CN112211744A - Cooling energy conversion aerospace engine - Google Patents
Cooling energy conversion aerospace engine Download PDFInfo
- Publication number
- CN112211744A CN112211744A CN202011202774.4A CN202011202774A CN112211744A CN 112211744 A CN112211744 A CN 112211744A CN 202011202774 A CN202011202774 A CN 202011202774A CN 112211744 A CN112211744 A CN 112211744A
- Authority
- CN
- China
- Prior art keywords
- energy
- spray pipe
- temperature
- chamber
- cooling
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
- F02K1/78—Other construction of jet pipes
- F02K1/82—Jet pipe walls, e.g. liners
- F02K1/822—Heat insulating structures or liners, cooling arrangements, e.g. post combustion liners; Infra-red radiation suppressors
-
- 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
-
- 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
-
- 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
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F03—MACHINES OR ENGINES FOR LIQUIDS; WIND, SPRING, OR WEIGHT MOTORS; PRODUCING MECHANICAL POWER OR A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
- F03H—PRODUCING A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
- F03H1/00—Using plasma to produce a reactive propulsive thrust
- F03H1/0006—Details applicable to different types of plasma thrusters
- F03H1/0031—Thermal management, heating or cooling parts of the thruster
Abstract
The invention discloses a cooling energy-conversion aerospace engine, wherein an ignition or energy emission device is arranged in an energy chamber; small holes are distributed on the inner wall of the energy chamber, and the small holes are communicated with the working medium compression regulator and the working medium constant-temperature storage tank through a working medium conduit; the energy chamber is connected with the inner spray pipe and is provided with an inner spray nozzle; the outer layers of the energy chamber and the inner spray pipe are provided with temperature detectors which are communicated with a temperature controller by temperature signal wires; cooling covers are sleeved outside the energy chamber and the inner spray pipe, and a cavity is arranged between the energy chamber and the inner spray pipe to form a sleeve type outer spray pipe and an outer spray nozzle; the inner wall of the cooling cover is distributed with a small hole spray pipe, and one end of the small hole spray pipe is connected with a water pressure regulator and a constant temperature water tank through a cooling water pipe. The cooling cover, the pipeline and other devices convert heat dissipation into propulsion energy, greatly improve the temperature of the energy chamber and the inner spray pipe, and increase the specific impulse; the structure is simplified, the control difficulty is reduced, the device is repeatedly used, the volume and the weight are reduced, the manufacturing, maintenance and use costs are low, and the device is suitable for various space tasks.
Description
Technical Field
The invention relates to an aerospace engine.
Background
At present, the aerospace engine does not exist in the true sense, the prior aerospace plane does not realize interstellar flight, but only realizes the back-and-forth flight of the ground, a near-earth orbit outside an air layer and an atmosphere, and the back-and-forth useful large-scale plane is brought into high altitude and then sent into the space by a self rocket engine, and also directly sent into the space by a large rocket and then sent into the space by the self rocket engine for activity. In any mode, the problems that the specific impulse of the engine is small, the heat dissipation energy loss is serious, the efficiency is low, the structure and the control are complex, the size and the weight are large, the engine cannot be used repeatedly and the like exist at present. These problems are not well solved.
Disclosure of Invention
The invention aims to provide a cooling rotary energy aerospace engine to solve the technical problems of small specific impulse and low efficiency of aerospace engines; the technical problems of repeated use, overlarge volume and the like of the engine can be solved.
