Slip ring power loop optimal distribution method and system for reducing spacecraft slip ring heat concentration

Abstract

The invention provides a loop distribution optimization method and system for reducing spacecraft slip ring heat concentration, and belongs to the technical field of spacecrafts. Comprising the following steps: carrying out subarray division on + / -Y wing solar cells; setting a corresponding relation between each sub-array and a high-voltage sub-array and a low-voltage sub-array of a power supply control device, establishing a connection relation between each sub-array of the + / -Y-wing solar cell and a slip ring in a + / -Y-wing solar panel driving mechanism through the corresponding relation between each sub-array of the solar cell and the power supply control device, and dispersing a heating source in the slip ring; the heating source is a power loop of the slip ring of the solar panel driving mechanism which emits heat after current passes through, so that heat concentration in the slip ring is reduced, and the failure risk caused by long-time high-temperature work of the power loop is reduced.

Description

Technical Field

[0001] The present invention relates to the field of spacecraft technology, and in particular to a slip ring power loop optimization distribution method and system for reducing heat concentration in a spacecraft slip ring. Background Art

[0002] Each subarray of solar cells is connected to the power control device through a power slip ring, so that the solar cells can power the spacecraft. When the sun shines on the solar cells, the generated current is transmitted to the satellite through the power slip ring. The heat generated by the tightly arranged power rings can only be conducted through radiation, and the heat dissipation path is single and slow. During the long light period, the solar cells continuously transmit current to the slip rings, and the tightly arranged power loops generate a lot of heat. When the temperature rises, the conductor resistance will increase, thereby generating more heat, forming a vicious circle, causing the local temperature of the slip ring to rise rapidly. Long-term high-temperature operation causes the slip ring to have safety hazards such as overload and short circuit. In order to ensure that the spacecraft has sufficient energy supply, the spacecraft generally chooses an orbit with longer light, and the working state of the slip ring transmitting power for a long time cannot be avoided.

[0003] The power slip ring is used to transmit the power of each sub-array of solar cells to the satellite. When the power loop is over-current, a large amount of heat is generated. The closely arranged power loops have a single heat dissipation path and a slow heat dissipation method, resulting in local heat concentration in the power slip ring.

[0004] According to the current slip ring design requirements, there is no clear arrangement rule for the situation where the power loop generates large amounts of heat and heat is concentrated. During a long period of sunlight, the power ring accumulates heat as it works for a long time. The high heat generated by the power ring and slow heat dissipation cause local high temperatures in the power ring. On the one hand, high temperatures increase the conductor resistance and increase the heat generated by the power ring; on the other hand, high temperatures accelerate the aging of insulating materials and easily lead to the risk of leakage short circuits. Summary of the invention

[0005] In view of the defects in the prior art, an object of the present invention is to provide a method and system for optimizing the power loop distribution of a slip ring for reducing heat concentration in a spacecraft slip ring.

[0006] A method for optimizing the power distribution of a slip ring for reducing heat concentration of a spacecraft slip ring provided by the present invention comprises:

[0007] Step S1: Divide the ±Y wing solar cells into sub-arrays to obtain ±Y wing solar cell sub-arrays;

[0008] Step S2: setting the correspondence between each ±Y-wing solar cell subarray and the high voltage subarray and low voltage subarray of the power control device;

[0009] Step S3: establishing a connection relationship between each sub-array of ±Y-wing solar cells and the power control device and the slip ring power loop in the ±Y-wing solar sail driving mechanism through the corresponding relationship between each sub-array and the power control device, and dispersing the heat source inside the slip ring;

[0010] The heat source is a power loop of a slip ring of a solar panel driving mechanism that generates heat after current passes through it.

[0011] Preferably, the number of ±Y-wing solar cell sub-arrays and slip ring power loops is determined based on the power consumption requirements of the spacecraft and the use of high and low voltages.

