Lunar surface power supply

Abstract

The embodiment of the present application relates to the technical field of nuclear reaction control, and particularly relates to a lunar surface reactor power supply, which comprises a first fuel system, a second fuel system and a spacer, the first fuel system and the second fuel system are arranged to be separated by the spacer when being launched; when landing on the lunar surface, the first fuel system and the second fuel system are integrated to be capable of outputting rated power, and the fuels in the first fuel system and the second fuel system are arranged to be unable to be in a critical state alone. Compared with a general space reactor, the lunar surface reactor power supply of the embodiment of the present application can ensure critical safety in a falling accident, and does not need to arrange a safety rod and a spectral shift absorption material in the reactor, so that it is not needed to verify that the safety rod can ensure to be completely left in the reactor in the falling accident, the development and verification difficulty of the reactor is significantly reduced, and the fuel loading of the reactor core and the weight and volume of the reactor are reduced.

Description

Technical Field

[0001] Embodiments of this application relate to the field of control technology for nuclear reactions, and more particularly to a lunar reactor power source. Background Technology

[0002] The statements herein are provided only as background information in connection with this application and do not necessarily constitute prior art.

[0003] Space nuclear reactors, especially fast neutron reactors, can experience a significant increase in the neutron absorption cross-section of the fuel and a substantial decrease in the neutron leakage rate if they fall into water or wet sand after a launch failure. This could lead to a dramatic increase in the reactor's effective neutron multiplication coefficient, potentially causing it to reach a critical or supercritical state, which could pose a threat to the environment and the public. Therefore, the design and construction of space nuclear reactors must ensure that they do not enter a critical state in the event of a fall accident.

[0004] As a type of space nuclear reactor, the lunar reactor also needs to ensure that it meets critical safety requirements in the event of a fall accident. Summary of the Invention

[0005] A brief overview of this application is provided below to offer a basic understanding of certain aspects thereof. It should be understood that this overview is not an exhaustive summary of the application. It is not intended to identify key or essential parts of the application, nor is it intended to limit its scope. Its purpose is merely to present certain concepts in a simplified form as a prelude to the more detailed description that follows.

[0006] Embodiments of this application provide a lunar reactor power supply, which includes a first fuel system, a second fuel system, and a spacer. During launch, the first fuel system and the second fuel system are separated by the spacer. When landing on the lunar surface, the first fuel system and the second fuel system are integrated into one unit and can output rated power. The fuels in the first fuel system and the second fuel system are configured such that they cannot be in a critical state on their own.

[0007] The embodiments of this application separate two fuel systems, each unable to reach a critical state independently, by a spacer during launch. This ensures that neither fuel system reaches a critical state in the event of an accident, guaranteeing the critical safety of the lunar reactor power supply. After a successful launch and landing on the lunar surface, the two fuel systems can integrate and output rated power, enabling the lunar reactor power supply to operate normally. Compared to conventional space reactors, the lunar reactor power supply of this application can guarantee critical safety under re-entry accidents without requiring safety rods or spectral shift absorbing materials within the reactor. Therefore, it eliminates the need to verify that safety rods remain intact within the reactor under re-entry accidents, significantly reducing the difficulty of reactor development and verification. Furthermore, it reduces the fuel load in the reactor core, as well as the reactor's weight and volume. Attached Figure Description

[0008] To further illustrate the above and other advantages and features of this application, the specific embodiments of this application will be described in more detail below with reference to the accompanying drawings. The drawings, together with the following detailed description, are included in and form a part of this specification. Elements having the same function and structure are indicated by the same reference numerals. It should be understood that these drawings only depict typical examples of this application and should not be considered as limiting the scope of this application.