In order to achieve the purpose of the invention, the technical scheme adopted by the invention is as follows:
a cooling-to-energy aerospace engine, comprising: the device comprises an energy chamber, an ignition or energy emitting device, an inner spray pipe, an inner nozzle, a working medium conduit, a working medium constant-temperature storage tank, a working medium compression regulator, a temperature detector, a temperature signal line, a temperature controller, a cooling cover small-hole spray pipe, an outer nozzle, a cooling water pipeline, a water pressure regulator and a constant-temperature water tank; the energy chamber is connected with the inner spray pipe, and the outer end of the inner spray pipe is provided with an inner nozzle; the outer layers of the energy chamber and the inner spray pipe are sleeved with cooling hoods, and cavities are reserved between the cooling hoods and the outer layers of the energy chamber and the inner spray pipe, so that a sleeve type outer spray pipe and an outer spray nozzle are formed; the working medium in the working medium constant-temperature storage tank is controlled by a working medium compression regulator, and working medium capable of doing work is sprayed into the energy chamber through small holes distributed on the inner wall of the working medium guide pipe and the energy chamber, and is ignited or initiated to do work by an ignition or energy generation device; the working gas is sprayed out from the inner spray pipe and the inner nozzle; meanwhile, the water pressure regulator regulates out a proper amount of water from the constant-temperature water tank through a cooling water pipeline according to signals of the temperature controller, and the water pressure regulator generates working gas to be sprayed out through the outer spray pipe and the outer nozzle to do work while cooling the outer walls of the energy chamber and the inner spray pipe through the small-hole spray pipes distributed on the cooling cover; the energy transmission pipeline and the energy generating device are energy emitting devices installed aiming at different working media in an energy chamber, and comprise electric arc, plasma or energy field emitters.
If the ignition device is arranged in the energy chamber, a chemical propellant consisting of hydrogen and kerosene is sprayed into the small holes on the inner wall of the energy chamber, and the ignition device ignites to do work.
If the energy emitting device in the energy chamber causes work, the energy generating device comprises an electric arc, plasma or energy field emitter, the energy of the energy generating device enters the energy chamber through an energy transmission pipeline, non-chemical working media sprayed into small holes in the inner wall of the energy chamber are caused to do work, and the non-chemical working media comprise nuclear or counter substances.
The temperature detector detects the temperature of the outer walls of the energy chamber and the inner spray pipe, transmits a temperature signal to the temperature controller through a temperature signal line, and when the outer layers of the energy chamber and the inner spray pipe are about to reach the bearable highest temperature, the water pressure regulator regulates out a proper amount of water from the constant-temperature water tank through the cooling water pipeline according to the signal of the temperature controller, so that the small-hole spray pipe of the cooling cover is cooled while working gas is generated to be sprayed out through the outer spray pipe and the outer nozzle to do work.
The inner nozzle and the outer nozzle are of a steerable and variable-diameter structure.
The invention has the advantages that:
the aerospace engine combines the advantages of various engines. The design of the working medium compression regulator enables the working medium compression regulator to regulate the injection energy, oxygen in non-combustion air in the atmosphere flies by means of wings, the application range is wide, and the energy loss is reduced; the method removes the conversion risk among the combined power modes of the turbojet engine, the ramjet engine and the rocket engine, and greatly reduces the structure and the control difficulty; the aircraft has the advantages of reducing the volume, light weight, reducing the material consumption, greatly reducing the use cost and increasing the internal space and effective load of the aerospace aircraft, along with manufacturing, maintenance and repeated use; the ignition or energy emission device endows the energy in the energy chamber (combustion chamber) with a plurality of modes and a plurality of working media (propellants); the design of the cooling cover, the outer spray pipe and the outer nozzle greatly reduces the temperature control requirement on the engine, enables the engine to convert heat dissipation into propulsion energy, and greatly improves the temperature of gas in the energy chamber (combustion chamber) and the inner spray pipe, thereby greatly improving specific impulse and propulsion efficiency, really realizing interstellar flight and executing various space tasks.
Drawings
FIG. 1 is a schematic diagram of the structure and chemical energy operation of the present invention.
FIG. 2 is a schematic diagram of the structure and non-chemical energy operation of the present invention.
The reference numbers: 1. energy room (combustion chamber), 2, energy room inner wall aperture, 3, ignition or energy emitter, 4, interior spray tube, 5, interior spout, 6, working medium (propellant) pipe, 7, working medium constant temperature storage tank, 8, working medium compression modulator, 9, temperature detector, 10, temperature signal line, 11, temperature controller, 12, cooling cover, 13, cooling cover aperture spray tube, 14, outer spray tube, 15, outer spout, 16, cooling water pipeline, 17, water pressure modulator, 18, constant temperature water tank, 19, energy transmission pipeline, 20, energy generator.
