Method and device for calculating thermoelectric output characteristics of space heat pipe pile power supply

Abstract

The invention discloses a space heat pipe pile power supply thermoelectric output characteristic calculation method and device, and relates to the technical field of space heat pipe pile power supply system simulation, and the method comprises the steps: obtaining power supply system design parameters and a power demand of a nuclear power spacecraft in a deep space exploration task; inputting the power supply system design parameters into a pre-established space heat pipe reactor power supply system model, and obtaining the processed power supply system design parameters based on the power demand of the nuclear power spacecraft in the deep space exploration task; receiving a bus voltage reference value of the power supply system, determining a series-parallel connection mode based on the bus voltage reference value of the power supply system, and performing updating calculation on the processed power supply system design parameters according to the series-parallel connection mode to obtain thermoelectric parameters of the space heat pipe pile power supply under the load resistance value. And technical support is provided for the design of the power management system of the nuclear power spacecraft.

Description

Technical Field

[0001] The present invention relates to the technical field of space heat pipe reactor power system simulation, and specifically to a method and device for calculating the thermoelectric output characteristics of a space heat pipe reactor power supply. Background Art

[0002] Current research mainly focuses on the scheme design and component development of space heat pipe reactor power supplies, and the research on the interface integration between space heat pipe reactor power supplies and spacecraft power management systems is relatively limited. Traditional spacecraft mainly use solar cells and chemical batteries as the main energy sources, and have limited understanding of the thermoelectric output characteristics of space heat pipe reactor power supplies. Patent CN110060788A provides a method for analyzing the thermoelectric characteristics of a thermionic space reactor, but its analysis object is a thermionic reactor, which has significant differences in the generation mechanism from a heat pipe reactor. A heat pipe reactor is also a power source type with great potential in deep space exploration missions, and its thermoelectric output characteristics have unique laws. Therefore, it is necessary to design a method for calculating the thermoelectric output characteristics of a space heat pipe reactor power supply considering the coupling relationship between the spacecraft power system and the space heat pipe reactor, for the modeling and simulation research of future spacecraft power systems powered by space heat pipe reactors, to make up for the technical shortage in the power management simulation of nuclear-powered spacecraft. Summary of the Invention

[0003] To solve the deficiencies mentioned in the above background art, the purpose of the present invention is to provide a method and device for calculating the thermoelectric output characteristics of a space heat pipe reactor power supply.

[0004] In a first aspect, the purpose of the present invention can be achieved through the following technical solutions: A method for calculating the thermoelectric output characteristics of a space heat pipe reactor power supply, the method comprising the following steps: Obtain the power system design parameters and the power demand of a nuclear-powered spacecraft in a deep space exploration mission, input the power system design parameters into a pre-established space heat pipe reactor power system model, and obtain the processed power system design parameters based on the power demand of the nuclear-powered spacecraft in the deep space exploration mission; Receive the bus voltage reference value of the power system, determine the series-parallel connection mode based on the bus voltage reference value of the power system, and perform updated calculations on the processed power system design parameters according to the series-parallel connection mode to obtain the thermoelectric parameters of the space heat pipe reactor power supply under the load resistance.

[0005] In combination with the first aspect, in some implementation manners of the first aspect, the method further comprises: The determining the series-parallel connection mode based on the bus voltage reference value of the power system and performing updates on the processed power system design parameters according to the series-parallel connection mode includes: Initialize the design parameters of the power supply system, determine the series-parallel connection mode according to the reference value of the bus voltage of the power supply system, set the series load resistance value, perform thermoelectric coupling calculation based on the series load resistance value, obtain the thermoelectric parameters of the space heat pipe stack power supply at the load resistance value, and use the thermoelectric parameters of the space heat pipe stack power supply at the load resistance value obtained when the convergence condition is met as the final thermoelectric parameters of the space heat pipe stack power supply at the load resistance value.

[0006] Combined with the first aspect, in some implementation manners of the first aspect, the method further includes: after the thermoelectric parameters of the space heat pipe stack power supply at the load resistance value are calculated, a convergence determination needs to be performed. Calculate the relative difference between the thermoelectric parameters of the space heat pipe stack power supply at different load resistance values before and after, determine whether the relative difference meets the convergence condition. If the convergence condition is not met, use the thermoelectric parameters of the space heat pipe stack power supply at the load resistance value calculated in the later calculation as the input condition for recalculation until the calculation ends when the convergence condition is met.

[0007] Combined with the first aspect, in some implementation manners of the first aspect, the method further includes: the calculation of the thermoelectric parameters of the space heat pipe stack power supply at the load resistance value includes: Use the point reactor neutron kinetics model to calculate the core thermal power, use the lumped parameter method to solve the heat conduction equation to obtain the average temperature of the reactor core, use the thermal resistance network method to simulate the heat transfer effect of the heat pipe to obtain the temperature of each region inside the heat pipe, solve the electromotive force of the thermoelectric device based on the Seebeck effect, and calculate the radiation waste heat of the radiator after the thermoelectric generator device and the load form a closed loop, as well as the generated current, voltage and electric power.

[0008] Combined with the first aspect, in some implementation manners of the first aspect, the method further includes: the use of the point reactor neutron kinetics model to calculate the core thermal power includes: where is the neutron flux density, is t the reactivity at time β is the total fraction of delayed neutrons, β i is the i fraction of the λ i group of delayed neutrons, Λ is the neutron generation time, i is the decay constant of the C i group of delayed neutrons, i is the precursor concentration of the

[0009] Combined with the first aspect, in some implementations of the first aspect, the method further includes: The lumped parameter method is used to solve the heat conduction equation to obtain the average temperature of the reactor core, including: where, ρ F is the fuel density, c F is the specific heat capacity of the fuel, V F is the fuel volume, T F is the average temperature of the fuel, T HPe is the average temperature of the evaporation section of the heat pipe, R F is the heat transfer resistance between the core fuel and the evaporation section of the heat pipe, q F is the fuel heat release rate.

[0010] Combined with the first aspect, in some implementations of the first aspect, the method further includes: The heat transfer effect of the heat pipe is simulated by the thermal resistance network method to obtain the temperatures of each region inside the heat pipe, including: For a single thermal resistance, the transient operating characteristics of the single thermal resistance are calculated through the energy conservation equation to obtain the temperatures of each region inside the heat pipe. The energy conservation equations are expressed as: where, ρ i is the density of the i th thermal resistance, A i is the cross-sectional area of the i th thermal resistance, δ i is the thickness of the i th thermal resistance, c p,i is the specific heat capacity of the i th thermal resistance, T i is the central temperature of the i th thermal resistance, T i,1 and T i,2 are the front-end and back-end temperatures of the i th thermal resistance respectively, λ i is the i th thermal resistance of the thermal conductivity coefficient,α i is the thermal diffusivity of the i th thermal resistance, Q i,1 and Q i,2 are the heat transfer amounts at the front end and the back end of the i th thermal resistance respectively.

[0011] Solving for the electromotive force of the thermoelectric device based on the Seebeck effect includes: Among them, a i is the Seebeck coefficient of the i th thermoelectric material for the thermoelectric device, E i is the electromotive force of the i th thermoelectric device, ΔT i is the temperature difference across the thermoelectric device.

[0012] Combined with the first aspect, in some implementation manners of the first aspect, the method further includes: the calculation process of the current, voltage, and electric power generated after the thermoelectric generator device and the load form a closed loop, including: In the formula, I is the current, U is the voltage, P is the electric power, R i is the internal resistance of the i th thermoelectric device, R c is the wire resistance, R load is the load resistance.

[0013] Combined with the first aspect, in some implementation manners of the first aspect, the method further includes: the calculation of the radiative waste heat Q rad of the radiator, including: Among them, ε is the surface emissivity of the radiation plate, σ is the Stefan-Boltzmann constant, A is the temperature of the radiation plate, T rad is the temperature of the radiation plate, T space is the temperature of the space background radiation, and the superscript 4 represents the fourth power of the temperature.

[0014] In a second aspect, to achieve the above object, the present invention discloses a calculation device for the thermoelectric output characteristics of a space heat pipe reactor power supply, comprising: A parameter processing module, configured to obtain the power supply system design parameters and the power demand of a nuclear-powered spacecraft in a deep space exploration mission, input the power supply system design parameters into a pre-established space heat pipe reactor power supply system model, and obtain the processed power supply system design parameters based on the power demand of the nuclear-powered spacecraft in the deep space exploration mission; A parameter update module, configured to receive the bus voltage reference value of the power supply system, determine the series-parallel connection mode based on the bus voltage reference value of the power supply system, and perform an update calculation on the processed power supply system design parameters according to the series-parallel connection mode to obtain the thermoelectric parameters of the space heat pipe reactor power supply under the load resistance.

[0015] Advantages of the present invention: The present invention can provide technical support for the design of the power management system of a nuclear-powered spacecraft, thereby facilitating the engineering development of the nuclear-powered spacecraft in a deep space exploration mission. Brief Description of the Drawings

[0016] In order to more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the following will briefly introduce the drawings required for use in the description of the embodiments or the prior art. Obviously, for those of ordinary skill in the art, other drawings can be obtained based on these drawings without creative efforts.

[0017] Figure 1 It is a schematic flow chart of the thermoelectric characteristic calculation method described in the present invention; Figure 2 It is a schematic diagram of the power supply system of a nuclear-powered spacecraft of the present invention; Figure 3 It is a schematic overall flow chart of the present invention; Figure 4 It is a schematic architecture diagram of the specific implementation software of the present invention; Figure 5 It is a schematic diagram of the device structure of the present invention. Detailed Embodiments

[0018] The following will clearly and completely describe the technical solutions in the embodiments of the present invention with reference to the drawings in the embodiments of the present invention. Obviously, the described embodiments are only a part of the embodiments of the present invention, rather than all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative efforts belong to the scope of protection of the present invention.

[0019] Embodiment 1: As Figure 1As shown in the figure, a calculation method for the thermoelectric output characteristics of a space heat pipe reactor power supply, the method includes the following steps: S101: Obtain the power supply system design parameters and the power demand of the nuclear-powered spacecraft in the deep space exploration mission, input the power supply system design parameters into the pre-established space heat pipe reactor power supply system model, and obtain the processed power supply system design parameters based on the power demand of the nuclear-powered spacecraft in the deep space exploration mission; S102: Receive the bus voltage reference value of the power supply system, determine the series-parallel connection method based on the bus voltage reference value of the power supply system, update and calculate the processed power supply system design parameters according to the series-parallel connection method, obtain the thermoelectric parameters of the space heat pipe reactor power supply under the load resistance, determine whether the thermoelectric parameters calculated this time reach a steady state, output the core thermoelectric parameters after reaching the steady state, and the calculation ends. If the steady state is not reached, the system parameters are calculated again.

[0020] The determination of the series-parallel connection method based on the bus voltage reference value of the power supply system and the update of the processed power supply system design parameters according to the series-parallel connection method include: The power supply system is the power management system of the nuclear-powered spacecraft; Initialize the power supply system design parameters, determine the series-parallel connection method according to the bus voltage reference value of the power supply system, set a series of load resistance values, perform thermoelectric coupling calculations based on the series of load resistance values, obtain the thermoelectric parameters of the space heat pipe reactor power supply under the load resistance, and use the thermoelectric parameters of the space heat pipe reactor power supply under the load resistance obtained when the convergence condition is met as the final thermoelectric parameters of the space heat pipe reactor power supply under the load resistance; The thermoelectric parameters of the space heat pipe reactor power supply under the load resistance need to be judged for convergence after calculation. Calculate the relative difference between the thermoelectric parameters of the space heat pipe reactor power supply under different load resistances before and after. Taking the core temperature and output electric power of the space heat pipe reactor power supply as criteria, if the relative difference of the core temperature is lower than 0.1K and the relative difference of the output electric power is lower than 0.1W, it can be considered that the calculation reaches convergence. If the convergence condition is not met, the thermoelectric parameters of the space heat pipe reactor power supply under the load resistance calculated in the latter calculation are used as input conditions for recalculation until the convergence condition is met and the calculation ends.

[0021] The calculation of the thermoelectric parameters of the space heat pipe reactor power supply under the load resistance includes: The point reactor neutron kinetics model is a simplified model commonly used in nuclear reactor physics analysis to describe the change of neutron flux density in the reactor over time. The point reactor neutron kinetics model regards the reactor as a "point", ignores the spatial distribution of neutron flux density, analyzes the dynamic behavior of the change of neutron flux density in the reactor over time, and is applicable to reactor types with a compact core such as space heat pipe reactors.

[0022] The lumped parameter method is a commonly used simplified analysis method in heat transfer to study the variation of the temperature distribution inside an object with time. The lumped parameter method assumes that the temperature distribution inside the object is uniform, that is, the spatial distribution of the object's temperature is ignored, and only the variation of temperature with time is considered.

[0023] The thermal resistance network method is to equivalent the heat transfer process to thermal resistances. The heat transfer process inside a single thermal resistance is regarded as a quasi-steady state. By establishing thermal resistance models for different regions and solving their energy conservation equations, the temperature distributions of each region are obtained, which is a commonly used model for solving the temperature distribution of heat pipes.

[0024] When two different conductor or semiconductor materials are connected to form a loop and different temperatures are maintained at the joints, an electromotive force will be generated in the loop. Describing this phenomenon of potential difference caused by temperature gradient is the Seebeck effect. Based on the Seebeck effect, since there is a temperature gradient at both ends of the thermoelectric generator device of the space heat pipe stack, an electromotive force is generated at both ends of the device. After connecting them with wires, a current is formed.

[0025] The point reactor neutron kinetics model is used to calculate the core thermal power, the lumped parameter method is used to solve the heat conduction equation to obtain the average temperature of the reactor core, the thermal resistance network method is used to simulate the heat transfer effect of the heat pipe to obtain the temperature of each region inside the heat pipe, the electromotive force of the thermoelectric device is solved based on the Seebeck effect, and the current, voltage and electric power generated after the thermoelectric generator device and the load form a closed loop. The radiative waste heat of the radiator is calculated based on the principle of radiative heat dissipation.

[0026] Using the point reactor neutron kinetics model to calculate the core thermal power, including: In the formula is the neutron flux density, is t the reactivity at time β is the total fraction of delayed neutrons, β i is the i fraction of the λ i group of delayed neutrons, Λ is the neutron generation time, i is the decay constant of the C i is the i group of delayed neutron precursor concentrations.

[0027] Using the lumped parameter method to solve the heat conduction equation to obtain the average temperature of the reactor core: Among them, ρ F is the fuel density, c F is the specific heat capacity of the fuel,V F is the fuel volume, T F is the average fuel temperature, T HPe is the average temperature of the evaporation section of the heat pipe, R F is the heat transfer resistance between the core fuel and the evaporation section of the heat pipe, q F is the fuel heat release rate.

[0028] The heat transfer effect of the heat pipe is simulated by the thermal resistance network method. During the operation of the space heat pipe reactor power system, due to the good isothermal property of the heat pipe, the transient response time of the working fluid flow and heat transfer in the heat pipe is much smaller than the response of the heat conduction in the pipe wall and the wick. The circulation of the working fluid in the heat pipe can be considered quasi-steady, and a thermal resistance network model is established. For a single thermal resistance, its transient operating characteristics are calculated through the energy conservation equation to obtain the temperature of each region in the heat pipe. The energy conservation equations can be expressed as: Among them, ρ i is the density of the i th thermal resistance, A i is the cross-sectional area of the i th thermal resistance, δ i is the thickness of the i th thermal resistance, c p,i is the specific heat capacity of the i th thermal resistance, T i is the central temperature of the i th thermal resistance, T i,1 and T i,2 are the front-end and back-end temperatures of the i th thermal resistance respectively, λ i is the thermal conductivity of the i th thermal resistance, α i is the thermal diffusivity of the i th thermal resistance, Q i,1 and Q i,2 are the heat transferred at the front-end and back-end of the i th thermal resistance respectively.

[0029] Solve the electromotive force of the thermoelectric device based on the Seebeck effect. The heat of the nuclear reactor is transferred to the thermoelectric generator device through the heat pipe. Due to the different temperatures at both ends of the thermoelectric generator device, an electromotive force is generated under the action of the Seebeck effect. The total electromotive force formed by connecting the thermoelectric devices in series or parallel can be expressed as: Among them, a i is the Seebeck coefficient of the thermoelectric material of the i th thermoelectric device, E i is the electromotive force of the i th thermoelectric device, ΔT i is the temperature difference between both ends of the thermoelectric device.

[0030] After the thermoelectric generator device and the load form a closed loop, the generated current, voltage, and electric power can be expressed as: In the formula, I is the current, U is the voltage, P is the electric power, R i is the internal resistance of the i th thermoelectric device, R c is the wire resistance, R load is the load resistance.

[0031] The system waste heat of the space heat pipe reactor power supply is radiated into space through the radiator heat dissipation plate. The space background radiation temperature is set to 4 K. The calculation of the radiation waste heat can be expressed as: Among them, ε is the surface emissivity of the radiation plate, σ is the Stefan-Boltzmann constant, A is the radiation plate temperature, T rad is the radiation plate temperature, T space is the space background radiation temperature. The superscript 4 represents the fourth power of the temperature.

[0032] Specifically, the solution of the present invention will be further described below through embodiments: Such as Figure 2As shown in the figure, the main structure of the power supply system of a nuclear-powered spacecraft is presented. The space heat pipe reactor power supply is responsible for providing a stable and reliable power supply for the nuclear-powered spacecraft. Compared with conventional chemical power sources, solar cells, etc., the space heat pipe reactor power supply has a more complex structure, including components such as a reactor core, heat pipes, thermoelectric generators, and radiators. The core of the reactor generates heat through nuclear fission reactions, and the heat is exported from the evaporation section of the heat pipe in the core to the condensation section of the heat pipe. The condensation section of the heat pipe is welded to the hot end of the thermoelectric generator, and the heat is transferred to the thermoelectric generator through the heat conduction process. Due to the temperature difference between the hot end and the cold end of the thermoelectric device, the thermoelectric material generates an electromotive force based on the Seebeck effect. The thermoelectric devices are connected to the circuit load through different series and parallel methods to form a closed loop, generating a loop current. The electric energy generated by the space nuclear reactor power supply is transmitted to the shunt regulator for shunt regulation, and the shunted electric energy is processed by the charge and discharge regulator. The charge and discharge regulator adjusts the battery pack for charging or discharging operations according to the power consumption requirements at the load end. The power management system is responsible for uniformly allocating the electric energy generated by the space heat pipe.

[0033] As Figure 3 shown, the calculation process of the thermoelectric output characteristics of the space heat pipe reactor power supply is presented. First, the parameters are initialized, and the series and parallel methods are determined according to the bus voltage of the nuclear-powered spacecraft, and the series load resistance value is set. Subsequently, the system parameters are calculated, and the thermoelectric parameters of the space heat pipe reactor power supply under different load resistance values are calculated to determine whether the thermoelectric parameters reach a steady state; if not, iterative calculations are performed until a steady state is reached; after reaching the steady state, the core thermoelectric parameters are output, and the process ends.

[0034] As Figure 4 shown, the software cooperating with the calculation method of the present invention mainly consists of modules such as a reactor core, heat pipes, thermoelectric generators, radiators, a PID controller / control drum, a total reactivity / point reactor module, and a power management system.

[0035] The composition and functions of each module are as follows: Reactor core: With the temperature of the evaporation section of the heat pipe as the boundary, calculate the heat transfer of the core and the change in the core temperature.

[0036] Heat pipes: With the temperature of the hot end of the thermoelectric generator as the boundary, calculate the heat transfer of the heat pipes and the change in the heat pipe temperature.

[0037] Thermoelectric generators: With the temperature of the radiation plate as the boundary, calculate the heat transfer of the thermoelectric devices and parameters such as voltage, current, and electric power according to the load of the power management system.

[0038] Radiators: Calculate the change in the radiator temperature and the waste heat of radiation.

[0039] PID controller / control drum: Appropriately drive the control drum according to the reference electric power to introduce reactivity.

[0040] Total reactivity / Point reactor module: Calculate the control drum reactivity of the PID controller / control drum and the temperature negative reactivity generated by the core temperature. Calculate the change in core thermal power through the point reactor neutron kinetics equation and transfer the thermal power to the reactor core.

[0041] Power management system: Taking the thermoelectric output parameters of the space heat pipe reactor power supply as input, carry out power control simulation, calculate parameters such as charge-discharge power and load output power, and feedback signals such as load resistance change to the power calculation of the thermoelectric generator device.

[0042] Between each module, through the form of data transfer such as boundary conditions, the coupled calculation is used to obtain the thermoelectric output characteristic parameters of the space heat pipe reactor power supply.

[0043] As shown in Table 1, the relevant calculation verification of the present invention is mainly carried out through case verification using three-dimensional high-fidelity CFD (Computational Fluid Dynamics) software. The CFD software adopts a three-dimensional high-precision model, and the theoretical calculation accuracy is relatively high. It is a commonly used calculation method in the field of mass transfer and heat transfer, but its calculation efficiency is low, and the calculation time usually takes several days or even dozens of days. The calculation method adopted by the present invention has the characteristics of fast calculation speed and relatively high calculation accuracy. Key parameters such as temperature, voltage, and current are selected for comparison. Among them, the relative deviation of the average core temperature calculated by the two methods is 0.29%, and the relative deviation of the load current is 4.49%, which is lower than the commonly used 5% error range in research work. It can be considered that the calculation accuracy of this method is relatively high and can be applied to the calculation of the thermoelectric output characteristics of the space heat pipe reactor power supply, providing technical support for the design of the power management system of nuclear-powered spacecraft.

[0044] Table 1 Case verification Embodiment 2: As Figure 5 shown, in order to achieve the above object, based on Embodiment 1, the present invention discloses a device for calculating the thermoelectric output characteristics of a space heat pipe reactor power supply, including: Parameter processing module 11, used to obtain the power supply system design parameters and the power demand of the nuclear-powered spacecraft in the deep space exploration mission, input the power supply system design parameters into the pre-established space heat pipe reactor power supply system model, and obtain the processed power supply system design parameters based on the power demand of the nuclear-powered spacecraft in the deep space exploration mission; Parameter update module 12, used to receive the bus voltage reference value of the power supply system, determine the series-parallel connection method based on the bus voltage reference value of the power supply system, and perform update calculation on the processed power supply system design parameters according to the series-parallel connection method to obtain the thermoelectric parameters of the space heat pipe reactor power supply under the load resistance value.

[0045] Based on the same inventive concept, the present invention further provides a computer device, which includes: one or more processors, and a memory for storing one or more computer programs; the program includes program instructions, and the processor is configured to execute the program instructions stored in the memory. The processor may be a Central Processing Unit (CPU), or may also be other general-purpose processors, Digital Signal Processors (DSPs), Application Specific Integrated Circuits (ASICs), Field-Programmable Gate Arrays (FPGAs), or other programmable logic devices, discrete gate or transistor logic devices, discrete hardware components, etc. It is the computing core and control core of the terminal, and is used to implement one or more instructions. Specifically, it is used to load and execute one or more instructions in the computer storage medium to implement the above method.

[0046] It should be further noted that, based on the same inventive concept, the present invention further provides a computer storage medium, on which a computer program is stored, and the computer program, when run by a processor, executes the above method. The storage medium may be any combination of one or more computer-readable media. The computer-readable medium may be a computer-readable signal medium or a computer-readable storage medium. The computer-readable storage medium may, for example, but not be limited to, be an electrical, magnetic, optical, electrical, magnetic, infrared, or semiconductor system, apparatus, or device, or any combination of the above. More specific examples (non-exhaustive list) of the computer-readable storage medium include: an electrical connection having one or more wires, a portable computer disk, a hard disk, a Random Access Memory (RAM), a Read-Only Memory (ROM), an Erasable Programmable Read-Only Memory (EPROM or flash memory), an optical fiber, a portable compact disk read-only memory (CD-ROM), an optical storage device, a magnetic storage device, or any suitable combination of the above. In the present invention, the computer-readable storage medium may be any tangible medium that contains or stores a program, and the program may be used by or in combination with an instruction execution system, apparatus, or device.

[0047] In the description of this specification, the description referring to terms such as "one embodiment", "example", "specific example", etc. means that the specific features, structures, materials, or characteristics described in connection with the embodiment or example are included in at least one embodiment or example of the present disclosure. In this specification, the schematic representations of the above terms do not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials, or characteristics described may be combined in any one or more embodiments or examples in a suitable manner.

[0048] The above has shown and described the basic principles, main features and advantages of the present disclosure. Those skilled in the art should understand that the present disclosure is not limited by the above embodiments. What is described in the above embodiments and the specification only illustrates the principles of the present disclosure. Without departing from the spirit and scope of the present disclosure, the present disclosure will have various changes and improvements, and these changes and improvements all fall within the scope of the present disclosure claimed.

Claims

1. A calculation method for the thermoelectric output characteristics of a space heat pipe reactor power supply, characterized in that, The method includes the following steps: Obtain the power system design parameters and the power demand of the nuclear-powered spacecraft in the deep space exploration mission, input the power system design parameters into the pre-established space heat pipe reactor power system model, and obtain the processed power system design parameters based on the power demand of the nuclear-powered spacecraft in the deep space exploration mission; Receive the bus voltage reference value of the power system, determine the series-parallel connection mode based on the bus voltage reference value of the power system, and perform updated calculations on the processed power system design parameters according to the series-parallel connection mode to obtain the thermoelectric parameters of the space heat pipe reactor power supply under the load resistance.

2. The calculation method of the thermoelectric output characteristics of a space heat pipe reactor power supply according to claim 1, characterized in that, After the thermoelectric parameters of the space heat pipe reactor power supply under the load resistance are calculated, convergence determination needs to be performed. Calculate the relative difference between the thermoelectric parameters of the space heat pipe reactor power supply under different load resistances in the previous and subsequent times, and determine whether the relative difference meets the convergence condition. If the convergence condition is not met, use the thermoelectric parameters of the space heat pipe reactor power supply under the load resistance calculated in the subsequent calculation as the input condition for recalculation until the convergence condition is met and the calculation ends. Use the thermoelectric parameters of the space heat pipe reactor power supply under the load resistance obtained when the convergence condition is met and the calculation ends as the final thermoelectric parameters of the space heat pipe reactor power supply under the load resistance.

3. A method for calculating the thermoelectric output characteristics of a space heat pipe reactor power supply according to claim 2, characterized in that, The calculation of the thermoelectric parameters of the space heat pipe reactor power supply under the load resistance includes: Use the point reactor neutron kinetics model to calculate the core thermal power, use the lumped parameter method to solve the heat conduction equation to obtain the average temperature of the reactor core, use the thermal resistance network method to simulate the heat transfer effect of the heat pipe to obtain the temperature of each region inside the heat pipe, solve the electromotive force of the thermoelectric device based on the Seebeck effect, and calculate the radiation waste heat of the radiator after the thermoelectric generator device and the load form a closed loop, as well as the generated current, voltage, and electric power.

4. A method for calculating the thermoelectric output characteristics of a space heat pipe reactor power supply according to claim 3, characterized in that The use of the point reactor neutron kinetics model to calculate the core thermal power includes: where is the neutron flux density, is t the reactivity at time β is the total fraction of delayed neutrons, β i is the fraction of the i -th group of delayed neutrons, Λ is the neutron generation time, λ i is the i -th group delayed neutron decay constant, C i is the concentration of the i -th group delayed neutron precursors.

5. A method for calculating the thermoelectric output characteristics of a space heat pipe reactor power supply according to claim 4, characterized in that The use of the lumped parameter method to solve the heat conduction equation to obtain the average temperature of the reactor core includes: Among them, ρ F is the fuel density, c F is the specific heat capacity of the fuel, V F is the fuel volume, T F is the average temperature of the fuel, T HPe is the average temperature of the evaporation section of the heat pipe, R F is the heat transfer resistance between the core fuel and the evaporation section of the heat pipe, q F is the fuel heat release rate.

6. The calculation method for the thermoelectric output characteristics of a space heat pipe reactor power supply according to claim 5, wherein, The use of the thermal resistance network method to simulate the heat transfer effect of the heat pipe to obtain the temperature of each region inside the heat pipe includes: For a single thermal resistance, calculate the operating transient characteristics of the single thermal resistance through the energy conservation equation to obtain the temperature of each region inside the heat pipe. The energy conservation equation set is expressed as: Among them, ρ i is the density of the i th thermal resistance, A i is the cross-sectional area of the i th thermal resistance, δ i is the thickness of the i th thermal resistance, c p,i is the specific heat capacity of the i th thermal resistance, T i is the central temperature of the i th thermal resistance, T i,1 and T i,2 are respectively the front-end and back-end temperatures of the i th thermal resistance, λ i is the thermal conductivity of the i th thermal resistance, α i is the thermal diffusivity of the i th thermal resistance, Q i,1 and Q i,2 are respectively the heat transferred at the front-end and back-end of the i th thermal resistance; The method for solving the electromotive force E of a thermoelectric device based on the Seebeck effect includes: Among them, a i is the Seebeck coefficient of the thermoelectric material for the i th thermoelectric device, E i is the electromotive force of the i th thermoelectric device, Δ T i is the temperature difference between both ends of the thermoelectric device.

7. A method for calculating the thermoelectric output characteristics of a space heat pipe reactor power supply according to claim 6, characterized in that, The calculation process of the current, voltage, and electric power generated after the thermoelectric generator device and the load form a closed loop includes: Wherein, R i is the internal resistance of the thermoelectric generator device, R c is the contact resistance between the thermoelectric generator device and the wire, R load is the load resistance, I is the current, U is the voltage, P is the electric power.

8. A method for calculating the thermoelectric output characteristics of a space heat pipe reactor power supply according to claim 7, characterized in that, The radiant waste heat of the radiator Q rad Calculation of Q rad The magnitude of is related to the fourth power of the radiant panel temperature and the fourth power of the space background radiation temperature, including: Among them, ε is the emissivity of the radiation plate surface, σ is the Stefan-Boltzmann constant, A is the temperature of the radiation plate, T rad is the temperature of the radiation plate, T space is the temperature of the space background radiation. The superscript 4 represents the fourth power of the temperature.

9. A calculation device for the thermoelectric output characteristics of a space heat pipe reactor power supply, which adopts a calculation method for the thermoelectric output characteristics of a space heat pipe reactor power supply according to any one of claims 1 to 8, is characterized in that, Includes: A parameter processing module, used to obtain the power system design parameters and the power demand of the nuclear-powered spacecraft in the deep space exploration mission, input the power system design parameters into the pre-established space heat pipe reactor power system model, and obtain the processed power system design parameters based on the power demand of the nuclear-powered spacecraft in the deep space exploration mission; A parameter update module, used to receive the bus voltage reference value of the power system, determine the series-parallel connection mode based on the bus voltage reference value of the power system, and perform updated calculations on the processed power system design parameters according to the series-parallel connection mode to obtain the thermoelectric parameters of the space heat pipe reactor power supply under the load resistance.

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