CN116557171A - Propulsion system and method of using a propulsion system - Google Patents
Propulsion system and method of using a propulsion system Download PDFInfo
- Publication number
- CN116557171A CN116557171A CN202310815415.3A CN202310815415A CN116557171A CN 116557171 A CN116557171 A CN 116557171A CN 202310815415 A CN202310815415 A CN 202310815415A CN 116557171 A CN116557171 A CN 116557171A
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- heat exchange
- path
- cavity
- propellant
- propulsion system
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- 238000000034 method Methods 0.000 title claims abstract description 18
- 239000003380 propellant Substances 0.000 claims abstract description 98
- 238000002485 combustion reaction Methods 0.000 claims abstract description 73
- 238000005057 refrigeration Methods 0.000 claims description 54
- 238000001816 cooling Methods 0.000 claims description 41
- 239000000126 substance Substances 0.000 abstract description 8
- 239000007789 gas Substances 0.000 description 7
- 239000012530 fluid Substances 0.000 description 5
- 238000010992 reflux Methods 0.000 description 4
- 230000017525 heat dissipation Effects 0.000 description 3
- 238000009835 boiling Methods 0.000 description 2
- 230000005855 radiation Effects 0.000 description 2
- 238000011144 upstream manufacturing Methods 0.000 description 2
- 230000004308 accommodation Effects 0.000 description 1
- 230000008094 contradictory effect Effects 0.000 description 1
- 239000002737 fuel gas Substances 0.000 description 1
- 231100000252 nontoxic Toxicity 0.000 description 1
- 230000003000 nontoxic effect Effects 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
- F02K9/44—Feeding propellants
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
- F02K9/44—Feeding propellants
- F02K9/56—Control
Abstract
The application relates to the technical field of aircraft propulsion and provides a propulsion system and a use method of the propulsion system. Therefore, the refrigerating mechanism is driven to work by utilizing the chemical energy of the first propellant, the chemical energy of the first propellant is fully utilized, the propellant is prevented from being wasted, and when a large amount of electric energy is needed or insufficient, the refrigerating mechanism can be directly driven to work by the combustion mechanism.
Description
Technical Field
The application relates to the technical field of propulsion of aircrafts, in particular to a propulsion system and a using method of the propulsion system.
Background
The low-temperature propellant is high in specific impulse, non-toxic and pollution-free, is the most efficient and economical chemical propellant for on-orbit residence and orbit transfer of the aircraft, and is also the ideal chemical propellant for deep space exploration, manned lunar boarding and manned fire boarding.
However, low temperature propellants are difficult to store for long periods of time in harsh space environments due to their relatively low boiling point. In the prior art, the common solution is to ensure the low temperature in the storage tank by exhaust loss and to ensure the low temperature in the storage tank by external refrigeration. However, the exhaust loss causes the loss of propellant and is wasteful, and the external refrigeration requires a continuous supply of large amounts of electrical energy.
Disclosure of Invention
In view of the above, the present application provides a propulsion system and a method for using the propulsion system, and aims to solve the above technical problems to a certain extent.
In a first aspect, the present application provides a propulsion system comprising:
a storage member comprising a first cavity for storing a first propellant;
the refrigerating mechanism comprises an input end and an output end, the input end and the output end are communicated with the first cavity, and the refrigerating mechanism is used for cooling a first propellant entering the refrigerating mechanism from the input end;
the heat exchange assembly comprises a backflow path, a heat exchange path communicated with the backflow path, a heat exchange member communicated with the heat exchange path and an expansion valve arranged on the heat exchange path, wherein the backflow path is communicated with the first cavity and the output end, so that the first propellant cooled by the refrigeration mechanism flows back to the first cavity, and the heat exchange member is used for cooling the backflow path;
and the heat exchange component is communicated with the combustion mechanism, and the combustion mechanism burns the first propellant conveyed by the heat exchange component so as to drive the refrigeration mechanism.
Preferably, the return path includes a cooling portion for being cooled by the heat exchange member, the cooling portion being disposed within the first cavity.
