CN106050475A - Liquid-solid coupling type rocket engine - Google Patents
Liquid-solid coupling type rocket engine Download PDFInfo
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- CN106050475A CN106050475A CN201610629210.6A CN201610629210A CN106050475A CN 106050475 A CN106050475 A CN 106050475A CN 201610629210 A CN201610629210 A CN 201610629210A CN 106050475 A CN106050475 A CN 106050475A
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- rocket
- engine
- fluid
- solid coupling
- liquid
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/72—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid and solid propellants, i.e. hybrid rocket-engine plants
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- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
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Abstract
The invention discloses a liquid-solid coupling type rocket engine. The liquid-solid coupling type rocket engine comprises a cylindrical rocket outer shell. A solid powder column is arranged in the cylindrical rocket outer shell. A central cone is arranged at the front end of the cylindrical rocket outer shell. The central cone comprises a front body, a rear body and a central cone shell. An external air inlet is formed between the front body and the cylindrical rocket outer shell. The central cone is internally provided with a liquid engine and a first combustion chamber ignited through the liquid engine. A second combustion chamber is formed between an outlet of the first combustion chamber and the solid powder column. The liquid engine is arranged in the central cone and comprises an incendiary agent storage tank, an oxidizing agent storage tank, a liquid collection mixer and injectors. By means of the liquid-solid coupling type rocket engine, the external dimension of the first combustion chamber is decreased; the internal space is saved; and the structure of the rocket engine is simplified, thereby the size of the solid powder column can be increased, and performance of a power system of the liquid-solid coupling type rocket engine is improved.
Description
Technical field
The present invention relates to a kind of engine art, particularly relate to a kind of fluid-solid coupling formula rocket engine.
Background technology
Along with the development of science, people have invented the rocket having made various model, and rocket engine is jet
The one of electromotor, becomes the reactant (propellant) in propellant storage tank or vehicle into high-speed jet, due to newton
Three law of motions and produce thrust.
Liquid-propellant rocket engine makes oxidant and incendiary agent respectively enter combustor by pump or gases at high pressure, and two kinds push away
Enter agent composition and mix combining combustion at combustor；And solid propellant rocket direct filling solid propellant in combustor, solid
Rocket engine is made up of powder column, combustor, nozzle component and igniter etc., and powder column is by propellant and a small amount of additive system
The middle tune cylinder (hollow space is combustion front) become；Hybrid rocket uses the electromotor that solid and liquid mixing advance；
In recent years due to people's further investigation to hypersonic vehicle；Especially rocket based combined cycle electromotor is inquired into and wound
Newly so that solid-liquid combination formula cycle engine has given play to maximum performance and advantage, thus becomes and realize Aero-Space Powered Propulsion
Optimum selection, and turbine base combined cycle engine is applicable to carry out hypersonic flight in low latitude, but at Practical Project
During use, propeller for turboprop machine technology being required height, turbine pump structure is complicated, rigorous service condition, and pressure head is high, therefore designs
The turbine pump that efficiency is high is also the key in reseach of engine.
No matter these rocket internal structures have the most complicated, and its major part can be summarized as housing and burning housing is round
Tubular, front end is the tip closed, and there is jet pipe rear end, and the high-temperature high-pressure combustion gas that fuel combustion produces is sprayed rapidly from jet pipe
Going out, rocket is to utilize recoil strength to fly to forward；During practical engineering application, the reliability of rocket and safety are the most very
Important, in order to ensure rocket reliability and safety, improve payload weight simultaneously, first have to ensure Propellant Supply system
System, engine control system is properly functioning, next deadweight being necessary for reducing rocket, and in the 3rd rocket to be saved, body is practical empty
Between；And reliability and reduction deadweight cannot meet in the design process simultaneously.
Summary of the invention
It is an object of the invention to by providing a kind of fluid-solid coupling formula rocket engine, it can the structure of cylinder electromotor
Innovation and optimization engine fuel supply system, save rocket engine inner space simultaneously, and improve fluid-solid coupling formula rocket
The thermodynamic efficiency that electromotor is overall, the performance of dynamical system and economic performance.
