CN211819719U - Two-component nitrous oxide engine - Google Patents
Two-component nitrous oxide engine Download PDFInfo
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- CN211819719U CN211819719U CN202020408671.2U CN202020408671U CN211819719U CN 211819719 U CN211819719 U CN 211819719U CN 202020408671 U CN202020408671 U CN 202020408671U CN 211819719 U CN211819719 U CN 211819719U
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Abstract
The utility model provides a two-component nitrous oxide engine. The two-component nitrous oxide engine comprises: the thrust chamber comprises a decomposition chamber and a combustion chamber which are communicated with each other, the volume of the decomposition chamber is smaller than that of the combustion chamber, a catalyst is placed in the decomposition chamber, and a first propellant inlet and a second propellant inlet are formed in the combustion chamber; a heating device for heating the catalyst in the decomposition chamber. The utility model discloses a two component nitrous oxide engines can be used to install in rocket, satellite, spacecraft etc to a driving system for controlling its track or attitude control, and this propellant can be stored under normal atmospheric temperature, low temperature, thereby can reduce and finally eliminate liquid propellant's toxicity, and improve the low temperature environment adaptability of engine.
Description
Technical Field
The utility model relates to a power equipment technical field particularly, relates to a two-component nitrous oxide engine.
Background
Self-pressurized rocket propellants have recently become of increasing interest to researchers. In particular, nitrous oxide is used as a liquid oxidizer for rocket self-pressurization. Nitrous oxide has a saturated vapor Pressure (PV) of about 730psi (5.03 MPa) at room temperature. Some important thermodynamic properties of nitrous oxide are shown in table 1. This makes nitrous oxide an attractive rocket power system propellant because it can be discharged from the tank without the need for complex pressurization systems or turbo pumps (hence the name self-pressurization). Nitrous oxide is easy to store, relatively non-toxic and easy to control. Thus, conventional oxidizers and single-component propellants commonly used in current launching systems (e.g., Liquid Oxygen (LOX), dinitrogen tetroxide (N)2O4) Hydrazine (N)2H4) It is generally considered a safe alternative.
TABLE 1N2Important thermodynamic properties of O
However, it should be noted that the use of nitrous oxide, as with all propellants, has its associated risks and should therefore always be considered. In particular, nitrous oxide decomposition is an exothermic reaction. In some cases, the continuous decomposition reaction can result in an increase in pressure in the pressure vessel leading to explosion. Such explosions have occurred in rocket power systems in the past and have even caused death of personnel. However, with proper precautions and controls, nitrous oxide can be safely used as a rocket propellant.
Conventional engines used for controlling satellite orbit or attitude control, etc., can be classified into monopropellant engines (using a single propellant) and bipropellant engines (using a propellant containing an oxidizer and a fuel).
FIG. 1 shows a schematic diagram of a conventional two-component engine. The engine 1 is constructed by adding, for example, hydrazine (N)2H4) Or methylhydrazine (MMH), oxidizing agents such as nitrous oxide (N)2O4) The fuel and the oxidant are mixed and combusted in the combustion chamber 3 through the electromagnetic valve 2 and the electromagnetic valve 5 respectively to generate high-temperature fuel gas which is sprayed out from a spray pipe of the engine 1 to generate thrust.
The conventional engines described above use highly toxic propellants. Therefore, when a power system composed of these engines is operated on the ground, environmental protection and safe disposal are essential. Researchers throughout the world are currently working on developing liquid engines that can use low or no toxicity propellants.
In addition, hydrazine is currently used as the mainstream propellant for satellite and spacecraft attitude control monopropellants, which has problems with high freezing points (about 1 ℃). When the satellite or spacecraft is used in a low temperature space environment, it is necessary to provide heating or thermal insulation means to the entire propellant supply system to prevent the hydrazine from freezing in the low temperature environment, rendering the engine inoperative.
Nitrous oxide solves the above problems very well and can react with many hydrocarbon fuels, such as ethanol, methane, propane, etc.
SUMMERY OF THE UTILITY MODEL
The main object of the present invention is to provide a bipropellant nitrous oxide engine, which can reduce and finally eliminate the toxicity of liquid propellant, and improve the low temperature environment adaptability of the power system.
