CN115822816B - Liquid single component thruster based on spray and microwave co-ignition - Google Patents
Liquid single component thruster based on spray and microwave co-ignition Download PDFInfo
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- CN115822816B CN115822816B CN202211465478.2A CN202211465478A CN115822816B CN 115822816 B CN115822816 B CN 115822816B CN 202211465478 A CN202211465478 A CN 202211465478A CN 115822816 B CN115822816 B CN 115822816B
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Abstract
The invention provides a liquid single-component thruster based on spray and microwave cooperative ignition, which belongs to the technical field of space engines and comprises: the cylindrical resonator body is internally provided with a cylindrical resonant cavity; one end of the cylindrical resonant cavity is communicated with the spray pipe; an end plate is arranged at the other end of the cylindrical resonant cavity; the end plate is connected with a microwave plug; the end plate is connected with a plurality of nozzles; the end plate is provided with a plurality of air inlets. The invention uses microwave excitation to generate high-energy electromagnetic field, and then ionizes gas to generate plasma jet combustion-supporting single-component propellant, which cancels the design of catalytic bed, does not need preheating, has simple structure and low cost, and effectively improves ignition performance and combustion efficiency because a large amount of active particles are generated in the ionization process.
Description
Technical Field
The invention relates to the technical field of space engines, in particular to a liquid single-component thruster based on spray and microwave co-ignition.
Background
Because the traditional propellant has high toxicity and pollution, the traditional propellant has very strict operation flow, specification and safety protection measures in the links of production, transportation, storage, filling and the like, and needs a long preparation period. The green propellant can obviously enhance the safety, reduce the risk of personnel operation, simplify the operation flow and technical specifications, and reduce the level and standard of safety protection, thereby obviously reducing the preparation period and the emission cost and having good economic benefit. Single-component propellants such As Dinitramide (ADN) based and hydroxylamine nitrate (HAN) based represent the development direction of green propellants due to their high performance and low toxicity, and have been widely paid attention in the fields of military, aerospace, materials and the like in recent years. The existing thruster generally comprises a catalytic bed, a combustion chamber, a spray pipe, a capillary filling system and an electromagnetic valve, the internal structure is complex, the cost is high, and especially the process for installing catalyst particles on the catalytic bed is complex, the problems that the catalyst particles can be sintered, fire and the like when running for a long time under a high-temperature working environment exist, and the popularization and the application of the thruster are not facilitated.
Disclosure of Invention
The invention aims to provide a liquid single-component thruster which reduces the structural complexity of a combustion chamber, improves the ignition characteristic of a propellant under the coupling effect of spray and microwave field, enables the propellant to burn more completely and is based on the cooperative ignition of spray and microwave, and solves at least one technical problem in the background technology.
In order to achieve the above purpose, the present invention adopts the following technical scheme:
the invention provides a liquid single-component thruster based on spray and microwave co-ignition, which comprises: the cylindrical resonator body is internally provided with a cylindrical resonant cavity; one end of the cylindrical resonant cavity is communicated with the spray pipe; the other end of the cylindrical resonant cavity is an end plate; the end plate is connected with a microwave plug; the end plate is connected with a plurality of nozzles; the end plate is provided with a plurality of air inlets.
Preferably, the microwave plug includes: the microwave plug comprises a microwave plug body, wherein one end of the microwave plug body is connected with a radio frequency female connector, and the other end of the microwave plug body is a connector.
Preferably, a through cavity is arranged in the microwave plug main body, an ignition conductor is arranged in the through cavity, one end of the ignition conductor is connected with a conductor in the radio frequency female connector, and the other end of the ignition conductor extends out of the connector and is arranged in the cylindrical resonant cavity.
Preferably, an insulating layer is arranged between the inner wall of the through cavity and the ignition conductor.
Preferably, the connector is provided with external threads, and the connector is in threaded connection with the end plate through the external threads.
Preferably, the spray pipe comprises a transition body connected with the cylindrical resonance body, a first conical body connected with the transition body, and a second conical body connected with the first conical body.
Preferably, a transition cavity matched with the cylindrical resonant cavity is arranged in the transition body, and a baffle is arranged in the transition cavity; and a through hole for communicating the transition cavity with the first conical cavity in the first conical body is formed in the baffle.
Preferably, the edges of the transition body and the cylindrical resonator body are provided with flanges, the flanges are provided with connecting holes, and the connection between the transition body and the cylindrical resonator body is realized by arranging bolts in the connecting holes.
