CN211819716U - Nitrous oxide power system - Google Patents
Nitrous oxide power system Download PDFInfo
- Publication number
- CN211819716U CN211819716U CN202020408659.1U CN202020408659U CN211819716U CN 211819716 U CN211819716 U CN 211819716U CN 202020408659 U CN202020408659 U CN 202020408659U CN 211819716 U CN211819716 U CN 211819716U
- Authority
- CN
- China
- Prior art keywords
- propellant
- nitrous oxide
- chamber
- thrust chamber
- power system
- 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.)
- Active
Links
Images
Abstract
The utility model provides a nitrous oxide driving system. The nitrous oxide power system comprises: a single component thrust chamber; a two-component thrust chamber; a propellant delivery assembly for delivering propellant to the monopropellant thrust chamber and the bipropellant thrust chamber; a switching assembly connected between the propellant delivery assembly, the monopropellant thrust chamber, and the bipropellant thrust chamber such that the propellant delivery assembly delivers propellant to the monopropellant thrust chamber or the bipropellant thrust chamber, or both the monopropellant thrust chamber and the bipropellant thrust chamber. The utility model provides a nitrous oxide driving system has improved the security, and the cost is reduced can be used to single component engine, bipropellant engine. Meanwhile, the nitrous oxide power system has practical performance capability, can be stored in normal-temperature and low-temperature environments, and is expected to have higher use value in planetary exploration tasks.
Description
Technical Field
The utility model relates to a power equipment technical field particularly, relates to a nitrous oxide driving system.
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 one-component engine. The engine 1 is fed into a combustion chamber 3 through an electromagnetic valve 2 to generate thrust. For the traditional propellant, namely hydrazine, hydrazine is catalytically decomposed by a catalyst 4 to generate pyrolysis gas which is sprayed out from an engine spray pipe to generate thrust.
Fig. 2 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 utility model is to provide a nitrous oxide driving system can reduce and finally eliminate liquid propellant's toxicity to improve driving system's low temperature environment adaptability.
In order to achieve the above object, the present invention provides a nitrous oxide power system, including: a single component thrust chamber; a two-component thrust chamber; a propellant delivery assembly for delivering propellant to the monopropellant thrust chamber and the bipropellant thrust chamber; a switching assembly connected between the propellant delivery assembly, the monopropellant thrust chamber, and the bipropellant thrust chamber such that the propellant delivery assembly delivers propellant to the monopropellant thrust chamber or the bipropellant thrust chamber, or both the monopropellant thrust chamber and the bipropellant thrust chamber.
Further, the single component thrust chamber includes: a first decomposition chamber having a catalyst disposed therein; a first heating device for heating the catalyst within the first decomposition chamber.
Further, the two-component thrust chamber comprises: the device comprises a second decomposition chamber and a combustion chamber which are communicated with each other, wherein the volume of the second decomposition chamber is smaller than that of the combustion chamber, a catalyst is placed in the second decomposition chamber, and a first propellant inlet and a second propellant inlet are formed in the combustion chamber; a second heating device for heating the catalyst within the second decomposition chamber.
Further, the second decomposition chamber is provided with a first inlet and a second inlet.
Further, the propellant delivery assembly comprises: a first propellant reservoir in communication with the first decomposition chamber through a first conduit, the first propellant reservoir being connected to the first inlet through a second conduit, the first propellant reservoir being connected to the first propellant inlet through a third conduit; a second propellant reservoir connected to a second inlet via a fourth conduit, the second propellant reservoir being connected to the second propellant inlet via a fifth conduit.
Further, the nitrous oxide power system also comprises a gas source, and the gas source is connected with the inlet of the first decomposition chamber through a sixth pipeline.
Further, the nitrous oxide power system further comprises: a first main pipe, a first end of which is connected with the first propellant storage, and a second end of which is respectively connected with the first pipeline, the second pipeline and the third pipeline; a first end of the second main pipeline is connected with the second propellant storage, and a second end of the second main pipeline is respectively connected with the fourth pipeline and the fifth pipeline; wherein the switching assembly includes first control valves disposed on the first, second, third, fourth, and fifth conduits.