Preferably, the return path includes a cooling portion for being cooled by the heat exchange member, the cooling portion includes a middle path and an outer path communicating with each other, an accommodating space is defined by the outer path, the heat exchange member is sleeved outside the middle path, and at least part of the heat exchange member is disposed in the accommodating space.
Preferably, the heat exchange member is located within the first cavity.
Preferably, the storage member further comprises a second cavity disposed adjacent to the first cavity, the second cavity for containing a second propellant, the second cavity in communication with the combustion mechanism.
Preferably, the propulsion system further comprises a first engine block and a second engine block, the first engine block being in communication with the combustion mechanism for driving the first engine block, the first cavity and the second cavity each being in communication with the second engine block for driving the second engine block.
Preferably, the propulsion system further comprises a heat dissipating member that exchanges heat with the refrigeration mechanism to dissipate heat in the first propellant flowing through the refrigeration mechanism into the space.
In a second aspect, the present application provides a method of using a propulsion system comprising:
a storage member comprising a first cavity for storing a first propellant;
the refrigerating mechanism comprises an input end and an output end, the input end and the output end are communicated with the first cavity, and the refrigerating mechanism is used for cooling a first propellant entering the refrigerating mechanism from the input end;
the heat exchange assembly comprises a backflow path, a heat exchange path communicated with the backflow path, a heat exchange member communicated with the heat exchange path and an expansion valve arranged on the heat exchange path, wherein the backflow path is communicated with the first cavity and the output end, so that the first propellant cooled by the refrigeration mechanism flows back to the first cavity, and the heat exchange member is used for cooling the backflow path;
a combustion mechanism in communication with the heat exchange member, the combustion mechanism combusting a first propellant delivered by the heat exchange member to drive the refrigeration mechanism;
a first engine block in communication with the combustion mechanism for driving the first engine block;
the using method comprises the following steps:
and controlling a path between the heat exchange member and the combustion mechanism to be opened, wherein the first propellant flowing through the heat exchange member enters the combustion mechanism, and the combustion mechanism drives the refrigeration mechanism and the first engine unit.
Preferably, the propulsion system further comprises a second cavity and a second engine block, the second cavity is arranged adjacent to the first cavity and is used for containing a second propellant, the second cavity is communicated with the combustion mechanism, and the first cavity and the second cavity are both communicated with the second engine block;
the using method further comprises the following steps:
and controlling a path between the heat exchange member and the combustion mechanism to be closed, controlling the refrigeration mechanism to be driven by electric energy, and driving the second engine unit by the first propellant of the first cavity and the second propellant of the second cavity.
Preferably, the using method further comprises: and controlling the path between the heat exchange component and the combustion mechanism to be closed, controlling the path between the second cavity and the combustion mechanism to be disconnected, controlling the paths between the first cavity and the second engine unit to be disconnected, and controlling the refrigeration mechanism to be driven by electric energy.
According to the propulsion system provided by the application, under the condition that the path between the heat exchange component and the combustion mechanism is closed, the first propellant does not flow through the expansion valve, the refrigeration mechanism can be utilized to cool the first propellant in the first cavity, and under the working condition, the first propellant in the first cavity flows through the first cavity and then flows back into the first cavity through the backflow path. Under the condition that a path between the heat exchange component and the combustion mechanism is opened, the refrigeration mechanism still cools the first propellant flowing through the refrigeration mechanism, on the basis, the heat exchange component shunts a part of the first propellant in the reflux path, the part of the first propellant passes through the expansion valve and becomes low-temperature and low-pressure fluid, the part of the low-temperature and low-pressure fluid is used for cooling the reflux path, so that the first propellant in the reflux path is further cooled, the first propellant in the heat exchange component after cooling the reflux path flows to the combustion mechanism, is combusted in the combustion mechanism and drives the refrigeration mechanism to work. Therefore, according to the propulsion system provided by the application, when the first propellant needs to be exhausted for cooling or needs to be cooled with high power, the chemical energy of the first propellant is utilized to drive the refrigeration mechanism to work. On one hand, the chemical energy of the first propellant is fully utilized, the propellant is prevented from being wasted, and on the other hand, when a large amount of electric energy is needed or the electric energy is insufficient, the refrigerating mechanism can be directly driven to work through the combustion mechanism, so that the use requirement can be met or the use of the electric energy can be reduced.