In order to achieve the above object, the present invention provides a two-component nitrous oxide engine, comprising: the thrust chamber comprises a decomposition chamber and a combustion chamber which are communicated with each other, the volume of the decomposition chamber is smaller than that of the combustion chamber, a catalyst is placed in the decomposition chamber, and a first propellant inlet and a second propellant inlet are formed in the combustion chamber; a heating device for heating the catalyst in the decomposition chamber.
Further, the heating device is an electric heating device.
Further, the heating device includes: the heater is sleeved on the periphery of the decomposition chamber; a power supply coil for supplying power to the heater.
Further, a first inlet and a second inlet are arranged on the decomposition chamber, the first inlet is arranged at one end of the decomposition chamber far away from the combustion chamber, and the second inlet is arranged at one end of the decomposition chamber close to the combustion chamber.
Further, the heater is prepared by adopting an oxidation-resistant material, and the surface of the oxidation-resistant material is coated with a high-heat-resistance material.
Further, the oxidation resistant material is SiC.
Further, the high heat-resistant material is ceramic.
Further, the bi-component nitrous oxide engine further comprises an injector, the injector is arranged at one end, close to the decomposition chamber, of the combustion chamber, and the first propellant inlet, the second propellant inlet and the second inlet are all connected with an inlet of the injector.
Use the technical scheme of the utility model, the utility model discloses a two component nitrous oxide engines can be used to install in rocket, satellite, spacecraft etc to be used for controlling its track or attitude control's driving system, and this propellant can be stored under normal atmospheric temperature, low temperature, thereby can reduce and finally eliminate liquid propellant's toxicity, and improve the low temperature environment adaptability of engine.
In addition to the above-described objects, features and advantages, the present invention has other objects, features and advantages. The present invention will be described in further detail with reference to the drawings.
Drawings
The accompanying drawings, which form a part of the specification, are included to provide a further understanding of the invention, and are incorporated in and constitute a part of this specification, illustrate embodiments of the invention and together with the description serve to explain the invention without unduly limiting the scope of the invention. In the drawings:
FIG. 1 schematically illustrates a cross-sectional view of a prior art two-component engine;
figure 2 schematically illustrates a cross-sectional view of a two-component nitrous oxide engine of the present invention.
Wherein the figures include the following reference numerals:
10. a thrust chamber; 11. a decomposition chamber; 12. a combustion chamber; 121. a first propellant inlet; 122. a second propellant inlet; 131. a first inlet; 132. a second inlet; 20. a heating device; 21. a heater; 22. a power supply coil; 30. an injector; 40. a catalyst.
Detailed Description
It should be noted that, in the present invention, the embodiments and features of the embodiments may be combined with each other without conflict. The present invention will be described in detail below with reference to the accompanying drawings in conjunction with embodiments.
In order to make the technical solution of the present invention better understood, the technical solution of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative efforts shall belong to the protection scope of the present invention.
It should be noted that the terms "first," "second," and the like in the description and claims of the present invention and in the drawings described above are used for distinguishing between similar elements and not necessarily for describing a particular sequential or chronological order. It is to be understood that the terms so used are interchangeable under appropriate circumstances for describing embodiments of the invention herein. Furthermore, the terms "comprises," "comprising," and "having," and any variations thereof, are intended to cover a non-exclusive inclusion, such that a process, method, system, article, or apparatus that comprises a list of steps or elements is not necessarily limited to those steps or elements expressly listed, but may include other steps or elements not expressly listed or inherent to such process, method, article, or apparatus.
It is noted that the terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting of example embodiments according to the present application. As used herein, the singular forms "a", "an" and "the" are intended to include the plural forms as well, and it should be understood that when the terms "comprises" and/or "comprising" are used in this specification, they specify the presence of stated features, steps, operations, devices, components, and/or combinations thereof, unless the context clearly indicates otherwise.
Referring to fig. 2, a two-component nitrous oxide engine is provided according to an embodiment of the present invention. Nitrous oxide has the possibility of realizing a deep space exploration task of about 223.15K in a low-temperature environment in the near future. The freezing point of nitrous oxide is 183K.
