CN105257429B - Composite rocket engine - Google Patents
Composite rocket engine Download PDFInfo
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- CN105257429B CN105257429B CN201510853470.7A CN201510853470A CN105257429B CN 105257429 B CN105257429 B CN 105257429B CN 201510853470 A CN201510853470 A CN 201510853470A CN 105257429 B CN105257429 B CN 105257429B
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- air intake
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Abstract
The invention provides a kind of composite rocket engine, including shell, fixed guide post, detonation engine, external admission road, the second combustor and system for solid rocket grain.Detonation engine and system for solid rocket grain are integrated in inside the shell by composite rocket engine, and the high-temperature fuel gas that in detonation engine, the burning of fuel and system for solid rocket grain generates can significantly increase the thrust of generation, and then improve the thermodynamic efficiency of composite rocket engine and the performance of dynamical system；Detonation engine is arranged at the front end of shell, reduces the size of the first combustor, saves inner space, simplifies the structure of composite rocket engine；The inner space saved can increase the volume of system for solid rocket grain, the performance of the dynamical system of lifting composite rocket engine；When the system for solid rocket grain afterburnt, unburned fuel in the high-temperature fuel gas being sprayed by the outlet of housing with via external admission road leaked-in air reactive combustion to produce thrust, it is to avoid the waste of fuel, improve the economic performance of composite rocket engine.
Description
Technical field
The present invention relates to engine art, more particularly, to a kind of composite rocket engine.
Background technology
In recent years, deepening continuously along with the research to hypersonic vehicle and Single Stage To Orbit dynamical system, air-breathing
Formula combined cycle engine technology has obtained quick development, particularly to rocket based combined cycle electromotor and the basis set conjunction of turbine
The further investigation of cycle engine, has just had begun to the research of related application technology from the eighties in 20th century.Wherein rocket
Base combined cycle engine is exactly the composite engine effectively being combined rocket and punching engine, and in difference
Working condition under so that two kinds of different electromotors play respective maximum performance advantages, thus successfully realizing Aero-Space
Powerpropelled best of breed.And turbine base combined cycle engine is then to carry out effectively turbogenerator and punching engine
A kind of composite engine of combination.Certainly both composite engines all can play spy in different space flight and aviation tasks
Play the role of, such as when low latitude carries out hypersonic flight, select voyage remote, the low turbine base combined cycle engine of oil consumption.
But during Practical Project uses, turboram combined cycle engine is sufficiently complex due to building block, simultaneously to whirlpool
Turbine technical requirements are also excessively harsh and be subject to very big development restriction；Although and rocket punching press combined cycle engine knot
Structure is relatively easy, but its overall performance cannot further improve.
Content of the invention
In view of problem present in background technology, it is an object of the invention to provide a kind of composite rocket engine, its
The structure of electromotor can be simplified, and improve the overall thermodynamic efficiency of electromotor, the performance of dynamical system and economic performance.
To achieve these goals, the invention provides a kind of composite rocket engine, it includes shell, fixed guide
Post, detonation engine, external admission road, the second combustor and system for solid rocket grain.
Shell has：Air intake, is arranged at the front end of shell, ringwise, connects outside atmosphere；And supersonic speed spray
Mouthful, it is arranged at the rear end of shell.
Fixed guide post is provided with multiple fuel inlets, and fuel inlet is arranged on the outer surface of fixed guide post, connection
Outside fuel supply system.
Detonation engine includes conical inner body, housing, the first combustor, multiple interior air intake duct, oxidant storage tank, multiple oxygen
Agent outlet tube, multiple fuel inlet pipe, fuel collecting pipe, multiple fuel delivery pipe, fuel inlet pipe and multiple fuel nozzle ports.