In order to make the above objects, features and advantages of the present application more comprehensible, preferred embodiments accompanied with figures are described in detail below.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings that are needed in the embodiments will be briefly described below, it being understood that the following drawings only illustrate some embodiments of the present application and therefore should not be considered limiting the scope, and that other related drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.
Fig. 1 shows a schematic view of a propulsion system provided according to a first aspect of an embodiment of the present application.
Fig. 2 shows a schematic view of a partial structure of a propulsion system provided according to a first aspect of an embodiment of the present application.
Reference numerals:
1-a storage member; 12-a second cavity; 13-a first cavity; 21-an input path; 2-a refrigeration mechanism; 11-a second engine block; 22-a return path; 5-a circulation pump; 61-split front section; 62-split path; 6-an expansion valve; 63-splitting the rear part; 7-a heat exchange assembly; 71-a heat exchange member; 72-external path; 3-a power supply control system; 4-a heat dissipation member;
73-a first conveying path; 74-a second conveying path; an 8-valve assembly; 81-a first valve; 82-a second valve; 75-a third conveying path; 76-a fourth conveyance path; 9-a combustion mechanism; 91-a fifth conveying path; 92-drive path; 10-a first engine block; 111-sixth conveying path; 112-seventh conveying path.
Detailed Description
The following description of the embodiments of the present application will be made apparent and fully in view of the accompanying drawings, in which some, but not all embodiments of the invention are shown. All other embodiments, which can be made by one of ordinary skill in the art without undue burden from the present disclosure, are within the scope of the present disclosure.
In the description of the present application, it should be noted that the directions or positional relationships indicated by the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc. are based on the directions or positional relationships shown in the drawings, are merely for convenience of description of the present application 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 application. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.
In the description of the present application, it should be noted that, unless explicitly specified and limited otherwise, the terms "mounted," "connected," and "connected" are to be construed broadly, and may be either fixedly connected, detachably connected, or integrally connected, for example; can be mechanically or electrically connected; can be directly connected or indirectly connected through an intermediate medium, and can be communication between two elements. The specific meaning of the terms in this application will be understood by those of ordinary skill in the art in a specific context.
In addition, the technical solutions of the embodiments may be combined with each other, but it is necessary to base that the technical solutions can be realized by those skilled in the art, and when the technical solutions are contradictory or cannot be realized, the combination of the technical solutions should be regarded as not exist and not within the protection scope of the present application.
According to a first aspect of an embodiment of the present application, a propulsion system is provided, the structure and operation of which will be described in detail below in connection with fig. 1 and 2.
In an embodiment, a propulsion system according to the first aspect of the embodiments of the present application comprises a storage member 1, a refrigeration mechanism 2, a heat exchange assembly 7, and a combustion mechanism 9. Wherein the storage member 1 comprises a first cavity 13, the first cavity 13 being for storing a first propellant. The refrigeration mechanism 2 comprises an input and an output, both of which are in communication with the first cavity 13, the refrigeration mechanism 2 being adapted to cool a first propellant entering the refrigeration mechanism 2 from the input. The heat exchange assembly 7 includes a return path 22, a heat exchange path communicating with the return path 22, a heat exchange member 71 communicating with the heat exchange path, and an expansion valve 6 provided in the heat exchange path, the return path 22 communicating the first chamber 13 with the output end, so that the first propellant cooled by the refrigeration mechanism 2 returns to the first chamber 13, the heat exchange member 71 being used for cooling the return path 22. The heat exchanging member 71 communicates with the combustion mechanism 9, and the combustion mechanism 9 burns the first propellant conveyed by the heat exchanging member 71 to drive the cooling mechanism.
