CN111697681A - Multi-path charging shunt control system and method for spacecraft - Google Patents
Multi-path charging shunt control system and method for spacecraft Download PDFInfo
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- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02J—CIRCUIT ARRANGEMENTS OR SYSTEMS FOR SUPPLYING OR DISTRIBUTING ELECTRIC POWER; SYSTEMS FOR STORING ELECTRIC ENERGY
- H02J7/00—Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries
- H02J7/34—Parallel operation in networks using both storage and other DC sources, e.g. providing buffering
- H02J7/35—Parallel operation in networks using both storage and other DC sources, e.g. providing buffering with light sensitive cells
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- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02J—CIRCUIT ARRANGEMENTS OR SYSTEMS FOR SUPPLYING OR DISTRIBUTING ELECTRIC POWER; SYSTEMS FOR STORING ELECTRIC ENERGY
- H02J7/00—Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries
- H02J7/0063—Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries with circuits adapted for supplying loads from the battery
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- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02J—CIRCUIT ARRANGEMENTS OR SYSTEMS FOR SUPPLYING OR DISTRIBUTING ELECTRIC POWER; SYSTEMS FOR STORING ELECTRIC ENERGY
- H02J7/00—Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries
- H02J7/0068—Battery or charger load switching, e.g. concurrent charging and load supply
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
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- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
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Abstract
本发明公开了一种用于航天器的多路充电分流控制系统，包括：充电太阳阵；充电切换开关，第一端与充电太阳阵的正极连接；负载，第一端与充电切换开关的第二端连接，第二端与充电太阳阵的负极连接；蓄电池组，正极与充电切换开关的第三端连接，负极与充电太阳阵的负极连接；放电电路，第一端与蓄电池组的正极连接，第二端与负载的第一端连接；充电分流控制电路，第一端与充电太阳阵的正极连接，第二端与充电太阳阵的负极连接，第三端与负载连接，第四端与蓄电池组连接。此发明解决了传统电路结构复杂，放电损耗高的问题，通过充电太阳阵和蓄电池组共同对负载充电，降低了成本，保证了放电利用率，降低了损耗，提高了能量的利用率和航天器的性能。
The invention discloses a multi-channel charging and shunting control system for a spacecraft, comprising: a charging solar array; a charging switch, the first end of which is connected to the positive pole of the charging solar array; the load, the first end of which is connected to the first end of the charging switch. The two ends are connected, and the second end is connected to the negative electrode of the charging solar array; the battery pack, the positive electrode is connected to the third end of the charging switch, and the negative electrode is connected to the negative electrode of the charging solar array; the discharge circuit, the first end is connected to the positive electrode of the battery pack , the second end is connected to the first end of the load; the charging shunt control circuit, the first end is connected to the positive electrode of the charging solar array, the second end is connected to the negative electrode of the charging solar array, the third end is connected to the load, and the fourth end is connected to Battery pack connection. This invention solves the problems of complex structure of traditional circuit and high discharge loss. By charging the load with the solar array and the battery pack together, the cost is reduced, the discharge utilization rate is guaranteed, the loss is reduced, and the energy utilization rate and the spacecraft are improved. performance.
Description
技术领域technical field
本发明涉及空间电源技术领域，具体涉及一种用于航天器的多路充电分流控制系统及其方法。The invention relates to the technical field of space power supplies, in particular to a multi-channel charging shunt control system and a method thereof for spacecraft.
背景技术Background technique
空间电源系统设计的先进思想是小型化、集成化。同时，近年来航天器的电源系统多采用顺序开关分流串联调节器(S4R)型电路，其结构复杂，器件繁多，体积大、重量大，导致成本高。The advanced idea of space power system design is miniaturization and integration. At the same time, in recent years, the power system of spacecraft mostly adopts sequential switch shunt series regulator (S 4 R) type circuit, which has complex structure, many devices, large volume and heavy weight, resulting in high cost.