Conical inner body has：Precursor, stretches out from the front end of shell and rear portion is connected to fixed guide post；And after body, in shell,
It is integrally formed with the precursor of conical inner body.Housing around body after entirely and is fixedly installed on the outer surface at precursor rear portion, and whole
The outer surface of body surrounds axially extended first combustor afterwards, and the first combustor end in the axial direction is outlet；Multiple interior enter
Air flue, one end of each interior air intake duct is connected with air intake via the first valve, the other end and the first combustion chamber.Oxidant stores up
Tank is contained in precursor.Multiple oxidizer discharge pipes are arranged in precursor, and each oxidizer discharge pipe one end is via the second valve and oxygen
Agent storage tank connects, and the other end is connected with corresponding interior air intake duct.Multiple fuel inlet pipes are arranged in precursor, each fuel input
Pipe one end is connected with corresponding fuel inlet.Fuel collecting pipe and is located at conical inner body between the precursor and rear body of conical inner body
Precursor and rear internal portion, connect fuel inlet pipe, collect the fuel that inputted by fuel inlet pipe.Multiple fuel delivery pipe settings
Conical inner body rear internal and circumferentially distributed, radially extend, one end of each fuel delivery pipe connection fuel collecting pipe.Fuel
The rear internal portion of the centrally disposed cone of inlet pipe, ringwise, is all connected with the other end of the plurality of fuel delivery pipe, receives warp
The fuel being passed through by the plurality of fuel delivery pipe.Multiple fuel nozzle ports circumferences are evenly distributed on the rear body of centrally disposed cone
Interior and opening and radially extends on the outer surface of the rear body of conical inner body, and each fuel nozzle ports connection fuel inlet pipe and first fires
Burn room.
External admission road is arranged between shell and detonation engine, and one end is communicated in the air intake of shell.
Second combustor is arranged at the space positioned at housing and the rear body rear of conical inner body of inside the shell, and front end is communicated in
The outlet of the first combustor and the other end in external admission road, rear end is communicated in the supersonic speed spout of shell.
System for solid rocket grain houses and is fixed on inside the shell and is located at the second burning interior, and inner hollow is for air flow.
Wherein, when described composite rocket engine starts, outside air cannot be passed through and enter the via interior air intake duct
One combustor, starts the second valve, and the oxidant in oxidant storage tank enters first via oxidizer discharge pipe and interior air intake duct
Combustor, and with via fuel inlet, fuel inlet pipe, fuel collecting pipe, fuel delivery pipe, fuel inlet pipe and fuel nozzle ports
Enter the fuel reaction of the first combustor, complete the startup of described composite rocket engine；Described composite rocket engine
After startup, open the first valve and close the second valve, from the substantial amounts of air of outside injection via interior air intake duct enter the first combustor,
Enter the second combustor, in described composite rocket engine running afterwards, air and entrance via external admission road
The fuel knock burning of the first combustor, sprays high-temperature fuel gas and via the second combustor and supersonic speed via the outlet of housing
Spout is quickly discharged to produce thrust；The high-temperature fuel gas being sprayed by the outlet of housing, when the second combustor, light solid medicine
Post, with via external admission road leaked-in air reactive combustion and produce high-temperature fuel gas, high-temperature fuel gas are via supersonic speed for system for solid rocket grain
Spout is quickly discharged to produce thrust；Unburned combustion in system for solid rocket grain afterburnt, the high-temperature fuel gas being sprayed by the outlet of housing
Material with via external admission road leaked-in air again reactive combustion to produce thrust.
Beneficial effects of the present invention are as follows：
In the composite rocket engine according to the present invention, detonation engine and system for solid rocket grain are integrated in inside the shell,
And the high-temperature fuel gas that in detonation engine, the burning of the burning of fuel and system for solid rocket grain generates can significantly increase described group
The thrust that box-like rocket engine produces, and then improve thermodynamic efficiency and the dynamical system of described composite rocket engine
The performance of system；Detonation engine is arranged at the front end of shell, reduces the size of the first combustor, saves inner space, simplifies
The structure of described composite rocket engine；Meanwhile, the inner space of saving can increase the volume of system for solid rocket grain, and lifting is described
The performance of the dynamical system of composite rocket engine；When system for solid rocket grain afterburnt, the high-temperature fuel gas being sprayed by the outlet of housing
In unburned fuel with via external admission road leaked-in air again reactive combustion to produce thrust, it is to avoid the waste of fuel, carry
The high economic performance of described composite rocket engine.
Brief description
Fig. 1 is the schematic diagram of the composite rocket engine according to the present invention；
Fig. 2 is the sectional view of an angle of the composite rocket engine according to the present invention；
Fig. 3 is the sectional view that the composite rocket engine A-A along the line shown in Fig. 2 makes；
Fig. 4 is the sectional view that the composite rocket engine B-B along the line shown in Fig. 2 makes；
Fig. 5 is the sectional view of another angle of the composite rocket engine according to the present invention；
Fig. 6 is the enlarged drawing of the encircled portion of composite rocket engine shown in Fig. 5；And
Fig. 7 is the sectional view that the composite rocket engine C-C along the line shown in Fig. 5 makes.