Thus, according to the propulsion system provided by the first aspect of the embodiment of the present application, the first propellant does not flow through the expansion valve in the case where the path between the heat exchanging member and the combustion mechanism is closed, and the first propellant in the first chamber 13 can be cooled by the refrigerating mechanism 2, and under such a condition, the first propellant in the first chamber 13 flows through the first chamber 13 and then flows back into the first chamber 13 via the return path 22. With the path between the heat exchange member and the combustion means being opened, the refrigeration means 2 still cools the first propellant flowing through the refrigeration means 2, on the basis of which the heat exchange member 71 shunts a part of the first propellant in the return path 22, which part of the first propellant passes through the expansion valve 6 and becomes a low-temperature, low-pressure fluid, which part of the low-temperature, low-pressure fluid is used for cooling the return path 22, so that the first propellant in the return path 22 is further cooled, and the first propellant in the heat exchange member 71 after cooling the return path 22 flows to the combustion means 9, burns in the combustion means 9, driving the refrigeration means 2 into operation.
Thus, according to the propulsion system provided by the first aspect of the embodiments of the present application, when the first propellant needs to be exhausted for cooling or needs to be cooled with high power, the refrigeration mechanism 2 is driven to operate by the chemical energy of the first propellant itself. On the one hand, the chemical energy of the first propellant is fully utilized, the propellant is prevented from being wasted, and on the other hand, when a large amount of electric energy is needed or the electric energy is insufficient, the refrigerating mechanism 2 can be directly driven to work through the combustion mechanism 9, so that the use requirement can be met or the use of the electric energy can be reduced.
In an embodiment, the combustion mechanism 9 may be a gas generator, and the refrigeration mechanism 2 may be a refrigerator, where the refrigerator may include a compressor, and the gas generator may burn a first propellant to drive the compressor of the refrigerator, so as to drive the refrigerator to operate. In an embodiment, the exhaust gas generated by the combustion of the gas generator may be subjected to a rail-controlled or gesture-controlled operation via the engine, which will be described later in the description.
In an embodiment, the first chamber 13 may be connected to an input of the refrigeration mechanism 2 via an input path 21, and in an embodiment the propulsion system may further comprise a circulation pump 5, which circulation pump 5 may be arranged in a return path 22, thereby powering the circulation of the first propellant between the first chamber 13 and the refrigeration mechanism 2.
According to the propulsion system provided by the embodiment of the present application, the return path 22 may include a cooling portion for being cooled by the heat exchange member 71, and the cooling portion may be disposed in the first chamber 13. In an embodiment, the cooling portion is arranged in the first cavity 13, which is advantageous for enabling the first propellant passing through the cooling portion to flow into the first cavity 13 directly after being cooled, thereby avoiding the loss of cold and reducing the space occupied by the propulsion system.
According to the propulsion system provided in the embodiment of the present application, the backflow path 22 may include a cooling portion for being cooled by the heat exchange member 71, the cooling portion may include a middle path and an outer path 72 that are communicated with each other, an accommodating space may be defined by the outer path 72, the heat exchange member 71 may be sleeved outside the middle path, and at least a portion of the heat exchange member 71 may be disposed in the accommodating space.
Thus, according to the propulsion system provided in the embodiment of the present application, the cooling portion is provided as the inner middle path and the outer path 72, and the heat exchange member 71 is provided between the middle path and the outer path 72, so that on the one hand, the arrangement of the heat exchange member 71 and the return path 22 is made more compact, and on the other hand, sufficient contact between the heat exchange member 71 and the cooling portion is facilitated, and the heat exchange efficiency is improved.
As shown in fig. 2, fig. 2 shows a schematic view of an enlarged view of the cooling portion and the heat exchange member 71, while showing schematic arrows of the flow direction of the first propellant in the cooling portion of the return path 22. Wherein the heat exchange member 71 may be sleeve-shaped as a whole, the middle path may be formed as a tube, the outer path 72 may be formed as a cylindrical structure having an annular cavity, and the heat exchange member 71 may be interposed between the middle path and the outer path 72.