[0012] Preferably, the method of determining the number of ±Y-wing solar cell sub-arrays and slip ring power loops according to the power consumption requirements of the spacecraft and the use of high and low voltages includes:

[0013] Determine the power demand P of the spacecraft, and obtain the voltage value U1 of the high-voltage solar cell subarray and the voltage value U2 of the low-voltage solar cell subarray according to the use demand of each single machine; obtain the current value I1 of the high-voltage solar cell subarray and the current value I2 of the low-voltage solar cell subarray according to the series-parallel relationship of the solar cell panels; set n high-voltage solar cell subarrays and m low-voltage solar cell subarrays to meet the power consumption demand of the spacecraft, and ensure that the electric energy generated by the solar cells is not less than the power consumption demand of the spacecraft;

[0014] n×U1×I1+m×U2×I2≥P

[0015] After dividing the n high-voltage solar cell subarrays and the m low-voltage solar cell subarrays equally, the number of each type of solar cell subarrays in the ±Y-wing solar cells is: n / 2 high-voltage solar cell subarrays and m / 2 low-voltage solar cell subarrays.

[0016] Each solar cell subarray corresponds to two power loops, the ±Y-wing solar array drive mechanism has n high-voltage power loops and m low-voltage power loops.

[0017] Preferably, the high-voltage power loop is equally distributed at both ends of the slip ring; and the low-voltage power loop is equally distributed in sequence inside the high-voltage power loop.

[0018] Preferably, several signal switching channels are arranged inside the two groups of symmetrical low-voltage power loops for isolation as required.

[0019] Preferably, the resistance values ​​of the low-voltage power loop and the high-voltage power loop are comparable, and after currents of different voltages flow through them, there is a difference in the amount of heat generated; the high-voltage power loop generates a large amount of heat, while the low-voltage power loop generates a small amount of heat.

[0020] According to the present invention, a slip ring power loop optimization distribution system for reducing heat concentration of a spacecraft slip ring is provided, comprising:

[0021] Module M1: divide the ±Y wing solar cells into sub-arrays to obtain the ±Y wing solar cell sub-arrays;

[0022] Module M2: Set the correspondence between each subarray of ±Y-wing solar cells and the high-voltage subarray and low-voltage subarray of the power control device;

[0023] Module M3: through the corresponding relationship between each sub-array of ±Y-wing solar cells and the power control device, the connection relationship between each sub-array of ±Y-wing solar cells and the slip ring power loop in the ±Y-wing solar sail driving mechanism is established to disperse the heat source inside the slip ring;

[0024] The heat source is a power loop of a slip ring of a solar panel driving mechanism that generates heat after current passes through it.

[0025] Preferably, the number of ±Y-wing solar cell sub-arrays and slip ring power loops is determined according to the power consumption requirements of the spacecraft and the use of high and low voltages;

[0026] Determining the number of ±Y-wing solar cell sub-arrays and slip ring power loops according to the power consumption requirements of the spacecraft and the use of high and low voltages includes:

[0027] Determine the power demand P of the spacecraft, and obtain the voltage value U1 of the high-voltage solar cell subarray and the voltage value U2 of the low-voltage solar cell subarray according to the use demand of each single machine; obtain the current value I1 of the high-voltage solar cell subarray and the current value I2 of the low-voltage solar cell subarray according to the series-parallel relationship of the solar cell panels; set n high-voltage solar cell subarrays and m low-voltage solar cell subarrays to meet the power consumption demand of the spacecraft, and ensure that the electric energy generated by the solar cells is not less than the power consumption demand of the spacecraft;

[0028] n×U1×I1+m×U2×I2≥P

[0029] After dividing the n high-voltage solar cell subarrays and the m low-voltage solar cell subarrays equally, the number of each type of solar cell subarrays in the ±Y-wing solar cells is: n / 2 high-voltage solar cell subarrays and m / 2 low-voltage solar cell subarrays.

[0030] Each solar cell subarray corresponds to two power loops, the ±Y-wing solar array drive mechanism has n high-voltage power loops and m low-voltage power loops.