Furthermore, the first propellant storage device and the second propellant storage device are both provided with exhaust ports, the exhaust ports are connected with exhaust pipes, and the exhaust pipes are provided with second control valves.
Furthermore, the first propellant storage device and the second propellant storage device are both provided with filling ports, the filling ports are provided with filling pipes, and the filling pipes are provided with third control valves.
Furthermore, the sixth pipeline is communicated with a filling pipe on the first propellant storage and a filling pipe on the second propellant storage, and a fourth control valve used for controlling the gas source to convey gas to the first propellant storage, the second propellant storage and the first decomposition chamber is arranged on the sixth pipeline.
Use the technical scheme of the utility model, the utility model provides a be provided with the switching subassembly among the nitrous oxide driving system, through the effect of this switching subassembly, can control propellant transport assembly, make propellant transport assembly carry propellant to single component thrust room or bipropellant thrust room, perhaps carry the extrusion agent to single component thrust room and bipropellant thrust room simultaneously to realize the function of single component engine, perhaps the function of multicomponent engine, perhaps realize the function of single component engine and multicomponent engine simultaneously.
The utility model discloses an engine uses the catalyst that has high decomposition performance, under the condition that does not obviously reduce conventional engine performance, has realized nontoxic and low temperature environment adaptability. The utility model discloses an engine has improved the security, and the cost is reduced can be used to single component engine, bipropellant engine. Meanwhile, the engine has practical performance capability, can be stored in normal temperature and low temperature environments, and is expected to have greater use value in planet exploration tasks.
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 monocomponent engine;
FIG. 2 schematically illustrates a cross-sectional view of a prior art two-component engine;
fig. 3 schematically shows a connection diagram of the nitrous oxide power system according to the present invention.
Wherein the figures include the following reference numerals:
10. a single component thrust chamber; 11. a first decomposition chamber; 12. a first heating device; 20. a two-component thrust chamber; 21. a second decomposition chamber; 211. a first inlet; 212. a second inlet; 22. a combustion chamber; 221. a first propellant inlet; 222. a second propellant inlet; 23. a second heating device; 30. a propellant delivery assembly; 31. a first propellant store; 32. a second propellant store; 33. a first conduit; 34. a second conduit; 35. a third pipeline; 36. a fourth conduit; 37. a fifth pipeline; 38. an exhaust pipe; 39. a third control valve; 310. a filling pipe; 311. a second control valve; 312. a first main pipe; 313. a second main pipe; 314. an exhaust port; 315. a filling port; 40. a switching component; 41. a first control valve; 50. a gas source; 60. a sixth pipeline; 70. a fourth control valve.
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. 3, according to an embodiment of the present invention, a nitrous oxide power system is provided, the nitrous oxide power system in this embodiment mainly utilizes nitrous oxide as a propellant, and during actual operation, the nitrous oxide power system in this embodiment can realize functions of a single-component engine, a multi-component engine, or both the single-component engine and the multi-component engine. The two-component engine is used for a high-performance and high-thrust track engine, and the single-component engine is used for a low-thrust attitude control engine.
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. Thus, when nitrous oxide is used as a propellant in a low temperature environment, there is no need to use a heating and thermal insulation device in the propellant supply system of the engine. Nitrous oxide is used as a propellant for a single-unit engine and has the same working principle with a hydrazine single-unit engine, the catalyst needs to be heated, and in the working process of the engine, a heating device is usually needed to be arranged in order to prevent the catalyst from generating local stress and being damaged due to overlarge temperature gradient change inside and outside the catalyst.
Specifically, the nitrous oxide power system in this embodiment includes a monopropellant thrust chamber 10, a bipropellant thrust chamber 20, a propellant feed assembly 30, and a switch assembly 40.
Wherein propellant feed assembly 30 is adapted to feed propellant to monopropellant thrust chamber 10 and bipropellant thrust chamber 20; a switch assembly 40 is connected between propellant delivery assembly 30, monopropellant thrust chamber 10 and bipropellant thrust chamber 20 to allow propellant delivery assembly 30 to deliver propellant to monopropellant thrust chamber 10 or bipropellant thrust chamber 20, or to deliver propellant to both monopropellant thrust chamber 10 and bipropellant thrust chamber 20.