Detailed Description
FIG. 1 is a schematic structural view of a first embodiment of the present invention, showing that the energy chamber (combustion chamber) of the present invention is filled with a mixed gas of oxygen and kerosene, and ignited by an ignition device to spray out from an inner nozzle and an inner nozzle to do work, and at the same time, a cooling cover sprays water to cool the outer layers of the energy chamber and the inner nozzle and converts the cooled water into energy to spray out from an outer nozzle and an outer nozzle to do work; FIG. 2 is the same as FIG. 1, showing that the energy chamber of the machine is filled with fluid working medium, the energy is given to the working medium by the energy emitting device, and the working medium is sprayed out from the inner spray pipe and the inner nozzle to do work, and at the same time, the cooling cover sprays water to the energy chamber and the outer layer of the inner spray pipe to cool and convert the water into energy, and then the energy is sprayed out from the outer spray pipe and the outer nozzle to.
Referring to fig. 1 to 2, a cooling-to-energy air-to-air engine, an energy chamber (combustion chamber) 1 of which is provided with evenly distributed pores 2, the other ends of the pores 2 are communicated with a working medium conduit (propellant) 6, and the working medium conduit 6 is communicated with a working medium compression regulator 8 and a working medium constant temperature storage tank 7; the energy chamber (combustion chamber) 1 is connected with the inner spray pipe 4, and the energy sprayed by the inner spray nozzle 5 corresponding to the inner spray pipe 4 does work; an ignition device or various energy emitting devices 3 can be arranged in the energy chamber (combustion chamber) 1, and the energy emitting devices 3 are communicated with an energy generating device 20 through an energy transmission pipeline 19; the outer layers of the energy chamber (combustion chamber) 1 and the inner spray pipe 4 are provided with temperature detectors 9 which are connected with a temperature controller 11 by temperature signal lines 10, meanwhile, the outer layers of the energy chamber 1 and the inner spray pipe 4 are sleeved with a cooling cover 12, and a certain cavity is left between the cooling cover 12 and the outer layers of the energy chamber 1 and the inner spray pipe 4, thereby forming a sleeve type outer spray pipe 14 and an outer nozzle 15 and spraying gas to do work; the inner wall of the cooling cover 12 is evenly distributed with small-hole spray pipes 13, the small-hole spray pipes 13 of the cooling cover are closer to the outer walls of the energy chamber 1 and the inner spray pipe 4 as required, the other ends of the small-hole spray pipes 13 of the cooling cover are connected with a cooling water pipeline 16, the cooling water pipeline 16 is connected with a water pressure regulator 17, the temperature controller 11 is connected with the water pressure regulator 17, and the water pressure regulator 17 is connected with a constant temperature water tank 18.
The energy chamber (combustion chamber) 1 is made of high-temperature-resistant high-strength materials, and small holes 2 are uniformly distributed on the inner wall of the energy chamber 1 to play a role of uniformly supplying working media and simultaneously cooling the inner wall of the energy chamber 1 to a certain extent;
the other end of the small hole 2 on the inner wall of the energy chamber (combustion chamber) 1 is communicated with a working medium guide pipe (propellant) 6, and the working medium guide pipe 6 is communicated with a working medium compression regulator 8 and a working medium constant-temperature storage tank 7. The working medium compression regulator 8 plays a role in regulating the working quality of the working medium entering the energy chamber (combustion chamber) 1, so that the effect of regulating the power of the engine is achieved, and the working medium constant-temperature storage tank 7 ensures that the properties of the working medium are not changed.
