CN103758662A - Liquid air hybrid power rocket engine method and equipment - Google Patents

Liquid air hybrid power rocket engine method and equipment Download PDF

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Publication number
CN103758662A
CN103758662A CN201410048331.2A CN201410048331A CN103758662A CN 103758662 A CN103758662 A CN 103758662A CN 201410048331 A CN201410048331 A CN 201410048331A CN 103758662 A CN103758662 A CN 103758662A
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liquid air
rocket motor
liquid
storage tank
ejection
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CN201410048331.2A
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CN103758662B (en
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苟仲武
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Jiangsu Luzi Mali Food Co., Ltd
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苟仲武
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Abstract

The invention discloses a liquid air hybrid power rocket engine method and equipment. The liquid air hybrid power rocket engine method comprises the following steps that a rocket engine is provided with a liquid air storage tank, a liquid air nozzle is formed in the throat part at the narrowest part of the rear portion of the rocket engine, and the liquid air nozzle is connected with the liquid air storage tank through an ultra-low temperature liquid pump; liquid air is contained in the liquid air storage tank; the liquid air in the liquid air storage tank is ejected when the rocket engine runs; the liquid air ejected out of the liquid air storage tank is mixed with ultra-temperature supersonic speed wake flame gas ejected by the rocket engine; the temperature of the liquid air ejected by the liquid air nozzle rises sharply, the liquid air is expanded, and driving force of the rocket engine is increased. According to the liquid air hybrid power rocket engine method and equipment, liquid air media are used in a hybrid mode, heat generated by fuels is utilized fully, and environment pollution is reduced; under the condition of ensuring same driving force, the using amount of the fuels is lowered to a large extent, using cost is lowered, infrared characteristics and ultraviolet characteristics are reduced to a large extent, and a large effect is performed on the guided missile invisibility aspect.

Description

A kind of rocket motor method and apparatus of liquid air mixed power
Technical field
The invention belongs to rocket motor field, be specifically related to a kind of rocket motor method and apparatus of liquid air mixed power.
Background technique
Rocket motor utilizes impulse principle exactly, carries propellant agent, does not rely on the jet engine of ambient air.Rocket motor is the one of air breathing engine, the reaction mass in propellant container or launch vehicle (propellant agent) is become to high-speed jet, because Newton's third law produces thrust.Most of rocket motor obtains thrust by discharging high temperature and high speed tail gas, and solid or liquid propellant (by oxygenant and fuel composition) produce tail gas in firing chamber mesohigh (10-200bar) burning.
Rocket tube is one (normally gradually wealthy jet pipe of the convergent) thrust nozzle for motivation.It advances by combustion chambers burn the combustion gas producing for expanding and accelerating, and makes it to reach superelevation velocity of sound.
, in use there is following problem at present all rockets using:
1. fuel availability is low, from the long flame of rocket tube ejection, finds out, a large amount of heats is discharged in air, because the speed of rocket is relevant with the speed of material with the quality of the material ejecting, and the temperature of material is irrelevant, so heat waste is huge;
2. because fuel availability is low, so environmental pollution is serious, such as the Apollo of the U.S. fuel that number consume a second is more than ten times of the fuel that consumes across Atlantic aircraft first then of the mankind.
3. fuel availability is low, and fuel cost is also just very high; While taking part in international competition aspect launching an artificial satellite especially, fuel cost also becomes important one side;
4. because temperature is high, heat is strong, and infrared characteristic and ultraviolet characteristic are also just very strong, are easy to be detected, and are difficult to accomplish that the section of taking off is stealthy, after missile takeoff, can be found by the other side at once, and the other side can give warning in advance and prepare reply, counterattack, interception.
The fuel of rocket is no matter be solid or liquid, when burning, heat up rapidly, gasification, reaches 2,000 degree to 3,000 degree degree Celsius, because expanded by heating, be limited within the scope of firing chamber, form very large pressure, when the waste gas of burning sprays backward, the tail gas of ejection speed after Laval nozzle has reached supersonic speed.Along with expansion, speed increases, pressure decreased, and temperature is also in a slight decrease, and finally the gas of ejection and atmosphere mix, and amount of heat is wasted.
Liquid air is the light blue gas of liquefy after the air pressurized of nature is lowered the temperature again, there is lower heat of vaporization and the storing temperature of ultralow temperature, if after liquid air and superhigh temperature, ultrasonic wake flame are mixed, the heat of superhigh temperature, ultrasonic wake flame expands the liquid air that makes ultralow temperature gasify rapidly, when liquid air becomes gas by liquid, expanding in 1 atmospheric situation, volume can expand more than 800 times, volume acutely expands, and can more increase the Driving force of rocket motor.
Summary of the invention
The object of the invention is, by mixing, use liquid air medium, make full use of the heat that fuel produces, reduce environmental pollution, in the situation that guaranteeing same thrust, significantly reduce the use amount of fuel, make cost, because the temperature first mate of sprayed wake flame gas declines, the infrared characteristic of sprayed wake flame gas and ultraviolet characteristic are significantly reduced simultaneously; The liquid air that uses air liquefaction to obtain, utilizes natural resource as far as possible, utilizes to greatest extent fuel thermal energy, makes the pollution of environment drop to minimum.
The present invention is directed to the problems referred to above, a kind of rocket motor method and apparatus of liquid air mixed power is provided.
According to an aspect of the present invention, provide a kind of rocket motor method of liquid air mixed power, comprised the following steps:
S1, rocket motor arranges liquid air storage tank;
S2, the rocket motor rear portion venturi position at narrow place arranges liquid air nozzle, and described liquid air nozzle connects liquid air storage tank by super-low liquid pump;
S3, is equipped with liquid air in described liquid air storage tank;
S4, the liquid air in described liquid air storage tank sprays when rocket motor moves;
S5, superhigh temperature, the supersonic speed wake flame mixed gases of the liquid air of described liquid air storage tank ejection and rocket motor ejection;
S6, expansions that sharply raise, gasify of the liquid-air temperature of liquid air nozzle ejection, the Driving force of increase rocket motor.
Further, described step S2 is specially: the rocket motor rear portion venturi position at narrow place arranges liquid air nozzle, described liquid air nozzle connects liquid air storage tank by super-low liquid pump, and described liquid air nozzle is connected by super-low liquid pump seal with liquid air storage tank.Further, described step S3 is specially: at the in-built liquid air of described liquid air storage tank, seal described liquid air storage tank.
Further, described step S5 is specially: superhigh temperature, the ultrasonic wake flame mixed gases of the liquid air of described liquid air nozzle ejection and rocket motor ejection, the heat of superhigh temperature, ultrasonic wake flame gas makes the liquid air of ultralow temperature expand and gasify rapidly, when liquid air becomes gas by liquid, liquid air volume can expand more than hundreds of times, and temperature significantly reduces.
Further, described step S6 is specially: after the liquid air of described liquid air nozzle ejection and the superhigh temperature of rocket motor ejection, ultrasonic wake flame gas mix, become low temperature high pressure gas, by mixing, progressively complete, gas pressure continues to expand, and temperature reduces rapidly, along with the expansion of liquid air nozzle ejection gas, rocket speed increases, and the total amount of ejected matter increases, and motor power increases considerably.
According to another aspect of the invention, provide a kind of rocket motor equipment of liquid air mixed power, comprised following part:
Liquid air storage tank: in order to load liquid air;