[0031] Preferably, the high-voltage power loops are equally arranged at both ends of the slip ring; the low-voltage power loops are equally arranged in sequence inside the high-voltage power loops;

[0032] Inside the two sets of symmetrical low-voltage power loops, several signal switching channels are arranged as needed for isolation.

[0033] Preferably, the resistance values ​​of the low-voltage power loop and the high-voltage power loop are comparable, and after currents of different voltages flow through them, there is a difference in the amount of heat generated; the high-voltage power loop generates a large amount of heat, while the low-voltage power loop generates a small amount of heat.

[0034] Compared with the prior art, the present invention has the following beneficial effects:

[0035] 1. By unifying the slip ring power loop arrangement rules, the standardization of the slip ring interface is achieved, the consistency of the slip ring product design status is improved, and a certain reference value is provided for the allocation of slip rings with high heat generation;

[0036] 2. By arranging the power rings on both sides of the slip ring, the heat source inside the slip ring is dispersed, avoiding the heat concentration caused by the high heat generated by the power ring, and greatly reducing the power supply safety risks caused by high temperature operation.

[0037] 3. By dividing the high-voltage solar cell array into equal parts and arranging them at both ends of the slip ring, and dividing the low-voltage solar cell array into equal parts and arranging them inside the high-voltage solar cell array, the signal loop is arranged inside the two groups of low-voltage battery subarrays; the power ring with high heat generation is arranged at both ends of the slip ring, which is conducive to the heat diffusion outward, and at the same time, the heat is transferred to the signal ring with low heat generation arranged inside. The power ring and the signal ring dissipate heat to the outside through thermal radiation, which effectively avoids the heat concentration inside the slip ring and avoids the risk of local high temperature of the slip ring, which may cause leakage and short circuit.

[0038] 4. In view of the general high power consumption demand of current spacecraft, in order to ensure sufficient energy supply, long-term sunlight becomes a hard requirement that the slip ring must adapt to; and the slip ring itself is a component with high heat generation and slow heat dissipation; by dispersing the arrangement of power slip rings, the heat source of the power ring is dispersed, thereby ensuring that the slip ring can work stably for a long time under harsh heat dissipation conditions. BRIEF DESCRIPTION OF THE DRAWINGS

[0039] Other features, objects and advantages of the present invention will become more apparent from the detailed description of non-limiting embodiments made with reference to the following drawings:

[0040] Figure 1 Flow chart of the method for optimizing the power distribution of slip rings to reduce slip ring heat concentration.

[0041] Figure 2 Assign a flow chart to the slip ring circuit. DETAILED DESCRIPTION

[0042] The present invention is described in detail below in conjunction with specific embodiments. The following embodiments will help those skilled in the art to further understand the present invention, but are not intended to limit the present invention in any form. It should be noted that, for those of ordinary skill in the art, several changes and improvements can also be made without departing from the concept of the present invention. These all belong to the protection scope of the present invention.

[0043] Example 1

[0044] A method for optimizing the power distribution of a slip ring for reducing heat concentration of a spacecraft slip ring provided by the present invention comprises:

[0045] Step S1: Divide the ±Y wing solar cells into sub-arrays to obtain ±Y wing solar cell sub-arrays;

[0046] Step S2: setting the correspondence between each ±Y-wing solar cell subarray and the high voltage subarray and low voltage subarray of the power control device;

[0047] Step S3: establishing a connection relationship between each sub-array of ±Y-wing solar cells and the power control device and the slip ring power loop in the ±Y-wing solar sail driving mechanism through the corresponding relationship between each sub-array and the power control device, and dispersing the heat source inside the slip ring;

[0048] The heat source is a power loop of a slip ring of a solar panel driving mechanism that generates heat after current passes through it.

[0049] This embodiment provides a slip ring power loop optimization distribution method for reducing slip ring heat concentration, which disperses the heat source inside the slip ring and reduces the risk of power supply safety such as overload and short circuit caused by high-temperature operation.

