Nuclear power platform heat source on-orbit simulation device

Abstract

The invention discloses a nuclear power platform heat source on-orbit simulation device which comprises a light condensation device, a heat energy absorption mechanism and a heat energy conversion mechanism, the light condensation device focuses solar energy, the light receiving side of the heat energy absorption mechanism is of a wedge-shaped structure, and the light receiving side of the heat energy conversion mechanism is of a wedge-shaped structure. The heat energy conversion mechanism comprises a heat transfer part, a heat source adapter and a thermoelectric converter, the first end of the heat transfer part is in heat transfer connection with the backlight side of the heat energy absorption mechanism, the second end of the heat transfer part is in heat transfer connection with the heat source adapter, and the thermoelectric converter is in heat transfer connection with the heat source adapter. The nuclear power platform heat source on-orbit simulation device provided by the invention has the advantage of high photothermal conversion efficiency.

Description

Technical Field

[0001] The present invention relates to the field of aerospace application technology, and in particular to an on-orbit simulation device for a heat source of a nuclear power platform. Background Art

[0002] With the continuous development and progress of spacecraft technology, the power consumption of the entire spacecraft during the on-orbit service process is increasing. With the development of deep space exploration, space bases and other projects, the traditional power supply method of using a combination of solar arrays and batteries can no longer meet the energy needs of spacecraft during the on-orbit process. The main reasons include two points. First, as the on-orbit energy demand of spacecraft gradually increases, the on-orbit energy demand of some spacecraft is as high as hundreds of kilowatts to megawatts, or even larger. If traditional solar arrays are used to provide spacecraft energy, the size of the sails will be very large, which poses higher challenges to on-orbit deployment technology and launch technology, or even makes it impossible to achieve. In addition, deep space exploration spacecraft cannot use solar arrays to provide the required energy for spacecraft due to insufficient available solar energy. Based on the above two main reasons, there is an urgent need to develop space nuclear power technology.

[0003] With the continuous development of my country's nuclear power technology, the power generation technology using nuclear energy has become relatively mature. However, when actually migrating ground nuclear power technology to space nuclear power technology, the main technical difficulty is no longer how to stably use nuclear energy technology, but rather the supporting technical difficulties such as space high-temperature heat transfer technology, ultra-high power heat dissipation technology, long-distance deployment truss technology, and high-efficiency thermoelectric conversion technology. In addition, due to safety requirements, funding restrictions and other conditions, before actually using nuclear fuel to participate in space missions, it is necessary to use a non-nuclear fuel nuclear power platform to conduct on-orbit key technology verification.

[0004] At the current stage, the low photothermal conversion efficiency of related technologies cannot meet the on-orbit verification requirements of nuclear power platforms. Summary of the invention

[0005] The present invention aims to solve at least one of the technical problems in the related art to a certain extent. To this end, an embodiment of the present invention provides an on-orbit simulation device for a heat source of a nuclear power platform, which has the advantage of high light-to-heat conversion efficiency.

[0006] According to an embodiment of the present invention, the on-orbit simulation device for a nuclear-powered platform heat source includes a focusing device, a heat energy absorption mechanism and a heat energy conversion mechanism. The focusing device focuses solar energy, the light-receiving side of the heat energy absorption mechanism is a wedge-shaped structure, the heat energy conversion mechanism includes a heat transfer element, a heat source adapter and a thermoelectric converter, the first end of the heat transfer element is heat-transferably connected to the backlight side of the heat energy absorption mechanism, the second end of the heat transfer element is heat-transferably connected to the heat source adapter, and the thermoelectric converter is heat-transferably connected to the heat source adapter.

[0007] The on-orbit simulation device for a nuclear power platform heat source according to an embodiment of the present invention has the advantage of high light-to-heat conversion efficiency. The present application has the following advantages:

[0008] 1. No need to consume the energy of the entire satellite, directly use solar energy to heat the on-orbit simulation device;

[0009] 2. Removed active heating components to improve equipment reliability;

[0010] 3. The maximum temperature of the simulated heat source has been increased to meet the on-orbit test temperature level of different thermoelectric conversion devices.

[0011] In some embodiments, the condenser is a concave mirror, and the condenser is arranged opposite to the wedge-shaped structure.

[0012] In some embodiments, a multi-layer heat insulation layer is provided on the backlight surface of the condenser.

[0013] In some embodiments, the light-facing surface of the condenser is a high-reflectivity mirror surface, and the light-facing surface is opposite to the wedge-shaped structure.

[0014] In some embodiments, the wedge-shaped structure includes a plurality of wedge-shaped blocks, and the distance between the wedge-shaped blocks and adjacent wedge-shaped blocks increases as the distance from the focusing device decreases.

[0015] In some embodiments, the heat transfer element includes a high temperature heat transfer tube, the high temperature heat transfer tube corresponds to the wedge block one by one, and at least part of the high temperature heat transfer tube is located inside the wedge block.

[0016] In some embodiments, surfaces of the wedge blocks of the wedge-shaped structure opposite to adjacent wedge blocks are subjected to blackening treatment.

[0017] In some embodiments, the wedge-shaped structure is made of porous metal material.

[0018] In some embodiments, high temperature insulation material is disposed around the outer surface of the wedge-shaped structure.

[0019] In some embodiments, the thermal energy conversion mechanism further includes an energy load, and the energy load is electrically connected to the thermoelectric converter. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] Figure 1 It is a schematic diagram of the structure of an on-orbit simulation device for a heat source of a nuclear power platform according to an embodiment of the present invention.

[0021] Figure 2 It is a schematic diagram of the structure of the heat energy absorption mechanism of the on-orbit simulation device of the heat source of the nuclear power platform according to an embodiment of the present invention.

[0022] Figure numerals: 1. condenser; 2. heat energy absorption mechanism; 21. high temperature insulation material; 22. wedge block; 3. heat transfer tube; 4. heat source adapter; 5. thermoelectric converter; 6. energy load. DETAILED DESCRIPTION

[0023] Embodiments of the present invention are described in detail below, and examples of the embodiments are shown in the accompanying drawings. The embodiments described below with reference to the accompanying drawings are exemplary and intended to be used to explain the present invention, but should not be understood as limiting the present invention.

[0024] According to an on-orbit simulation device for a nuclear power platform heat source according to an embodiment of the present invention, Figure 1 and Figure 2 As shown, the nuclear power platform heat source on-orbit simulation device includes a light-concentrating device, a heat energy absorption mechanism 2 and a heat energy conversion mechanism. The light-concentrating device focuses solar energy. The light-receiving side of the heat energy absorption mechanism 2 is a wedge-shaped structure. The heat energy conversion mechanism includes a heat transfer element, a heat source adapter 4 and a thermoelectric converter 5. The first end of the heat transfer element is heat-conductingly connected to the backlight side of the heat energy absorption mechanism 2, the second end of the heat transfer element is heat-conductingly connected to the heat source adapter 4, and the thermoelectric converter 5 is heat-conductingly connected to the heat source adapter 4. The light-concentrating device focuses sunlight onto the wedge-shaped structure of the heat energy absorption mechanism 2. The wedge-shaped structure absorbs the reflected light of the sun and uses solar energy to heat the wedge-shaped structure to a specified temperature. The heat transfer element transfers heat to the heat source adapter 4, and the heat source adapter 4 generates electricity using the thermoelectric converter 5.

[0025] The on-orbit simulation device for a nuclear power platform heat source according to an embodiment of the present invention has the advantage of high light-to-heat conversion efficiency.

[0026] In some embodiments, the condenser 1 is a concave mirror, and the condenser 1 is arranged opposite to the wedge-shaped structure.

[0027] Specifically, the condenser 1 uses a concave mirror to collect parallel beams of sunlight and reflect them to the wedge-shaped structure, and the wedge-shaped structure converts light energy into heat energy.

[0028] In some embodiments, a multi-layer heat insulation layer is disposed on the backlight surface of the condenser 1 .

[0029] Specifically, the back of the condenser 1 is coated with a multi-layer insulation layer to reduce the heat radiation of the condenser 1 to the space environment, thereby improving the energy collection efficiency. The insulation layer is a high-temperature aircraft insulation component such as polyimide material, alumina foam ceramic material, phenolic foam material, etc.

[0030] In some embodiments, the light-facing surface of the condenser 1 is a high-reflectivity mirror surface, and the light-facing surface is opposite to the wedge-shaped structure.

[0031] Specifically, the light-facing surface is made of a mirror material with high reflectivity to reflect the projected sunlight onto the wedge-shaped structure, and the wedge-shaped structure is arranged opposite to the light-facing surface to fully receive the reflected light.

[0032] In some embodiments, the wedge-shaped structure includes a plurality of wedge-shaped blocks 22, and the distance between the wedge-shaped blocks 22 and adjacent wedge-shaped blocks 22 increases as the distance from the focusing device decreases.

[0033] Specifically, the shapes of the multiple wedge blocks 22 of the wedge structure can be the same or different. The cross section of the wedge block 22 can be an isosceles trapezoid, or a right-angled trapezoid. The inclined surfaces of the two wedge blocks 22 are arranged opposite to each other. When the cross sections of the wedge blocks 22 are all isosceles trapezoids, the multiple wedge blocks 22 are arranged at equal intervals, and the light is reflected and absorbed multiple times between the inclined surfaces of the wedge blocks 22. When the cross sections of the wedge blocks 22 are all right-angled trapezoids, the inclined surfaces of the right-angled trapezoids on both sides face the center of the wedge structure, and the wedge blocks 22 located in the center are grouped in two, and their cross sections are assembled to form an isosceles trapezoid. The wedge blocks 22 can also be mixed and formed by a combination of right-angled trapezoids, right-angled triangles, isosceles trapezoids, etc. The wedge structure is formed by the multiple wedge blocks 22. As the distance from the condenser 1 increases, the distance between the inclined surfaces shortens, so that the light is reflected and absorbed multiple times between the inclined surfaces of the wedge blocks 22. The shape of the wedge blocks 22 meets the purpose of multiple reflections.

[0034] In some embodiments, the heat transfer element includes a high temperature heat transfer tube 3 , and the high temperature heat transfer tube 3 corresponds to the wedge block 22 one by one, and at least part of the high temperature heat transfer tube 3 is located inside the wedge block 22 .

[0035] Specifically, the high temperature heat transfer pipe 3 can be a high temperature liquid metal heat transfer pipe 3, which transfers the heat of the wedge block 22 to the heat adapter through heat transfer between the high temperature heat transfer pipe 3 and the wedge block 22. The corresponding number of high temperature heat transfer pipes 3 and wedge blocks 22 can fully transfer heat to avoid heat accumulation in individual wedge blocks 22.

[0036] In some embodiments, the surfaces of the wedge-shaped blocks 22 of the wedge-shaped structure opposite to the adjacent wedge-shaped blocks 22 are subjected to blackening treatment, and the blackening treatment may be spraying inorganic black paint on the surface or performing blackening oxidation treatment on the surface.

[0037] Specifically, the blackening treatment can increase the infrared absorption rate of the material body of the wedge block 22 and more efficiently convert light energy into heat energy.

[0038] In some embodiments, the wedge-shaped structure is made of porous metal material, and the porous metal material has a plurality of hollow structures, and the hollow structures increase the reflection and absorption process of energy inside the material.

[0039] Specifically, porous materials have a high absorption rate, and metal materials can withstand higher temperatures and are only limited by the melting point of the metal materials, meeting the on-orbit test temperature levels of different thermoelectric conversion devices.

[0040] In some embodiments, a high temperature insulation material 21 is disposed around the outer surface of the wedge-shaped structure.

[0041] Specifically, the high-temperature thermal insulation material 21 is arranged around the wedge-shaped structure to prevent the wedge-shaped structure from radiating heat into space and causing heat loss, thereby improving efficiency. The high-temperature thermal insulation material 21 can be thermal insulation materials such as aerogel and ceramic fiber.

[0042] In some embodiments, the thermal energy conversion mechanism further includes an energy load 6 , which is electrically connected to the thermoelectric converter 5 .

[0043] Specifically, the energy load 6 is used to consume the electric energy generated by the thermoelectric converter 5. The thermoelectric converter 5 can use thermoelectric materials to realize the conversion of thermal energy into electric energy and a Stirling generator, which converts thermal energy into electric energy through a Stirling generator and a temperature difference power generation module.

[0044] Working principle: The concentrator works in orbit by maintaining a directional attitude towards the sun. When the parallel sunlight hits the concentrator, it is reflected to the heat absorption structure at the focal position through the highly reflective mirror material on its surface. The heat absorption structure reflects and absorbs the sun's reflected light multiple times through the blackened wedge-shaped structure on the sunward side, and uses solar energy to heat the heat absorption structure to a specified temperature. The heat is transferred to the heat exchange adapter through the heat transfer pipe and then used to generate electricity using a thermoelectric converter.

[0045] In the description of the present invention, it is to be understood that the terms “center”, “longitudinal”, “lateral”, “length”, “width”, “thickness”, “up”, “down”, “front”, “back”, “left”, “right”, “vertical”, “horizontal”, “top”, “bottom”, “inside”, “outside”, “clockwise”, “counterclockwise”, “axial”, “radial”, “circumferential”, etc., indicating orientations or positional relationships based on the orientations or positional relationships shown in the accompanying drawings, are only for the convenience of describing the present invention and simplifying the description, and do not indicate or imply that the referred device or element must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as limiting the present invention.

[0046] In addition, the terms "first" and "second" are used for descriptive purposes only and should not be understood as indicating or implying relative importance or implicitly indicating the number of the indicated technical features. Therefore, the features defined as "first" and "second" may explicitly or implicitly include at least one of the features. In the description of the present invention, the meaning of "plurality" is at least two, such as two, three, etc., unless otherwise clearly and specifically defined.

[0047] In the present invention, unless otherwise clearly specified and limited, the terms "installed", "connected", "connected", "fixed" and the like should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral one; it can be a mechanical connection, an electrical connection, or communication with each other; it can be a direct connection, or an indirect connection through an intermediate medium, it can be the internal connection of two elements or the interaction relationship between two elements, unless otherwise clearly defined. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0048] In the present invention, unless otherwise clearly specified and limited, a first feature being "above" or "below" a second feature may mean that the first and second features are in direct contact, or the first and second features are in indirect contact through an intermediate medium. Moreover, a first feature being "above", "above" or "above" a second feature may mean that the first feature is directly above or obliquely above the second feature, or simply means that the first feature is higher in level than the second feature. A first feature being "below", "below" or "below" a second feature may mean that the first feature is directly below or obliquely below the second feature, or simply means that the first feature is lower in level than the second feature.

[0049] In the present invention, the terms "one embodiment", "some embodiments", "examples", "specific examples", or "some examples" etc. mean that the specific features, structures, materials or characteristics described in conjunction with the embodiment or example are included in at least one embodiment or example of the present invention. In this specification, the schematic representations of the above terms do not necessarily refer to the same embodiment or example. Moreover, the described specific features, structures, materials or characteristics may be combined in any one or more embodiments or examples in a suitable manner. In addition, those skilled in the art may combine and combine the different embodiments or examples described in this specification and the features of the different embodiments or examples, without contradiction.

[0050] Although the embodiments of the present invention have been shown and described above, it is to be understood that the above embodiments are illustrative and are not to be construed as limitations on the present invention. Changes, modifications, substitutions and variations of the above embodiments by those of ordinary skill in the art are all within the scope of protection of the present invention.

Claims

1. An on-orbit simulation device for heat source of nuclear power platform, It is characterized in that include: A concentrator that focuses solar energy; A heat energy absorption mechanism, wherein the light receiving side of the heat energy absorption mechanism is a wedge-shaped structure; A heat energy conversion mechanism, the heat energy conversion mechanism includes a heat transfer element, a heat source adapter and a thermoelectric converter, the first end of the heat transfer element is heat-conductingly connected to the backlight side of the heat energy absorption mechanism, the second end of the heat transfer element is heat-conductingly connected to the heat source adapter, and the thermoelectric converter is heat-conductingly connected to the heat source adapter.

2. The on-orbit simulation device for heat source of a nuclear power platform according to claim 1, It is characterized in that The condenser is a concave mirror, and the condenser is arranged opposite to the wedge-shaped structure.

3. The on-orbit simulation device for heat source of a nuclear power platform according to claim 2, It is characterized in that The backlight surface of the condenser is provided with multiple layers of heat insulation layers.

4. The on-orbit simulation device for heat source of a nuclear power platform according to claim 2, It is characterized in that The light-facing surface of the condenser is a high-reflectivity mirror surface, and the light-facing surface is opposite to the wedge-shaped structure.

5. The on-orbit simulation device for heat source of a nuclear power platform according to claim 1, It is characterized in that The wedge-shaped structure includes a plurality of wedge-shaped blocks, and the distance between the wedge-shaped blocks and adjacent wedge-shaped blocks increases as the distance from the focusing device decreases.

6. The on-orbit simulation device for heat source of a nuclear power platform according to claim 5, It is characterized in that The heat transfer element comprises a high temperature heat transfer tube, the high temperature heat transfer tube corresponds to the wedge block one by one, and at least part of the high temperature heat transfer tube is located inside the wedge block.

7. The on-orbit simulation device for heat source of a nuclear power platform according to claim 5, It is characterized in that The surfaces of the wedge blocks of the wedge-shaped structure opposite to the adjacent wedge blocks are subjected to blackening treatment.

8. The on-orbit simulation device for heat source of a nuclear power platform according to claim 7, It is characterized in that The wedge-shaped structure is made of porous metal material.

9. The on-orbit simulation device for heat source of a nuclear power platform according to claim 1, It is characterized in that A high temperature heat insulating material is arranged around the outer surface of the wedge-shaped structure.

10. The on-orbit simulation device for heat source of a nuclear power platform according to claim 1, It is characterized in that Also included is an energy load, which is electrically connected to the thermoelectric converter.

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