Technical scheme: for achieving the above object, technical scheme is as follows:
A kind of fluid-solid coupling formula rocket engine, including rocket cylinder blanket, is provided with solid in described rocket cylinder blanket
Body powder column, is formed with rocket supersonic speed spout at described rocket cylinder blanket afterbody, it is characterised in that: at described rocket cylinder
The front end of shape shell is provided with a conical inner body, and conical inner body includes precursor, rear body and is coaxially disposed and position with described rear body
In the centrum housing of rear external side, between described precursor and described rocket cylinder blanket, it is formed with outside air enters
Mouthful, in described conical inner body, it is provided with liquid engine and the first combustor lighted a fire by described liquid engine, in institute
Stating and be formed with the second combustor between outlet and the system for solid rocket grain of the first combustor, the rear body of described conical inner body is fixedly installed on
In rocket cylinder blanket, it is formed with to enter with described outside air between described conical inner body housing and rocket cylinder blanket
The ambient inlet air passage of mouth connection, the outlet of this ambient inlet air passage and described second combustion chamber；Described liquid engine
In centrally disposed cone, liquid engine includes incendiary agent storage tank, oxidant storage tank, collection liquid mixer and ejector filler, institute
Stating incendiary agent storage tank to be connected with described collection liquid mixer by pipeline respectively with oxidant storage tank, described ejector filler is connected to described
On collection liquid mixer.
Described precursor is conical top cover, and described rear body is cylindrical structure, and described precursor is before rocket cylinder blanket
End stretches out, and rear portion is connected to the front end of rear body.
Body by integral forming before described in described rear body.
It is provided with multiple oxidizer discharge pipe, multiple oxidizer discharge between described oxidant storage tank and collection liquid mixer
One end of pipe is connected with the oxidant inlet of collection liquid mixer, the other end concatenation oxidant hydraulic pump of multiple oxidizer discharge pipes
With corresponding oxidant outlet connection.
The described auxiliary tube being connected with electromagnetism auxiliary valve that is provided with on the side outer wall of oxidant storage tank, described auxiliary tube
The other end and the first combustion chamber.
When described fluid-solid coupling formula rocket engine starts, outside air cannot be passed through and enter via internal inlet channel
First combustor, starts pilot solenoid valve, and the oxidant in oxidant storage tank enters via auxiliary tube and internal inlet channel
First combustor, and with via multiple incendiary agent outlet tubes, collection liquid mixer and propellant spray device enter the first combustor
Fuel reaction, complete the startup of described fluid-solid coupling formula rocket engine；After described fluid-solid coupling formula rocket engine starts,
Open control damper and hydraulic pump, and simultaneously close off pilot solenoid valve, so from the outside substantial amounts of air of injection via inside
Inlet channel enters the first combustor, then enters the second combustor via external admission road；Described fluid-solid coupling formula rocket engine
In running upon actuation, air mixes fission burning with entering the first chamber fuel, via the outlet of conical inner body
Ejection high-temperature fuel gas and quickly discharge to produce thrust, by body after conical inner body through the second combustor and supersonic speed spout
The high-temperature fuel gas of outlet ejection through the second combustor, light system for solid rocket grain, system for solid rocket grain flows into via external admission road
Air reaction burn and produce high-temperature fuel gas, high-temperature fuel gas quickly discharges to produce thrust via supersonic speed spout.
Further, described conical inner body precursor is taper, is provided with liquid engine unit in precursor.
Further, described rear body is cylindrical structure, is provided with incendiary agent storage tank and oxidant storage in cylinder
Tank, collection liquid mixer and ejector filler and the first combustor.
Further, the rear end in described rear body exit is tapered taper, so that the first combustor is at cylinder
Laterally (axially) on the exit of end be conical funnel shape spout.
