CN109026440A - A kind of empty day propulsion system based on rocket combined engine - Google Patents
A kind of empty day propulsion system based on rocket combined engine Download PDFInfo
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- CN109026440A CN109026440A CN201810779138.4A CN201810779138A CN109026440A CN 109026440 A CN109026440 A CN 109026440A CN 201810779138 A CN201810779138 A CN 201810779138A CN 109026440 A CN109026440 A CN 109026440A
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- chamber
- wall
- air
- intake duct
- heat exchanger
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
- F02C7/042—Air intakes for gas-turbine plants or jet-propulsion plants having variable geometry
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/12—Cooling of plants
- F02C7/14—Cooling of plants of fluids in the plant, e.g. lubricant or fuel
- F02C7/141—Cooling of plants of fluids in the plant, e.g. lubricant or fuel of working fluid
- F02C7/143—Cooling of plants of fluids in the plant, e.g. lubricant or fuel of working fluid before or between the compressor stages
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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
- F02K7/00—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof
- F02K7/10—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof characterised by having ram-action compression, i.e. aero-thermo-dynamic-ducts or ram-jet engines
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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
- F02K7/00—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof
- F02K7/10—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof characterised by having ram-action compression, i.e. aero-thermo-dynamic-ducts or ram-jet engines
- F02K7/18—Composite ram-jet/rocket engines
-
- 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
- F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
-
- 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
- F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
- F02K9/60—Constructional parts; Details not otherwise provided for
- F02K9/62—Combustion or thrust chambers
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Geometry (AREA)
- Exhaust Gas After Treatment (AREA)
Abstract
The empty day propulsion system based on rocket combined engine that the invention discloses a kind of, empty day propulsion system include the combustion chamber of the air intake duct of front, intermediate duct compressor and tail portion；It include: air intake duct, duct compressor, combustion chamber；Wherein air intake duct includes two parts: variable area formula air inlet and forecooling heat exchanger；Variable area formula air inlet includes: shell, pointed cone, deflector.The air-breathing rocket engine that the present invention designs can be combined by turbocompressor with rocket engine and punching engine, in aerial flight using the oxygen in atmosphere, and use rocket engine in exoatmosphere.So that its height is unrestricted, initial velocity is unrestricted, and can greatly promote performance, quality of taking off is reduced, to reduce manufacture and launch cost.
Description
Technical field
The present invention relates to aerospace field more particularly to a kind of empty day propulsion systems based on rocket combined engine.
Background technique
Existing dynamical system, including all kinds of aero-engines, punching engine, rocket engine and piston engine,
There are respective performance advantage and ideal flying area；The characteristics of aero-engine is performance height, but is difficult to height 20Km
Or the dynamical system of 3.0 Mach of speed or more aircraft；Punching engine has higher performance, but flight maneuver is poor, and needs
Boost motor is wanted to solve the problems, such as initial velocity；Rocket engine is not limited by height limitation and initial velocity, but performance is relatively low, propellant
Consumption is big.
Summary of the invention
In view of the problems in the background art, in order to work in wider airspace, the present invention is past according to the world
Transportation system's requirement and rocket and air suction type combined engine feature are returned, reusable single stage orbit to orbit vehicle is proposed
The empty day propulsion system of rocket combined engine reduces launching costs, reduces energy as space task is towards commercialized development
Consumption, improving market competition becomes one of the core objective of development of new dynamical system.
The present invention adopts the following technical scheme: empty day propulsion system includes the air intake duct of front, intermediate duct compressor
With the combustion chamber of tail portion；
The air intake duct includes variable area formula air inlet, forecooling heat exchanger, bypass air intake duct, variable area formula air inlet packet
Pointed cone, deflector, air inlet outer wall, inner wall and the open circles post jamb body of end are included, pointed cone is located in variable area formula air inlet
Heart position, using the perpendicular bisector of pointed cone length direction as boundary, the front end of air inlet outer wall is convergent contour channel, and rear end is that expansion shape is logical
Road, inner wall is parabolic, and deflector is symmetrical by basic point of pointed cone, connects inner wall and pointed cone, and air inlet connects precooling heat
Exchanger, the circular ring path between forecooling heat exchanger and air intake duct inner wall are bypass air intake duct.
Variable area formula air inlet is located at the empty day propulsion system front end of rocket combined engine, can capture air incoming flow,
First time deceleration is carried out to incoming flow；Incoming flow is effectively compressed under supersonic speed, improves flowing static pressure, for indoor combustion of burning
It burns and oxidant and sufficiently high combustion chamber pressure is provided；Pointed cone is located at variable area formula air inlet axis centre position, and through whole
Air inlet is stretched out in a air inlet, pointed cone front end, and the main inlet channel that incoming flow in forecooling heat exchanger passes through is protruded into rear end；Two pieces are led
The symmetrical connection inner walls of flowing plate and pointed cone, purpose one can carry out for the first time incoming flow for fixing pointed cone, purpose two
Slow down；Further, since variable area formula air inlet inner wall be parabolic type, in variable area formula air inlet formed convergent contour channel and
Shape channel is expanded, this is designed so that the air intake duct is suitable for subsonic speed and supersonic flight.
When hypersonic aircraft is with High Mach number speed flight, air inlet stagnation temperature is increased, and air inflow subtracts great
It is small, while compressed air work done will also increased dramatically, and cause large effect to the performance of engine, and by starting
Machine air intake duct, which installs precool heat exchanger device additional, can reduce intake air temperature, and reduce the pressure of duct compressor while increasing air inflow
Contracting function has important meaning for extended flight device flight envelope and raising engine thrust-weight ratio.
The duct compressor is the supercharging device of empty day propulsion system, including duct engine, converging portion；Duct starts
One end connection forecooling heat exchanger outlet of machine, the other end connect the throat section of converging portion, and the wide opening part of converging portion passes through
The air collecting chamber of hyperbaric oxygen entrance connection combustion chamber；Air incoming flow is by forecooling heat exchanger cooling, deceleration, and pressure is far below fire
Stagnation pressure in arrow engine combustion room, it is therefore desirable to which duct engine is individually pressurized；Due to rocket thrust chamber internal oxidition agent
Flow demand is greater than air inlet flow rate after pressurization, needs further to promote air inlet flow rate by converging portion, reach
To the pressure of air incoming flow and the requirement of flow in combustion chamber.
The combustion chamber includes: air collecting chamber, liquid collecting cavity, airborne oxygen cathete, airborne petroleum pipeline, precombustion chamber, thrust chamber, clock
Type jet pipe；Cylinder type hollow precombustion chamber is set in the middle part of the liquid collecting cavity；Converging portion is connected by hyperbaric oxygen entrance and air collecting chamber
It connects, opens a threaded through-hole in the inner wall of air collecting chamber top half, be connected through a screw thread airborne oxygen cathete outward；In injection mould
Under formula and pure rocket mode, hyperbaric oxygen entrance is closed, and airborne hyperbaric oxygen enters air collecting chamber, air-breathing mode by airborne oxygen therapy tube inlet
Under, airborne oxygen cathete is closed, and oxygen enters air collecting chamber by hyperbaric oxygen entrance；Liquid collecting cavity surrounds the lower half of air collecting chamber from outside
Point；A threaded through-hole is opened in the inner wall of liquid collecting cavity, connects airborne petroleum pipeline outward；Fuel passes through airborne petroleum pipeline constantly quilt
It is pressed into liquid collecting cavity；Liquid collecting cavity bottom is circumferentially uniformly distributed 6 nebulization channels, and two neighboring channel central angle is 60 °, air collecting chamber with
It is combined closely between liquid collecting cavity by the screw thread being arranged；
The forecooling heat exchanger includes: finned coil and forecooling heat exchanger shell；Finned coil is hollow cylinder, circle
The central axis of column is overlapped with the central axis of air intake duct with pointed cone central axis, and pointed cone latter half protrudes into finned coil
It is internal；Forecooling heat exchanger mechanically connected inside air intake duct, through bolt and fixed pre- heat exchanger shell and into
The inner wall of air flue.
Forecooling heat exchanger liquid cooling medium selects liquid helium, since specific heat capacity is greater than liquid nitrogen, heat can be more effectively absorbed, by outer
Boundary's pump housing provides circulation power, and liquid helium is circulated up by forecooling heat exchanger bottom, is exported by top；After output with low temp fuel
Heat exchange is carried out, circulation heat absorption again after temperature is reduced；In addition, liquid helium is better than liquid nitrogen in terms of preventing frost and icing.
The bottom of the liquid collecting cavity is circumferentially uniformly distributed 6 nebulization channels, and two neighboring channel central angle is 60 °；Its is right
2 nebulization channels claimed are connect by two smaller diameter passages with precombustion chamber respectively, and a part of fuel passes through this channel and hyperbaric oxygen
Incoming flow forms 3 strands of collision mixed aerosols, through plug ignition, realizes precombustion；Remaining 4 nebulization channels pass through atomizer
Connect thrust chamber.
The precombustion chamber inner wall sets a small through hole, and through-hole wall sets interior tapping, and spark plug makes firing tip by screw thread
Face is fixed on pre-burning chamber internal surface, can light a fire in precombustion chamber；Thrust chamber is located at after precombustion chamber, and fuel and oxidant exist
The expansion of this full combustion, generates high temperature and high pressure gas, accelerates to spray the huge motive force of generation by bell jet pipe thereafter；Combustion
It burns between chamber outer wall and whole outer wall for bypass combustion chamber.
The present invention has the advantage that: the air-breathing rocket engine that the present invention designs can be by turbocompressor and rocket
Engine and punching engine combine, and in aerial flight using the oxygen in atmosphere, and use rocket in exoatmosphere
Engine.So that its height is unrestricted, initial velocity is unrestricted, and can greatly promote performance, reduces quality of taking off, thus
Reduce manufacture and launch cost.
Detailed description of the invention
Fig. 1 is that the whole semi-cutaway of a kind of empty day propulsion system based on rocket combined engine and three is sat according to the present invention
Mark system.
Fig. 2 is the half of a kind of air inlet of the empty day propulsion system air intake duct based on rocket combined engine according to the present invention
Figure is cutd open, a figure is along Z negative sense semi-cutaway, and b is along X negative sense semi-cutaway.
Fig. 3 is a kind of semi-cutaway a of the combustion chamber of the empty day propulsion system based on rocket combined engine according to the present invention
Figure be it is half-sectional along X negative sense, b figure is half-sectional along Y forward direction.
Fig. 4 is 6 nebulization channel figures for failing display in Fig. 3.
Wherein, the reference numerals are as follows:
1 duct compressor of air intake duct, 2 combustion chamber 3
11 forecooling heat exchanger 12 of air inlet bypasses air intake duct 13
111 deflector of pointed cone, 112 air inlet outer wall 113
114 finned coil of air inlet inner wall, 121 forecooling heat exchanger shell 122
The 21 airborne petroleum pipeline 32 of airborne oxygen cathete 31 of compressor
Bypass 33 hyperbaric oxygen entrance of combustion chamber, 34 convergent contour channel A
Expanding channel B converging portion C air collecting chamber D
Liquid collecting cavity E precombustion chamber F igniter plug F1
Nebulization channel F2 thrust chamber G jet pipe H.
Specific embodiment
It is described in detail rocket base combined engine according to the present invention with reference to the accompanying drawings.
Referring to figs. 1 to Fig. 4, rocket base combined engine according to the present invention includes: air intake duct (1), duct compressor
(2), combustion chamber (3).
The air intake duct (1) includes: variable area formula air inlet (11), forecooling heat exchanger (12), bypass air intake duct (13)；
Variable area formula air inlet (11) includes: that pointed cone (111), deflector (112), inner wall (114), convergent contour channel (A), expanding are logical
Road (B), air inlet (11) are hollow cylinder, but inner wall (114) is parabolic；Pointed cone (111) is located at variable area formula air inlet
The center of mouth (11), using the perpendicular bisector of pointed cone length direction as boundary, front end is convergent contour channel (A), and rear end is expansion shape
Channel (B)；And the cross-sectional area of convergent contour channel (A) is less than the cross-sectional area of expansion shape channel (B)；Deflector (112) is with point
Boring (111) is that basic point is symmetrical, connects inner wall (114) and pointed cone (111).
Forecooling heat exchanger (12) includes: finned coil (121) and forecooling heat exchanger shell (122)；Finned coil
It (121) is hollow cylinder, central axis and pointed cone (111) central axis of cylinder is overlapped with the central axis of air intake duct, with
Axis centre is symmetrical；And pointed cone (111) latter half protrudes into inside finned coil (i.e. main air intake)；Due to forecooling heat exchanger
Inside air intake duct, therefore cross-sectional area is small, is connected and fixed in pre- heat exchanger shell (122) and air intake duct using bolt machinery
Wall (114)；
Circular ring path between exchanger shell (122) and air intake duct inner wall (114) is bypass air intake duct (13).
Duct compressor (2) is used as supercharging device, including duct engine (21), converging portion (C).
One end connection forecooling heat exchanger (12) outlet of duct engine (21), the other end connect the narrow of converging portion (C)
Oral area point, the gas collection that the wide opening part of converging portion (C) passes through a bit of pipeline (i.e. hyperbaric oxygen entrance (34)) connection combustion chamber (3)
Chamber (D).
Combustion chamber (3) includes: air collecting chamber (D), liquid collecting cavity (F), airborne oxygen cathete (31), airborne petroleum pipeline (32), spark
Fill in (F1), precombustion chamber (F), thrust chamber (G), bell jet pipe (H).
Converging portion (C) is connect by hyperbaric oxygen entrance (34) with air collecting chamber (D), in the inner wall of air collecting chamber (D) top half
A threaded through-hole is opened, is connected through a screw thread airborne oxygen cathete (31) outward；Under injection mode and pure rocket mode, high pressure
Oxygen entrance (34) is closed, and airborne hyperbaric oxygen is entered air collecting chamber (D) by airborne oxygen cathete (31) entrance, airborne defeated under air-breathing mode
Oxygen pipe (31) is closed, and oxygen enters air collecting chamber (D) by hyperbaric oxygen entrance (34).
Liquid collecting cavity (E) surrounds the lower half portion air collecting chamber (D) from outside；It is threaded that one is opened in the inner wall of liquid collecting cavity (E)
Through-hole connects airborne petroleum pipeline (32) outward；Fuel is constantly pressed into liquid collecting cavity (E) by airborne petroleum pipeline (32)；Gas collection
It is combined closely between chamber (D) and liquid collecting cavity (E) by the screw thread being arranged；Cylinder type hollow precombustion is set in the middle part of liquid collecting cavity (E)
Room (F)；The bottom liquid collecting cavity (E) is circumferentially uniformly distributed 6 nebulization channels (F2)；Two neighboring channel central angle is 60 °；It is wherein right
2 nebulization channels (F2) claimed are separately connected two minor diameter oil transportation channels, and two minor diameter oil transportation channels and precombustion chamber (F)
Central axis be in 45 ° of angles, a part of fuel forms 3 strands of collision mixed aerosols by this channel and hyperbaric oxygen incoming flow；It is surplus
4 nebulization channels (F2) that remaining are by atomizer connection thrust chamber (G)；A small through hole is opened in precombustion chamber (F) inner wall, inside attacks spiral shell
Line, spark plug (F1) make igniting end face be fixed on precombustion chamber (F) inner surface by screw thread, can the igniting in precombustion chamber (F).
Thrust chamber (G) is located at after precombustion chamber (F), and fuel and oxidant are expanded in this full combustion, and it is high to generate high temperature
It calms the anger body, accelerates to spray by jet pipe (H) thereafter and generate huge motive force；It is connected with precombustion chamber (F) and thrust
Room (G)；It is bypass combustion chamber (33) between outer wall of combustion chamber and whole outer wall.
Not limited to this, any change or replacement expected without creative work should all be covered in guarantor of the invention
Within the scope of shield.Therefore, protection scope of the present invention should be determined by the scope of protection defined in the claims.
Claims (4)
1. a kind of empty day propulsion system based on rocket combined engine, which is characterized in that empty day propulsion system includes front
The combustion chamber (3) of air intake duct (1), intermediate duct compressor (2) and tail portion；
The air intake duct (1) includes variable area formula air inlet (11), forecooling heat exchanger (12), bypass air intake duct (13), becomes face
Product formula air inlet (11) includes the pointed cone (111) of end, deflector (112), air inlet outer wall (113), inner wall (114) and hollow
Cylindrical wall body, pointed cone (111) are located at the center of variable area formula air inlet (11), and the perpendicular bisector with pointed cone length direction is
Boundary, the front end of air inlet outer wall (113) are convergent contour channel (A), and rear end is to expand shape channel (B) inner wall (114) parabolically
Shape, deflector (112) are that basic point is symmetrical with pointed cone (111), connect inner wall (114) and pointed cone (111), air inlet (11) is even
It connects forecooling heat exchanger (12), the circular ring path between forecooling heat exchanger (12) and air intake duct inner wall is bypass air intake duct
(13)；
The duct compressor (2) is the supercharging device of empty day propulsion system, including duct engine (21), converging portion (C)；Contain
One end connection forecooling heat exchanger (12) outlet of road engine (21), the other end connect the throat section of converging portion (C), convergence
The air collecting chamber (D) that the wide opening part of section passes through hyperbaric oxygen entrance (34) connection combustion chamber (3)；
The combustion chamber (3) includes: air collecting chamber (D), liquid collecting cavity (E), airborne oxygen cathete (31), airborne petroleum pipeline (32), pre-burning
Burn room (F), thrust chamber (G), bell jet pipe (H)；
Cylinder type hollow precombustion chamber (F) is set in the middle part of the liquid collecting cavity (E)；Converging portion (C) by hyperbaric oxygen entrance (34) with
Air collecting chamber (D) connection, opens a threaded through-hole in the inner wall of air collecting chamber (D) top half, is connected through a screw thread outward airborne
Oxygen cathete (31)；Under injection mode and pure rocket mode, hyperbaric oxygen entrance (34) is closed, and airborne hyperbaric oxygen is by airborne oxygen cathete
(31) entrance enters air collecting chamber (D), and under air-breathing mode, airborne oxygen therapy (31) pipe is closed, and oxygen is entered by hyperbaric oxygen entrance (34)
Air collecting chamber (D)；Liquid collecting cavity (E) surrounds the lower half portion of air collecting chamber (D) from outside；A band spiral shell is opened in the inner wall of liquid collecting cavity (E)
The through-hole of line connects airborne petroleum pipeline (32) outward；Fuel is constantly pressed into liquid collecting cavity (E) by airborne petroleum pipeline (32)；Collection
The bottom sap cavity (E) is circumferentially uniformly distributed 6 nebulization channels (F2), and two neighboring channel central angle is 60 °, air collecting chamber (D) and collection
It is combined closely between sap cavity (E) by the screw thread being arranged.
2. the empty day propulsion system according to claim 1 based on rocket combined engine, which is characterized in that the pre-cooling
Heat exchanger (12) includes: finned coil (121) and forecooling heat exchanger shell (122)；Finned coil (121) is open tubular column
The central axis of body, cylinder is overlapped with the central axis of air intake duct with pointed cone central axis, and pointed cone (111) latter half is stretched
It is internal to enter finned coil (121)；Forecooling heat exchanger (12) is internal in air intake duct (1), is mechanically connected simultaneously by bolt
The inner wall (114) of fixed pre- heat exchanger shell (122) and air intake duct.
3. the empty day propulsion system according to claim 1 based on rocket combined engine, which is characterized in that the liquid collecting
The bottom of chamber (E) is circumferentially uniformly distributed 6 nebulization channels, and two neighboring channel central angle is 60 °, wherein symmetrical 2 atomizations
Channel (F2) is separately connected two minor diameter oil transportation channels, and the central axis of two minor diameter oil transportation channels and precombustion chamber (F)
In 45 ° of angles, a part of fuel forms 3 strands of collision mixed aerosols by this channel and hyperbaric oxygen incoming flow；Remaining 4 atomizations are logical
Road (F2) is by atomizer connection thrust chamber (G).
4. the empty day propulsion system according to claim 1 based on rocket combined engine, which is characterized in that the pre-burning
It burns room (F) inner wall and sets a small through hole, through-hole wall sets interior tapping, and it is pre- that spark plug (F1) by screw thread is fixed on igniting end face
Room (F) inner surface is fired, it can the igniting in precombustion chamber (F)；Thrust chamber (G) is located at after precombustion chamber (F), fuel and oxidant
It is expanded in this full combustion, generates high temperature and high pressure gas, accelerate to spray the huge promotion of generation by bell jet pipe (H) thereafter
Power；It is bypass combustion chamber (33) between outer wall of combustion chamber and whole outer wall.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810779138.4A CN109026440A (en) | 2018-07-16 | 2018-07-16 | A kind of empty day propulsion system based on rocket combined engine |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810779138.4A CN109026440A (en) | 2018-07-16 | 2018-07-16 | A kind of empty day propulsion system based on rocket combined engine |
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| Publication Number | Publication Date |
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| CN109026440A true CN109026440A (en) | 2018-12-18 |
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| CN201810779138.4A Pending CN109026440A (en) | 2018-07-16 | 2018-07-16 | A kind of empty day propulsion system based on rocket combined engine |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111140399A (en) * | 2020-01-15 | 2020-05-12 | 清华大学 | Continuous rotation detonation rocket engine manufactured through additive manufacturing and additive manufacturing method thereof |
| CN112228246A (en) * | 2020-10-30 | 2021-01-15 | 华中科技大学 | Rocket-based detonation and stamping combined cycle engine and use method and application thereof |
-
2018
- 2018-07-16 CN CN201810779138.4A patent/CN109026440A/en active Pending
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111140399A (en) * | 2020-01-15 | 2020-05-12 | 清华大学 | Continuous rotation detonation rocket engine manufactured through additive manufacturing and additive manufacturing method thereof |
| CN112228246A (en) * | 2020-10-30 | 2021-01-15 | 华中科技大学 | Rocket-based detonation and stamping combined cycle engine and use method and application thereof |
| CN112228246B (en) * | 2020-10-30 | 2021-11-02 | 华中科技大学 | Rocket-based detonation and stamping combined cycle engine and use method and application thereof |
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Application publication date: 20181218 |