Wherein, description of reference numerals is as follows：
1 shell 35 oxidant storage tank
11 air intake 36 oxidizer discharge pipe
12 supersonic speed spout 37 fuel inlet pipe
2 fixed guide post 38 fuel collecting pipe
21 fuel inlet 39 fuel delivery pipe
3 detonation engine 3A fuel inlet pipes
31 conical inner body 3B fuel nozzle ports
311 precursor 4 external admission road
Body 5 second combustor after 312
32 housing 6 system for solid rocket grain
33 first combustor V1 the first valves
331 outlet V2 second valves
Air intake duct in 34
Specific embodiment
To describe in detail with reference to the accompanying drawings the present invention composite rocket engine.
Referring to figs. 1 to Fig. 7, shell 1 is included according to the composite rocket engine of the present invention, fixed guide post 2, pinking are sent out
Motivation 3, external admission road 4, the second combustor 5 and system for solid rocket grain 6.
Shell 1 has：Air intake 11, is arranged at the front end of shell 1, ringwise, connects outside atmosphere；And supersonic speed
Spout 12, is arranged at the rear end of shell 1.
Fixed guide post 2 is provided with multiple fuel inlets 21, and fuel inlet 21 is arranged at the outer surface of fixed guide post 2
On, connection outside fuel supply system.
Detonation engine 3 includes conical inner body 31, housing 32, the first combustor 33, multiple interior air intake duct 34, oxidant storage
Tank 35, multiple oxidizer discharge pipe 36, multiple fuel inlet pipe 37, fuel collecting pipe 38, multiple fuel delivery pipe 39, fuel enter
Pipe 3A and multiple fuel nozzle ports 3B.Conical inner body 31 has：Precursor 311, stretches out from the front end of shell 1 and rear portion is connected to admittedly
Determine lead 2；And after body 312, in shell 1, be integrally formed with the precursor 311 of conical inner body 31.Housing 32 is around whole
Individual rear body 312 is simultaneously fixedly installed on the outer surface at precursor 311 rear portion, with entirely after body 312 outer surface surround axially extended
First combustor 33, the first combustor 33 end in the axial direction is outlet 331；Multiple interior air intake ducts 34, each interior air intake duct 34
One end connect with air intake 11 via the first valve V1, the other end is connected with the first combustor 33.Oxidant storage tank 35 houses
In precursor 311.Multiple oxidizer discharge pipes 36 are arranged in precursor 311, and each oxidizer discharge pipe 36 one end is via the second valve
V2 is connected with oxidant storage tank 35, and the other end is connected with corresponding interior air intake duct 34.Multiple fuel inlet pipes 37 are arranged at precursor
In 311, each fuel inlet pipe 37 one end is connected with corresponding fuel inlet 21.Fuel collecting pipe 38 is in the precursor of conical inner body 31
Between 311 and rear body 312 and be located inside the precursor 311 of conical inner body 31 and rear body 312, connect fuel inlet pipe 37, collect
The fuel being inputted by fuel inlet pipe 37.In the rear body 312 of the centrally disposed cone 31 of multiple fuel delivery pipe 39 and circumferential
It is distributed, radially extend, one end connection fuel collecting pipe 38 of each fuel delivery pipe 39.The centrally disposed cone of fuel inlet pipe 3A 31
Rear body 312 inside, ringwise, all connect with the other end of the plurality of fuel delivery pipe 39, receive via the plurality of combustion
The fuel that material outlet tube 39 is passed through.Multiple fuel nozzle ports 3B circumferences are evenly distributed in the rear body 312 of centrally disposed cone 31
And opening and radially extends on the outer surface of the rear body 312 of conical inner body 31, each fuel nozzle ports 3B connect fuel inlet pipe 3A
With the first combustor 33.
External admission road 4 is arranged between shell 1 and detonation engine 3, and one end is communicated in the air intake 11 of shell 1.
Second combustor 5 is arranged at the space positioned at housing 32 and rear body 312 rear of conical inner body 31 in shell 1,
Front end is communicated in the outlet 331 of the first combustor 33 and the other end in external admission road 4, and rear end is communicated in the supersonic speed of shell 1
Spout 12.
System for solid rocket grain 6 houses and is fixed in shell 1 and is located in the second combustor 5, and inner hollow is for air stream
Dynamic.