Nitrous oxide is used as a propellant for a bipropellant engine and has the same working principle with a hydrazine monopropellant engine, the catalyst needs to be heated, and in the working process of the engine, in order to prevent the catalyst from generating local stress and being damaged due to overlarge gradient change of the temperature inside and outside the catalyst. Further, in the case of a two-component engine, when high saturated vapor pressure nitrous oxide is used, a different supercharged gas system can be obtained by filling the liquid temperature, and even if the saturated vapor pressure of the fuel is not too high, the vapor pressure of nitrous oxide gas can be used as the fuel supercharged gas, thereby reducing the number of system components and the difficulty of design. To achieve two-component engine operation, nitrous oxide in combination with a hydrocarbon fuel requires an ignition device to achieve combustion.
Specifically, the two-component nitrous oxide engine in the present embodiment includes a thrust chamber 10 and a heating device 20.
The thrust chamber 10 comprises a decomposition chamber 11 and a combustion chamber 12 which are communicated with each other, the volume of the decomposition chamber 11 is smaller than that of the combustion chamber 12, a catalyst 40 is placed in the decomposition chamber 11, and the combustion chamber 12 is provided with a first propellant inlet 121 for nitrous oxide to enter and a second propellant inlet 122 for other hydrocarbon fuels to enter; the heating device 20 is used to heat the catalyst 40 in the decomposition chamber 11.
The catalyst 40 of the present invention is a substance capable of decomposing nitrous oxide into gaseous oxygen and gaseous nitrogen with high efficiency. For example, the catalyst 40 carrier is a catalyst using aluminum, magnesium and rhodium. Alternatively, the catalyst 40 of the present invention may also suitably use noble metals such as rhodium, ruthenium and palladium, and the catalyst carrier is selected from SiO2Or Al2O3. Using these catalysts, nitrous oxide can be decomposed into gaseous oxygen and gaseous nitrogen at near 100% efficiency. The catalyst 40 in the utility model is designed into a honeycomb or porous form, and the catalyst can catalyze and decompose the mixed gas with the nitrogen oxide content of 2% -3%.
Preferably, the engine of the present invention uses a rhodium catalyst with alumina as a carrier, wherein the alumina carrier has a ceramic honeycomb structure. Nitrous oxide has a stable chemical nature, does not cause harm to the human body when inhaled in small amounts, and is also approved as a food additive. When the nitrous oxide is used as a propellant of a mono-component engine, the fuel gas generated by catalytic decomposition is non-toxic. Based on the relatively high saturated vapor pressure of nitrous oxide (e.g., about 0.64Mpa at-223.15K and about 7.25Mpa at 309K), the use of pressurized gas may not be required when nitrous oxide is used as a propellant in conventional engines, and nitrous oxide itself may be used as the pressurized gas.
The utility model discloses two groupsThe nitrous oxide engine generates thrust by mixing and combusting fuel and nitrous oxide. Because of the toxicity of dinitrogen tetroxide (N) used in the conventional two-component nitrous oxide engine2O4) Hydrazine (N)2H4) Unlike the propellants of (a) the nitrous oxide/hydrocarbon fuel combination does not have the characteristic of self-ignition at normal temperatures and therefore an additional ignition device needs to be provided. The ignition mode can adopt gaseous oxygen-containing high-temperature fuel gas or high-temperature combustion gas generated by mixing and combusting nitrous oxide catalytic decomposition gas and fuel. Therefore, if the mixture of fuel and nitrous oxide can be ignited by the heat generated by catalytic decomposition of a small amount of nitrous oxide, the ignition device and the required propellant of the igniter can be reduced, resulting in a simple structure, reduced weight, and simplified control procedure.
As shown in fig. 2, the combustion chamber 12 of the present embodiment is provided with a first propellant inlet 121 for the introduction of nitrous oxide and a second propellant inlet 122 for the introduction of other hydrocarbon fuels for feeding nitrous oxide and fuel, respectively, to the combustion chamber 12. The ignition device energy source is realized by decomposing nitrous oxide by itself, and specifically, the heating device 20 is adopted to heat the catalyst 40 in the decomposition chamber 11 to decompose nitrous oxide so as to provide ignition energy.