[0050] Specifically, the number of solar cell sub-arrays and slip ring power loops is determined based on the power consumption requirements of the spacecraft and the use of high and low voltages;

[0051] More specifically, according to the power consumption requirements of the spacecraft and the use of high and low voltages, the number of high-voltage solar cell subarrays and low-voltage solar cell subarrays is determined, thereby obtaining the required number of slip ring power loops. First, the power demand P of the spacecraft is determined, and the voltage value U1 of the high-voltage solar cell subarray and the voltage value U2 of the low-voltage solar cell subarray are obtained according to the use requirements of each single machine. According to the series-parallel relationship of the solar cell sheets, the current value I1 of the high-voltage solar cell subarray and the current value I2 of the solar cell subarray are obtained. In order to meet the power consumption requirements of the spacecraft, n high-voltage solar cell subarrays and m low-voltage solar cell subarrays are set to ensure that the electric energy generated by the solar cell is not less than the power consumption requirements of the spacecraft, n×U1×I1+m×U2×I2≥P. After the n high-voltage solar cell subarrays and the m low-voltage solar cell subarrays are equally divided, the number of ±Y wing solar cell subarrays is obtained as follows: n / 2 high-voltage solar cell subarrays and m / 2 low-voltage solar cell subarrays. Each solar cell subarray requires a power loop for the positive and negative sides respectively, that is, each solar cell subarray corresponds to two power loops, that is, the ±Y-wing solar array drive mechanism has n high-voltage power loops and m low-voltage power loops.

[0052] The drive mechanism slip ring is distributed in a loop. The high-voltage power loop is divided equally and arranged at both ends of the slip ring. The low-voltage power loop is divided equally and arranged in sequence on the inner side of the high-voltage power loop. Inside the two groups of low-voltage power loops, several signal loops are arranged as needed for isolation.

[0053] Furthermore, a matching method for establishing each sub-array of ±Y-wing solar cells and the power loops of the ±Y-wing solar sail panel driving mechanism is as follows: a positional arrangement relationship between the high-voltage power loop and the low-voltage power loop is established so that the power loops with high heat generation are located at both ends of the slip ring, which is beneficial for heat radiation to the outside of the slip ring, and the low-voltage power loop and the signal ring with low heat generation are arranged on the inside, which isolates the power loops on both sides on the one hand and avoids high temperature inside the slip ring on the other hand.

[0054] Furthermore, the resistance values ​​of the power rings are similar, and when currents of different voltages flow through them, the heat generated is significantly different. When current passes through the power slip rings, the high-voltage sub-array generates more heat, while the low-voltage sub-array generates less heat.

[0055] Furthermore, the heat concentration is generated by overcurrent in the power loop.

[0056] The present invention also provides a slip-ring power loop optimization distribution system for reducing spacecraft slip-ring heat concentration. The slip-ring power loop optimization distribution system for reducing spacecraft slip-ring heat concentration can be implemented by executing the process steps of the slip-ring power loop optimization distribution method for reducing spacecraft slip-ring heat concentration, that is, those skilled in the art can understand the slip-ring power loop optimization distribution method for reducing spacecraft slip-ring heat concentration as a preferred implementation of the slip-ring power loop optimization distribution system for reducing spacecraft slip-ring heat concentration.

[0057] Example 2

[0058] According to the present invention, a slip ring power loop optimization allocation method for reducing spacecraft slip ring heat concentration is provided, such as Figure 1 ,include:

[0059] Step 1: Divide the ±Y wing solar cell subarrays;

[0060] Specifically, the number of solar cell sub-arrays and slip ring power loops is determined according to the power consumption requirements of the spacecraft;

[0061] Step 2: Establish the corresponding relationship between each sub-array of ±Y-wing solar cells and the power control device;

[0062] Specifically, a correspondence between the ±Y-wing solar cell subarrays and the power control device is established, and the number of high-voltage subarrays and low-voltage subarrays of the ±Y-wing solar cell subarrays is determined, thereby obtaining the number of high-voltage and low-voltage power loops of the power loop of the ±Y-wing solar sail driving mechanism;

[0063] Step 3: The high-voltage power loop is divided equally and arranged at both ends of the slip ring. The low-voltage power loop is divided equally and arranged inside the high-voltage power loop in sequence. Inside the two groups of low-voltage power loops, several signal loops are arranged as needed for isolation;

[0064] The specific implementation of the present invention is further described in detail below in conjunction with the accompanying drawings and examples.