[0009] Figure 1 This is a schematic diagram of the lunar reactor power supply of an embodiment of this application not assembled at launch; Figure 2 This is a schematic diagram of the lunar surface power supply assembly completed after landing on the lunar surface, according to an embodiment of this application. Figure 3 This is a cross-sectional schematic diagram of a first fuel system according to an embodiment of this application; Figure 4 This is a cross-sectional schematic diagram of a second fuel system according to an embodiment of this application; Figure 5 This is a cross-sectional schematic diagram of the first fuel being inserted into the second fuel system after the lunar reactor power supply assembly is completed, according to an embodiment of this application. Figure 6 This is a schematic diagram of the structure of a first thermally conductive power generation component and a first radiative heat dissipation fin, or a second thermally conductive power generation component and a second radiative heat dissipation fin, according to an embodiment of this application.

[0010] Explanation of reference numerals in the attached figures: 100. Lunar stack power supply; 10. First fuel system; 11. First fuel; 12. First thermally conductive power generation component; 121. First heat pipe; 122. First heat collector; 123. First power generation component; 13. First shield; 14. First radiative heat dissipation fins; 15. First axial reflective layer; 20. Second fuel system; 21. Second fuel; 211. Central channel; 22. Second thermally conductive power generation assembly; 221. Second heat pipe; 222. Second heat collector; 223. Second power generation component; 23. Second shield; 24. Second radiative heat dissipation fins; 25. Second axial reflective layer; 26. Radial reflective layer; 27. Control drum assembly; 271. Control drum; 272. Control drum drive component; 30. Spacers. Detailed Implementation

[0011] Exemplary embodiments of this application will be described below with reference to the accompanying drawings. For clarity and brevity, not all features of actual implementations are described in the specification. However, it should be understood that many implementation-specific decisions must be made in the development of any such actual embodiment to achieve the developer's specific goals, such as complying with constraints related to the system and business, and these constraints may vary depending on the implementation. Furthermore, it should be understood that while development work can be very complex and time-consuming, such development work is merely a routine task for those skilled in the art who benefit from the content of this application.

[0012] It should also be noted that, in order to avoid obscuring this application with unnecessary details, only the equipment structure and / or processing steps closely related to the solution according to this application are shown in the accompanying drawings, while other details that are not closely related to this application are omitted.

[0013] The following disclosure provides several different implementations or examples for carrying out this application. To simplify the disclosure of this application, specific examples of components and methods are described below. Of course, these are merely examples and are not intended to limit this application. In the description of the embodiments of this application, "multiple" means at least two, such as two, three, etc., unless otherwise explicitly specified.

[0014] In existing technologies, to ensure the critical safety of space reactors in the event of an accident, the design typically employs methods such as installing safety rods or spectral shift absorbing materials within the reactor core. However, installing safety rods requires ensuring their intact retention within the reactor core during an accident, which increases the difficulty of reactor development and verification. Furthermore, both installing safety rods and spectral shift absorbing materials increase the fuel load in the reactor core, as well as the overall weight and volume of the reactor.

[0015] To address the aforementioned issues, embodiments of this application provide a lunar stack power source. Figure 1 This is a schematic diagram of the lunar surface reactor power supply, according to an embodiment of this application, before launch. Figure 2This is a schematic diagram showing the lunar surface power supply according to an embodiment of this application assembled after landing on the lunar surface. Figure 1 and Figure 2 As shown, the lunar reactor power supply 100 includes a first fuel system 10, a second fuel system 20, and a spacer 30. During launch, the first fuel system 10 and the second fuel system 20 are separated by the spacer 30. When landing on the lunar surface, the first fuel system 10 and the second fuel system 20 are integrated into one unit and can output rated power. The fuels in the first fuel system 10 and the second fuel system 20 are configured such that they cannot be in a critical state on their own.

[0016] The embodiments of this application separate two fuel systems, which cannot be in a critical state independently, by a spacer 30 during launch. This ensures that neither fuel system reaches a critical state in the event of an accident, guaranteeing the critical safety of the lunar reactor power supply 100. After a successful launch and landing on the lunar surface, the two fuel systems can integrate and output rated power, enabling the lunar reactor power supply 100 to operate normally. Compared to conventional space reactors, the lunar reactor power supply 100 of this application can ensure critical safety under fall accidents without the need for safety rods and spectral shift absorbing materials within the reactor. Therefore, it eliminates the need to verify that the safety rods remain intact within the reactor under fall accidents, significantly reducing the difficulty of reactor development and verification. Furthermore, it reduces the fuel load in the reactor core, as well as the weight and volume of the reactor.