Preferably, the cylindrical resonator body is provided with an installation groove communicated with the cylindrical resonator cavity, and a transparent baffle window is arranged in the installation groove.
Preferably, a plurality of the nozzles are symmetrically disposed around the microwave plug, and a plurality of the air inlets are symmetrically disposed around the microwave plug.
The invention has the beneficial effects that: the high-energy electromagnetic field is generated by utilizing microwave excitation, so that ionized gas is generated into the plasma jet combustion-supporting unit propellant, the design of a catalytic bed is canceled, preheating is not needed, the structure is simple, the cost is low, and the ignition performance and the combustion efficiency are effectively improved because a large amount of active particles are generated in the ionization process.
Additional aspects and advantages of the invention will be set forth in part in the description which follows, and in part will be obvious from the description, or may be learned by practice of the invention.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings required for the description of the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and other drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.
Fig. 1 is a perspective structure diagram of a liquid single-component thruster based on spray and microwave co-ignition according to an embodiment of the invention.
Fig. 2 is a schematic cross-sectional view of a liquid single-component thruster based on spray and microwave co-ignition according to an embodiment of the present invention.
Fig. 3 is a schematic diagram of a microwave plug of a liquid single-component thruster based on spray and microwave co-ignition according to an embodiment of the present invention.
Wherein: 1-a cylindrical resonator body; 2-a cylindrical resonant cavity; 3-end plates; 4-a microwave plug; 5-nozzle; 6-air inlet; 7-a microwave plug body; 8-a radio frequency female interface; 9-a connector; 10-a through cavity; 11-an ignition conductor; 12-an insulating layer; 13-transition body; 14-a first cone; 15-a second taper; 16-a transition chamber; 17-baffle; 18-a first conical cavity; 19-a through hole; 20-flanges; 21-connecting holes; 22-mounting slots; 23-transparent window; 24-a second conical cavity.
Description of the embodiments
Reference will now be made in detail to embodiments of the present invention, examples of which are illustrated in the accompanying drawings, wherein like or similar reference numerals refer to like or similar elements throughout or elements having like or similar functionality. The embodiments described below by way of the drawings are exemplary only and should not be construed as limiting the invention.
It will be understood by those skilled in the art that, unless otherwise defined, all terms (including technical and scientific terms) used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this invention belongs.
It will be further understood that terms, such as those defined in commonly used dictionaries, should be interpreted as having a meaning that is consistent with their meaning in the context of the prior art and will not be interpreted in an idealized or overly formal sense unless expressly so defined herein.
As used herein, the singular forms "a", "an", "the" and "the" are intended to include the plural forms as well, unless expressly stated otherwise, as understood by those skilled in the art. It will be further understood that the terms "comprises" and/or "comprising," when used in this specification, specify the presence of stated features, integers, steps, operations, elements, and/or components, but do not preclude the presence or addition of one or more other features, integers, steps, operations, elements, and/or groups thereof.
In the description of the present specification, a description referring to terms "one embodiment," "some embodiments," "examples," "specific examples," or "some examples," etc., means that a particular feature, structure, material, or characteristic described in connection with the embodiment or example is included in at least one embodiment or example of the present invention. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples. Furthermore, the different embodiments or examples described in this specification and the features of the different embodiments or examples may be combined and combined by those skilled in the art without contradiction.
In the description of this specification, the terms "first," "second," and the like are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defining "a first" or "a second" may explicitly or implicitly include at least one such feature. In the description of the present invention, the meaning of "a plurality" is two or more, unless explicitly defined otherwise.
In the description of the present specification, the terms "center," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," and the like indicate an orientation or positional relationship based on that shown in the drawings, merely for convenience of description and to simplify the description, and do not indicate or imply that the devices or elements referred to must have a specific orientation, be configured and operated in a specific orientation, and thus should not be construed as limiting the present technology.
The terms "mounted," "connected," and "disposed" are to be construed broadly, and may be, for example, fixedly connected, disposed, detachably connected, or integrally connected, disposed, unless otherwise specifically defined and limited. The specific meaning of the above terms in the present technology can be understood by those of ordinary skill in the art according to the specific circumstances.
In order that the invention may be readily understood, a further description of the invention will be rendered by reference to specific embodiments that are illustrated in the appended drawings and are not to be construed as limiting embodiments of the invention.
It will be appreciated by those skilled in the art that the drawings are merely schematic representations of examples and that the elements of the drawings are not necessarily required to practice the invention.