The nitrous oxide power system in this embodiment is provided with a switching assembly 40, and the propellant conveying assembly 30 can be controlled by the action of the switching assembly 40, so that the propellant conveying assembly 30 conveys a propellant to the single-component thrust chamber 10 or the two-component thrust chamber 20, or simultaneously conveys a propellant to the single-component thrust chamber 10 and the two-component thrust chamber 20, thereby realizing the functions of a single-component engine, or a multi-component engine, or simultaneously realizing the functions of the single-component engine and the multi-component engine.
The single-component thrust chamber 10 in the present embodiment comprises a first decomposition chamber 11 and a first heating device 12, wherein a catalyst is placed in the first decomposition chamber 11; the first heating device 12 is used for heating the catalyst in the first decomposition chamber 11.
In practice, when the nitrous oxide power system in the present embodiment is used to realize the monopropellant engine function, nitrous oxide is delivered into the first decomposition chamber 11 through the propellant delivery assembly 30, and then the catalyst in the first decomposition chamber 11 is heated by the first heating device 12. The catalyst in the utility model is a substance which can efficiently decompose nitrous oxide into gaseous oxygen and gaseous nitrogen. For example, the catalyst support is a catalyst using aluminum, magnesium and rhodium. Alternatively, the catalyst 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 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 a single unit thrust room 10 can produce the high temperature oxygen nitrogen mist that surpasss 1000 ℃ through the catalyst decomposition, discharges through the spray tube of nitrous oxide afterbody, produces thrust. Compared with the prior art, the method adopts Liquid Oxygen (LOX) and dinitrogen tetroxide (N)2O4) Hydrazine (N)2H4) As for the structure of the propellant, the nitrous oxide power system in the present embodiment can reduce and eventually eliminate the toxicity of the liquid propellant and improve the low temperature environmental adaptability of the nitrous oxide engine.
Preferably, the first heating device 12 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 first heating device 12 can be set as other heating devices convenient for operation, 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 first heating device 12 in this embodiment includes a heater and a power supply coil, wherein the heater is disposed inside the first decomposition chamber 11, and the heater contains the catalyst; the power supply coil is connected with the heater to supply power to the heater.
In other embodiments of the present invention, the first heating device 12 only includes a power supply coil, and no heater is provided, and in actual use, the power supply coil in this embodiment is used for directly heating the catalyst in the first decomposition chamber 11.
The utility model discloses nitrous oxide driving system is with the operating time of two component engine, and it produces thrust through fuel and nitrous oxide mixing, burning. Because of the toxicity of dinitrogen tetroxide (N) used in the conventional two-component 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.
Specifically, the two-component thrust chamber 20 in the present embodiment includes a second decomposition chamber 21 and a combustion chamber 22 which are communicated with each other, the volume of the second decomposition chamber 21 is smaller than the volume of the combustion chamber 22, a catalyst is placed in the second decomposition chamber 21, and a first propellant inlet 221 and a second propellant inlet 222 are arranged on the combustion chamber 22; the two-component thrust chamber 20 further comprises a second heating device 23, the second heating device 23 being used for heating the catalyst in the second decomposition chamber 21.
Further, the second decomposition chamber 21 in the present embodiment is provided with a first inlet 211 and a second inlet 212. The propellant delivery assembly 30 comprises a first propellant reservoir 31 and a second propellant reservoir 32, the first propellant reservoir 31 being in communication with the first decomposition chamber 11 through a first conduit 33; the second propellant reservoir 32 is connected to the second inlet 212 via a fourth conduit 36, and the second propellant reservoir 32 is connected to the second propellant inlet 222 via a fifth conduit 37.
The combustion chamber 22 in this embodiment is provided with a first propellant inlet 221 for the ingress of nitrous oxide and a second propellant inlet 222 for the ingress of other hydrocarbon fuels for feeding nitrous oxide and fuel, respectively, to the combustion chamber 22. The ignition device energy source is realized by decomposing nitrous oxide by itself, and specifically, the second heating device 23 is adopted to heat the catalyst in the second decomposition chamber 21 to decompose nitrous oxide so as to provide ignition energy.