[0017] Figure 3 This is a cross-sectional schematic diagram of a first fuel system according to an embodiment of this application. Figure 3 As shown, in some embodiments, the first fuel system 10 includes: a first fuel 11, a first thermally conductive power generation component 12, a first shield 13, a first radiative heat dissipation fin 14, and a first axial reflective layer 15. The first axial reflective layer 15 is disposed on the first fuel 11, the first shield 13 is disposed on the first axial reflective layer 15, the first thermally conductive power generation component 12 is configured to conduct heat from the first fuel 11 and generate electricity, the first radiative heat dissipation fin 14 is disposed on the first thermally conductive power generation component 12 and is configured to conduct waste heat from the first thermally conductive power generation component 12; and is configured such that when the first fuel system 10 and the second fuel system 20 are integrated, the first fuel 11 is inserted into the second fuel system 20.

[0018] In this embodiment, the first axial reflective layer 15 can reflect leaked neutrons back to the area where the first fuel 11 is located, thereby improving the neutron utilization rate of the first fuel system 10. The first thermally conductive power generation component 12 conducts heat generated by the first fuel 11 to generate electricity, the first radiative heat dissipation fins 14 conduct waste heat from the first thermally conductive power generation component 12, and the first shield 13 absorbs and blocks radiation from the first fuel 11 to prevent radiation from damaging the first thermally conductive power generation component 12, etc. Thus, the first fuel system 10 can generate electricity as an independent fuel system. Furthermore, the first fuel system 10 is inserted into the second fuel system 20, so that when the first fuel system 10 and the second fuel system 20 are integrated, they occupy less space and are tightly connected.

[0019] Figure 4 This is a cross-sectional schematic diagram of the second fuel system according to an embodiment of this application. Figure 5 This is a cross-sectional schematic diagram showing the insertion of the first fuel into the second fuel system after the lunar reactor power supply assembly is completed, according to an embodiment of this application. Figure 4 and Figure 5 As shown, in some embodiments, the second fuel system 20 includes a second fuel 21, a second thermally conductive power generation component 22, a second shield 23, a second radiative heat dissipation fin 24, a second axial reflective layer 25, a radial reflective layer 26, and a control drum assembly 27. The second axial reflective layer 25 is disposed on the second fuel 21, the radial reflective layer 26 is disposed on the outside of the second fuel 21, the second shield 23 is disposed on the radial reflective layer 26, the second radiative heat dissipation fin 24 is disposed on the second thermally conductive power generation component 22 and is configured to discharge the waste heat of the second thermally conductive power generation component 22; and the second fuel 21 forms a central channel 211 and is configured such that when the first fuel system 10 and the second fuel system 20 are integrated, the first fuel 11 of the first fuel system 10 is inserted into the central channel 211.

[0020] In this embodiment, the second axial reflective layer 25 and the radial reflective layer 26 can reflect leaked neutrons back to the area where the second fuel 21 is located, thereby improving the neutron utilization rate of the second fuel system 20. The second thermally conductive power generation component 22 conducts heat generated by the second fuel 21 to generate electricity, the second radiative heat dissipation fins 24 conduct waste heat from the second thermally conductive power generation component 22, and the second shield 23 absorbs and blocks radiation from the second fuel 21 to prevent radiation from damaging the second thermally conductive power generation component 22, etc. Thus, the second fuel system 20 can generate electricity as an independent fuel system. Furthermore, the first fuel 11 is inserted into the central channel 211 of the second fuel 21, enabling the lunar reactor power supply 100 to integrate the thermal power of the first fuel 11 and the second fuel 21, thereby outputting rated power.

[0021] In some embodiments, the first fuel 11 and the second fuel 21 may be blocky uranium-molybdenum alloys.

