diffused the flame ignition of pipe (a) 6 and push in diffusing tube (b) 15, meanwhile another part air is stamped to 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, import the typhon mouth place of diffusing tube (b) 15, light a fire with igniting place (b) 18, spray in rocket chamber 7, burn at rocket chamber, the thrust produced makes rocket flight.
When rocket enters space, closeall valve 8, enables rocket chamber meet the requirement of space flight.
Accompanying drawing explanation
Fig. 1 is many interior gas duct superposition ram 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, first time air-breathing by these 4 interior air-breathing ducts through induction chamber 4, enter diffusing tube (a) 6, diffusing tube (a) 6 adds the high velocity air that fuel ignition burning produces, when spraying into diffusing tube (b) 15 (Open valve 8), the vacuum of producing shouts 17 air intakes that will be stamped by outer air-breathing duct (b) 16 and air-breathing, flame flow through diffusing tube pushes in firing chamber 7, meanwhile another part air is stamped to two punching press sucking pipes 19 and (opens two valves 8 on this two tubes, can to annotate before punching press sucking pipe 19 rocket fuel) if needed, import the typhon mouth place of diffusing tube (b) 15, spray in rocket chamber 7, or light a fire with igniting place (b) 18, burn at rocket chamber 7, make rocket flight.
Fig. 2 is inside and outside gas duct superposition ram 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, air-breathing enters diffusing tube (a) 6 by these 4 interior air-breathing ducts and outer air-breathing duct 3 for the first time, the high velocity air that rocket fuel produces in diffusing tube (a) 6 burning, when spraying into diffusing tube (b) 15 (and Open valve 8), the vacuum of producing can be shouted 17 by outer air-breathing duct (b) 16 and air-breathing and be sucked by ram-air, be pushed in induction chamber 7, meanwhile another part air is stamped to two punching press sucking pipes 19 and (opens two valves 8 on this two tubes, can to annotate before punching press sucking pipe 19 rocket fuel) if needed, import the typhon mouth place of diffusing tube (b) 15, spray in rocket chamber 7, or light a fire with igniting place (b) 18, the rocket fuel of entrained air mixes, burn at rear portion rocket chamber, the thrust produced makes rocket flight.。
Fig. 3 is outer air-breathing duct superposition ram rocket figure, as shown in Figure 3, this design only has outer air-breathing duct 3, air-breathing enters diffusing tube (a) 6 by outer air-breathing duct 3 for the first time, the high velocity air that diffusing tube (a) 6 produces, when spraying into diffusing tube (b) 15 (Open valve 8), the vacuum of producing can shout 17 by air intake by outer air-breathing duct (b) 16 and air-breathing, be pushed in induction chamber 7, meanwhile another part air is stamped to two punching press sucking pipes 19 and (opens two valves 8 on this two tubes, can to annotate before punching press sucking pipe 19 rocket fuel) if needed, import the typhon mouth place of diffusing tube (b) 15, spray in rocket chamber 7, or light a fire with igniting place (b) 18, mix in the rocket fuel diffusing tube 15 of entrained air, burn at rocket chamber, the thrust produced makes rocket flight.
Fig. 4 is single interior gas duct superposition ram rocket figure, as shown in Figure 4, 1 interior air-breathing duct 2, penetrate inside from head mouse 1 front dead center centre to 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, calculate the distance between intersection point and diffusing tube or position, vacuum (being similar to fluid eddies principle) can be produced for first time air-breathing in this process hopper centre, vacuum is produced for second time air-breathing after injecting diffusing tube (a) 6, 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 filling rocket fuel, the high velocity air produced after fuel burns in diffusing tube 6, spray in diffusing tube (b) 15 (Open valve 8), the vacuum of producing can shout 17 by air intake through outer air-breathing duct (b) 16 and air-breathing, in fuel adding point (c) 13, fuel adding point (d) l4 annotates rocket fuel, be pushed in induction chamber 7 and just become third time air-breathing, meanwhile another part air is stamped to two punching press sucking pipes 19 and (opens two valves 8 on this two tubes, if needed can punching press sucking pipe 19 suction port place filling rocket fuel), import the typhon mouth place of diffusing tube (b) 15, spray in rocket chamber 7, light a fire with igniting place (b) 18 or light a fire with diffusing tube (a) 6, burn at rocket chamber, the thrust produced makes rocket flight.