The second decomposition chamber 21 is provided with a first inlet 211 for delivering nitrous oxide from the first inlet 211 to the second decomposition chamber 21, and is in communication with the combustion chamber 22 after catalytic decomposition. A small amount of decomposition catalyst is supplied in the second decomposition chamber 21, and in this process, the second heating device 23 is electrically operated to heat the catalyst, thereby effecting catalytic decomposition of nitrous oxide. The second heating device 23 in this embodiment includes a power supply coil and a heater, in which the heater is powered by the power supply coil, the heater 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 second decomposition chamber 21 is close to combustion chamber 22 is provided with second entry 212, is convenient for carry the gas in to second decomposition chamber 21, mixes, burns with the gas that decomposes in the second decomposition chamber 21, produces the ignition source that high temperature gas is used for combustion chamber 22.
The utility model discloses a driving system adopts the during operation of two component nitrous oxide transmitters: first, in the second decomposition chamber 21, 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 22. Meanwhile, in the combustion chamber 22, nitrous oxide and fuel are supplied from the first propellant inlet 221 and the second propellant inlet 222, respectively, to the combustion chamber 22, mixed and combusted, and ejected from a nozzle at the rear of the engine to generate thrust.
For convenience of connection and control, the nitrous oxide power system in the embodiment further includes a first main pipe 312 and a second main pipe 313, a first end of the first main pipe 312 is connected to the first propellant storage 31, and a second end of the first main pipe 312 is connected to the first pipe 33, the second pipe 34, and the third pipe 35 respectively; a first end of the second main pipe 313 is connected with the second propellant storage 32, and a second end of the second main pipe 313 is respectively connected with the fourth pipe 36 and the fifth pipe 37; wherein the switching assembly 40 comprises a first control valve 41 arranged on the first, second, third, fourth and fifth conduits 33, 34, 35, 36, 37.
In actual use, the direction of feed of the first propellant reservoir 31 and the second propellant reservoir 32 and thus the flow direction of the propellant in the first propellant reservoir 31 and the second propellant reservoir 32 can be controlled by controlling the first control valve 41 in the first conduit 33, the second conduit 34, the third conduit 35, the fourth conduit 36 and the fifth conduit 37.
The first propellant storage container 31 and the second propellant storage container 32 are provided with a vent 314, the vent 314 is connected with a vent pipe 38, and the vent pipe 38 is provided with a second control valve 311, so that the gas in the first propellant storage container 31 and the second propellant storage container 32 can be conveniently discharged.
In order to facilitate the addition of propellant to the first propellant storage 31 and the second propellant storage 32, in the present embodiment, each of the first propellant storage 31 and the second propellant storage 32 is provided with a filling port 315, a filling pipe 310 is provided on the filling port 315, and a third control valve 39 is provided on the filling pipe 310, so as to facilitate the addition of propellant to the first propellant storage 31 and the second propellant storage 32.
Further, the nitrous oxide power system further comprises a gas source 50, and the gas source 50 is connected with the inlet of the first decomposition chamber 11 through a sixth pipeline 60. The sixth conduit 60 in this embodiment is in communication with both the fill tube 310 on the first propellant reservoir 31 and the fill tube 310 on the second propellant reservoir 32. the sixth conduit 60 is provided with a fourth control valve 70 for controlling the gas supply 50 to deliver gas to the first propellant reservoir 31, the second propellant reservoir 32 and the first decomposition chamber 11.
The gas nitrogen or helium provides a source pressure from the gas source 50 through the action of the gas source 50 and the fourth control valve 70, facilitating pressurization of the system at the appropriate time. In operation, the utility model discloses a nitrous oxide can realize a complete self-pressurization feed system, uses nitrous oxide steam as the pressure boost air supply. It is noted that nitrous oxide is as little premixed with the hydrocarbon fuel as possible in the tank and the conduit.
The utility model discloses liquid engine and conventional liquid engine are synthesized comparatively, see table 2.