In an embodiment, the heat exchange member 71 may be entirely interposed between the middle path and the outer path 72, and the diverting path 62 (i.e., diverting line) for delivering the low-temperature, low-pressure first propellant may be connected at an end of the heat exchange member 71. Alternatively, in fig. 2, a section of the heat exchange member 71 may be exposed outside the accommodation space of the external path 72, and the diverting path 62 for conveying the low-temperature, low-pressure first propellant may be connected to the side of the section of the heat exchange member 71.
In the embodiment, the return path 22 further includes the post-split portion 63 and the pre-split portion 61 provided on the upstream side of the cooling portion, the post-split portion 63 being closer to the cooling portion, the post-split portion 63 and the pre-split portion 61 being determined by the position at which the split path 62 communicates with the return path 22, that is, the post-split portion 63 at a portion downstream of the communication position of the split path 62 with the return path 22, the pre-split portion 61 at a portion upstream of the communication position of the split path 62 with the return path 22, and in the embodiment, the circulation pump 5 may be provided at the pre-split portion 61.
In an embodiment, the propulsion system may further comprise a power supply control system 3 and a heat dissipation member 4, wherein the power supply control system 3 may be electrically connected to the refrigeration mechanism 2, thereby controlling the power supply state of the refrigeration mechanism 2, and the heat dissipation member 4 may exchange heat with the refrigeration mechanism 2 to dissipate heat in the first propellant flowing through the refrigeration mechanism 2 into the space. As an example, the heat radiation member 4 may be a space heat radiation cold plate through which heat can be radiated into an external space. Furthermore, in an embodiment, the expansion valve 6 may be a J-T valve (Joule-Thomson throttling expansion valve).
In the embodiment, the heat exchanging member 71 may communicate with the combustion mechanism 9 via both the first conveying path 73 and the third conveying path 75, which will be specifically described in the subsequent description.
In an embodiment, according to the propulsion system provided in an embodiment of the present application, the storage member 1 may further comprise a second cavity 12, the second cavity 12 may be arranged adjacent to the first cavity 13, the second cavity 12 may be used for containing a second propellant, and the second cavity 12 may be in communication with the combustion mechanism 9. In an embodiment, a second propellant can be stored using the second chamber 12, preferably a higher boiling propellant can be stored within the second chamber 12. In an embodiment, the second propellant in the second chamber 12 may also be fed to the combustion mechanism 9 for combustion, thereby operating the refrigeration mechanism 2.
According to the propulsion system provided in the embodiment of the present application, the propulsion system may further include a first engine unit 10 and a second engine unit 11, the first engine unit 10 may be in communication with the combustion mechanism 9, the combustion mechanism 9 may be used to drive the first engine unit 10, and the first cavity 13 and the second cavity 12 may each be in communication with the second engine unit 11 for driving the second engine unit 11.
According to the propulsion system provided by the embodiment of the application, through the first engine unit 10 (for example, through the fifth conveying path 91) which is communicated with the combustion mechanism 9, the first engine can be driven by the combustion mechanism 9 to perform the orbit control or attitude control operation, so that the orbit control or attitude control operation can be performed while the first propellant is cooled under the working condition when the first propellant needs to be cooled by exhaust gas or needs to be cooled under high power. In addition, the second engine block 11 can be used to directly deliver the first propellant and the second propellant to the second engine block 11 to perform the rail control or attitude control operation, so that the rail control or attitude control operation can be performed under normal working conditions.
In an embodiment, the heat exchanging member 71 may communicate with the combustion mechanism 9 via the first conveying path 73, the first valve 81, and the third conveying path 75 in sequence, the second chamber 12 may communicate with the combustion mechanism 9 via the second conveying path 74 and the fourth conveying path 76, and the second valve 82 may be disposed between the second conveying path 74 and the fourth conveying path 76. In the embodiment, the first valve 81 and the second valve 82 may control the opening and closing of the paths in which the respective valves are located and the opening degree.