Further, in body housing, it is additionally provided with multiple incendiary agent outlet tube in the rear, and the most circumferentially distributed；
One end of described incendiary agent outlet tube connects the incendiary agent entrance of collection liquid mixer, the other end concatenation of described incendiary agent outlet tube
The outlet of incendiary agent hydraulic pump and corresponding incendiary agent storage tank.The plurality of fuel delivery pipe is 8 and consecutive fuel
Angle between outlet tube is 45 degree.
Further, described rear internal multiple inside inlet channel that is provided with, multiple internal inlet channels are 8, and
Angle between adjacent inner inlet channel is 45 degree.
Further, described rear body connects by being weldingly connected with conical inner body precursor；Described rear body and infundibulate spout
By being welded into one.
Further, described system for solid rocket grain is hollow cylindrical structure, system for solid rocket grain, houses and is fixed on rocket cylinder
In shape shell, between shell and the inner barrel of fixing powder column, it is welded into a hollow cylinder by both sides end plate, in cylinder
Portion's hollow is as gas channel.
Further, the most internal it is provided with collection liquid mixer；The described liquid mixer that integrates as disk structure,
Ordered distribution multiple incendiary agent entrance and multiple oxidant inlet on the extrados of described disc, at described collection liquid mixer
Being provided with multiple propellant spray device on one side end face in order, the ejector filler of embodiment of the present invention is 8, and consecutive fuel spray
Angle between device is 45 degree, ejector filler connection fuel inlet and the first combustor.
Beneficial effect
(1) the fluid-solid coupling formula rocket engine of the present invention, is housed in liquid engine and system for solid rocket grain outside rocket cylinder
In shell, and the high-temperature fuel gas that in liquid engine, the burning of the first fuel in combustion chamber and the burning of system for solid rocket grain generate passes through
The thrust that can be greatly increased described fluid-solid coupling formula rocket engine discharged by arrow jet pipe, also can improve fluid-solid coupling formula simultaneously
The thermodynamic efficiency of rocket engine and the performance of dynamical system.
(2) the fluid-solid coupling formula rocket engine of the present invention, its liquid engine is arranged at rocket cylindrical housings front end
Centrum in, reduce the size of the first combustor, save inner space, simplify the knot of fluid-solid coupling formula rocket engine
Structure, the inner space simultaneously saved can increase the volume of system for solid rocket grain, promotes the dynamical system of fluid-solid coupling formula rocket engine
The performance of system.
(3) the fluid-solid coupling formula rocket engine of the present invention, by incendiary agent storage tank, oxidant storage tank, collection liquid mixer complete
Portion is contained in conical inner body；System uses collection liquid mixer, it is possible to ensure system fuel supply stability and reliability, simultaneously
The safety of lifting system.
Accompanying drawing explanation
Fig. 1 is the schematic diagram of the fluid-solid coupling formula rocket engine of the present invention；
Fig. 2 is the sectional view of an angle of the fluid-solid coupling formula rocket engine of the present invention；
Fig. 3 is the sectional view of the collection liquid mixer of the fluid-solid coupling formula rocket engine of the present invention；
Fig. 4 is the sectional view of the incendiary agent storage tank of the fluid-solid coupling formula rocket engine of the present invention；
Fig. 5 is the sectional view of the oxidant storage tank of the fluid-solid coupling formula rocket engine of the present invention；
Fig. 6 is the air intake of fluid-solid coupling formula rocket engine of the present invention, control damper and internal inlet channel
Partial schematic diagram.
Fig. 7 is the conical inner body structural representation of the fluid-solid coupling formula rocket engine of the present invention.
Label in figure
1 rocket cylinder blanket, 2 conical inner bodies, 3 oxidizer discharge pipes, 4 fuel inlets, 5 outside air openings, 6 liquid start
Machine, 7 incendiary agent storage tanks, 8 oxidant storage tanks, 9 oxidant outlet, 10 collection liquid mixers, 11 precursors, 12 internal air inlets are led to
Road, 13 first combustor, 14 external admission roads, 15 ejector fillers, 16 incendiary agent outlet tubes, 17 incendiary agent entrances, 18 oxidant inlets,
19 incendiary agent outlet, 20 incendiary agent hydraulic pumps, 21 pilot solenoid valves, 22 fuel auxiliary tubes, 23 centrum housings, 24
Two combustor, 25 conical funnel shape spouts, 26 supersonic speed spouts, 27 system for solid rocket grains, 28 oxidant hydraulic pumps, 29 gas flow optimized
Valve.Body after 30.