The energy chamber (combustion chamber) 1 is connected with an inner spray pipe 4, and the inner spray pipe 4 of the inner spray pipe is matched with a corresponding inner nozzle 5 and sprays energy to do work. The inner spray pipe 4 and the inner nozzle 5 are made of high-temperature-resistant high-strength materials, and the inner nozzle is designed with the functions of turning and diameter changing;
in the energy chamber (combustion chamber) 1, if an ignition device 3 is installed, chemical combustion propellants such as oxygen, kerosene and the like are sprayed into small holes 2 in the inner wall of the energy chamber, and the ignition device 3 ignites to do work;
if various energy emitting devices 3 such as an arc emitter, a plasma emitter, an energy field emitter and the like are arranged in the energy chamber (combustion chamber) 1, small holes 2 in the inner wall of the energy chamber are sprayed with fluid or gas working media, and little working media are used, and the energy emitting devices 3 are endowed with great energy to push the engine to work in a non-chemical energy mode. The energy transmitting device 3 is communicated with the energy generating device 20 by an energy transmission pipeline 19. The energy generating device 20 is a device which can generate energy by using nuclear, counter-material and the like, and converts the energy into forms of electricity, plasma, field and the like to be transmitted to the energy transmitting device 3 through the energy transmission pipeline 19, thereby giving energy to the working medium to do work. The design of the energy emitter and the energy generating device also reserves an expansion space for new technology in the future;
the outer layers of the energy chamber (combustion chamber) 1 and the inner spray pipe 4 are provided with temperature detectors 9 which are connected with a temperature controller 11 by temperature signal wires 10. The temperature controller 11 controls the energy chamber (combustion chamber) 1 and the inner spray pipe 4 to be near the bearable highest temperature, and water is sprayed to cool when the highest temperature is reached, so that the outer wall of the energy chamber (combustion chamber) 1 and the inner spray pipe 4 is in a proper high-temperature state on the premise of ensuring the strength of the energy chamber (combustion chamber) 1 and the inner spray pipe 4, thereby providing the maximum energy for cooling water, saving water and increasing the specific impulse of an engine;
the outer layers of the energy chamber (combustion chamber) 1 and the inner spray pipe 4 are sleeved with a cooling cover 12 in a matching mode, the cooling cover 12 is made of high-temperature-resistant high-strength materials, and a cavity is reserved between the cooling cover 12 and the outer layers of the energy chamber 1 and the inner spray pipe 4, so that a sleeve type outer spray pipe 14 and an outer spray nozzle 15 are formed, and gas is sprayed to do work. The outer nozzle 15 is also designed to be steerable and variable-diameter;
the inner wall of the cooling cover 12 is uniformly distributed with small-hole spray pipes 13, the small-hole spray pipes 13 of the cooling cover are closer to the outer walls of the energy chamber (combustion chamber) 1 and the inner spray pipe 4 as required, the other ends of the small-hole spray pipes 13 of the cooling cover are connected with a cooling water pipeline 16, the cooling water pipeline 16 is connected with a water pressure regulator 17, the temperature controller 11 is connected with the water pressure regulator 17, and the water pressure regulator 17 is connected with a constant-temperature water tank 18. Because the outer walls of the energy chamber 1 and the inner spray pipe 4 are cooled. The problem of heat dissipation and not losing energy is solved, and simultaneously modes such as increase inner spray tube 4 length or reduce bore make energy room (combustion chamber) 1 and the inside acting temperature of inner spray tube 4 greatly improve to greatly improve specific impulse.
When the engine is started, a working medium constant-temperature storage tank 7 is controlled by a working medium compression regulator 8, chemical energy is sprayed into an energy chamber (combustion chamber) 1 through a working medium (propellant) guide pipe 6 and small holes 2 on the inner wall of the energy chamber, and the working medium (propellant hydrogen and kerosene are selected here) is ignited by an ignition or energy emitting device 3 to do work. The working gas is sprayed out from the inner spray pipe 4 and the inner nozzle 5. Meanwhile, the temperature detector 9 detects the temperature of the outer walls of the energy chamber (combustion chamber) 1 and the inner spray pipe 4, and transmits a temperature signal to the temperature controller 11 through the temperature signal line 10, the water pressure regulator 17 regulates out a proper amount of water from the constant-temperature water tank 18 through the cooling water pipeline 16 according to the signal of the temperature controller 11, and the water passes through the cooling cover small-hole spray pipe 13 to cool the outer walls of the energy chamber 1 and the inner spray pipe 4 and simultaneously generate acting gas to be sprayed out for acting through the outer spray pipe 14 and the outer spray nozzle 15. In the process of the engine after ignition, the working medium compression regulator 8 controls the operation power of the engine. The invention not only solves the problem of heat dissipation, but also converts the heat dissipation into energy pushing, and simultaneously greatly improves the working temperature inside the energy chamber (combustion chamber) 1 and the inner spray pipe 4, thereby greatly improving the specific impulse.