Fig. 5 is gas duct superposition ram 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, outside the head mouse 1 front dead center heart, penetrate head mouse 1 inner, 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 in centre around air-breathing duct 2, the flame of Laval nozzle 5 (nozzle group) sprays and meets at a bit with funnel-like, and set intersection point the distance of diffusing tube or position (this is vacuum important indicator), the flame of Laval nozzle sprays with funnel-like, can produce vacuum (approximate flow eddies) in funnel is first time air-breathing, flame produces vacuum for second time air-breathing after injecting diffusing tube (a) 6, 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), diffusing tube (a) 6 adds the high velocity air produced after rocket fuel point burns, when spraying into diffusing tube (b) 15 (valve 8 is in normally open), the vacuum of producing can shout 17 by with the air intake be stamped by outer air-breathing duct (b) 16 and air-breathing, be pushed in induction chamber 7 and just become third time air-breathing, meanwhile another part air is stamped to two punching press sucking pipes 19 and (opens two valves 8 on this two tubes, can to annotate before punching press sucking pipe 19 rocket fuel) if needed, import the typhon mouth place of diffusing tube (b) 15, spray in rocket chamber 7, or light a fire with igniting place (b) 18, burn at rocket chamber, the thrust produced makes rocket flight.
Fig. 6 is the thin chart of rocket part name of superposition ram rocket.
Embodiment
Superposition ram rocket method of work.The composition of its equipment unit: head mouse 1, interior air-breathing duct 2 (or, and outer suction duct 3), induction chamber 4, Laval nozzle 5, diffusing tube (a) 6, 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) this 14, diffusing tube b15, outer air-breathing duct (b) 16, air-breathing shout 17, igniting place (b) 18, punching press sucking pipe 19.
Superposition ram rocket operating principle, as shown in Figure 1, when rocket flight speed can meet punching press condition, head mouse quits work, atmospheric air is stamped and inhales duct 2 in 4, continue and enter induction chamber 4, portion of air is stamped in diffusing tube (a) 6, meanwhile fuel adding point (a) 10, fuel adding point (b) 11 filling rocket liquid, solid rocket fuel and catalyzer, lighted a fire by igniting (a) 9, in the typhon mouth combustion of diffusing tube (a) 6, flame is ejected in diffusing tube (b) 15, gap is provided with between diffusing tube (a) 6 and diffusing tube (b) 15, vacuum can be produced around gap and diffusing tube (b) 15 mouth of pipe, vacuum shouts 17 air intakes that will be stamped by outer air-breathing duct (b) 16 and air-breathing, meanwhile fuel adding point (c) 13, fuel adding point (d) 14 filling rocket liquid, solid rocket fuel and catalyzer, the flame ignition sprayed by igniting (b) 18 or diffusing tube (a) 6, burn in firing chamber 7 and promote rocket flight, meanwhile another part air is stamped to two punching press sucking pipes 19 and (opens two valves 8 on these two punching press sucking pipes 19, can to annotate before punching press sucking pipe 19 rocket fuel) if needed, import on certain position of typhon mouth of diffusing tube (b) 15, spray in rocket chamber 7, the thrust produced makes rocket flight, superposition ram rocket method of work important feature is, compared with the rocket not having to superpose, consume the oxygen of same quantity, superposition rocket can produce much bigger rocket thrust.Thus rocket launching cost can be reduced.
The data of " water-vapour spray vacuum pump " and < sparger >, can search out on the net.