Wherein, when described composite rocket engine starts, outside air cannot be passed through and enter via interior air intake duct 34
First combustor 33, starts the second valve V2, the oxidant in oxidant storage tank 35 is via oxidizer discharge pipe 36 and interior air inlet
Road 34 enter the first combustor 33, and with via fuel inlet 21, fuel inlet pipe 37, fuel collecting pipe 38, fuel delivery pipe
39th, the fuel reaction of fuel inlet pipe 3A and fuel nozzle ports 3B entrance the first combustor 33, completes described rocket combination and starts
The startup of machine；After described composite rocket engine starts, open the first valve V1 and close the second valve V2, a large amount of from outside injection
Air via interior air intake duct 34 enter the first combustor 33, via external admission road 4 enter the second combustor 5, described combination type
In rocket engine running afterwards, air is burnt with the fuel knock entering the first combustor 33, via housing 32
Outlet 331 spray high-temperature fuel gas quickly discharging to produce thrust via the second combustor 5 and supersonic speed spout 12；By shell
The high-temperature fuel gas that the outlet 331 of body 32 sprays, when the second combustor 5, light system for solid rocket grain 6, system for solid rocket grain 6 with via outer
Air intake duct 4 leaked-in air reactive combustion simultaneously produces high-temperature fuel gas, and high-temperature fuel gas are quickly discharged via supersonic speed spout 12 to produce
Raw thrust；When the unburned fuel in system for solid rocket grain 6 afterburnt, the high-temperature fuel gas being sprayed by the outlet 331 of housing 32 with via outer
Air intake duct 4 leaked-in air again reactive combustion to produce thrust.
In the composite rocket engine according to the present invention, detonation engine 3 and system for solid rocket grain 6 are integrated in shell 1
Interior, and the high-temperature fuel gas that in detonation engine 3, the burning of the burning of fuel and system for solid rocket grain 6 generates can significantly increase institute
State the thrust of composite rocket engine generation, and then improve the thermodynamic efficiency of described composite rocket engine and move
The performance of Force system；Detonation engine 3 is arranged at the front end of shell 1, reduces the size of the first combustor 33, saves internal empty
Between, simplify the structure of described composite rocket engine；Meanwhile, the inner space of saving can increase the volume of system for solid rocket grain 6,
Lift the performance of the dynamical system of described composite rocket engine；When system for solid rocket grain 6 afterburnt, by the outlet 331 of housing 32
Unburned fuel in the high-temperature fuel gas spraying is with via external admission road 4 leaked-in air, reactive combustion, to produce thrust, is kept away again
Exempt from the waste of fuel, improve the economic performance of described composite rocket engine.
In the composite rocket engine according to the present invention, with reference to Fig. 1, Fig. 2 and Fig. 5, in one embodiment, supersonic speed
Spout 12 flare.
In the composite rocket engine according to the present invention, with reference to Fig. 1, Fig. 2 and Fig. 5, in one embodiment, precursor
311 profile is tapered.
In the composite rocket engine according to the present invention, with reference to Fig. 1, Fig. 2 and Fig. 5, in one embodiment, center cone
The rear end of the rear body 312 of body 31 is tapered taper, so that the outlet 331 of the first combustor 33 end in the axial direction is plug
Spout.
In the composite rocket engine according to the present invention, with reference to Fig. 3 and Fig. 7, in one embodiment, the plurality of combustion
Material entrance 21 is four.
In the composite rocket engine according to the present invention, with reference to Fig. 3 and Fig. 7, in one embodiment, the plurality of interior
Air intake duct 34 is the angle between four and adjacent interior air intake duct 34 is 90 degree.
In the composite rocket engine according to the present invention, with reference to Fig. 5 and Fig. 6, in one embodiment, interior air intake duct 34
Inner surface be variable cross-section, and narrow from the width axially towards the direction of the first combustor 33.
In the composite rocket engine according to the present invention, with reference to Fig. 4, in one embodiment, the plurality of fuel is defeated
Outlet pipe 39 is the angle between four and consecutive fuel outlet tube 39 is 90 degree.
In the composite rocket engine according to the present invention, in one embodiment, the rear body 312 of conical inner body 31 with front
Body 311 passes through to be welded into one.
In the composite rocket engine according to the present invention, with reference to Fig. 1, Fig. 2 and Fig. 5, in one embodiment, solid medicine
Post 6 is annular.
In the composite rocket engine according to the present invention, in one embodiment, system for solid rocket grain 6 is described after burning completely
The speed of composite rocket engine can reach 3 Mach.