The invention relates to two devices, namely an energy transmission pipeline 19 and an energy generating device 20, which are designed aiming at installing various energy emitting devices 3, such as electric arc emitters, plasma emitters, energy fields and the like, in an energy chamber (combustion chamber) 1. The design has the same operation mode except that the modes of spraying the working medium into the small holes 2 on the inner wall of the energy chamber and giving energy to the working medium are different, and the design is an expansion space reserved for new technology in the future.
Claims (5)
1. A cooling-to-energy aerospace engine, comprising: the device comprises an energy chamber, an ignition or energy emitting device, an inner spray pipe, an inner nozzle, a working medium conduit, a working medium constant-temperature storage tank, a working medium compression regulator, a temperature detector, a temperature signal line, a temperature controller, a cooling cover small-hole spray pipe, an outer nozzle, a cooling water pipeline, a water pressure regulator and a constant-temperature water tank; the energy chamber is connected with the inner spray pipe, and the outer end of the inner spray pipe is provided with an inner nozzle; the outer layers of the energy chamber and the inner spray pipe are sleeved with cooling hoods, and cavities are reserved between the cooling hoods and the outer layers of the energy chamber and the inner spray pipe, so that a sleeve type outer spray pipe and an outer spray nozzle are formed; the working medium in the working medium constant-temperature storage tank is controlled by a working medium compression regulator, and working medium capable of doing work is sprayed into the energy chamber through small holes distributed on the inner wall of the working medium guide pipe and the energy chamber, and is ignited or initiated to do work by an ignition or energy generation device; the working gas is sprayed out from the inner spray pipe and the inner nozzle; meanwhile, the water pressure regulator regulates out a proper amount of water from the constant-temperature water tank through a cooling water pipeline according to signals of the temperature controller, and the water pressure regulator generates working gas to be sprayed out through the outer spray pipe and the outer nozzle to do work while cooling the outer walls of the energy chamber and the inner spray pipe through the small-hole spray pipes distributed on the cooling cover; the energy transmission pipeline and the energy generating device are energy emitting devices installed aiming at different working media in an energy chamber, and comprise electric arc, plasma or energy field emitters.
2. The aerospace engine of claim 1, wherein the ignition device is installed in the energy chamber, and the chemical propellant comprising hydrogen and kerosene is sprayed into the small holes on the inner wall of the energy chamber and is ignited by the ignition device to do work.
3. The aerospace engine of claim 1, wherein if the energy emitting device in the energy chamber causes work, the energy generating device comprises an electric arc, plasma or energy field emitter, energy of the energy generating device enters the energy chamber through an energy transmission pipeline to cause non-chemical working media sprayed from the small holes in the inner wall of the energy chamber to cause work, and the non-chemical working media comprise nuclei or counter substances.
4. The air-to-energy cooling air-to-air engine as claimed in claim 1, wherein the temperature detector detects the temperature of the outer walls of the energy chamber and the inner nozzle and transmits the temperature signal to the temperature controller through a temperature signal line, and when the outer layers of the energy chamber and the inner nozzle are about to reach the highest bearable temperature, the water pressure regulator regulates out a proper amount of water from the constant temperature water tank through the cooling water pipeline according to the signal of the temperature controller, the water passes through the small-hole nozzle of the cooling cover, the outer walls of the energy chamber and the inner nozzle are cooled, and simultaneously working gas is generated and sprayed out through the outer nozzle and the outer nozzle to do work.