[0022] In some embodiments, the control drum assembly 27 includes a control drum 271 and a control drum drive 272. The control drum drive 272 is configured to drive the control drum 271 to rotate, and is configured to drive the control drum 271 to rotate when the first fuel system 10 and the second fuel system 20 are integrated, so that the first fuel system 10 and the second fuel system 20 output rated power.

[0023] In such an embodiment, the control drum drive 272 drives the control drum 271 to rotate, which can adjust the ratio of neutron absorption and reflection in the first fuel system 10 and the second fuel system 20, thereby precisely controlling the reactivity of the first fuel system 10 and the second fuel system 20, so that the first fuel system 10 and the second fuel system 20 output rated power.

[0024] Figure 6 This is a schematic diagram of the structure of a first thermally conductive power generation component and a first radiative heat dissipation fin, or a second thermally conductive power generation component and a second radiative heat dissipation fin, according to embodiments of this application. Figure 6 As shown, in some embodiments, the first thermally conductive power generation component 12 includes: a plurality of first heat pipes 121, a plurality of first heat collectors 122, and a plurality of first power generators 123. The plurality of first heat pipes 121 are disposed on the first fuel 11 and are configured to extend through the first shield 13 in a direction away from the first fuel 11 to conduct heat out of the first fuel 11; the plurality of first heat collectors 122 are disposed on the first heat pipes 121, and the plurality of first power generators 123 are respectively disposed on the plurality of first heat collectors 122; the first radiative heat dissipation fins 14 are disposed on the first power generators 123 to conduct waste heat out of the first power generators 123.

[0025] In this embodiment, multiple first heat pipes 121 conduct heat from the first fuel 11, utilizing the phase change heat transfer of the working fluid. This achieves passive cooling of the first fuel 11 without relying on external energy to drive the coolant, thus avoiding the risk of accidents caused by external energy failure. Furthermore, because multiple first heat pipes 121 are provided, even if one or more heat pipes fail, the others can still conduct heat, resulting in high reliability and safety.

[0026] In some embodiments, the first heat pipe 121 is configured to bend through the first shield 13. In such embodiments, the bending of the first heat pipe 121 through the first shield 13 can prevent radiation from the reactor core from passing directly through the first shield 13 via the channel, which helps to ensure the integrity of the shield.

[0027] In some embodiments, the first shield 13 is disposed below the lunar surface, and the first heat pipe 121 passes through and extends above the lunar surface.

[0028] See also Figure 6 In some embodiments, the second thermally conductive power generation assembly 22 includes: a plurality of second heat pipes 221, a plurality of second heat collectors 222, and a plurality of second power generation devices 223; the plurality of second heat pipes 221 are disposed on the second fuel 21 and extend through the second shield 23 in a direction away from the second fuel 21 to conduct heat out of the second fuel 21; the plurality of second heat collectors 222 are disposed on the second heat pipes 221, and the plurality of second power generation devices 223 are respectively disposed on the plurality of second heat collectors 222; the second radiative heat dissipation fins 24 are disposed on the second power generation devices 223 to conduct waste heat out of the second power generation devices 223.

[0029] In this embodiment, multiple second heat pipes 221 conduct heat from the second fuel 21, utilizing the phase change heat transfer of the working fluid. This achieves passive cooling of the second fuel 21 without relying on external energy to drive the coolant, thus avoiding the risk of accidents caused by external energy failure. Furthermore, because multiple second heat pipes 221 are provided, even if one or more heat pipes fail, the others can still conduct heat, resulting in high reliability and safety.

[0030] In some embodiments, the second heat pipe 221 is configured to bend through the second shield 23. In such embodiments, the second heat pipe 221 completely passes through the second shield 23, which can prevent radiation from the reactor core from passing directly through the second shield 23 through the channel, thus helping to ensure the integrity of the shield.

[0031] In some embodiments, the second shield 23 is disposed below the lunar surface, and the second heat pipe 221 passes through and extends above the lunar surface.

[0032] The lunar stack power supply 100 of this application embodiment has no moving parts other than the control drum assembly 27. Therefore, the lunar stack power supply 100 can be in a completely static state during operation, thereby improving the reliability and safety of the lunar stack power supply 100 and reducing the difficulty and cost of operation and maintenance.