TABLE 2 the engine of the present invention compares with the conventional engine
Note: the specific impulse is inversely proportional to the mass of the propellant. To obtain nitrous oxide (N)2O) and hydrazine (N)2H4) The same thrust is the case for the monopropellant engine, with a nitrous oxide flow rate 1.11 times the hydrazine 210s/190 s. Since the tank volume is almost inversely proportional to the propellant density, the tank volume of nitrous oxide is N2H41.11 × 1.0/0.78=1.42 times.
From the above description, it can be seen that the above-mentioned embodiments of the present invention achieve the following technical effects:
the utility model discloses an engine uses the catalyst that has high decomposition performance (decomposition rate is nearly 100%), under the condition that does not obviously reduce conventional engine performance, has realized nontoxic and low temperature environment adaptability. The utility model discloses an engine has improved the security, and the cost is reduced can be used to single component engine, bipropellant engine. Meanwhile, the engine has practical performance capability, can be stored in normal temperature and low temperature environments, and is expected to have greater use value in planet exploration tasks.
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 (10)
1. A nitrous oxide power system, comprising:
a single component thrust chamber (10);
a two-component thrust chamber (20);
a propellant delivery assembly (30), said propellant delivery assembly (30) for delivering propellant to said single-component thrust chamber (10) and said dual-component thrust chamber (20);
a switching assembly (40), said switching assembly (40) being connected between said propellant delivery assembly (30), said monopropellant thrust chamber (10), and said bipropellant thrust chamber (20) such that said propellant delivery assembly (30) delivers propellant to said monopropellant thrust chamber (10) or said bipropellant thrust chamber (20), or delivers an extrusion agent to both said monopropellant thrust chamber (10) and said bipropellant thrust chamber (20).
2. The nitrous oxide power system of claim 1, wherein said single-component thrust chamber (10) comprises:
a first decomposition chamber (11), wherein a catalyst is placed in the first decomposition chamber (11);
a first heating device (12), said first heating device (12) being adapted to heat the catalyst inside said first decomposition chamber (11).
3. The nitrous oxide power system of claim 2, wherein said two-component thrust chamber (20) comprises:
a second decomposition chamber (21) and a combustion chamber (22) which are communicated with each other, wherein the volume of the second decomposition chamber (21) is smaller than that of the combustion chamber (22), a catalyst is placed in the second decomposition chamber (21), and a first propellant inlet (221) and a second propellant inlet (222) are arranged on the combustion chamber (22);
a second heating device (23), the second heating device (23) being used for heating the catalyst in the second decomposition chamber (21).
4. The nitrous oxide power system according to claim 3, characterized in that said second decomposition chamber (21) is provided with a first inlet (211) and a second inlet (212).
5. The nitrous oxide power system of claim 4, wherein the propellant feed assembly (30) comprises:
a first propellant reservoir (31), said first propellant reservoir (31) being in communication with said first decomposition chamber (11) through a first conduit (33), said first propellant reservoir (31) being connected to said first inlet (211) through a second conduit (34), said first propellant reservoir (31) being connected to said first propellant inlet (221) through a third conduit (35);
a second propellant reservoir (32), the second propellant reservoir (32) being connected to the second inlet (212) by a fourth conduit (36), the second propellant reservoir (32) being connected to the second propellant inlet (222) by a fifth conduit (37).
6. The nitrous oxide power system according to claim 5, further comprising a gas source (50), said gas source (50) being connected to an inlet of said first decomposition chamber (11) through a sixth conduit (60).
7. The nitrous oxide power system of claim 5, further comprising:
a first main pipe (312), a first end of the first main pipe (312) being connected with the first propellant storage (31), a second end of the first main pipe (312) being connected with the first pipe (33), the second pipe (34) and the third pipe (35), respectively;
a second main pipe (313), a first end of the second main pipe (313) is connected with the second propellant storage (32), and a second end of the second main pipe (313) is respectively connected with the fourth pipe (36) and the fifth pipe (37);
wherein the switching assembly (40) comprises a first control valve (41) arranged on the first duct (33), the second duct (34), the third duct (35), the fourth duct (36) and the fifth duct (37).