Detailed description of the invention
Below in conjunction with the accompanying drawings the present invention is further described:
As shown in Figure 1 and Figure 2, a kind of solid-liquid coupling formula rocket engine, it includes rocket cylindrical shell 1, conical inner body 2, outer
Boundary's air intake 5, liquid engine 6, ambient inlet air passage 14, internal inlet channel 12, fuel inlet the 4, first combustor 13,
Incendiary agent storage tank 7, oxidant storage tank 8, collection liquid mixer 10, propellant spray device the 15, second combustor 24 and system for solid rocket grain 27 with
And supersonic speed spout.
It is provided with outside air opening 5 in the front end of rocket cylindrical shell body 1, connects outside atmosphere, cylindrical at rocket
The rear end of shell 1 is provided with supersonic speed spout.
A conical inner body 2 it is provided with, at this conical inner body and rocket cylinder blanket 1 in the front end of rocket cylinder blanket
Between be formed with outside air opening, in conical inner body 2, be provided with liquid engine 6 and lighted a fire by liquid engine
One combustor 13, is formed with the second combustor 24 between the outlet and system for solid rocket grain 27 of described first combustor,
The rear body of conical inner body is fixedly installed in rocket cylinder blanket 1, between this rear body 30 and rocket cylinder blanket
It is formed with the ambient inlet air passage 14 connected with outside air opening 5, the outlet of this ambient inlet air passage and the second combustor 24
Connection；In the centrally disposed cone of liquid engine 6, liquid engine includes that incendiary agent storage tank 7, oxidant storage tank 8, liquid collecting mix
Clutch 10 and ejector filler 15, incendiary agent storage tank 7 and oxidant storage tank 8 are connected with collection liquid mixer 10 by pipeline respectively, spray
Note device 15 is connected to collect on liquid mixer.
Being provided with the rear body of conical inner body in rocket cylinder blanket 1, rear internal at conical inner body is respectively arranged with
Incendiary agent storage tank 7 and oxidant storage tank 8, rear internal at conical inner body is additionally provided with collection liquid mixer 10 and the first combustor
13, thus ensure the reliability and stability of combustion supply system.
As shown in Figure 1, Figure 2, shown in Fig. 7, outside the front end of described rocket cylinder blanket and conical inner body junction are provided with
Boundary's air intake.
Conical inner body includes that precursor 11, rear body 30 and centrum housing 23, described precursor 11 are conical top cover, rear body
30 is cylindrical structure, and described precursor 11 stretches out from the front end of rocket cylinder blanket 1, and rear portion is connected to body 30 after drum type brake
Front end；Described rear body 30, is positioned in rocket cylinder blanket 1, and is integrally formed with the precursor 11 of conical inner body 2；Described liquid
In the centrally disposed cone of body electromotor 6；Described liquid engine includes incendiary agent storage tank 7, oxidant storage tank 8, liquid collecting mixing
Device 10, ejector filler 15 and the first combustor 13 all house and are fixed in conical inner body.
Rear body 30 connects by being weldingly connected with conical inner body precursor 11；Conical inner body housing is around whole rear body 30 and fixes
It is arranged at the external rear face of conical inner body precursor.Rear body 30 end in the axial direction is the outlet of conical funnel shape.
As shown in Figure 6, between the outer wall and rocket cylindrical shell body 1 of the first combustor 13, it is provided with multiple inside to enter
Gas passage 12；Internal inlet channel 12 one end connects with the first combustor 13, and other end concatenation control damper 29 is empty with the external world
Gas entrance 5 connects.
As shown in Fig. 2, Fig. 3, Fig. 4, Fig. 5, between oxidant storage tank 7 and collection liquid mixer 10, it is provided with multiple oxidant
Outlet tube 3.One end of multiple oxidizer discharge pipes 3 is connected with the oxidant inlet 18 of collection liquid mixer 10, other end concatenation oxygen
Agent hydraulic pump 28 connects with corresponding oxidant outlet 9.
Multiple incendiary agent outlet tube 16 it is additionally provided with in rear body 30, and the most circumferentially distributed；Incendiary agent outlet tube 16
One end connect collection liquid mixer 10 incendiary agent entrance 17, incendiary agent outlet tube 16 the other end concatenation incendiary agent hydraulic pump 20
Outlet 19 with corresponding incendiary agent storage tank connects；Multiple incendiary agent outlet tubes 16 are 8, and adjacent incendiary agent outlet tube it
Between angle be 45 degree.
Multiple propellant spray devices 15, circumference is evenly distributed in rear body 30, and liquid-propellant rocket engine opening is located at rear body
On the outer surface of 30, also radial taper extends, and multiple propellant spray devices 15 connect fuel inlet 4 and the first combustor 13.
The side outer wall of oxidant storage tank 8 is provided with system initial start electromagnetism auxiliary valve 21, is connected with auxiliary tube
22；The other end and first combustor 13 of institute's auxiliary tube 22 connect.
External admission passage 14, is arranged between rocket cylinder blanket 1 and liquid engine 6, and one end is communicated in rocket circle
The outside air opening 5 of cylindrical outer cover 1.
Second combustor 24, the space being positioned at rear body 30 rear being arranged in rocket cylinder blanket 1, the second combustor
24 front ends are communicated in outlet and the other end of external admission passage 14 of the first combustor 13, and rear end is communicated in the supersonic speed of shell
Spout 26.
System for solid rocket grain 27 is cylindrical structure, houses and is fixed in rocket cylinder blanket and is positioned at the second combustor
In, the passage that its inner hollow flows for air.
Rear body 30 is cylindrical structure, is provided with incendiary agent storage tank 7 and oxidant storage tank 8 in cylinder, and liquid collecting mixes
Device and ejector filler and the first combustor.
The rear end in rear body 30 exit is tapered taper, so that the first combustor 13 is on cylinder laterally (axially)
The exit of end be conical funnel shape spout 25.
The most internal multiple inside inlet channel 12 that is provided with, multiple internal inlet channels are 8, and adjacent inner air inlet is led to
Angle between road is 45 degree.
Described rear body 30 connects by being weldingly connected with conical inner body precursor 11；Described rear body 30 passes through with infundibulate spout 25
It is welded into one.
System for solid rocket grain 27 is hollow cylindrical structure, system for solid rocket grain 27, houses and is fixed in rocket cylinder blanket, Gu
Determining to be welded into a hollow cylinder by both sides end plate between the shell of powder column and inner barrel, cylinder inner hollow is as gas
Circulation road.
Collection liquid mixer 10 it is provided with in the rear in body 30；Integrate liquid mixer 10 as disk structure, at disc
Ordered distribution multiple incendiary agent entrance and multiple oxidant inlet on extrados, on a side end face of collection liquid mixer 10 in order
Being provided with multiple propellant spray device, the ejector filler of embodiment of the present invention is that the angle between 8, and consecutive fuel ejector filler is
45 degree, ejector filler connection fuel inlet and the first combustor.