[0065] Specifically, the step 1 includes:

[0066] According to the power consumption demand of the spacecraft and the use of high and low voltages, the number of solar cell sub-arrays and slip ring power loops is determined to make the number of ±Y wing solar cell sub-arrays consistent with the number of ±Y wing solar sail panel drive mechanism power loops, and try to avoid empty loops; taking a certain spacecraft as an example, the power demand of the whole satellite is 4500W, the high voltage power is 80V, 8 circuits, and the low voltage power is 16V, 16 circuits. After equal distribution, the ±Y wings each have 4 high-voltage sub-arrays and 8 low-voltage sub-arrays, that is, each solar sail panel drive mechanism slip ring of the ±Y wings has 4 high-voltage power loops and 8 low-voltage power loops, and 8 signal loops are arranged in the middle.

[0067] According to the power consumption requirements of the spacecraft and the use of high and low voltages, the number of high-voltage solar cell subarrays and low-voltage solar cell subarrays is determined, thereby obtaining the required number of slip ring power loops. First, the power demand P of the spacecraft is determined. According to the use requirements of each single machine, the voltage value U1 of the high-voltage solar cell subarray and the voltage value U2 of the low-voltage solar cell subarray are obtained. According to the series-parallel relationship of the solar cell sheets, the current value I1 of the high-voltage solar cell subarray and the current value I2 of the solar cell subarray are obtained. In order to meet the power consumption requirements of the spacecraft, n high-voltage solar cell subarrays and m low-voltage solar cell subarrays are set to ensure that the electric energy generated by the solar cell is not less than the power consumption requirements of the spacecraft, n×U1×I1+m×U2×I2≥P. The number of slip ring power loops of the solar sail driving mechanism is consistent with the number of high-voltage and low-voltage solar cell subarrays. After dividing the n high-voltage solar cell subarrays and the m low-voltage solar cell subarrays equally, the number of ±Y wing solar cell subarrays is obtained as follows: n / 2 high-voltage solar cell subarrays and m / 2 low-voltage solar cell subarrays. Each solar cell subarray requires a power loop for the positive and negative sides respectively, that is, each solar cell subarray corresponds to two power loops, that is, the ±Y-wing solar array drive mechanism has n high-voltage power loops and m low-voltage power loops. Taking a certain spacecraft as an example, if the power demand of the entire satellite is 8000W, assuming that the voltage value of the high-voltage solar cell subarray required by the spacecraft is U1=80V, the voltage value of the low-voltage solar cell subarray is U2=30V, the current value of the high-voltage solar cell subarray is I1=8A, and the current value of the solar cell subarray is I2=6A, in order to meet the power consumption requirements of the spacecraft, n=8 high-voltage solar cell subarrays and m=16 low-voltage solar cell subarrays are set to ensure that the power input of the solar cell subarrays is not less than the power consumption requirement of the entire satellite of 8000W. It is calculated that: n×U1×I1+m×U2×I2=8×80V×8A+16×30V×6A=8320W≥8000W. Therefore, the above 8 high-voltage solar cell subarrays and 16 low-voltage solar cell subarrays meet the power consumption requirements of the entire satellite. After dividing the high-voltage and low-voltage solar cell subarrays equally, the number of ±Y wing solar cell subarrays is: 4 high-voltage solar cell subarrays after being equally divided to the ±Y wings, and 8 low-voltage solar cell subarrays after being equally divided to the ±Y wings. Each solar cell subarray requires a power loop for the positive and negative sides respectively, that is, each solar cell subarray corresponds to two power loops, that is, the ±Y wing solar array drive mechanism has 8 high-voltage power loops and 16 low-voltage power loops. Assuming that each wing needs 8 signal loops, there are 8 high-voltage power loops, 16 low-voltage power loops and 8 signal loops in the slip ring of the ±Y wing solar sail drive mechanism.