Examples
As shown in fig. 1 to 3, in this embodiment, there is provided a liquid unit thruster based on co-ignition of spray and microwave, including: a cylindrical resonant body 1, wherein a cylindrical resonant cavity 2 is arranged inside the cylindrical resonant body 1; one end of the cylindrical resonant cavity 2 is communicated with the spray pipe; an end plate 3 is arranged at the other end of the cylindrical resonant cavity 2; the end plate 3 is connected with a microwave plug 4; the end plate 3 is connected with a plurality of nozzles 5; the end plate 3 is provided with a plurality of air inlets 6. The radial end face of the cylindrical resonator body 1 is provided with a mounting groove 22 communicated with the cylindrical resonator cavity 2, and a transparent baffle window 23 is arranged in the mounting groove 22. A plurality of the nozzles 5 are symmetrically disposed around the microwave plug 4, and a plurality of the air inlets 6 are symmetrically disposed around the microwave plug 4.
The microwave plug 4 includes: the microwave plug comprises a microwave plug body 7, wherein one end of the microwave plug body 7 is connected with a radio frequency female connector 8, and the other end of the microwave plug body 7 is a connector 9. The microwave plug is characterized in that a through cavity 10 is arranged in the microwave plug body 7, an ignition conductor 11 is arranged in the through cavity 10, one end of the ignition conductor 11 is connected with a conductor in the radio frequency female connector 8, and the other end of the ignition conductor 11 extends out of the connector 9 and is arranged in the cylindrical resonant cavity 2. An insulating layer 12 is provided between the inner wall of the through cavity 10 and the ignition conductor 11. The connector 9 is provided with external threads, and the connector 9 is in threaded connection with the end plate 3 through the external threads.
The spray pipe comprises a transition body 13 connected with the cylindrical resonator body 1, a first conical body 14 connected with the transition body 13, and a second conical body 15 connected with the first conical body 14. A transition cavity 16 matched with the cylindrical resonant cavity 2 is arranged in the transition body 13, and a baffle 17 is arranged in the transition cavity 16; the baffle 17 is provided with a through hole 19 for communicating the transition cavity 16 with a first conical cavity 18 in the first conical body 14. The edges of the transition body 13 and the cylindrical resonator body 1 are respectively provided with a flange 20, the flanges 20 are provided with connecting holes 21, and the connection between the transition body 13 and the cylindrical resonator body 1 is realized by arranging bolts in the connecting holes 21. The first conical cavity 18 communicates with a second conical cavity 24 in the second conical body 15.
Specifically, as shown in fig. 2, a threaded hole is formed in the center of the end plate 3 at the top end of the cylindrical resonant cavity 2, and the threaded hole is matched with the external thread of the connector 9 to realize threaded connection between the connector 9 and the end plate 3.
Specifically, the rf female connector 8 on the microwave plug 4 is an N-type rf female connector, and may be connected to a standard N-type rf male connector of a coaxial transmission line. The ignition conductor 11 in the microwave plug 4 is connected with a central copper conductor in the N-type radio frequency female connector. The nozzle 5 is provided with external threads, the end plate 3 of the cylindrical resonator 1 is symmetrically provided with threaded holes around the microwave plug 4, the threaded holes are internally provided with internal threads, and the internal threads are matched with the external threads on the nozzle 5 to realize threaded connection of the nozzle 5 and the end plate 3.
An insulating layer 12 is provided on the side wall of the through cavity 10 inside the microwave plug 4, the insulating layer 12 being made of a material such as polytetrafluoroethylene, a stainless steel casing separating the microwave plug body in a manner covering the ignition conductor 11. The design has the advantages that: the insulating layer 12 plays an insulating role between the ignition conductor 11 and the stainless steel shell of the microwave plug main body, prevents microwave leakage in the transmission process, reduces the electromagnetic field intensity in the cylindrical resonant cavity 2, and plays a role in fixing the ignition conductor.
As shown in fig. 2, the diameter of the cylindrical resonant cavity 2 is D 1 The distance between the lower surface of the end plate at the top of the cylindrical cavity 2 and the upper surface of the baffle 17 is L 1 Wherein D is 1 And L 1 The relation of (2) satisfies the formula: 93mm is greater than or equal to D 1 =L 1 And more than or equal to 80mm. The design has the advantages that: when the resonance frequency is 2.45GHz, the diameter of the cylindrical resonant cavity 2 is [80,93 ]]In the interval, the cylindrical resonant cavity 2 is in a single resonant mode (TM) 010 ). The design has the advantages that: TM (TM) 010 The frequency range of the single resonance mode is less crossed with other resonance modes, so that the interference of other resonance modes can be effectively avoided; TM (TM) 010 The quality factor of the resonant mode is higher, which is beneficial to improving the intensity of the electromagnetic field in the cylindrical resonant cavity 2.