同时，传统S4R型电路的放电效率损耗高，技术性能差，灵活性差，太阳电池阵的能量利用率低，其航天器的性能和效益都有待改进。At the same time, the traditional S 4 R type circuit has high discharge efficiency loss, poor technical performance and poor flexibility, and the energy utilization rate of the solar array is low, and the performance and benefits of its spacecraft need to be improved.
发明内容SUMMARY OF THE INVENTION
本发明的目的是提供一种用于航天器的多路充电分流控制系统。此系统旨在解决传统S4R型电路的结构复杂，且放电效率损耗高的问题，通过设置多路充电分流控制电路和充电切换开关，利用充电太阳阵和蓄电池组共同对负载充电，节省器件，降低成本，且保证放电的利用率，降低放电损耗，提高能量的利用率和航天器的性能。The purpose of the present invention is to provide a multi-channel charging shunt control system for spacecraft. This system is designed to solve the problems of complex structure and high discharge efficiency loss of the traditional S 4 R circuit. By setting up multiple charging shunt control circuits and charging switching switches, the charging solar array and the battery pack are used to jointly charge the load, saving components. , reduce the cost, and ensure the utilization rate of discharge, reduce the discharge loss, improve the utilization rate of energy and the performance of the spacecraft.
为达到上述目的，本发明提供了一种用于航天器的多路充电分流控制系统，包括充电太阳阵、充电切换开关、负载、蓄电池组、放电电路和充电分流控制电路；充电太阳阵将太阳能转换为电能；充电切换开关的第一端与充电太阳阵的正极连接；负载的第一端与充电切换开关的第二端连接，第二端与充电太阳阵的负极连接，构成第一回路；通过切换充电切换开关接通第一回路，充电太阳阵为负载供电；蓄电池组的正极与充电切换开关的第三端连接，负极与充电太阳阵的负极连接，构成第二回路；通过切换充电切换开关接通第二回路，充电太阳阵为蓄电池组供电；放电电路的第一端与蓄电池组的正极连接，第二端与负载的第一端连接，则蓄电池组、放电电路和负载构成第三回路，蓄电池组通过放电电路为负载供电；充电分流控制电路的第一端与充电太阳阵的正极连接，第二端与充电太阳阵的负极连接，则充电分流控制电路与充电太阳阵构成第四回路；且充电分流控制电路的第三端与负载连接，第四端与蓄电池组连接，根据负载和蓄电池组的分压电压，判定充电太阳阵的供电回路，来输出充电太阳阵的电能。In order to achieve the above object, the present invention provides a multi-channel charging shunt control system for spacecraft, including a charging solar array, a charging switch, a load, a battery pack, a discharge circuit and a charging shunt control circuit; Converted into electrical energy; the first end of the charging switch is connected to the positive electrode of the charging solar array; the first end of the load is connected to the second end of the charging switch, and the second end is connected to the negative electrode of the charging solar array, forming a first loop; The first loop is connected by switching the charging switch, and the charging solar array supplies power to the load; the positive pole of the battery pack is connected to the third end of the charging switch, and the negative pole is connected to the negative pole of the charging solar array to form the second loop; by switching the charging switch The switch is connected to the second circuit, and the charging solar array supplies power to the battery pack; the first end of the discharge circuit is connected to the positive pole of the battery pack, and the second end is connected to the first end of the load, then the battery pack, the discharge circuit and the load constitute the third loop, the battery pack supplies power to the load through the discharge circuit; the first end of the charging shunt control circuit is connected to the positive pole of the charging solar array, and the second end is connected to the negative pole of the charging solar array, then the charging shunt control circuit and the charging solar array form the fourth The third end of the charging shunt control circuit is connected to the load, and the fourth end is connected to the battery pack. According to the partial voltage of the load and the battery pack, the power supply circuit of the charging solar array is determined to output the electric energy of the charging solar array.
最优选的，充电分流控制电路包括开关管、运算放大器、三角波发射器和PI信号器；开关管的第一端与充电太阳阵的正极连接，第二端与充电太阳阵的负极连接；运算放大器的第一端与开关管的第三端连接，第二端与三角波发射器连接；三角波发射器用于发射基准信号；PI信号器的第一端与运算放大器的第三端连接，第二端与负载连接，第三端与蓄电池组连接，用于分别获取负载的分压电压和蓄电池组的分压电压，从而得到充电太阳阵的PI信号；运算放大器将PI信号与基准信号进行比较计算，以控制开关管的开闭。Most preferably, the charging shunt control circuit includes a switch tube, an operational amplifier, a triangular wave transmitter and a PI annunciator; the first end of the switch tube is connected to the positive pole of the charging solar array, and the second end is connected to the negative pole of the charging solar array; the operational amplifier The first end of the PI signal device is connected to the third end of the switch tube, and the second end is connected to the triangular wave transmitter; the triangular wave transmitter is used to transmit the reference signal; the first end of the PI signal device is connected to the third end of the operational amplifier, and the second end is connected to the The load is connected, and the third end is connected to the battery pack, which is used to obtain the partial voltage of the load and the partial voltage of the battery pack respectively, so as to obtain the PI signal of the charging solar array; the operational amplifier compares the PI signal with the reference signal to calculate Control the opening and closing of the switch tube.
最优选的，PI信号器包括信号切换开关、母线基准信号器和充电基准信号器；信号切换开关的第一端与运算放大器的第三端连接；母线基准信号器的第一端与信号切换开关的第二端连接，第二端与负载连接，用于获取负载的分压电压；充电基准信号器的第一端与信号切换开关的第三端连接，第二端与蓄电池组连接，用于获取蓄电池组的分压电压；信号切换开关根据负载的分压电压和蓄电池组的分压电压，分别切换母线基准信号器和充电基准信号器，从而获得充电太阳阵的PI信号。Most preferably, the PI annunciator includes a signal switch, a bus reference annunciator and a charging reference annunciator; the first end of the signal switch is connected to the third end of the operational amplifier; the first end of the bus reference annunciator is connected to the signal switch. The second end of the charging reference signal device is connected to the second end, and the second end is connected to the load, which is used to obtain the divided voltage of the load; the first end of the charging reference signal device is connected to the third end of the signal switch, and the second end is connected to the battery pack for use. Obtain the divided voltage of the battery pack; the signal switch switches the bus reference annunciator and the charging reference annunciator respectively according to the divided voltage of the load and the divided voltage of the battery pack, so as to obtain the PI signal of the charging solar array.
最优选的，充电太阳阵与充电切换开关之间还设置有二极管。Most preferably, a diode is also arranged between the charging solar array and the charging switch.
最优选的，充电太阳阵的数量为若干个，则充电分流控制电路和二极管的数量对应为若干个。Most preferably, the number of charging solar arrays is several, and the number of charging shunt control circuits and diodes corresponds to several.
最优选的，充电切换开关与蓄电池组之间还设置有充电开关，用于控制第二回路的通断。Most preferably, a charging switch is also provided between the charging switch and the battery pack, which is used to control the on-off of the second loop.
最优选的，蓄电池组与放电电路之间还设置有放电开关，用于控制第三回路的通断。Most preferably, a discharge switch is also provided between the battery pack and the discharge circuit for controlling the on-off of the third loop.
最优选的，充电切换开关为若干个。Most preferably, there are several charging switches.
本发明还提供了一种用于航天器的多路充电分流控制方法，该方法是基于一种用于航天器的多路充电分流控制系统实现的，该方法包括以下步骤：The present invention also provides a multi-channel charging shunt control method for spacecraft, the method is realized based on a multi-channel charging shunt control system for spacecraft, and the method includes the following steps:
步骤1：充电分流控制电路分别获取负载和蓄电池组的分压电压，并第一次判断负载的分压电压是否小于充电太阳阵的基准信号；Step 1: The charging shunt control circuit obtains the divided voltages of the load and the battery pack respectively, and judges for the first time whether the divided voltage of the load is less than the reference signal of the charging solar array;
步骤2：若是，即负载的分压电压小于基准信号，则信号切换开关切换至母线基准信号器，第四回路断开，第一回路和第三回路导通，充电太阳阵和蓄电池组同时为负载供电；Step 2: If it is, that is, the partial voltage of the load is less than the reference signal, the signal switch is switched to the bus reference signal, the fourth circuit is disconnected, the first circuit and the third circuit are connected, and the charging solar array and the battery pack are at the same time. load power supply;
步骤3：若否，即负载的分压电压大于额定电压，信号切换开关切换至充电基准信号器，则第二次判断蓄电池组的分压电压是否小于基准信号；Step 3: If no, that is, the divided voltage of the load is greater than the rated voltage, and the signal switch is switched to the charging reference signal device, then judge for the second time whether the divided voltage of the battery pack is less than the reference signal;
步骤4：若是，即负载的分压电压大于额定电压，且蓄电池组的分压电压小于基准信号，第四回路断开，第二回路导通，充电太阳阵为蓄电池组供电；Step 4: If yes, that is, the partial voltage of the load is greater than the rated voltage, and the partial voltage of the battery pack is less than the reference signal, the fourth loop is disconnected, the second loop is turned on, and the charging solar array supplies power to the battery pack;
步骤5：若否，即负载和蓄电池组的分压电压均大于基准信号，则第四回路导通，充电太阳阵的电能直接分流掉。Step 5: If no, that is, the divided voltages of the load and the battery pack are both greater than the reference signal, the fourth loop is turned on, and the electric energy of the charging solar array is directly shunted.
最优选的，充电分流控制电路分别通过母线基准信号器和充电基准信号器，分别获取负载和蓄电池组的分压电压。Most preferably, the charging current split control circuit obtains the divided voltages of the load and the battery pack respectively through the bus reference annunciator and the charging reference annunciator.
运用此发明，解决了传统S4R型电路的结构复杂，且放电效率损耗高的问题，通过设置多路充电分流控制电路和充电切换开关，采用充电太阳阵和蓄电池组共同对负载充电，节省了器件，降低了成本，且保证了放电的利用率，降低了放电损耗，提高了能量的利用率和航天器的性能。This invention solves the problems of complex structure of traditional S 4 R type circuit and high loss of discharge efficiency. By setting up multiple charging shunt control circuits and charging switching switches, the charging solar array and battery pack are used to jointly charge the load, saving energy. The device is reduced, the cost is reduced, the utilization rate of discharge is guaranteed, the discharge loss is reduced, and the utilization rate of energy and the performance of the spacecraft are improved.
相对于现有技术，本发明具有以下有益效果：Compared with the prior art, the present invention has the following beneficial effects:
1、本发明提供的多路充电分流控制系统结构简单，易于实现，技术性能高、灵活性强，节省了器件，减小了体积，降低了成本。1. The multi-channel charging shunt control system provided by the present invention is simple in structure, easy to implement, high in technical performance, strong in flexibility, saves components, reduces volume, and reduces cost.
2、本发明提供的多路充电分流控制系统相比于传统的S4R型电路，避免了放电效率的损耗，提高了能量利用率和航天器的性能。2. Compared with the traditional S 4 R type circuit, the multi-channel charging and shunt control system provided by the present invention avoids the loss of discharge efficiency and improves the energy utilization rate and the performance of the spacecraft.
附图说明Description of drawings
图1为本发明提供的多路充电分流控制系统的结构示意图。FIG. 1 is a schematic structural diagram of a multi-channel charging shunt control system provided by the present invention.
具体实施方式Detailed ways
以下结合附图通过具体实施例对本发明作进一步的描述，这些实施例仅用于说明本发明，并不是对本发明保护范围的限制。The present invention will be further described below with reference to the accompanying drawings through specific embodiments. These embodiments are only used to illustrate the present invention, and are not intended to limit the protection scope of the present invention.
本发明是一种用于航天器的多路充电分流控制系统，如图1所示，包括充电太阳阵1、充电切换开关K、负载2、蓄电池组3、放电电路4和充电分流控制电路5。The present invention is a multi-channel charging shunt control system for spacecraft, as shown in FIG. .
其中，充电太阳阵1将太阳能转换为电能；充电切换开关K的第一端与充电太阳阵1的正极连接；负载2的第一端与充电切换开关K的第二端连接，第二端与充电太阳1阵的负极连接，构成第一回路；通过切换充电切换开关K接通第一回路，充电太阳阵1为负载2供电。Among them, the charging solar array 1 converts solar energy into electrical energy; the first end of the charging switch K is connected to the positive electrode of the charging solar array 1; the first end of the load 2 is connected to the second end of the charging switch K, and the second end is connected to The negative pole of the charging solar array 1 is connected to form the first loop; the first loop is connected by switching the charging switch K, and the charging solar array 1 supplies power to the load 2.
蓄电池组3的正极与充电切换开关K的第三端连接，负极与充电太阳阵1的负极连接，构成第二回路；通过切换充电切换开关K接通第二回路，充电太阳阵1为蓄电池组3供电。The positive pole of the battery pack 3 is connected to the third end of the charging switch K, and the negative pole is connected to the negative pole of the charging solar array 1 to form a second loop; by switching the charging switch K to connect the second loop, the charging solar array 1 is the battery pack 3 power supply.
放电电路4的第一端与蓄电池组3的正极连接，第二端与负载1的第一端连接，则蓄电池组3、放电电路4和负载2构成第三回路，蓄电池组3通过放电电路4为负载2供电。The first end of the discharge circuit 4 is connected to the positive pole of the battery pack 3, and the second end is connected to the first end of the load 1, then the battery pack 3, the discharge circuit 4 and the load 2 form a third loop, and the battery pack 3 passes through the discharge circuit 4. Supply power to load 2.
充电分流控制电路5的第一端与充电太阳阵1的正极连接，第二端与充电太阳阵1的负极连接，则充电分流控制电路5与充电太阳阵1构成第四回路；且充电分流控制电路5的第三端与负载2连接，第四端与蓄电池组3连接，根据负载2和蓄电池组3的分压电压，判定充电太阳阵1的供电回路，来输出充电太阳阵1的电能。The first end of the charging shunt control circuit 5 is connected to the positive electrode of the charging solar array 1, and the second end is connected to the negative electrode of the charging solar array 1, then the charging shunt control circuit 5 and the charging solar array 1 form a fourth loop; and the charging shunt control The third end of the circuit 5 is connected to the load 2, and the fourth end is connected to the battery pack 3. According to the divided voltage between the load 2 and the battery pack 3, the power supply circuit for charging the solar array 1 is determined to output the electric energy for charging the solar array 1.
在本实施例中，充电分流控制电路5包括开关管M、运算放大器C、三角波发射器6和PI信号器。In this embodiment, the charging shunt control circuit 5 includes a switch tube M, an operational amplifier C, a triangular wave transmitter 6 and a PI annunciator.
其中，开关管M的第一端与充电太阳阵1的正极连接，第二端与充电太阳阵1的负极连接；运算放大器C的第一端与开关管M的第三端连接，第二端与三角波发射器6连接；三角波发射器用于发射基准信号；PI信号器的第一端与运算放大器C的第三端连接，第二端与负载2连接，第三端与蓄电池组3连接，用于分别获取负载2的分压电压和蓄电池组3的分压电压，从而得到充电太阳阵1的PI信号。The first end of the switch tube M is connected to the positive pole of the charging solar array 1, and the second end is connected to the negative pole of the charging solar array 1; the first end of the operational amplifier C is connected to the third end of the switch tube M, and the second end Connect with the triangular wave transmitter 6; the triangular wave transmitter is used to transmit the reference signal; the first end of the PI signal device is connected with the third end of the operational amplifier C, the second end is connected with the load 2, and the third end is connected with the battery pack 3, with In order to obtain the divided voltage of the load 2 and the divided voltage of the battery pack 3 respectively, the PI signal for charging the solar array 1 is obtained.
其中，PI信号器包括信号切换开关S、母线基准信号器7和充电基准信号器8；信号切换开关S的第一端与运算放大器C的第三端连接；母线基准信号器7的第一端与信号切换开关S的第二端连接，第二端与负载2连接，用于获取负载2的分压电压；充电基准信号器8的第一端与信号切换开关S的第三端连接，第二端与蓄电池组3连接，用于获取蓄电池组3的分压电压；信号切换开关S根据负载2的分压电压和蓄电池组3的分压电压，分别切换母线基准信号器7和充电基准信号器8，从而获得充电太阳阵1的PI信号；运算放大器C将PI信号与基准信号进行比较计算，以控制开关管M的开闭。The PI annunciator includes a signal switch S, a bus reference annunciator 7 and a charging reference annunciator 8; the first end of the signal switch S is connected to the third end of the operational amplifier C; the first end of the bus reference annunciator 7 It is connected to the second end of the signal switch S, and the second end is connected to the load 2 to obtain the divided voltage of the load 2; the first end of the charging reference annunciator 8 is connected to the third end of the signal switch S, and the first The two terminals are connected to the battery pack 3 to obtain the divided voltage of the battery pack 3; the signal switch S switches the bus reference signal device 7 and the charging reference signal respectively according to the divided voltage of the load 2 and the divided voltage of the battery pack 3 The device 8 is used to obtain the PI signal of the charged solar array 1; the operational amplifier C compares the PI signal with the reference signal to control the opening and closing of the switch tube M.
充电太阳阵1与充电切换开关K之间还设置有二极管D；充电切换开关K与蓄电池组3之间还设置有充电开关KC，用于控制第二回路的通断；蓄电池组3与放电电路4之间还设置有放电开关KF，用于控制第三回路的通断。A diode D is also set between the charging solar array 1 and the charging switch K; a charging switch K C is also set between the charging switch K and the battery pack 3 to control the on-off of the second loop; the battery pack 3 is connected to the discharge A discharge switch K F is also arranged between the circuits 4 for controlling the on-off of the third loop.
在本实施例中，充电开关KC为两个并联的继电器开关，控制第二回路的通断；放电开关KF为两个并联的继电器开关，控制第三回路的通断。In this embodiment, the charging switch K C is two parallel relay switches that control the on-off of the second loop; the discharge switch K F is two parallel-connected relay switches that control the on-off of the third loop.
充电太阳阵1的数量为n个，则充电分流控制电路5和二极管D的数量对应为n个。The number of charging solar arrays 1 is n, and the number of charging shunt control circuits 5 and diodes D corresponds to n.
充电切换开关K为m个；在本实施例中，当充电分流电路5的数量较多时，可以采用每两路共用一个充电切换开关K以节省数量，即当充电分流控制电路5为n个时，充电切换开关m为n/2个。The number of charging switching switches K is m; in this embodiment, when the number of charging shunt circuits 5 is large, one charging switching switch K can be shared for every two circuits to save the number, that is, when the number of charging shunt control circuits 5 is n , the charging switch m is n/2.
蓄电池组3为单体串联的锂离子蓄电池组。The battery pack 3 is a lithium-ion battery pack with cells connected in series.
本发明还提供了一种用于航天器的多路充电分流控制方法，该方法是基于一种用于航天器的多路充电分流控制系统实现的，该方法包括以下步骤：The present invention also provides a multi-channel charging shunt control method for spacecraft, the method is realized based on a multi-channel charging shunt control system for spacecraft, and the method includes the following steps:
步骤1：充电分流控制电路5分别通过母线基准信号器7和充电基准信号器8，分别获取负载2和蓄电池组3的分压电压，并通过运算放大器C第一次判断负载2的分压电压是否小于三角波发射器6发射的基准信号。Step 1: The charging shunt control circuit 5 obtains the divided voltages of the load 2 and the battery pack 3 through the bus reference annunciator 7 and the charging reference annunciator 8 respectively, and judges the divided voltage of the load 2 for the first time through the operational amplifier C Is it smaller than the reference signal transmitted by the triangular wave transmitter 6 .