The work process of rocket engine of the present invention is:
When fluid-solid coupling formula rocket engine starts, outside air cannot be passed through and enter the first combustion via internal inlet channel 12
Burning room 13, start pilot solenoid valve 21, the oxidant in oxidant storage tank 8 enters via auxiliary tube 22 and internal inlet channel 12
Enter the first combustor 13, and enter with via multiple incendiary agent outlet tubes 16, collection liquid mixer 10 and propellant spray device 15
The fuel reaction of the first combustor, completes the startup of fluid-solid coupling formula rocket engine；Fluid-solid coupling formula rocket engine starts
After, open control damper 29 and hydraulic pump, and simultaneously close off pilot solenoid valve 21, so from outside injection substantial amounts of air warp
Entered the first combustor 13 by internal inlet channel 12, then enter the second combustor 24 via external admission road 14；Fluid-solid coupling formula
In rocket engine running upon actuation, air mixes fission burning with entering the first chamber fuel, via center
After cone, body exports the high-temperature fuel gas sprayed and quickly discharges to produce via the second combustor 24 and supersonic speed spout 26 excessively
Raw thrust, through the second combustor, is lighted system for solid rocket grain 27 by the high-temperature fuel gas of the outlet ejection of body after conical inner body, Gu
Body powder column 27 is with via external admission road 14 leaked-in air reactive combustion and produce high-temperature fuel gas, and high-temperature fuel gas sprays via supersonic speed
Mouth 26 is quickly discharged to produce thrust.
The fluid-solid coupling formula rocket engine of the present invention, its liquid engine and integrated column are arranged at rocket cylindrical housings
Front end, reduce the size of the first combustor, save inner space, simplify the structure of fluid-solid coupling formula rocket engine, with
Time the inner space saved can increase the volume of system for solid rocket grain, promote the dynamical system of described fluid-solid coupling formula rocket engine
Performance.
Claims (10)
1. a fluid-solid coupling formula rocket engine, including rocket cylinder blanket, is provided with in described rocket cylinder blanket
System for solid rocket grain, is formed with rocket supersonic speed spout at described rocket cylinder blanket afterbody, it is characterised in that: at described rocket circle
The front end of cylindrical outer cover is provided with a conical inner body, and conical inner body includes precursor, rear body and is coaxially disposed also with described rear body
After being positioned at, the centrum housing of external side, is formed with outside air between described precursor and described rocket cylinder blanket and enters
Mouthful, in described conical inner body, it is provided with liquid engine and the first combustor lighted a fire by described liquid engine, in institute
Stating and be formed with the second combustor between outlet and the system for solid rocket grain of the first combustor, the rear body of described conical inner body is fixedly installed on
In rocket cylinder blanket, it is formed with to enter with described outside air between described conical inner body housing and rocket cylinder blanket
The ambient inlet air passage of mouth connection, the outlet of this ambient inlet air passage and described second combustion chamber；Described liquid engine
In centrally disposed cone, liquid engine includes incendiary agent storage tank, oxidant storage tank, collection liquid mixer and ejector filler, institute
Stating incendiary agent storage tank to be connected with described collection liquid mixer by pipeline respectively with oxidant storage tank, described ejector filler is connected to described
On collection liquid mixer.
Fluid-solid coupling formula rocket engine the most according to claim 1, it is characterised in that: described precursor is conical top cover,
Described rear body is cylindrical structure, before described precursor stretches out from the front end of rocket cylinder blanket, and rear portion is connected to rear body
End.
Fluid-solid coupling formula rocket engine the most according to claim 2, it is characterised in that: precursor one described in described rear body
Molding.
Fluid-solid coupling formula rocket engine the most according to claim 3, it is characterised in that: outside described first combustor
Multiple internal inlet channel it is provided with between wall and rocket cylindrical shell body；Described internal inlet channel one end and the first burning
Room connects, and internal inlet channel other end concatenation control damper connects with outside air opening.
Fluid-solid coupling formula rocket engine the most according to claim 4, it is characterised in that: the plurality of internal inlet channel
It is 8, and the angle between adjacent interior inlet channel is 45 degree.
Fluid-solid coupling formula rocket engine the most according to claim 1, it is characterised in that: described ejector filler is that circumference is uniform
It is distributed the most internal multiple, multiple propellant spray devices connection fuel inlet and the first combustor.
Fluid-solid coupling formula rocket engine the most according to claim 6, it is characterised in that: propellant spray device is 8, and
Angle between consecutive fuel ejector filler is 45 degree.
Fluid-solid coupling formula rocket engine the most according to claim 1, it is characterised in that: at described oxidant storage tank and collection
Multiple oxidizer discharge pipe, one end of multiple oxidizer discharge pipes and the oxidant collecting liquid mixer it is provided with between liquid mixer
Entrance connects, and the other end concatenation oxidant hydraulic pump of multiple oxidizer discharge pipes is with corresponding oxidant outlet even
Logical.