8. The nitrous oxide power system according to claim 5, characterized in that, be provided with gas vent (314) on first propellant storage ware (31) and the second propellant storage ware (32), be connected with blast pipe (38) on gas vent (314), be provided with second control valve (311) on blast pipe (38).
9. The nitrous oxide power system according to claim 5, characterized in that, each of the first propellant storage tank (31) and the second propellant storage tank (32) is provided with a filling port (315), a filling pipe (310) is arranged on the filling port (315), and a third control valve (39) is arranged on the filling pipe (310).
10. Nitrous oxide power system according to claim 6, characterized in that, said sixth pipeline (60) is communicated with a filling pipe (310) on said first propellant storage (31) and a filling pipe (310) on said second propellant storage (32), said sixth pipeline (60) is provided with a fourth control valve (70) for controlling the gas source (50) to deliver gas to said first propellant storage (31), said second propellant storage (32) and said first decomposition chamber (11).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202020408659.1U CN211819716U (en) | 2020-03-26 | 2020-03-26 | Nitrous oxide power system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202020408659.1U CN211819716U (en) | 2020-03-26 | 2020-03-26 | Nitrous oxide power system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN211819716U true CN211819716U (en) | 2020-10-30 |
Family
ID=73147851
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202020408659.1U Active CN211819716U (en) | 2020-03-26 | 2020-03-26 | Nitrous oxide power system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN211819716U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116557171A (en) * | 2023-07-05 | 2023-08-08 | 北京未来宇航空间科技研究院有限公司 | Propulsion system and method of using a propulsion system |
-
2020
- 2020-03-26 CN CN202020408659.1U patent/CN211819716U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116557171A (en) * | 2023-07-05 | 2023-08-08 | 北京未来宇航空间科技研究院有限公司 | Propulsion system and method of using a propulsion system |
| CN116557171B (en) * | 2023-07-05 | 2023-10-27 | 北京未来宇航空间科技研究院有限公司 | Propulsion system and method of using a propulsion system |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| JP4232820B2 (en) | Thruster device using nitrous oxide | |
| CN111156101A (en) | Nitrous oxide power system | |
| US6779335B2 (en) | Burning nitrous oxide and a fuel | |
| US8024918B2 (en) | Rocket motor having a catalytic hydroxylammonium (HAN) decomposer and method for combusting the decomposed HAN-based propellant | |
| US20110167793A1 (en) | Hybrid rocket using catalytic decomposition of oxidizer | |
| CN111173647A (en) | Two-component nitrous oxide engine | |
| US20140290212A1 (en) | Reactants sprayed into plasma flow for rocket propulsion | |
| US7966805B2 (en) | Hydroxyl amine based staged combustion hybrid rocket motor | |
| Cong et al. | Propulsive performance of hypergolic H202/kerosene bipropellant | |
| CN211819716U (en) | Nitrous oxide power system | |
| Jeong et al. | Demonstration of ammonia borane-based hypergolic ignitor for hybrid rocket | |
| US20130199155A1 (en) | Rocket Propulsion Systems, and Related Methods | |
| JP4061382B2 (en) | Two-component liquid propellant, flying object propulsion method and propulsion device | |
| US3811280A (en) | Process of using storable propellant fuels in supersonic combustion ramjets | |
| CN211819719U (en) | Two-component nitrous oxide engine | |
| US3336753A (en) | Propulsion devices | |
| CN211819718U (en) | Nitrous oxide engine | |
| US3230701A (en) | Two step reaction propulsion method | |
| Natan et al. | Advances in gel propulsion | |
| US8814562B2 (en) | Igniter/thruster with catalytic decomposition chamber | |
| Gallo et al. | Experimental Investigation of N 2 O Decomposition with Pd/Al 2 O 3 Cylindrical Pellets Catalyst | |
| Peretz et al. | Development of a laboratory-scale system for hybrid rocket motor testing | |
| CN111173646A (en) | Nitrous oxide engine | |
| KR20090073642A (en) | Novel propulsion system combined with bipropellant rocket using hydrogen peroxide gas generator and operating method of the same | |
| Kuznetsov et al. | Development of a lab-scale gel fuel ramjet combustor |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant |