Optimal distribution method and system for reducing spacecraft slip ring heat concentration of slip ring power ring channel
By dividing the spacecraft slip ring into subarrays and optimizing the power loop arrangement, the problem of heat concentration in the slip ring was solved, and stable power supply and improved safety of the slip ring were achieved.
Patent Information
- Application Number
- CN202411242452.0
- Authority / Receiving Office
- CN · China
- Patent Type
- Patents(China)
- Current Assignee / Owner
- Filing Date
- 2024-09-05
- Publication Date
- 2025-11-18
- Estimated Expiration
- 2044-09-05
AI Technical Summary
The heat concentration in the power loop of a spacecraft slip ring leads to increased conductor resistance and aging of insulation materials, posing safety hazards such as overload and short circuit. Existing technologies lack effective heat dissipation solutions.
By dividing the ±Y-wing solar cells into subarrays, establishing the correspondence between high-voltage and low-voltage subarrays, and equally distributing the high-voltage power loop at both ends of the slip ring, while equally distributing the low-voltage power loop inside the high-voltage loop, combined with signal loop isolation, the heat source inside the slip ring is dispersed.
It effectively disperses heat inside the slip ring, reduces the power supply safety risks caused by high-temperature operation, avoids the risks of leakage and short circuit, and ensures that the slip ring can work stably for a long time under harsh heat dissipation conditions.
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Figure CN119099884B_ABST
Abstract
Description
TECHNICAL FIELD
[0001] The present application relates to the technical field of spacecraft, in particular, to a method and system for optimizing distribution of power ring channels of a spacecraft slip ring to reduce heat concentration of the spacecraft slip ring. BACKGROUND
[0002] Solar cells are connected to power supply control devices through power slip rings, so that the solar cells supply power to the spacecraft. When the sun shines on the solar cells, the generated current is transmitted to the spacecraft through the power slip rings. The heat generated by the closely arranged power ring 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 ring, and the closely arranged power ring channels generate a large amount of heat. When the temperature rises, the resistance of the conductor increases, thereby generating more heat, forming a vicious cycle, causing the local temperature of the slip ring to rise rapidly, and long-term high-temperature work causing the slip ring to have the safety hazards of overload and short circuit. In order to ensure sufficient energy supply of the spacecraft, the spacecraft generally selects an orbit with longer light period, and the working state of the slip ring for long-time power transmission cannot be avoided.
[0003] The power slip ring is used to transmit power of each solar cell subarray to the spacecraft. A large amount of heat is generated after the power ring channel overcurrent. The closely arranged power ring channels have a single heat dissipation path and slow heat dissipation, resulting in local heat concentration of the power slip ring.
[0004] According to the current design requirements of the slip ring, no specific arrangement rule is proposed for the large amount of heat generated by the power ring channel and the heat concentration. During the long light period, the power ring works for a long time and the heat accumulates. The large amount of heat generated by the power ring and the slow heat dissipation cause local high temperature of the power ring. On the one hand, high temperature leads to an increase in the resistance of the conductor, thereby increasing the heat generated by the power ring. On the other hand, high temperature accelerates the aging of the insulating material, which easily causes the risk of electric leakage and short circuit. SUMMARY
[0005] In view of the defects in the prior art, the purpose of the present application is to provide a method and system for optimizing distribution of power ring channels of a spacecraft slip ring to reduce heat concentration of the spacecraft slip ring.
[0006] According to the method for optimizing distribution of power ring channels of a spacecraft slip ring to reduce heat concentration of the spacecraft slip ring provided by the present application, the method comprises the following steps:
[0007] Step S1: dividing the ±Y wing solar cells into subarrays to obtain each solar cell subarray of the ±Y wing solar cells;
[0008] Step S2: setting a corresponding relationship between each solar cell subarray of the ±Y wing solar cells and high-voltage subarrays and low-voltage subarrays of the power supply control device;
[0009] Step S3: By establishing the correspondence between each subarray of the ±Y-wing solar cell and the power control device, establish the connection relationship between each subarray of the ±Y-wing solar cell and the slip ring power loop in the ±Y-wing solar panel drive mechanism, and disperse the heat source inside the slip ring.
[0010] The heat source is the power loop of the slip ring of the solar panel drive mechanism, which heats up after current passes through it.
[0011] Preferably, the number of ±Y-wing solar cell subarrays and slip ring power channels is determined based on the spacecraft's power consumption requirements and high and low voltage usage.
[0012] Preferably, determining the number of ±Y-wing solar cell subarrays and slip ring power channels based on the spacecraft's power consumption requirements and high / low voltage usage includes:
[0013] Determine the spacecraft's power requirement P, and obtain the voltage values U1 of the high-voltage solar cell subarray and U2 of the low-voltage solar cell subarray based on the usage requirements of each unit; obtain the current values I1 of the high-voltage solar cell subarray and I2 of the low-voltage solar cell subarray based on the series and parallel connection relationship of the solar cells; set up n high-voltage solar cell subarrays and m low-voltage solar cell subarrays to meet the spacecraft's power consumption requirements, ensuring that the electrical energy generated by the solar cells is not less than the spacecraft's power consumption requirements;
[0014] n×U1×I1+m×U2×I2≥P
[0015] After dividing the high-voltage solar cell subarray into n and the low-voltage solar cell subarray into m, the number of each type of solar cell subarray in the ±Y-wing solar cell is as follows: 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 evenly distributed at both ends of the slip ring; the low-voltage power loop is evenly distributed sequentially inside the high-voltage power loop.
[0018] Preferably, within the two sets of symmetrical low-voltage power loops, several signal switching channels are arranged for isolation as needed.
[0019] Preferably, the resistance values of the low-voltage power loop and the high-voltage power loop are similar, and the heat generated after currents of different voltages flow through them differs; the high-voltage power loop generates more heat, while the low-voltage power loop generates less heat.
[0020] According to the present invention, a slip ring power loop optimization allocation system for reducing heat concentration in spacecraft slip rings includes:
[0021] Module M1: Divide the ±Y-wing solar cells into subarrays to obtain each subarray of the ±Y-wing solar cells;
[0022] Module M2: Sets the correspondence between each subarray of the ±Y-wing solar cells and the high-voltage and low-voltage subarrays of the power control equipment;
[0023] Module M3: By establishing the correspondence between each subarray of the ±Y-wing solar cell and the power control equipment, the connection relationship between each subarray of the ±Y-wing solar cell and the slip ring power loop in the ±Y-wing solar panel drive mechanism is established, thereby dispersing the heat source inside the slip ring.
[0024] The heat source is the power loop of the slip ring of the solar panel drive mechanism, which heats up after current passes through it.
[0025] Preferably, the number of ±Y-wing solar cell subarrays and slip ring power channels is determined based on the spacecraft's power consumption requirements and high and low voltage usage.
[0026] The determination of the number of ±Y-wing solar cell subarrays and slip ring power channels based on spacecraft power consumption requirements and high / low voltage usage includes:
[0027] Determine the spacecraft's power requirement P, and obtain the voltage values U1 of the high-voltage solar cell subarray and U2 of the low-voltage solar cell subarray based on the usage requirements of each unit; obtain the current values I1 of the high-voltage solar cell subarray and I2 of the low-voltage solar cell subarray based on the series and parallel connection relationship of the solar cells; set up n high-voltage solar cell subarrays and m low-voltage solar cell subarrays to meet the spacecraft's power consumption requirements, ensuring that the electrical energy generated by the solar cells is not less than the spacecraft's power consumption requirements;
[0028] n×U1×I1+m×U2×I2≥P
[0029] After dividing the high-voltage solar cell subarray into n and the low-voltage solar cell subarray into m, the number of each type of solar cell subarray in the ±Y-wing solar cell is as follows: 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 loop is evenly distributed at both ends of the slip ring; the low-voltage power loop is evenly distributed and sequentially distributed inside the high-voltage power loop.
[0032] Inside the two sets of symmetrical low-voltage power loops, several signal switching channels are arranged for isolation as needed.
[0033] Preferably, the resistance values of the low-voltage power loop and the high-voltage power loop are similar, and the heat generated after currents of different voltages flow through them differs; the high-voltage power loop generates more heat, while the low-voltage power loop generates less heat.
[0034] Compared with the prior art, the present invention has the following beneficial effects:
[0035] 1. By unifying the rules for the arrangement of slip ring power channels, the standardization of slip ring interfaces has been achieved, the consistency of slip ring product design has been improved, and certain reference value has been provided for the allocation of slip ring channels for high-heat-generating slip rings.
[0036] 2. By arranging the power rings on both sides of the slip ring, the heat source inside the slip ring is dispersed, avoiding heat concentration caused by the large 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 subarray into equal parts and arranging them at both ends of the slip ring, and dividing the low-voltage solar cell subarray into equal parts and arranging them inside the high-voltage solar cell subarray, and arranging signal loops inside the two sets of low-voltage cell subarrays, the high-heat-generating power loops are arranged at both ends of the slip ring, which is conducive to the outward diffusion of heat. At the same time, heat is conducted to the low-heat-generating signal loops arranged inside. The power loops and signal loops dissipate heat to the outside through thermal radiation, effectively avoiding heat concentration inside the slip ring and avoiding the risk of leakage and short circuit caused by local high temperature in the slip ring.
[0038] 4. In response to the high power consumption requirements of modern spacecraft, long periods of sunlight exposure are a necessary requirement for slip rings to ensure a sufficient power supply. Slip rings themselves are components that generate a lot of heat and dissipate it slowly. By arranging power slip rings in a distributed manner, the heat source of the power ring is dispersed, thereby ensuring that the slip rings can work stably for a long time under harsh heat dissipation conditions. Attached Figure Description
[0039] Other features, objects, and advantages of the present invention will become more apparent from the following detailed description of non-limiting embodiments with reference to the accompanying drawings:
[0040] Figure 1 Flowchart of a method for optimizing the distribution of slip ring power loops to reduce slip ring heat concentration.
[0041] Figure 2 Flowchart for assigning slip ring tracks. Detailed Implementation
[0042] The present invention will now be described in detail with reference to specific embodiments. These embodiments will help those skilled in the art to further understand the present invention, but do not limit the invention in any way. It should be noted that those skilled in the art can make several changes and improvements without departing from the concept of the present invention. These all fall within the protection scope of the present invention.
[0043] Example 1
[0044] A method for optimizing slip ring power loop allocation to reduce slip ring heat concentration in spacecraft, provided by the present invention, includes:
[0045] Step S1: Divide the ±Y wing solar cells into subarrays to obtain each subarray of the ±Y wing solar cells;
[0046] Step S2: Set the correspondence between each subarray of the ±Y-wing solar cells and the high-voltage and low-voltage subarrays of the power control equipment;
[0047] Step S3: By establishing the correspondence between each subarray of the ±Y-wing solar cell and the power control device, establish the connection relationship between each subarray of the ±Y-wing solar cell and the slip ring power loop in the ±Y-wing solar panel drive mechanism, and disperse the heat source inside the slip ring.
[0048] The heat source is the power loop of the slip ring of the solar panel drive mechanism, which heats up after current passes through it.
[0049] This embodiment provides a method for optimizing the power distribution of slip rings to reduce heat concentration. This method disperses the heat sources inside the slip ring, reducing the risk of power supply safety issues such as overload and short circuits caused by high-temperature operation.
[0050] Specifically, the number of solar cell subarrays and slip ring power loops is determined based on the spacecraft's power consumption requirements and high and low voltage usage.
[0051] More specifically, based on the spacecraft's power consumption requirements and the high and low voltage usage, the number of high-voltage and low-voltage solar cell subarrays is determined, thereby obtaining the required number of slip ring power channels. First, the spacecraft's power requirement P is determined. Based on the usage requirements of each individual unit, the voltage values U1 of the high-voltage solar cell subarray and U2 of the low-voltage solar cell subarray are obtained. Based on the series and parallel connection relationship of the solar cells, the current values I1 and I2 of the high-voltage and low-voltage solar cell subarrays are obtained. To meet the spacecraft's power consumption requirements, n high-voltage solar cell subarrays and m low-voltage solar cell subarrays are set, ensuring that the electrical energy generated by the solar cells is not less than the spacecraft's power consumption requirement: n×U1×I1+m×U2×I2≥P. After equally dividing the n high-voltage and m low-voltage solar cell subarrays, 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 both positive and negative sides, meaning each solar cell subarray corresponds to two power loops. Therefore, the ±Y-wing solar array drive mechanism has n high-voltage power loops and m low-voltage power loops.
[0052] The drive mechanism slip rings are distributed in loops. The high-voltage power loops are divided equally and arranged at both ends of the slip rings. The low-voltage power loops are divided equally and arranged sequentially inside the high-voltage power loops. Inside the two sets of low-voltage power loops, several signal loops are arranged for isolation as needed.
[0053] Furthermore, the matching method for establishing the power loop of the ±Y-wing solar cell subarray and the ±Y-wing solar panel drive mechanism is as follows: establish the positional arrangement relationship of the high-voltage power loop and the low-voltage power loop, so that the power loop with high heat generation is located at both ends of the slip ring, which is conducive to heat radiation to the outside of the slip ring, and the low-voltage power loop and signal loop with low heat generation are arranged on the inside, which isolates the power loops on both sides and avoids high temperature inside the slip ring.
[0054] Furthermore, since the resistance values of each power ring are similar, the heat generated varies significantly when current of different voltages flows through them. When current flows through the power slip rings, the high-voltage subarray generates more heat, while the low-voltage subarray generates less heat.
[0055] Furthermore, the heat concentration is generated by the power loop overcurrent.
[0056] This invention also provides a slip ring power loop optimization allocation system for reducing heat concentration in spacecraft slip rings. The slip ring power loop optimization allocation system for reducing heat concentration in spacecraft slip rings can be implemented by executing the process steps of the slip ring power loop optimization allocation method for reducing heat concentration in spacecraft slip rings. That is, those skilled in the art can understand the slip ring power loop optimization allocation method for reducing heat concentration in spacecraft slip rings as a preferred embodiment of the slip ring power loop optimization allocation system for reducing heat concentration in spacecraft slip rings.
[0057] Example 2
[0058] According to the present invention, a method for optimizing the allocation of slip ring power channels to reduce heat concentration in spacecraft slip rings is provided, such as... Figure 1 ,include:
[0059] Step 1: Divide the solar cell sub-arrays into ±Y wings;
[0060] Specifically, the number of solar cell subarrays and slip ring power channels is determined based on the spacecraft's power consumption requirements;
[0061] Step 2: Establish the correspondence between each subarray of the ±Y-wing solar cell and the power control equipment;
[0062] Specifically, the correspondence between the ±Y-wing solar cell subarray and the power control equipment is established, and the number of high-voltage and low-voltage subarrays of the ±Y-wing solar cell subarray is determined, thereby obtaining the number of high-voltage and low-voltage power loops of the ±Y-wing solar panel drive mechanism power loop.
[0063] Step 3: After the high-voltage power loop is divided into equal parts, it is arranged at both ends of the slip ring. After the low-voltage power loop is divided into equal parts, it is arranged sequentially inside the high-voltage power loop. Inside the two sets of low-voltage power loops, several signal loops are arranged for isolation as needed.
[0064] The specific embodiments of the present invention will be further described in detail below with reference to the accompanying drawings and examples.
[0065] Specifically, step 1 includes:
[0066] Based on the spacecraft's power consumption requirements and high and low voltage usage, the number of solar cell subarrays and slip ring power loops is determined to ensure that the number of solar cell subarrays on the ±Y wings matches the number of power loops in the ±Y wing solar panel drive mechanism, minimizing empty loops. Taking a certain spacecraft as an example, the total satellite power requirement is 4500W, with 80V high-voltage circuits and 16V low-voltage circuits. After equal distribution, the ±Y wings each have 4 high-voltage subarrays and 8 low-voltage subarrays, meaning that each solar panel drive mechanism slip ring on the ±Y wings has 4 high-voltage power loops and 8 low-voltage power loops, with 8 signal loops arranged in the middle.
[0067] Based on the spacecraft's power consumption requirements and the use of high and low voltage, the number of high-voltage and low-voltage solar cell subarrays is determined, thereby obtaining the required number of slip ring power channels. First, the spacecraft's power requirement P is determined. Based on the usage requirements of each individual unit, the voltage values U1 of the high-voltage solar cell subarray and U2 of the low-voltage solar cell subarray are obtained. Based on the series and parallel connection relationship of the solar cells, the current values I1 and I2 of the high-voltage and low-voltage solar cell subarrays are obtained. To meet the spacecraft's power consumption requirements, n high-voltage solar cell subarrays and m low-voltage solar cell subarrays are set, ensuring that the electrical energy generated by the solar cells is not less than the spacecraft's power consumption requirement: n×U1×I1+m×U2×I2≥P. The number of slip ring power channels for the solar panel drive mechanism is consistent with the number of high-voltage and low-voltage solar cell subarrays. After equally dividing the n high-voltage and m low-voltage solar cell subarrays, 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 both positive and negative sides, meaning each solar cell subarray corresponds to two power loops. Therefore, the ±Y-wing solar array drive mechanism has n high-voltage power loops and m low-voltage power loops. Taking a spacecraft as an example, if the overall satellite power requirement is 8000W, assuming the voltage of the high-voltage solar cell subarray required by the spacecraft is U1 = 80V, the voltage of the low-voltage solar cell subarray is U2 = 30V, the current of the high-voltage solar cell subarray is I1 = 8A, and the current of the low-voltage solar cell subarray is I2 = 6A, 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 up 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. The calculation is: n × U1 × I1 + m × U2 × I2 = 8 × 80V × 8A + 16 × 30V × 6A = 8320W ≥ 8000W. Therefore, the above-mentioned 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 solar cell subarrays in the ±Y wings is as follows: 4 high-voltage solar cell subarrays and 8 low-voltage solar cell subarrays. Each solar cell subarray requires one power loop for both positive and negative terminals, meaning each solar cell subarray corresponds to two power loops. Therefore, the ±Y wing solar array drive mechanism has 8 high-voltage power loops and 16 low-voltage power loops. Assuming each wing also requires 8 signal loops, the ±Y wing solar panel drive mechanism has 8 high-voltage power loops, 16 low-voltage power loops, and 8 signal loops within its slip rings.
[0068] Step 3 involves distributing the high-voltage and low-voltage subarrays into loops. The high-voltage subarray power loops are equally divided and arranged at both ends of the slip ring. The low-voltage subarray power loops are equally divided and arranged inside the high-voltage subarray. Several signal loops are then arranged inside the two sets of low-voltage subarray power loops as needed. Taking a certain spacecraft as an example...Figure 2 As shown, the ±Y-wing solar panel drive mechanism has 4 high-voltage power channels and 8 low-voltage power channels in each slip ring. The high-voltage subarray power channels are divided equally and arranged at both ends of the slip ring. The low-voltage subarray power channels are divided equally and arranged inside the high-voltage subarray. Inside the two sets of low-voltage subarray power channels, 8 signal channels are arranged as needed.
[0069] Those skilled in the art will understand that, besides implementing the system and its various devices, modules, and units provided by this invention in the form of purely computer-readable program code, the same functions can be achieved entirely through logical programming of the method steps, making the system and its various devices, modules, and units of this invention function in the form of logic gates, switches, application-specific integrated circuits, programmable logic controllers, and embedded microcontrollers. Therefore, the system and its various devices, modules, and units provided by this invention can be considered as a hardware component, and the devices, modules, and units included therein for implementing various functions can also be considered as structures within the hardware component; alternatively, the devices, modules, and units for implementing various functions can be considered as both software modules implementing the method and structures within the hardware component.
[0070] Specific embodiments of the present invention have been described above. It should be understood that the present invention is not limited to the specific embodiments described above, and those skilled in the art can make various changes or modifications within the scope of the claims, which do not affect the essence of the present invention. Unless otherwise specified, the embodiments and features described in this application can be arbitrarily combined with each other.