Super-low liquid pump: in order to liquid air is transported to the ejection of liquid air nozzle when rocket motor moves, and superhigh temperature, the ultrasonic wake flame mixed gases of rocket motor ejection;
Liquid air nozzle: in order to liquid air is ejected into the venturi position at narrow place and superhigh temperature, the ultrasonic wake flame mixed gases of rocket motor ejection of rocket motor rear portion when rocket motor moves.
The liquid air storage tank that described liquid air storage tank is built-in or external hanging type.
Advantage of the present invention:
1, be the continuity of existing rocket motor technology, existing rocket engine system is almost constant;
2, high efficiency realizes the gas physical expansion of ejection, and fuel availability improves, and rocket motor thrust increases.
3, liquid air easily obtains, and low pollution, low cost.
Except object described above, feature and advantage, the present invention also has other object, feature and advantage.Below with reference to figure, the present invention is further detailed explanation.
Accompanying drawing explanation
The accompanying drawing that forms the application's a part is used to provide a further understanding of the present invention, and schematic description and description of the present invention is used for explaining the present invention, does not form inappropriate limitation of the present invention.
Fig. 1 is the rocket motor method flow diagram of a kind of liquid air mixed power of the present invention;
Fig. 2 is liquid air hybrid solid rocket motor structure schematic diagram of the present invention;
Fig. 3 is external hanging type liquid air hybrid solid rocket motor structure schematic diagram of the present invention;
Fig. 4 is liquid air mixing material rocket motor structure schematic diagram of the present invention.
Reference character:
1 is that load, 2 is that liquid air storage tank, 3 is that rocket, 4 is that rocket motor, 5 is that super-low liquid pump and 6 is liquid air nozzle.
Embodiment
In order to make object of the present invention, technological scheme and advantage clearer, below in conjunction with drawings and Examples, the present invention is further elaborated.Should be appreciated that specific embodiment described herein, only in order to explain the present invention, is not intended to limit the present invention.
Embodiment 1
With reference to figure 1, the rocket motor method of a kind of liquid air mixed power as shown in Figure 1, comprises the following steps:
S1, rocket motor arranges liquid air storage tank 2;
S2, the rocket motor rear portion venturi position at narrow place arranges liquid air nozzle 6, and described liquid air nozzle connects liquid air storage tank 2 by super-low liquid pump 5;
S3, is equipped with liquid air in described liquid air storage tank 2;
S4, the liquid air in described liquid air storage tank 2 sprays when rocket motor moves;
S5, superhigh temperature, the supersonic speed wake flame mixed gases of the liquid air that described liquid air storage tank 2 sprays and rocket motor ejection;
S6, the liquid-air temperature that liquid air nozzle 6 the sprays expansion that sharply raises, gasifies, increases the Driving force of rocket motor.
Described step S2 is specially: the rocket motor rear portion venturi position at narrow place arranges liquid air nozzle 6, described liquid air nozzle 6 connects liquid air storage tank 2 by super-low liquid pump 5, and described liquid air nozzle 6 and liquid air storage tank 2 are tightly connected by super-low liquid pump 5.Described step S3 is specially: at the in-built liquid air of described liquid air storage tank 2, seal described liquid air storage tank 2.
Described step S5 is specially: superhigh temperature, the ultrasonic wake flame mixed gases of the liquid air that described liquid air nozzle 6 sprays and rocket motor ejection, the heat of superhigh temperature, ultrasonic wake flame gas makes the liquid air of ultralow temperature expand and gasify rapidly, when liquid air becomes gas by liquid, liquid air volume can expand more than hundreds of times, and temperature significantly reduces.
Described step S6 is specially: after the liquid air that described liquid air nozzle 2 sprays and the superhigh temperature of rocket motor ejection, ultrasonic wake flame gas mix, become low temperature high pressure gas, by mixing, progressively complete, gas pressure continues to expand, temperature reduces rapidly, and along with liquid air nozzle 2 sprays the expansion of gas, rocket speed increases, the total amount of ejected matter increases, and motor power increases considerably.
Embodiment 2
Referring to figs. 2 to Fig. 4, the rocket motor equipment of a kind of liquid air mixed power as shown in Figures 2 to 4, comprises following part:
Liquid air storage tank 2: in order to load liquid air;
Super-low liquid pump 5: in order to liquid air is transported to liquid air nozzle 6 when rocket motor moves, spray, and superhigh temperature, the ultrasonic wake flame mixed gases of rocket motor ejection;
Liquid air nozzle 6: in order to liquid air is ejected into the venturi position at narrow place and superhigh temperature, the ultrasonic wake flame mixed gases of rocket motor ejection of rocket motor rear portion when rocket motor moves.
Described liquid air storage tank 2 is the liquid air storage tank 2 of built-in or external hanging type.
The present invention can be used for solid propellant rocket or the also rocket motor of body rocket motor or liquid-solid mixing, and optimum is the rocket motor of liquid-solid mixing.
In the present invention, the design of liquid air nozzle in rocket motor do not limit, and liquid air liquid storage mode is not limit, and can be built-in, external hanging type or other mode.
The present invention will produce high temperature by chemical reaction, make medium and produce because temperature raises expansion change into newly-increased liquid air and by liquid, become gas and the physical reactions of hundreds of times of expanding because be heated, improve fuel utilization efficiency, improve Economy.By mixing, use liquid air medium, make full use of the heat that fuel produces, reduce environmental pollution, in the situation that guaranteeing same thrust, the use amount that significantly reduces fuel, makes cost, simultaneously because the temperature of sprayed gas significantly declines, sprayed infrared characteristic and ultraviolet characteristic are significantly reduced, almost complete absence of.
The foregoing is only preferred embodiment of the present invention, in order to limit the present invention, within the spirit and principles in the present invention not all, any modification of doing, be equal to replacement, improvement etc., within all should being included in protection scope of the present invention.