[0033] In some embodiments, the structural materials of the first heat pipe 121 and the second heat pipe 221 may be HAINS 230 alloy.

[0034] In some embodiments, the working fluid in the first heat pipe 121 and the second heat pipe 221 is liquid sodium metal.

[0035] In some embodiments, the first heat collector 122 and the second heat collector 222 may be made of dispersion-strengthened copper oxide.

[0036] In some embodiments, the first power generation element 123 and the second power generation element 223 may be made of SKD (skorthite).

[0037] In some embodiments, the first radiative heat dissipation fin 14 and the second radiative heat dissipation fin 24 may be made of carbon-carbon materials.

[0038] In some embodiments, when the first fuel system 10 and the second fuel system 20 are integrated, the first thermally conductive power generation component 12, the second thermally conductive power generation component 22, the first radiative heat dissipation fin 14 and the second radiative heat dissipation fin 24 are configured such that there is a predetermined distance between the first radiative heat dissipation fin 14 and the second radiative heat dissipation fin 24 in the extending direction of the first heat pipe 121.

[0039] In such an embodiment, when the first fuel system 10 and the second fuel system 20 are integrated, since there is a predetermined distance between the first radiative heat dissipation fin 14 of the first fuel system 10 and the second radiative heat dissipation fin 24 of the second fuel system 20 in the extension direction of the first heat pipe 121, the first radiative heat dissipation fin 14 and the second radiative heat dissipation fin 24 can dissipate the waste heat of the first fuel system 10 and the second fuel system 20 to the external space without interfering with each other when dissipating heat.

[0040] In some embodiments, when the first fuel system 10 and the second fuel system 20 are integrated, the first heat pipe 121 is configured to extend a distance away from the first fuel 11 beyond the distance that the second heat pipe 221 extends away from the first fuel 11; and the first radiative heat dissipation fins 14 are disposed on the portion of the first heat pipe 121 that extends beyond the second heat pipe 221.

[0041] In such an embodiment, the first heat pipe 121 extends beyond the second heat pipe 221 in the direction away from the first fuel 11, and the first radiative heat dissipation fin 14 is disposed on the portion of the first heat pipe 121 that extends beyond the second heat pipe 221. Therefore, both the first radiative heat dissipation fin 14 and the second radiative heat dissipation fin 24 can directly face the external space, avoiding interference between them when dissipating heat.

[0042] In some embodiments, when the first fuel system 10 and the second fuel system 20 are integrated, the first shield 13 and the second shield 23 are configured to cooperate so that rays from the first fuel 11 and the second fuel 21 cannot irradiate the first power generator 123 and the second power generator 223.

[0043] In such an embodiment, the first shield 13 and the second shield 23 can cooperate to prevent rays from the reactor core from passing through the gap between the first shield 13 and the second shield 23, thereby preventing them from irradiating the first generator 123 and the second generator 223 and causing them damage.

[0044] In some embodiments, the lunar reactor power supply 100 employs thermoelectric power generation, which can achieve power output in the range of kilowatts to several kilowatts.

[0045] In other embodiments, the lunar stack power supply 100 uses Stirling generators, which can achieve power output in the range of tens of kilowatts to hundreds of kilowatts.

[0046] Regarding the embodiments of this application, it should also be noted that, without conflict, the embodiments of this application and the features in the embodiments can be combined with each other to obtain new embodiments.

[0047] The above are merely specific embodiments of this application, but the scope of protection of this application is not limited thereto. The scope of protection of this application shall be determined by the scope of the claims.

Claims

1. A lunar surface stack power source, characterized in that, It includes: First fuel system, second fuel system, and spacers During launch, the first fuel system and the second fuel system are configured to be separated by the spacer; Upon landing on the lunar surface, the first fuel system and the second fuel system are integrated into one unit, capable of outputting rated power, and The fuels in the first fuel system and the second fuel system are configured such that they cannot be in a critical state on their own.