Claims
1. A method for optimizing the distribution of slip ring power loops to reduce heat concentration in spacecraft slip rings, characterized in that, include: Step S1: Divide the ±Y wing solar cells into subarrays to obtain each subarray of the ±Y wing solar cells; Step S2: Set the correspondence between each subarray of the ±Y-wing solar cells and the high-voltage and low-voltage subarrays of the power control equipment; Step S3: By establishing the correspondence between each subarray of the ±Y-wing solar cell and the power control device, establish the connection relationship between each subarray of the ±Y-wing solar cell and the slip ring power loop in the ±Y-wing solar panel drive mechanism, and disperse the heat source inside the slip ring. The heat source is the power loop of the slip ring of the solar panel drive mechanism, which heats up after current passes through it. The number of ±Y-wing solar cell subarrays and slip ring power channels is determined based on the spacecraft's power consumption requirements and high and low voltage usage. The determination of the number of ±Y-wing solar cell subarrays and slip ring power channels based on spacecraft power consumption requirements and high / low voltage usage includes: Determine the spacecraft's power requirement P, and obtain the voltage values U1 of the high-voltage solar cell subarray and U2 of the low-voltage solar cell subarray based on the usage requirements of each individual unit. The current values I1 of the high-voltage solar cell subarray and I2 of the low-voltage solar cell subarray are obtained based on the series and parallel connection relationship of the solar cells. 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 electrical energy generated by the solar cells is not less than the power consumption requirements of the spacecraft. After dividing the high-voltage solar cell subarray into n and the low-voltage solar cell subarray into m, the number of each type of solar cell subarray in the ±Y-wing solar cell is as follows: 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. The high-voltage power loop is evenly distributed at both ends of the slip ring; the low-voltage power loop is evenly distributed in sequence inside the high-voltage power loop.
2. The method for optimizing slip ring power distribution to reduce heat concentration in spacecraft slip rings according to claim 1, characterized in that, Inside the two sets of symmetrical low-voltage power loops, several signal switching channels are arranged for isolation as needed.
3. The method for optimizing slip ring power distribution to reduce heat concentration in spacecraft slip rings according to claim 1, characterized in that, The resistance values of the low-voltage power loop and the high-voltage power loop are similar, and the heat generated differs after current of different voltages flows through them; the high-voltage power loop generates more heat, while the low-voltage power loop generates less heat.
4. A slip ring power loop optimization distribution system for reducing heat concentration in spacecraft slip rings, characterized in that, include: Module M1: Divide the ±Y-wing solar cells into subarrays to obtain each subarray of the ±Y-wing solar cells; Module M2: Sets the correspondence between each subarray of the ±Y-wing solar cells and the high-voltage and low-voltage subarrays of the power control equipment; Module M3: By establishing the correspondence between each subarray of the ±Y-wing solar cell and the power control equipment, the connection relationship between each subarray of the ±Y-wing solar cell and the slip ring power loop in the ±Y-wing solar panel drive mechanism is established, thereby dispersing the heat source inside the slip ring. The heat source is the power loop of the slip ring of the solar panel drive mechanism, which heats up after current passes through it. The number of ±Y-wing solar cell subarrays and slip ring power channels is determined based on the spacecraft's power consumption requirements and high and low voltage usage. The determination of the number of ±Y-wing solar cell subarrays and slip ring power channels based on spacecraft power consumption requirements and high / low voltage usage includes: Determine the spacecraft's power requirement P, and obtain the voltage values U1 of the high-voltage solar cell subarray and U2 of the low-voltage solar cell subarray based on the usage requirements of each individual unit. The current values I1 of the high-voltage solar cell subarray and I2 of the low-voltage solar cell subarray are obtained based on the series and parallel connection relationship of the solar cells. 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 electrical energy generated by the solar cells is not less than the power consumption requirements of the spacecraft. After dividing the high-voltage solar cell subarray into n and the low-voltage solar cell subarray into m, the number of each type of solar cell subarray in the ±Y-wing solar cell is as follows: 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. The high-voltage power loop is evenly distributed at both ends of the slip ring; the low-voltage power loop is evenly distributed in sequence inside the high-voltage power loop.
5. The slip ring power loop optimization distribution system for reducing heat concentration in spacecraft slip rings according to claim 4, characterized in that, Inside the two sets of symmetrical low-voltage power loops, several signal switching channels are arranged for isolation as needed.
6. The slip ring power loop optimization distribution system for reducing heat concentration in spacecraft slip rings according to claim 4, characterized in that, The resistance values of the low-voltage power loop and the high-voltage power loop are similar, and the heat generated differs after current of different voltages flows through them; the high-voltage power loop generates more heat, while the low-voltage power loop generates less heat.
Citation Information
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