Claims (9)
1. superpose ram rocket method of work.It comprises head mouse 1, interior air-breathing duct 2 (or, and outer suction duct 3), induction chamber 4, Laval nozzle 5, diffusing tube (a) 6, 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) this 14, diffusing tube b15, outer air-breathing duct (b) 16, air-breathing shout 17, igniting place (b) 18, punching press sucking pipe 19, the superposition ram rocket be made up of 1-19.
2. superpose punching press can be regarded as: 2 grades of air-breathing punching presses.
3. punching press sucking pipe 19 suction port place arranges fuel adding point.
4. diffusing tube (a) 6 typhon mouth one end is as fuel chambers.
5. at fuel adding point (a) 13, fuel adding point (b) 14 filling rocket fuel and catalyzer.
6. the valve 8 of design in diffusing tube (b) 15.
7. the flame of diffusing tube (a) 6 ejection, for diffusing tube (b) 15 igniting/design 1 punching press sucking pipe, designs many punching press sucking pipes 19.
8. closeall valve 8, makes firing chamber 7 meet the condition of space flight.
9. many head mouses, drive 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.
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| CN201510005184.5A CN104727978A (en) | 2015-01-06 | 2015-01-06 | Working method of superimposed ram rocket |
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Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104963789A (en) * | 2015-07-11 | 2015-10-07 | 杜善骥 | Working method of Laval nozzle effect stamping oxygen production rocket |
| CN104963791A (en) * | 2015-06-29 | 2015-10-07 | 杜善骥 | Laval effect superposition air suction oxygen production rocket working method |
| CN105020054A (en) * | 2015-06-29 | 2015-11-04 | 杜善骥 | Laval effect superposition air-breathing rocket work method |
| CN105020055A (en) * | 2015-07-06 | 2015-11-04 | 杜善骥 | Work method for Laval nozzle effect air suction 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 |
| CN105156230A (en) * | 2015-07-12 | 2015-12-16 | 杜善骥 | Working method of Laval nozzle effect stacking ram rocket |
| CN107972892A (en) * | 2018-01-08 | 2018-05-01 | 梁思武 | One kind volume inhales boosting carrier rocket |
| RU186094U1 (en) * | 2018-01-11 | 2018-12-29 | Акционерное Общество "Государственное Машиностроительное Конструкторское Бюро "Радуга" Имени А.Я. Березняка" | Supersonic ramjet engine (options) |
| RU2696884C2 (en) * | 2018-01-11 | 2019-08-07 | Акционерное Общество "Государственное Машиностроительное Конструкторское Бюро "Радуга" Имени А.Я. Березняка" | Supersonic straight-flow air-jet engine (versions) |
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Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104963791A (en) * | 2015-06-29 | 2015-10-07 | 杜善骥 | Laval effect superposition air suction oxygen production rocket working method |
| CN105020054A (en) * | 2015-06-29 | 2015-11-04 | 杜善骥 | Laval effect superposition air-breathing rocket work method |
| CN105020055A (en) * | 2015-07-06 | 2015-11-04 | 杜善骥 | Work method for Laval nozzle effect air suction rocket |
| CN104963789A (en) * | 2015-07-11 | 2015-10-07 | 杜善骥 | Working method of Laval nozzle effect stamping oxygen production rocket |
| CN105156230A (en) * | 2015-07-12 | 2015-12-16 | 杜善骥 | Working method of Laval nozzle effect stacking ram 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 |
| CN107972892A (en) * | 2018-01-08 | 2018-05-01 | 梁思武 | One kind volume inhales boosting carrier rocket |
| RU186094U1 (en) * | 2018-01-11 | 2018-12-29 | Акционерное Общество "Государственное Машиностроительное Конструкторское Бюро "Радуга" Имени А.Я. Березняка" | Supersonic ramjet engine (options) |
| RU2696884C2 (en) * | 2018-01-11 | 2019-08-07 | Акционерное Общество "Государственное Машиностроительное Конструкторское Бюро "Радуга" Имени А.Я. Березняка" | Supersonic straight-flow air-jet engine (versions) |
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