Preferably, the heating device 20 in this embodiment is an electric heating device, which is convenient for being connected with a power generation system on the rocket to realize a heating function and is convenient for control. Of course, in other embodiments of the present invention, the heating device 20 can be further configured as other heating devices convenient for operation and control, as long as the other deformation modes under the concept of the present invention are all within the protection scope of the present invention.
The heating device 20 comprises a heater 21 and a power supply coil 22, wherein the heater 21 is sleeved on the periphery of the decomposition chamber 11; the power supply coil 22 is used to supply power to the heater 21.
In order to facilitate the transport of propellant nitrous oxide into the decomposition chamber 11, the decomposition chamber 11 is provided with a first inlet 131 and a second inlet 132, the first inlet 131 being arranged at an end of the decomposition chamber 11 remote from the combustion chamber 12 and the second inlet 132 being arranged at an end of the decomposition chamber 11 close to the combustion chamber 12.
The decomposition chamber 11 is provided with a first inlet 131 for delivering nitrous oxide from the first inlet 131 to the decomposition chamber 11, and after catalytic decomposition, the nitrous oxide is communicated with the combustion chamber 12. A small amount of decomposition catalyst 40 is provided in the decomposition chamber 11, and in the process, the power supply coil 22 is energized, the heater 21 is operated, and the catalyst 40 is heated, thereby achieving the catalytic decomposition of nitrous oxide. The heater 21 is made of an oxidation-resistant material, and the surface of the oxidation-resistant material is coated with a high heat-resistant material. Preferably, the oxidation resistant material is a SiC material and the high heat resistant material is a ceramic material. The silicon carbide (SiC) has high oxidation resistance and heat resistance, the applicable temperature can reach about 1600 ℃, the service environment of the engine is conveniently met, and the service life of the engine is prolonged.
The utility model discloses an one end that decomposition chamber 11 is close to combustion chamber 12 is provided with second entry 132, is convenient for carry the gas in 11 to decomposition chamber, with the gas mixture of decomposition in 11, the burning, produces the ignition source that high temperature gas is used for combustion chamber 12.
The utility model discloses a two component nitrous oxide transmitters's work as follows: first, in the decomposition chamber 11, the high-temperature catalytically decomposed fuel gas is mixed with the fuel, and the resulting high-temperature combustion gas is fed into the combustion chamber 12. Meanwhile, in the combustion chamber 12, nitrous oxide and fuel are supplied from the first propellant inlet 121 and the second propellant inlet 122, respectively, are mixed and combusted in the combustion chamber 12, and are ejected from a nozzle at the tail of the engine to generate thrust.
The two-component nitrous oxide engine in the embodiment further comprises an injector 30, the injector 30 is arranged at one end of the combustion chamber 12 close to the decomposition chamber 11, and the first propellant inlet 121, the second propellant inlet 122 and the second inlet 132 are all connected with the inlet of the injector 30. During actual operation, propellant enters the combustion chamber 12 through the injector 30.
Compared with the prior art, the method adopts Liquid Oxygen (LOX) and dinitrogen tetroxide (N)2O4) Hydrazine (N)2H4) As to the structure of the propellant, the two-component nitrous oxide engine in the embodiment can reduce and finally eliminate the toxicity of the liquid propellant and improve oxygenAdaptability of the nitrous oxide engine to low-temperature environment.
From the above description, it can be seen that the above-described embodiments of the present invention achieve the following technical effects.
The utility model discloses a two component nitrous oxide engines can be used to install in rocket, satellite, spacecraft etc to a driving system for controlling its track or attitude control, and this propellant can be stored under normal atmospheric temperature, low temperature, thereby can reduce and finally eliminate liquid propellant's toxicity, and improve the low temperature environment adaptability of engine.