[0068] In step 3, the high-voltage and low-voltage sub-arrays are distributed in the loops. The power loops of the high-voltage sub-arrays are equally divided and arranged at both ends of the slip ring. The power loops of the low-voltage sub-arrays are equally divided and arranged inside the high-voltage sub-arrays. Several signal loops are arranged inside the two groups of low-voltage sub-array power loops as needed. Taking a spacecraft as an example, Figure 2 As shown, there are 4 high-voltage power loops and 8 low-voltage power loops in the slip rings of the ±Y-wing solar panel drive mechanism. The high-voltage sub-array power loops are equally divided and arranged at both ends of the slip rings, and the low-voltage sub-array power loops are equally divided and arranged on the inner side of the high-voltage sub-array. Inside the two groups of low-voltage sub-array power loops, 8 signal loops are arranged as needed.

[0069] Those skilled in the art know that, in addition to realizing the system and its various devices, modules, and units provided by the present invention in a purely computer-readable program code, it is entirely possible to realize the same functions in the form of logic gates, switches, application-specific integrated circuits, programmable logic controllers, and embedded microcontrollers by logically programming the method steps. Therefore, the system and its various devices, modules, and units provided by the present invention can be considered as a hardware component, and the devices, modules, and units included therein for realizing various functions can also be regarded as structures within the hardware component; the devices, modules, and units for realizing various functions can also be regarded as both software modules for realizing the method and structures within the hardware component.

[0070] The above describes the specific embodiments of the present invention. It should be understood that the present invention is not limited to the above specific embodiments, and those skilled in the art can make various changes or modifications within the scope of the claims, which does not affect the essence of the present invention. In the absence of conflict, the embodiments of the present application and the features in the embodiments can be combined with each other arbitrarily.

Claims

1. A method for optimizing the power distribution of a slip ring for reducing heat concentration in a spacecraft slip ring, characterized in that: include: Step S1: Divide the ±Y wing solar cells into sub-arrays to obtain ±Y wing solar cell sub-arrays; Step S2: setting the correspondence between each ±Y-wing solar cell subarray and the high voltage subarray and low voltage subarray of the power control device; Step S3: establishing a connection relationship between each sub-array of ±Y-wing solar cells and the power control device and the slip ring power loop in the ±Y-wing solar sail driving mechanism through the corresponding relationship between each sub-array of ±Y-wing solar cells and the power control device, and dispersing the heat source inside the slip ring; The heat source is a power loop of a slip ring of a solar panel driving mechanism that generates heat after current passes through it.

2. The method for optimizing the slip ring power distribution for reducing heat concentration of a spacecraft slip ring according to claim 1, characterized in that: The number of ±Y-wing solar cell sub-arrays and slip ring power loops is determined based on the spacecraft power consumption requirements and the use of high and low voltages.

3. The method for optimizing the slip ring power distribution for reducing heat concentration of a spacecraft slip ring according to claim 2, characterized in that: Determining the number of ±Y-wing solar cell sub-arrays and slip ring power loops according to the power consumption requirements of the spacecraft and the use of high and low voltages includes: Determine the power demand P of the spacecraft, and obtain the voltage value U1 of the high-voltage solar cell subarray and the voltage value U2 of the low-voltage solar cell subarray according to the use demand of each single machine; obtain the current value I1 of the high-voltage solar cell subarray and the current value I2 of the low-voltage solar cell subarray according to the series-parallel relationship of the solar cell panels; set n high-voltage solar cell subarrays and m low-voltage solar cell subarrays to meet the power consumption demand of the spacecraft, and ensure that the electric energy generated by the solar cells is not less than the power consumption demand of the spacecraft; n×U1×I1+m×U2×I2≥P After dividing the n high-voltage solar cell subarrays and the m low-voltage solar cell subarrays equally, the number of each type of solar cell subarrays in the ±Y-wing solar cells is: n / 2 high-voltage solar cell subarrays and m / 2 low-voltage solar cell subarrays; Each solar cell subarray corresponds to two power loops, the ±Y-wing solar array drive mechanism has n high-voltage power loops and m low-voltage power loops.