Furthermore, in the embodiment, the first valve 81 and the second valve 82 may be formed together as a substantial valve assembly 8.
In an embodiment, the first cavity 13 may communicate with the second engine block 11 via a seventh conveying path 112, and the second cavity 12 may communicate with the second engine block 11 via a sixth conveying path 111. The combustion mechanism 9 may be in driving connection with the refrigeration mechanism 2 via a driving path 92, thereby driving the compressor of the refrigeration mechanism 2.
Thus, based on the technical features described above, essentially, according to embodiments of the present application, a two-component system is provided that enables orbital or attitude control operation in propulsion through mixed combustion of two propellants.
According to a second aspect of embodiments of the present application there is provided a vehicle, which may be, for example, an aircraft, such as a launch vehicle, comprising a propulsion system as above.
According to a third aspect of embodiments of the present application, a method of using a propulsion system is provided, wherein in embodiments the propulsion system may be a propulsion system as described above, i.e. an actively cooled propulsion system. The propulsion system comprises: the storage member 1, the storage member 1 comprising a first cavity 13, the first cavity 13 for storing a first propellant. The refrigeration mechanism 2, the refrigeration mechanism 2 includes an input end and an output end, both of which are communicated with the first cavity 13, and the refrigeration mechanism 2 is used for cooling the first propellant entering the refrigeration mechanism 2 from the input end. The heat exchange assembly 7, the heat exchange assembly 7 includes a return path 22, a heat exchange path communicating with the return path 22, a heat exchange member 71 communicating with the heat exchange path, and an expansion valve 6 disposed in the heat exchange path, the return path 22 communicates the first cavity 13 with the output end, so that the first propellant cooled by the refrigeration mechanism 2 returns to the first cavity 13, and the heat exchange member 71 is used for cooling the return path 22. And a combustion mechanism 9, the heat exchanging member 71 being in communication with the combustion mechanism 9, the combustion mechanism 9 combusting the first propellant conveyed by the heat exchanging member 71 to drive the cooling mechanism. The first engine group 10, the first engine group 10 communicates with the combustion mechanism 9, and the combustion mechanism 9 is used to drive the first engine group 10.
The using method of the propulsion system comprises the following steps: the path between the heat exchanging element 71 and the combustion means 9 is controlled to be opened (i.e. the first valve 81 in the propulsion system is controlled to be opened), the first propellant flowing through the heat exchanging element 71 enters the combustion means 9, and the cooling means 2 and the first engine unit 10 are driven by the combustion means 9.
When the pressure in the storage member 1 is too high, the exhaust gas is required to be cooled further, or the required electric quantity is too high, the aircraft cannot provide enough electric energy, a part of the first propellant enters the expansion valve 6 and becomes low-temperature and low-pressure fluid (such as gas), then enters the heat exchange member 71 to cool the first propellant in the return path 22 further, the temperature of the first propellant in the heat exchange member 71 after heat exchange is raised, and then enters the combustion mechanism 9, and in the condition that the second cavity 12 containing the second propellant is arranged as follows, the second propellant can enter the combustion mechanism 9, the two propellants are mixed and combusted in the combustion mechanism 9 to drive the compressor in the refrigeration mechanism 2 to work, and the discharged fuel gas enters the first engine set 10 to supply power for rail control or attitude control of the whole aircraft.
In an embodiment, as described above, the propulsion system may further comprise a second cavity 12 and a second engine block 11, the second cavity 12 being arranged adjacent to the first cavity 13, the second cavity 12 may be adapted to contain a second propellant, the second cavity 12 may be in communication with the combustion mechanism 9, and both the first cavity 13 and the second cavity 12 are in communication with the second engine block 11. The method of use may further comprise: the path between the heat exchange member 71 and the combustion mechanism 9 is controlled (i.e. the first valve 81 in the propulsion system described above is closed such that the first propellant does not flow through the expansion valve 6) to be closed, the refrigeration mechanism 2 is controlled to be driven by electrical energy (i.e. the electrical energy of the aircraft), and the second engine block 11 is driven by the first propellant of the first chamber 13 and the second propellant of the second chamber 12. In this step, the propulsion system is in a normal condition, in which the orbit or attitude of the aircraft is controlled by the second engine block 11, and the combustion of the two propellants in the second engine block 11 provides the orbit or attitude power.