2. The lunar stack power source according to claim 1, characterized in that, The first fuel system includes: a first fuel, a first thermally conductive power generation component, a first shield, a first radiative heat dissipation fin, and a first axial reflective layer. The first axial reflective layer is disposed on the first fuel. The first shield is disposed on the first axial reflective layer. The first thermally conductive power generation component is configured to export the heat of the first fuel and generate electricity, and the first radiative heat dissipation fins are disposed on the first thermally conductive power generation component and configured to export the waste heat of the first thermally conductive power generation component. It is configured such that when the first fuel system and the second fuel system are integrated, the first fuel is inserted into the second fuel system.

3. The lunar stack power source according to claim 2, characterized in that, The second fuel system includes a second fuel, a second thermally conductive power generation assembly, a second shield, second radiative heat dissipation fins, a second axial reflective layer, a radial reflective layer, and a control drum assembly. The second axial reflective layer is disposed on the second fuel. The radial reflective layer is disposed on the outside of the second fuel. The second shield is disposed on the radial reflective layer. The second radiative heat dissipation fins are disposed on the second thermally conductive power generation component and configured to dissipate the waste heat of the second thermally conductive power generation component; The second fuel forms a central channel, and is configured such that when the first fuel system and the second fuel system are integrated, the first fuel of the first fuel system is inserted into the central channel.

4. The lunar stack power source according to claim 3, characterized in that, The control drum assembly includes a control drum and a control drum drive. The control drum driver is configured to drive the control drum to rotate. It is configured such that when the first fuel system and the second fuel system are integrated, the control drum drive drives the control drum to rotate, so that the first fuel system and the second fuel system output rated power.

5. The lunar stack power source according to claim 4, characterized in that, The first thermally conductive power generation component includes: Multiple first heat pipes, multiple first heat collectors, and multiple first heating elements. The plurality of first heat pipes are disposed on the first fuel and are configured to extend through the first shield in a direction away from the first fuel, so as to conduct heat out of the first fuel; The plurality of first heat collectors are disposed on the first heat pipe, and the plurality of first power generators are respectively disposed on the plurality of first heat collectors; The first radiative heat dissipation fins are disposed on the first power generation device to dissipate the waste heat of the first power generation device.

6. The lunar stack power source according to claim 5, characterized in that, The first heat pipe is configured to bend through the first shield.

7. The lunar stack power source according to claim 3, characterized in that, The second thermally conductive power generation component includes: Multiple second heat pipes, multiple second heat collectors, and multiple second power generators; The plurality of second heat pipes are disposed on the second fuel and extend through the second shield in a direction away from the second fuel to conduct heat out of the second fuel; The plurality of second heat collectors are disposed on the second heat pipe, and the plurality of second power generators are respectively disposed on the plurality of second heat collectors; The second radiative heat dissipation fins are disposed on the second power generation device to dissipate the waste heat of the second power generation device.

8. The lunar stack power source according to claim 7, characterized in that, The second heat pipe is configured to bend through the second shield.

9. The lunar stack power source according to claim 5 or 8, characterized in that, When the first fuel system and the second fuel system are integrated, the first thermally conductive power generation component, the second thermally conductive power generation component, the first radiative heat dissipation fin, and the second radiative heat dissipation fin are configured such that there is a predetermined distance between the first radiative heat dissipation fin and the second radiative heat dissipation fin in the extension direction of the first heat pipe.

10. The lunar stack power source according to claim 9, characterized in that, When the first fuel system and the second fuel system are integrated, the first heat pipe is configured to extend a distance away from the first fuel beyond the distance the second heat pipe extends away from the first fuel. Furthermore, the first radiative heat dissipation fins are disposed on the portion of the first heat pipe that extends beyond the second heat pipe.

11. The lunar stack power source according to any one of claims 1-8 and 10, characterized in that, When the first fuel system and the second fuel system are integrated, the first shield and the second shield are configured to cooperate so that rays from the first fuel and the second fuel cannot irradiate the first power generation device and the second power generation device.

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