As shown in FIG. 2, the central axis of the nozzle 5 is at a distance L from the side inner wall of the cylindrical resonant cavity 2 2 Wherein L is 2 And D 1 The relation of (2) satisfies the formula: l is 1/4 or less 2 /D 1 And is less than or equal to 1/3. The design has the advantages that: the cross injection area of the nozzles 5 at the two sides is the area with the strongest electromagnetic field, and the spray particle size is small, so that the atomization combustion is easier; meanwhile, the nozzle 5 is arranged to be deviated to the center of the cylindrical resonant cavity 2 and away from the wall surface, so that the phenomenon that small spray droplets collide with the wall and adhere to the inner wall of the cylindrical resonant cavity 2 is avoided, and the oxidizing combustion of propellant spray is not facilitated. The existing microwave ignition device realizes gas phase discharge only by ionized gas, does not consider auxiliary combustion of liquid fuel, and realizes propellant spray mixed combustion under the coupling effect of spray droplet dynamics and microwave field by adding a nozzle for the first time.
As shown in FIG. 2, the baffle 17 has a diameter D at its center 3 Is 5mm thick, wherein D 3 And D 1 The relation of (2) satisfies the formula: d (D) 1 /D 3 =10. The design has the advantages that: when the diameter D of the through hole 3 Far less than D 1 （D 1 /D 3 10), the design of the baffle 17 with the through holes 19 does not affect the resonance effect in the original cylindrical resonant cavity, but ensures that the high-temperature gas generated by the combustion reaction can flow out through the through holes in the middle of the baffle.
As shown in fig. 2, the extension length of the ignition conductor in the microwave plug is L 3 The length of the tapered section of the spray pipe (i.e. the height of the first conical cavity) is L 4 Wherein L is 3 、L 4 And L 1 The relation of (2) satisfies the formula： 1/2L 1 ≤L 3 ≤1/2（L 1 + L 4 ). The design has the advantages that: according to simulation calculation, the electric field intensity is highest when the length of the ignition conductor is half of the height of the cylindrical resonant cavity, but considering that a baffle plate at the bottom of the cylindrical resonant cavity is provided with a through hole, the nozzle taper section can also be regarded as a region where resonance phenomenon occurs, and the length of the ignition conductor is slightly smaller than half of the sum of the lengths of the cylindrical resonant cavity and the nozzle taper section.
The transparent baffle window 23 is a visual quartz glass window and is arranged and placed at 3/4 of the height of the cylindrical resonant cavity 2, and the height is slightly longer than the depth length of the ignition conductor 11, which is the jet length and flame length when the tip of the ignition conductor 11 is subjected to discharge and combustion reaction, so that the reaction process in the cylindrical resonant cavity 2 can be more conveniently and intuitively shot. Visual quartz glass window diameter D 2 The thickness is 2mm, and the distance between the upper end of the visual quartz glass window and the end plate is L 5 The diameter of the pore canal of the mounting groove 22 is 6mm; wherein D is 2 、L 5 、L 1 And L 3 The relation of (2) satisfies the formula: l (L) 3 ≤D 2 +L 5 =3/4L 1 . The caliber of the visual window mounting groove is slightly larger than D 2 The depth is about 0.75 times the thickness of the quartz glass. The design has the advantages that: the visual quartz glass window is used for observing plasma discharge phenomenon and propellant combustion chemical reaction in the cylindrical resonant cavity 2, is made of quartz glass, has high temperature resistance, high hardness and good electrical insulation performance, and can be perfectly suitable for the conditions of high temperature and high pressure in the cylindrical resonant cavity. The visual quartz glass window 7 is glued into the visual window mounting groove by strong force, and the caliber of the visual window mounting groove is slightly larger than D 2 The depth is about 0.75 times the thickness of the quartz glass.
According to the liquid single-component thruster provided by the embodiment, the nozzle 5 is a BIMJ6004 type fuel nozzle, and is provided with two paths of inlets of gas and liquid, and the working medium gas inlet is arranged as a centrifugal nozzle, so that working medium gas in the centrifugal nozzle is accelerated through centrifugal rotation and is collided and mixed with propellant sprayed by a direct-current nozzle, the mixing uniformity of gas and propellant is ensured, the atomization effect and the combustion efficiency are improved, and the combustion performance of the propellant in a cylindrical resonant cavity is effectively improved.
As shown in fig. 2, the end plate 3 at the top end of the cylindrical resonant cavity 2 is provided with an air inlet 6 around two sides of the microwave plug 4, and the design is axially symmetrical; the diameter of both air inlets was 5mm. The design has the advantages that: the air inlet is used for supplying working medium gas, and the working medium gas is air, argon, nitrogen, helium and the like, and the symmetrical design uniformly conveys the working medium gas into the cylindrical resonant cavity 2, so that the possibility of gas discharge is improved.
As shown in fig. 3, the top of the ignition conductor 11 of the microwave plug according to the embodiment of the present invention is tapered to be a sharp corner, the curvature of the tip surface is high, the equipotential surfaces are dense, and the electric field strength is high. The ignition conductor is made of metal, such as copper, tungsten, iron, aluminum, alloy and the like; the ignition conductor 11 can effectively couple microwave energy transmitted from an external microwave transmission system into the cylindrical resonant cavity 2, and is a key device for effectively improving the incident energy of microwaves and reducing the reflected energy. The advantages of this design are: the ignition conductor tip design can realize plasma tip discharge under lower power, so that the working medium gas breakdown discharge can be realized more easily, and the stable and continuous discharge of microwave plasma can be realized.
In summary, according to the liquid single-component thruster based on the cooperative ignition of the spraying and the microwave provided by the embodiment of the invention, the thrust range is 50N-500N by establishing the liquid single-component thruster based on the cooperative ignition of the spraying and the microwave, so that the problem that the complex catalytic bed structure of the catalytic combustion technology is difficult to apply to the middle-large thrust magnitude thruster is solved. By utilizing working medium gas to enter a cylindrical resonant cavity in the thruster for pre-ionization, the ignition difficulty of single-component propellants (ADN base, HAN base and the like) is greatly reduced, the ignition time is shortened, and active particles in plasma jet flow are beneficial to strengthening the ignition capability, reducing the minimum ignition energy and improving the ignition efficiency. The contact area between the spray and the cylindrical resonant cavity is increased by symmetrically arranging the nozzle structures at two sides in the cylindrical resonant cavity, so that the propellant spray is completely mixed and combusted, and the single-component propellant can stably undergo high-temperature combustion decomposition reaction in the cylindrical resonant cavity. And the nozzle and the ignition conductor are matched, so that the spray can be precisely sprayed to the tip of the ignition conductor, the atomization effect is good, the particle size of the propellant spray is small, and the possibility of igniting the spray by the plasma jet is improved. By adding the baffle between the cylindrical resonant cavity and the spray pipe, the design of the baffle with the through holes does not influence the resonance effect in the original cylindrical resonant cavity, and ensures that high-temperature gas generated by the combustion reaction can flow out through the through holes in the middle of the baffle. The nozzle is directly communicated with the cylindrical resonant cavity, so that the catalytic bed structure and the capillary injection structure of the original thruster are replaced, the structural complexity of the original single-component thruster is reduced, the economical efficiency is greatly improved, and the low-cost and light-weight requirements of the thruster are met.
While the foregoing description of the embodiments of the present invention has been presented in conjunction with the drawings, it should be understood that it is not intended to limit the scope of the invention, but rather, it should be understood that various changes and modifications could be made by one skilled in the art without the need for inventive faculty, which would fall within the scope of the invention.
Claims (7)
1. A liquid single-component thruster based on co-ignition of spraying and microwaves, comprising: the cylindrical resonator comprises a cylindrical resonator body (1), wherein a cylindrical resonant cavity (2) is arranged in the cylindrical resonator body (1); one end of the cylindrical resonant cavity (2) is communicated with the spray pipe; an end plate (3) is arranged at the other end of the cylindrical resonant cavity (2); the end plate (3) is connected with a microwave plug (4); the end plate (3) is connected with a plurality of nozzles (5); a plurality of air inlets (6) are formed in the end plate (3); the microwave plug (4) comprises: the microwave plug comprises a microwave plug main body (7), wherein one end of the microwave plug main body (7) is connected with a radio frequency female connector (8), and the other end of the microwave plug main body (7) is a connector (9); a plurality of the nozzles (5) are symmetrically arranged around the microwave plug (4), and a plurality of the air inlets (6) are symmetrically arranged around the microwave plug (4);
the microwave plug is characterized in that a through cavity (10) is formed in the microwave plug body (7), an ignition conductor (11) is arranged in the through cavity (10), one end of the ignition conductor (11) is connected with a conductor in the radio frequency female connector (8), and the other end of the ignition conductor (11) extends out of the connector (9) and is arranged in the cylindrical resonant cavity (2).
2. Liquid unit thruster based on co-ignition of spraying and microwaves according to claim 1, characterized in that an insulating layer (12) is provided between the inner wall of said through cavity (10) and said ignition conductor (11).
3. The liquid single-component thruster based on the co-ignition of spraying and microwaves according to claim 1, characterized in that external threads are arranged on the connector (9), and the connector (9) is in threaded connection with the end plate (3) through the external threads.
4. Liquid unit thruster based on co-ignition of spray and microwave according to claim 1, characterized in that the nozzle comprises a transition body (13) connected to the cylindrical resonator body (1), a first cone (14) connected to the transition body (13), a second cone (15) connected to the first cone (14).
5. The liquid single-component thruster based on the co-ignition of spraying and microwaves according to claim 4, characterized in that a transition cavity (16) matched with the cylindrical resonant cavity (2) is arranged inside the transition body (13), and a baffle (17) is arranged in the transition cavity (16); the baffle (17) is provided with a through hole (19) for communicating the transition cavity (16) with a first conical cavity (18) in the first conical body (14); the first conical cavity (18) communicates with a second conical cavity (24) in the second conical body (15).
6. Liquid single-component thruster based on co-ignition of spraying and microwaves according to claim 4 or 5, characterized in that the edges of said transition body (13) and said cylindrical resonator body (1) are each provided with a flange (20), said flange (20) is provided with a connection hole (21), the connection of said transition body (13) and said cylindrical resonator body (1) being achieved by providing a bolt in the connection hole (21).
7. The liquid single-component thruster based on the co-ignition of spraying and microwaves according to claim 6, characterized in that a mounting groove (22) communicated with the cylindrical resonant cavity (2) is arranged on the radial end surface of the cylindrical resonant body (1), and a transparent baffle window (23) is arranged in the mounting groove (22).
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| CN109310003A (en) * | 2018-10-22 | 2019-02-05 | 安徽工业大学 | Coaxial resonant microwave discharge plasma large scale efficient combustion-supporting device |
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| US5370525A (en) * | 1993-03-22 | 1994-12-06 | Blue Pacific Environments Corporation | Microwave combustion enhancement device |
| US5689949A (en) * | 1995-06-05 | 1997-11-25 | Simmonds Precision Engine Systems, Inc. | Ignition methods and apparatus using microwave energy |
| DE102007054967A1 (en) * | 2007-11-17 | 2009-05-20 | Mtu Aero Engines Gmbh | Process and apparatus for plasma reforming of fuel for engine applications |
| CN101378616A (en) * | 2008-10-13 | 2009-03-04 | 电子科技大学 | Atmosphere plasma cylindrical microwave excitation cavity |
| CN104612835A (en) * | 2015-01-07 | 2015-05-13 | 大连理工大学 | Plasma ignition combustion-supporting device with microwave coaxial resonant cavity |
| RU2612232C1 (en) * | 2015-11-17 | 2017-03-03 | Николай Борисович Болотин | Liquid propellant rocket engine |
| CN108954390B (en) * | 2018-07-25 | 2020-05-12 | 北京控制工程研究所 | Catalytic combustion engine and combustion method for high-viscosity ionic liquid propellant |
| US10910198B2 (en) * | 2019-03-12 | 2021-02-02 | Momentus Inc. | Spacecraft propulsion devices and systems with microwave excitation |
| DE102022000797A1 (en) * | 2021-03-10 | 2022-09-15 | Mathias Herrmann | Ignition concept and combustion concept for engines and rockets; the most effective or directed excitation and ignition possible by means of adapted electromagnetic radiation or electromagnetic waves (e.g. radio waves, microwaves, magnetic waves) and catalytic absorbers to increase the energetic efficiency and thrust |
| CN114810427B (en) * | 2022-03-31 | 2023-06-16 | 北京控制工程研究所 | High-energy green liquid propeller ignition device and method for microwave excited plasma |
| CN114962077A (en) * | 2022-06-22 | 2022-08-30 | 北京交通大学 | Dinitramide ammonium-based liquid single-component engine based on electric ignition mode |
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| CN109310003A (en) * | 2018-10-22 | 2019-02-05 | 安徽工业大学 | Coaxial resonant microwave discharge plasma large scale efficient combustion-supporting device |
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