In an embodiment, the method of using the propulsion system may further comprise: the path between the heat exchange member 71 and the combustion mechanism 9 (i.e. closing the first valve 81 in the propulsion system described above, such that the first propellant does not flow through the expansion valve 6) is controlled to be closed, the path between the second chamber 12 and the combustion mechanism 9 (i.e. closing the second valve 82 in the propulsion system described above) is controlled to be disconnected, the path between both the first chamber 13 and the second chamber 12 and the second engine block 11 is controlled to be disconnected, and the refrigeration mechanism 2 is controlled to be driven by electric energy. Under such conditions, the refrigeration mechanism 2 operates without rail control or attitude control to cool the first propellant in the first chamber 13.
The foregoing description is only of the preferred embodiments of the present application, and is not intended to limit the scope of the present application, but rather, the present application is intended to cover any variations of the equivalent structures described herein or shown in the drawings, or the direct/indirect application of the present application to other related technical fields.
Claims (10)
1. A propulsion system, the propulsion system comprising:
a storage member comprising a first cavity for storing a first propellant;
the refrigerating mechanism comprises an input end and an output end, the input end and the output end are communicated with the first cavity, and the refrigerating mechanism is used for cooling a first propellant entering the refrigerating mechanism from the input end;
the heat exchange assembly comprises a backflow path, a heat exchange path communicated with the backflow path, a heat exchange member communicated with the heat exchange path and an expansion valve arranged on the heat exchange path, wherein the backflow path is communicated with the first cavity and the output end, so that the first propellant cooled by the refrigeration mechanism flows back to the first cavity, and the heat exchange member is used for cooling the backflow path;
and the heat exchange component is communicated with the combustion mechanism, and the combustion mechanism burns the first propellant conveyed by the heat exchange component so as to drive the refrigeration mechanism.
2. A propulsion system as in claim 1 wherein the return path includes a cooling portion for cooling by the heat exchange member, the cooling portion disposed within the first cavity.
3. A propulsion system as in claim 1 wherein,
the backflow path comprises a cooling part used for being cooled by the heat exchange component, the cooling part comprises a middle path and an outer path which are communicated with each other, an accommodating space is defined by the outer path, the heat exchange component is sleeved on the outer side of the middle path, and at least part of the heat exchange component is arranged in the accommodating space.
4. A propulsion system as in claim 3 wherein the heat exchange member is located within the first cavity.
5. The propulsion system of claim 1, wherein the storage member further comprises a second cavity disposed adjacent to the first cavity, the second cavity for containing a second propellant, the second cavity in communication with the combustion mechanism.
6. A propulsion system as in claim 5 further comprising a first engine block in communication with the combustion mechanism for driving the first engine block and a second engine block in communication with the second engine block for driving the second engine block.
7. The propulsion system of claim 1, further comprising a heat dissipating member in heat exchange relationship with the refrigeration mechanism to dissipate heat from the first propellant flowing through the refrigeration mechanism into the space.