4. The method for optimizing the slip ring power distribution for reducing heat concentration of a spacecraft slip ring according to claim 3, characterized in that: The high-voltage power loops are equally arranged at both ends of the slip ring; the low-voltage power loops are equally arranged in sequence inside the high-voltage power loops.

5. The method for optimizing the slip ring power distribution for reducing heat concentration of a spacecraft slip ring according to claim 4, characterized in that: Inside the two sets of symmetrical low-voltage power loops, several signal switching channels are arranged as needed for isolation.

6. The method for optimizing the slip ring power distribution for reducing heat concentration of a spacecraft slip ring according to claim 3, characterized in that: The resistance values ​​of the low-voltage power loop and the high-voltage power loop are similar, and after currents of different voltages flow through them, there is a difference in the heat generated; the high-voltage power loop generates a large amount of heat, while the low-voltage power loop generates a small amount of heat.

7. A slip ring power loop optimization distribution system for reducing heat concentration in a spacecraft slip ring, characterized in that: include: Module M1: divide the ±Y wing solar cells into sub-arrays to obtain the ±Y wing solar cell sub-arrays; Module M2: Set the correspondence between each subarray of ±Y-wing solar cells and the high-voltage subarray and low-voltage subarray of the power control device; Module M3: through the corresponding relationship between each sub-array of ±Y-wing solar cells and the power control device, the connection relationship between each sub-array of ±Y-wing solar cells and the slip ring power loop in the ±Y-wing solar sail driving mechanism is established to disperse the heat source inside the slip ring; The heat source is a power loop of a slip ring of a solar panel driving mechanism that generates heat after current passes through it.

8. The slip ring power loop optimization distribution system for reducing spacecraft slip ring heat concentration according to claim 7, characterized in that: Determine the number of ±Y-wing solar cell sub-arrays and slip ring power loops based on the spacecraft power consumption requirements and high and low voltage usage; Determining the number of ±Y-wing solar cell sub-arrays and slip ring power loops according to the power consumption requirements of the spacecraft and the use of high and low voltages includes: Determine the power demand P of the spacecraft, and obtain the voltage value U1 of the high-voltage solar cell subarray and the voltage value U2 of the low-voltage solar cell subarray according to the usage demand of each single machine; According to the series-parallel relationship of the solar cells, the current value I1 of the high-voltage solar cell subarray and the current value I2 of the low-voltage solar cell subarray are obtained; in order to meet the power consumption requirements of the spacecraft, n high-voltage solar cell subarrays and m low-voltage solar cell subarrays are set to ensure that the electric energy generated by the solar cells is not less than the power consumption requirements of the spacecraft; n×U1×I1+m×U2×I2≥P After dividing the n high-voltage solar cell subarrays and the m low-voltage solar cell subarrays equally, the number of each type of solar cell subarrays in the ±Y-wing solar cells is: n / 2 high-voltage solar cell subarrays and m / 2 low-voltage solar cell subarrays; Each solar cell subarray corresponds to two power loops, the ±Y-wing solar array drive mechanism has n high-voltage power loops and m low-voltage power loops.

9. The slip ring power loop optimization distribution system for reducing spacecraft slip ring heat concentration according to claim 8, characterized in that: The high-voltage power loops are equally arranged at both ends of the slip ring; the low-voltage power loops are equally arranged in sequence inside the high-voltage power loops; Inside the two sets of symmetrical low-voltage power loops, several signal switching channels are arranged as needed for isolation.

10. The slip ring power loop optimization distribution system for reducing spacecraft slip ring heat concentration according to claim 8, characterized in that: The resistance values ​​of the low-voltage power loop and the high-voltage power loop are similar, and after currents of different voltages flow through them, there is a difference in the heat generated; the high-voltage power loop generates a large amount of heat, while the low-voltage power loop generates a small amount of heat.

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