Claims (10)
1. a kind of composite rocket engine is it is characterised in that include：
Shell (1), has：
Air intake (11), is arranged at the front end of shell (1), ringwise, connects outside atmosphere；And
Supersonic speed spout (12), is arranged at the rear end of shell (1)；
Fixed guide post (2), is provided with multiple fuel inlets (21), and fuel inlet (21) is arranged at the outside of fixed guide post (2)
Fuel supply system on surface, outside connection；
Detonation engine (3), including：
Conical inner body (31), has：
Precursor (311), stretches out from the front end of shell (1) and rear portion is connected to fixed guide post (2)；And
Body (312) afterwards, in shell (1), are integrally formed with the precursor (311) of conical inner body (31)；
Housing (32), around body (312) after entirely and be fixedly installed on the outer surface at precursor (311) rear portion, with entirely after body
(312) outer surface surrounds axially extended first combustor (33), and the first combustor (33) end in the axial direction is outlet
(331)；
Multiple interior air intake ducts (34), one end is connected with air intake (11) via the first valve (V1), the other end and the first combustor
(33) connect；
Oxidant storage tank (35), is contained in precursor (311)；
Multiple oxidizer discharge pipes (36), are arranged in precursor (311), and one end is via the second valve (V2) and oxidant storage tank (35)
Connection, the other end is connected with corresponding interior air intake duct (34)；
Multiple fuel inlet pipes (37), are arranged in precursor (311), one end is connected with corresponding fuel inlet (21)；
Fuel collecting pipe (38), between the precursor (311) and rear body (312) of conical inner body (31) and positioned at conical inner body (31)
Precursor (311) and rear body (312) internal, connection fuel inlet pipe (37), collect the fuel being inputted by fuel inlet pipe (37)；
Multiple fuel delivery pipe (39), the rear body (312) of centrally disposed cone (31) is interior and circumferentially distributed, radially extend,
One end connection fuel collecting pipe (38) of each fuel delivery pipe (39)；
Fuel inlet pipe (3A), the rear body (312) of centrally disposed cone (31) is internal, ringwise, with the output of the plurality of fuel
The other end of pipe (39) all connects, and receives the fuel being passed through via the plurality of fuel delivery pipe (39)；And
Multiple fuel nozzle ports (3B), circumference be evenly distributed in the rear body (312) of centrally disposed cone (31) and opening located at
On the outer surface of rear body (312) of conical inner body (31) and radially extend, each fuel nozzle ports (3B) connection fuel inlet pipe (3A) and
First combustor (33)；
External admission road (4), is arranged between shell (1) and detonation engine (3), one end is communicated in the air intake of shell (1)
(11)；
Second combustor (5), is arranged at rear body (312) rear positioned at housing (32) and conical inner body (31) in shell (1)
Space, front end is communicated in the outlet (331) of the first combustor (33) and the other end of external admission road (4), and rear end is communicated in
The supersonic speed spout (12) of shell (1)；And
System for solid rocket grain (6), houses and is fixed in shell (1) and be located in the second combustor (5), and inner hollow is for air
Flowing；
Wherein, when described composite rocket engine starts, outside air cannot be passed through and enter the via interior air intake duct (34)
One combustor (33), starts the second valve (V2), the oxidant in oxidant storage tank (35) via oxidizer discharge pipe (36) and
Interior air intake duct (34) enters the first combustor (33), and with via fuel inlet (21), fuel inlet pipe (37), fuel collecting pipe
(38), fuel delivery pipe (39), fuel inlet pipe (3A) and fuel nozzle ports (3B) enter the fuel reaction of the first combustor (33),
Complete the startup of described composite rocket engine；After described composite rocket engine starts, open the first valve (V1) and close
Close the second valve (V2), from the substantial amounts of air of outside injection via interior air intake duct (34) enter the first combustor (33), via enter
Air flue (4) enters the second combustor (5), in described composite rocket engine running afterwards, air with enter the
The fuel knock burning of one combustor (33), sprays high-temperature fuel gas and via the second burning via the outlet (331) of housing (32)
Room (5) and supersonic speed spout (12) are quickly discharged to produce thrust；The high-temperature fuel gas being sprayed by the outlet (331) of housing (32)
When the second combustor (5), light system for solid rocket grain (6), system for solid rocket grain (6) is anti-with via external admission road (4) leaked-in air
Should burn and produce high-temperature fuel gas, high-temperature fuel gas are quickly discharged to produce thrust via supersonic speed spout (12)；Work as system for solid rocket grain
(6) afterburnt, the unburned fuel in the high-temperature fuel gas being sprayed by the outlet (331) of housing (32) flows with via external admission road (4)
The air entering again reactive combustion to produce thrust.