Unless specifically stated otherwise, the relative arrangement of the components and steps, the numerical expressions, and numerical values set forth in these embodiments do not limit the scope of the present invention. Meanwhile, it should be understood that the sizes of the respective portions shown in the drawings are not drawn in an actual proportional relationship for the convenience of description. Techniques, methods, and apparatus known to those of ordinary skill in the relevant art may not be discussed in detail but are intended to be part of the specification where appropriate. In all examples shown and discussed herein, any particular value should be construed as merely illustrative, and not limiting. Thus, other examples of the exemplary embodiments may have different values. It should be noted that: like reference numbers and letters refer to like items in the following figures, and thus, once an item is defined in one figure, further discussion thereof is not required in subsequent figures.
Spatially relative terms, such as "above … …," "above … …," "above … …," "above," and the like, may be used herein for ease of description to describe one device or feature's spatial relationship to another device or feature as illustrated in the figures. It will be understood that the spatially relative terms are intended to encompass different orientations of the device in use or operation in addition to the orientation depicted in the figures. For example, if a device in the figures is turned over, devices described as "above" or "on" other devices or configurations would then be oriented "below" or "under" the other devices or configurations. Thus, the exemplary term "above … …" can include both an orientation of "above … …" and "below … …". The device may be otherwise variously oriented (rotated 90 degrees or at other orientations) and the spatially relative descriptors used herein interpreted accordingly.
In the description of the present invention, it should be understood that the orientation or positional relationship indicated by the orientation words such as "front, back, up, down, left, right", "horizontal, vertical, horizontal" and "top, bottom" etc. are usually based on the orientation or positional relationship shown in the drawings, and are only for convenience of description and simplification of description, and in the case of not making a contrary explanation, these orientation words do not indicate and imply that the device or element referred to must have a specific orientation or be constructed and operated in a specific orientation, and therefore, should not be interpreted as limiting the scope of the present invention; the terms "inner and outer" refer to the inner and outer relative to the profile of the respective component itself.
The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention, and various modifications and changes may be made by those skilled in the art. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (8)
1. A bi-component nitrous oxide engine, comprising:
the thrust chamber (10) comprises a decomposition chamber (11) and a combustion chamber (12) which are communicated with each other, the volume of the decomposition chamber (11) is smaller than that of the combustion chamber (12), a catalyst (40) is placed in the decomposition chamber (11), and a first propellant inlet (121) and a second propellant inlet (122) are arranged on the combustion chamber (12);
a heating device (20), the heating device (20) being used for heating the catalyst (40) in the decomposition chamber (11).
2. The bipropellant nitrous oxide engine according to claim 1, characterized in that said heating means (20) is an electric heating means.
3. The bi-component nitrous oxide engine of claim 1, characterized in that said heating means (20) comprises:
the heater (21), the said heater (21) is fitted over the periphery of the said decomposition chamber (11);
a power supply coil (22), the power supply coil (22) being used to supply power to the heater (21).
4. The bipropellant nitrous oxide engine according to claim 3, characterized in that said decomposition chamber (11) is provided with a first inlet (131) and a second inlet (132), said first inlet (131) being arranged at an end of said decomposition chamber (11) remote from said combustion chamber (12), said second inlet (132) being arranged at an end of said decomposition chamber (11) close to said combustion chamber (12).
5. The bi-component nitrous oxide engine of claim 4, characterized in that said heater (21) is fabricated from an oxidation resistant material having a surface coated with a high heat resistant material.
6. The bi-component nitrous oxide engine of claim 5, wherein said oxidation resistant material is SiC.
7. The bi-component nitrous oxide engine of claim 5, wherein said high heat resistant material is a ceramic.
8. The twin nitrous oxide engine according to claim 4, further comprising an injector (30), said injector (30) being arranged at an end of said combustion chamber (12) adjacent to said decomposition chamber (11), said first propellant inlet (121), said second propellant inlet (122) and said second inlet (132) being connected to an inlet of said injector (30).
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202020408671.2U CN211819719U (en) | 2020-03-26 | 2020-03-26 | Two-component nitrous oxide engine |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202020408671.2U CN211819719U (en) | 2020-03-26 | 2020-03-26 | Two-component nitrous oxide engine |
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| CN211819719U true CN211819719U (en) | 2020-10-30 |
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| CN202020408671.2U Active CN211819719U (en) | 2020-03-26 | 2020-03-26 | Two-component nitrous oxide engine |
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