8. A method of using a propulsion system, characterized in that,
the propulsion system includes:
a storage member comprising a first cavity for storing a first propellant;
the refrigerating mechanism comprises an input end and an output end, the input end and the output end are communicated with the first cavity, and the refrigerating mechanism is used for cooling a first propellant entering the refrigerating mechanism from the input end;
the heat exchange assembly comprises a backflow path, a heat exchange path communicated with the backflow path, a heat exchange member communicated with the heat exchange path and an expansion valve arranged on the heat exchange path, wherein the backflow path is communicated with the first cavity and the output end, so that the first propellant cooled by the refrigeration mechanism flows back to the first cavity, and the heat exchange member is used for cooling the backflow path;
a combustion mechanism in communication with the heat exchange member, the combustion mechanism combusting a first propellant delivered by the heat exchange member to drive the refrigeration mechanism;
a first engine block in communication with the combustion mechanism for driving the first engine block;
the using method comprises the following steps:
and controlling a path between the heat exchange member and the combustion mechanism to be opened, wherein the first propellant flowing through the heat exchange member enters the combustion mechanism, and the combustion mechanism drives the refrigeration mechanism and the first engine unit.
9. The method of use of claim 8, wherein the propulsion system further comprises a second cavity disposed adjacent to the first cavity, the second cavity for containing a second propellant, the second cavity in communication with the combustion mechanism, the first cavity and the second cavity both in communication with the second engine block;
the using method further comprises the following steps:
and controlling a path between the heat exchange member and the combustion mechanism to be closed, controlling the refrigeration mechanism to be driven by electric energy, and driving the second engine unit by the first propellant of the first cavity and the second propellant of the second cavity.
10. The method of use of claim 9, further comprising: and controlling the path between the heat exchange component and the combustion mechanism to be closed, controlling the path between the second cavity and the combustion mechanism to be disconnected, controlling the paths between the first cavity and the second engine unit to be disconnected, and controlling the refrigeration mechanism to be driven by electric energy.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310815415.3A CN116557171B (en) | 2023-07-05 | 2023-07-05 | Propulsion system and method of using a propulsion system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310815415.3A CN116557171B (en) | 2023-07-05 | 2023-07-05 | Propulsion system and method of using a propulsion system |
Publications (2)
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Citations (6)
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| JP2015077825A (en) * | 2013-10-15 | 2015-04-23 | 株式会社Ｉｈｉエアロスペース | Cryogenic propellant storage |
| CN105674038A (en) * | 2016-02-25 | 2016-06-15 | 上海宇航系统工程研究所 | Device used for storing low-temperature liquid in orbit for long time and cooling method of device |
| CN106595759A (en) * | 2016-12-07 | 2017-04-26 | 上海宇航系统工程研究所 | Ground testing system for low temperature propellant storage technology |
| CN106762226A (en) * | 2016-12-01 | 2017-05-31 | 中国运载火箭技术研究院 | Suitable for the evaporation capacity Active Control Method of the long-term in-orbit storage of cryogenic propellant |
| CN109733644A (en) * | 2018-12-24 | 2019-05-10 | 西安交通大学 | A kind of cryogenic propellant is space-orbit to squeeze isolated thermodynamics exhaust system |
| CN211819716U (en) * | 2020-03-26 | 2020-10-30 | 北京宇航推进科技有限公司 | Nitrous oxide power system |
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Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2015077825A (en) * | 2013-10-15 | 2015-04-23 | 株式会社Ｉｈｉエアロスペース | Cryogenic propellant storage |
| CN105674038A (en) * | 2016-02-25 | 2016-06-15 | 上海宇航系统工程研究所 | Device used for storing low-temperature liquid in orbit for long time and cooling method of device |
| CN106762226A (en) * | 2016-12-01 | 2017-05-31 | 中国运载火箭技术研究院 | Suitable for the evaporation capacity Active Control Method of the long-term in-orbit storage of cryogenic propellant |
| CN106595759A (en) * | 2016-12-07 | 2017-04-26 | 上海宇航系统工程研究所 | Ground testing system for low temperature propellant storage technology |
| CN109733644A (en) * | 2018-12-24 | 2019-05-10 | 西安交通大学 | A kind of cryogenic propellant is space-orbit to squeeze isolated thermodynamics exhaust system |
| CN211819716U (en) * | 2020-03-26 | 2020-10-30 | 北京宇航推进科技有限公司 | Nitrous oxide power system |
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| CN116557171B (en) | 2023-10-27 |
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