5. The aerospace engine of claim 1, wherein the inner and outer jets are steerable and variable diameter.
Priority Applications (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011202774.4A CN112211744A (en) | 2020-11-02 | 2020-11-02 | Cooling energy conversion aerospace engine |
| CN202111000593.8A CN113513427B (en) | 2020-11-02 | 2021-08-30 | Cooling energy conversion aerospace engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011202774.4A CN112211744A (en) | 2020-11-02 | 2020-11-02 | Cooling energy conversion aerospace engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN112211744A true CN112211744A (en) | 2021-01-12 |
Family
ID=74057942
Family Applications (2)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202011202774.4A Pending CN112211744A (en) | 2020-11-02 | 2020-11-02 | Cooling energy conversion aerospace engine |
| CN202111000593.8A Active CN113513427B (en) | 2020-11-02 | 2021-08-30 | Cooling energy conversion aerospace engine |
Family Applications After (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202111000593.8A Active CN113513427B (en) | 2020-11-02 | 2021-08-30 | Cooling energy conversion aerospace engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (2) | CN112211744A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113513427A (en) * | 2020-11-02 | 2021-10-19 | 曹建峰 | Cooling energy conversion aerospace engine |
Family Cites Families (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE4321393C2 (en) * | 1993-06-26 | 1996-08-22 | Daimler Benz Aerospace Ag | Wall structure, in particular for a ramjet engine |
| CN104632567B (en) * | 2014-12-04 | 2017-04-12 | 中国科学院力学研究所 | Electric arc heating device capable of generating ultra-high-speed airflow |
| CN107091168B (en) * | 2017-05-27 | 2018-11-16 | 中国科学院深海科学与工程研究所 | A kind of underwater turbine jet engine |
| CN107701312B (en) * | 2017-11-10 | 2020-11-03 | 中国空气动力研究与发展中心计算空气动力研究所 | Hypersonic engine |
| CN110318878B (en) * | 2019-06-13 | 2022-08-09 | 内蒙动力机械研究所 | Aerospace plane active cooling system based on magnetofluid energy bypass |
| CN112211744A (en) * | 2020-11-02 | 2021-01-12 | 曹建峰 | Cooling energy conversion aerospace engine |
-
2020
- 2020-11-02 CN CN202011202774.4A patent/CN112211744A/en active Pending
-
2021
- 2021-08-30 CN CN202111000593.8A patent/CN113513427B/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113513427A (en) * | 2020-11-02 | 2021-10-19 | 曹建峰 | Cooling energy conversion aerospace engine |
Also Published As
| Publication number | Publication date |
|---|---|
| CN113513427B (en) | 2022-04-12 |
| CN113513427A (en) | 2021-10-19 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN110118136B (en) | Thrust-adjustable hydrogen peroxide single-component thruster | |
| CN113404621B (en) | Solid-liquid mixed engine and method for Mars ascending aircraft | |
| CN108894894B (en) | Powder fluidizing device easy to fill | |
| CN113464311B (en) | Rotating detonation engine with adjustable detonation wave propagation mode and application method | |
| CN110707521B (en) | Premixed carbon dioxide pneumatic laser driven by continuous rotation detonation rocket combustion | |
| CN100394011C (en) | Steam booster device and method for jet engine | |
| EP2853736B1 (en) | Chemical-electromagnetic hybrid propulsion system with variable specific impulse | |
| CN110718843A (en) | Air-breathing type continuous rotation detonation combustion driven premixing type carbon dioxide pneumatic laser | |
| CN112211744A (en) | Cooling energy conversion aerospace engine | |
| CN114934863A (en) | Pneumatic variable-throat spray pipe device and solid-liquid hybrid rocket engine | |
| CN109505711B (en) | Gas-gas small rocket device for generating high-temperature supersonic gas | |
| CN114776478B (en) | Liquid rocket engine double-component propulsion system utilizing resonance ignition | |
| CN114165354B (en) | Design method of multi-adjoint vector thrust engine | |
| CN114109643B (en) | Multi-adjoint vector thrust engine | |
| CN114320667A (en) | Extrusion type oxidant supply solid-liquid mixing engine | |
| RU2490173C1 (en) | Vtol aircraft | |
| CN109681344B (en) | Jet single-point impact compression combustion engine, axisymmetric aircraft and lifting body aircraft | |
| CN114776482B (en) | Liquid rocket engine propulsion system utilizing resonance ignition | |
| CN104963788B (en) | Hybrid engine applicable for aviation, spaceflight and navigation | |
| CN115342380A (en) | Nonlinear detonation combustion chamber | |
| CN219160417U (en) | Detonation engine with pre-detonation tube and multi-ring cavity combustion chamber | |
| RU2760369C1 (en) | Liquid rocket propulsion system of a space vehicle | |
| CN220434898U (en) | Rotary detonation engine device and aircraft | |
| CN116291953B (en) | Full-continuous detonation mode turbine rocket ram combined cycle engine and operation method | |
| CN112177797B (en) | Solid rocket engine without spray pipe |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20210112 |
|
| WD01 | Invention patent application deemed withdrawn after publication |