Fluid-solid coupling formula rocket engine the most according to claim 1, it is characterised in that: the most internal it is additionally provided with
Multiple incendiary agent outlet tubes, and the most circumferentially distributed；One end of described incendiary agent outlet tube connects the burning of collection liquid mixer
Agent entrance, the other end concatenation incendiary agent hydraulic pump of described incendiary agent outlet tube is with the outlet of corresponding incendiary agent storage tank even
Logical.
Fluid-solid coupling formula rocket engine the most according to claim 1, it is characterised in that: at described oxidant storage tank
The auxiliary tube being connected with electromagnetism auxiliary valve it is provided with, the other end of described auxiliary tube and the first combustion chamber on the outer wall of side.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610629210.6A CN106050475A (en) | 2016-08-03 | 2016-08-03 | Liquid-solid coupling type rocket engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610629210.6A CN106050475A (en) | 2016-08-03 | 2016-08-03 | Liquid-solid coupling type rocket engine |
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| Publication Number | Publication Date |
|---|---|
| CN106050475A true CN106050475A (en) | 2016-10-26 |
Family
ID=57196328
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610629210.6A Pending CN106050475A (en) | 2016-08-03 | 2016-08-03 | Liquid-solid coupling type rocket engine |
Country Status (1)
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| CN (1) | CN106050475A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107503862A (en) * | 2017-10-10 | 2017-12-22 | 北京航空航天大学 | A kind of hybrid rocket combination circulation propulsion system and its control method |
| CN112879178A (en) * | 2021-01-22 | 2021-06-01 | 南京理工大学 | Solid rocket ramjet based on detonation combustion |
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| CN1343282A (en) * | 1999-03-10 | 2002-04-03 | 威廉国际有限责任公司 | Rocket engine |
| US20030102408A1 (en) * | 2001-11-30 | 2003-06-05 | Casillas Eduardo D. | Reusable space access launch vehicle system |
| US20060145018A1 (en) * | 2003-03-28 | 2006-07-06 | Rutan Elbert L | Unitized hybrid rocket system |
| CN105257429A (en) * | 2015-11-30 | 2016-01-20 | 清华大学 | Combined type rocket engine |
| CN105351113A (en) * | 2015-11-30 | 2016-02-24 | 清华大学 | Rocket based combined engine |
| CN205841036U (en) * | 2016-08-03 | 2016-12-28 | 杨斯涵 | A kind of fluid-solid coupling formula rocket engine |
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2016
- 2016-08-03 CN CN201610629210.6A patent/CN106050475A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1343282A (en) * | 1999-03-10 | 2002-04-03 | 威廉国际有限责任公司 | Rocket engine |
| US20030102408A1 (en) * | 2001-11-30 | 2003-06-05 | Casillas Eduardo D. | Reusable space access launch vehicle system |
| US20060145018A1 (en) * | 2003-03-28 | 2006-07-06 | Rutan Elbert L | Unitized hybrid rocket system |
| CN105257429A (en) * | 2015-11-30 | 2016-01-20 | 清华大学 | Combined type rocket engine |
| CN105351113A (en) * | 2015-11-30 | 2016-02-24 | 清华大学 | Rocket based combined engine |
| CN205841036U (en) * | 2016-08-03 | 2016-12-28 | 杨斯涵 | A kind of fluid-solid coupling formula rocket engine |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107503862A (en) * | 2017-10-10 | 2017-12-22 | 北京航空航天大学 | A kind of hybrid rocket combination circulation propulsion system and its control method |
| CN112879178A (en) * | 2021-01-22 | 2021-06-01 | 南京理工大学 | Solid rocket ramjet based on detonation combustion |
| CN112879178B (en) * | 2021-01-22 | 2022-11-04 | 南京理工大学 | Solid rocket ramjet based on detonation combustion |
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Application publication date: 20161026 |
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