Claims (7)

1. a rocket motor method for liquid air mixed power, is characterized in that, comprises the following steps:
S1, rocket motor arranges liquid air storage tank (2);
S2, the rocket motor rear portion venturi position at narrow place arranges liquid air nozzle (6), and described liquid air nozzle connects liquid air storage tank (2) by super-low liquid pump (5);
S3, is equipped with liquid air in described liquid air storage tank (2);
S4, the liquid air in described liquid air storage tank (2) sprays when rocket motor moves;
S5, superhigh temperature, the supersonic speed wake flame mixed gases of the liquid air of described liquid air storage tank (2) ejection and rocket motor ejection;
S6, expansions that sharply raise, gasify of the liquid-air temperature of liquid air nozzle (6) ejection, the Driving force of increase rocket motor.
2. the rocket motor method of liquid air mixed power according to claim 1, it is characterized in that, described step S2 is specially: the rocket motor rear portion venturi position at narrow place arranges liquid air nozzle (6), described liquid air nozzle (6) connects liquid air storage tank (2) by super-low liquid pump (5), and described liquid air nozzle (6) and liquid air storage tank (2) are tightly connected by super-low liquid pump (5).
3. the rocket motor method of liquid air mixed power according to claim 1, it is characterized in that, described step S3 is specially: at the in-built liquid air of described liquid air storage tank (2), seal described liquid air storage tank (2).
4. the rocket motor method of liquid air mixed power according to claim 1, it is characterized in that, described step S5 is specially: superhigh temperature, the ultrasonic wake flame mixed gases of the liquid air of described liquid air nozzle (6) ejection and rocket motor ejection, the heat of superhigh temperature, ultrasonic wake flame gas makes the liquid air of ultralow temperature expand and gasify rapidly, when liquid air becomes gas by liquid, liquid air volume can expand more than hundreds of times, and temperature significantly reduces.
5. the rocket motor method of liquid air mixed power according to claim 1, it is characterized in that, described step S6 is specially: after the liquid air of described liquid air nozzle (2) ejection and the superhigh temperature of rocket motor ejection, ultrasonic wake flame gas mix, become low temperature high pressure gas, by mixing, progressively complete, gas pressure continues to expand, temperature reduces rapidly, along with the expansion of liquid air nozzle (2) ejection gas, rocket speed increases, the total amount of ejected matter increases, and motor power increases considerably.
6. a rocket motor equipment for liquid air mixed power, is characterized in that, comprises following part:
Liquid air storage tank (2): in order to load liquid air;
Super-low liquid pump (5): in order to liquid air is transported to liquid air nozzle (6) ejection when rocket motor moves, and superhigh temperature, the ultrasonic wake flame mixed gases of rocket motor ejection;
Liquid air nozzle (6): in order to liquid air is ejected into the venturi position at narrow place and superhigh temperature, the ultrasonic wake flame mixed gases of rocket motor ejection of rocket motor rear portion when rocket motor moves.
7. the rocket motor equipment of liquid air mixed power according to claim 7, is characterized in that, described liquid air storage tank (2) is the liquid air storage tank (2) of built-in or external hanging type.
CN201410048331.2A 2014-02-12 2014-02-12 A kind of rocket motor method and apparatus of liquid air mixed power Active CN103758662B (en)

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Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN105822459A (en) * 2016-05-31 2016-08-03 河南海力特装备工程有限公司 Novel rocket engine
CN112800562A (en) * 2021-03-29 2021-05-14 星河动力(北京)空间科技有限公司 Thrust control method, thrust control device, electronic device, and storage medium

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3768254A (en) * 1962-07-09 1973-10-30 Boeing Co Rocket propulsion method and means
CN1506567A (en) * 2002-12-09 2004-06-23 浦晓亭 Attachment for rocket engine
CN103437914A (en) * 2013-08-23 2013-12-11 中国航天科技集团公司第六研究院第十一研究所 Variable-cycle air turbine combined engine of rocket
CN203702370U (en) * 2014-02-12 2014-07-09 苟仲武 Liquid air hybrid power rocket engine equipment

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3768254A (en) * 1962-07-09 1973-10-30 Boeing Co Rocket propulsion method and means
CN1506567A (en) * 2002-12-09 2004-06-23 浦晓亭 Attachment for rocket engine
CN103437914A (en) * 2013-08-23 2013-12-11 中国航天科技集团公司第六研究院第十一研究所 Variable-cycle air turbine combined engine of rocket
CN203702370U (en) * 2014-02-12 2014-07-09 苟仲武 Liquid air hybrid power rocket engine equipment

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN105822459A (en) * 2016-05-31 2016-08-03 河南海力特装备工程有限公司 Novel rocket engine
CN112800562A (en) * 2021-03-29 2021-05-14 星河动力(北京)空间科技有限公司 Thrust control method, thrust control device, electronic device, and storage medium

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Effective date of registration: 20191127

Address after: 221000 room 607, block B, University Pioneer Park, No. 99, University Road, Tongshan District, Xuzhou high tech Industrial Development Zone, Jiangsu Province

Patentee after: Jiangsu Luzi Mali Food Co., Ltd

Address before: 100190, Beijing, Zhongguancun Academy of Sciences Haidian District South Road, No. 8, Cheung garden, No. 1507

Patentee before: Gou Zhongwu

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