2. composite rocket engine according to claim 1 is it is characterised in that supersonic speed spout (12) flare.
3. composite rocket engine according to claim 1 is it is characterised in that the profile of precursor (311) is tapered.
4. composite rocket engine according to claim 1 is it is characterised in that the rear body (312) of conical inner body (31)
Rear end be tapered taper so that the outlet (331) of the first combustor (33) end in the axial direction be plug spout.
5. composite rocket engine according to claim 1, the plurality of fuel inlet (21) is four.
6. composite rocket engine according to claim 1, the plurality of interior air intake duct (34) is four and adjacent interior
Angle between air intake duct (34) is 90 degree.
7. composite rocket engine according to claim 1, the inner surface of interior air intake duct (34) is variable cross-section, and along axle
Narrow from the width to towards the direction of the first combustor (33).
8. composite rocket engine according to claim 1, the plurality of fuel delivery pipe (39) is four and adjacent
Angle between fuel delivery pipe (39) is 90 degree.
9. composite rocket engine according to claim 1 is it is characterised in that the rear body (312) of conical inner body (31)
Pass through to be welded into one with precursor (311).
10. composite rocket engine according to claim 1 is it is characterised in that system for solid rocket grain (6) is annular.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201510853470.7A CN105257429B (en) | 2015-11-30 | 2015-11-30 | Composite rocket engine |
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|---|---|---|---|
| CN201510853470.7A CN105257429B (en) | 2015-11-30 | 2015-11-30 | Composite rocket engine |
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| CN105257429A CN105257429A (en) | 2016-01-20 |
| CN105257429B true CN105257429B (en) | 2017-03-08 |
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Families Citing this family (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106050475A (en) * | 2016-08-03 | 2016-10-26 | 杨斯涵 | Liquid-solid coupling type rocket engine |
| CN106438108B (en) * | 2016-08-26 | 2018-10-12 | 南京理工大学 | It is big to adjust than type solid rocket ramjet gas flow regulating device |
| CN108757221A (en) * | 2018-05-30 | 2018-11-06 | 南京理工大学 | A kind of liquid Asia burning ramjet |
| CN108825405B (en) * | 2018-07-03 | 2020-09-08 | 西北工业大学 | Axial symmetry structure RBCC full flow channel adopting multi-stage rocket |
| CN109667683B (en) * | 2018-12-26 | 2020-07-17 | 中国人民解放军战略支援部队航天工程大学 | Variable thrust continuous detonation rocket-based engine and aircraft |
| CN109404165B (en) * | 2018-12-26 | 2019-11-19 | 中国人民解放军战略支援部队航天工程大学 | The continuous pinking rocket base engine and aircraft of thruster vector control |
| CN112879178B (en) * | 2021-01-22 | 2022-11-04 | 南京理工大学 | Solid rocket ramjet based on detonation combustion |
| CN114320666B (en) * | 2022-01-06 | 2023-06-30 | 中南大学 | Air turbine rocket engine system |
| CN116291954B (en) * | 2023-05-23 | 2023-08-01 | 陕西普利美材料科技有限公司 | Reusable high-efficiency energy conversion solid rocket thrust device |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| FR2629136B1 (en) * | 1985-09-17 | 1990-11-09 | Aerospatiale | STATOREACTOR PROVIDED WITH A PLURALITY OF CARBIDE AND MISSILE AIR SUPPLY HANDLES PROVIDED WITH SUCH A STATOREACTOR |
| CN104295406B (en) * | 2014-05-26 | 2016-08-24 | 清华大学 | A kind of rocket punching press combined engine with ring-like ejection structure |
| CN104110325B (en) * | 2014-07-30 | 2016-01-13 | 清华大学 | Combined cycle engine |
| CN204041270U (en) * | 2014-07-30 | 2014-12-24 | 清华大学 | Combined cycle engine |
| CN105065138A (en) * | 2015-07-19 | 2015-11-18 | 杜善骥 | Working method of detonation punching oxygen-generation rocket based on Laval nozzle effect |
| CN205190059U (en) * | 2015-11-30 | 2016-04-27 | 清华大学 | Modular rocket engine |
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