步骤2：若是，即负载2的分压电压小于三角波发射器6发射的基准信号，则信号切换开关S切换采集负载2分压电压的至母线基准信号器7，开关管M断开，第四回路断开，充电切换开关K切换为第一回路，充电开关KC断开，放电开关KF闭合，则第一回路和第三回路导通，充电太阳阵1和蓄电池组3同时为负载2供电。Step 2: If it is, that is, the divided voltage of load 2 is smaller than the reference signal transmitted by triangular wave transmitter 6, then the signal switch S switches from the divided voltage of load 2 to the bus reference signal device 7, the switch M is disconnected, and the fourth The circuit is disconnected, the charging switch K is switched to the first circuit, the charging switch K C is opened, and the discharging switch K F is closed, then the first circuit and the third circuit are connected, and the charging solar array 1 and the battery pack 3 are the load 2 at the same time. powered by.
步骤3：若否，即负载2的分压电压大于三角波发射器6发射的基准信号，此时，负载2无需充电太阳阵1提供电能，信号切换开关S切换为采集蓄电池3分压电压的充电基准信号器8；为避免充电太阳阵1的电能浪费，则通过运算放大器C第二次判断蓄电池组3的分压电压是否小于三角波发射器6发射的基准信号。Step 3: If no, that is, the divided voltage of the load 2 is greater than the reference signal transmitted by the triangular wave transmitter 6. At this time, the load 2 does not need to charge the solar array 1 to provide power, and the signal switch S is switched to collect the charging of the divided voltage of the battery 3. Reference signal device 8; in order to avoid waste of electric energy for charging the solar array 1, the operational amplifier C is used to judge whether the divided voltage of the battery pack 3 is smaller than the reference signal transmitted by the triangular wave transmitter 6 for the second time.
步骤4：若是，即负载2的分压电压大于三角波发射器6发射的基准信号，且蓄电池组3的分压电压小于三角波发射器6发射的基准信号，则开关管M断开，第四回路断开，充电切换开关K切换为第二回路，充电开关KC闭合，则第二回路导通，充电太阳阵1将电能传输至蓄电池组3，为蓄电池组3供电。Step 4: If it is, that is, the partial voltage of the load 2 is greater than the reference signal transmitted by the triangular wave transmitter 6, and the divided voltage of the battery pack 3 is smaller than the reference signal transmitted by the triangular wave transmitter 6, then the switch M is disconnected, and the fourth loop Disconnected, the charging switch K is switched to the second loop, and the charging switch K C is closed, the second loop is turned on, and the charging solar array 1 transmits electric energy to the battery pack 3 to supply power to the battery pack 3 .
步骤5：若否，即负载2和蓄电池组3的分压电压均大于三角波发射器6发射的基准信号，此时，负载2和蓄电池组3均无需充电太阳阵1提供电能，则开关管M闭合，第四回路导通，充电太阳阵1的电能直接分流掉。Step 5: If no, that is, the partial voltages of the load 2 and the battery pack 3 are both greater than the reference signal transmitted by the triangular wave transmitter 6, at this time, the load 2 and the battery pack 3 do not need to charge the solar array 1 to provide electrical energy, then the switch tube M When closed, the fourth loop is turned on, and the electric energy of the charging solar array 1 is directly shunted.
本发明的工作原理：The working principle of the present invention:
充电分流控制电路分别获取负载和蓄电池组的分压电压，并第一次判断负载的分压电压是否小于三角波发射器发射的基准信号；若是，即负载的分压电压小于基准信号，则第四回路断开，第一回路和第三回路导通，充电太阳阵和蓄电池组同时为负载供电；若否，即负载的分压电压大于基准信号，则第二次判断蓄电池组的分压电压是否小于基准信号；若是，即负载的分压电压大于基准信号，且蓄电池组的分压电压小于基准信号，则第四回路断开，第二回路导通，充电太阳阵为蓄电池组供电；若否，即负载和蓄电池组的分压电压均大于基准信号，则第四回路导通，充电太阳阵的电能直接分流掉。The charging shunt control circuit obtains the divided voltages of the load and the battery pack respectively, and judges for the first time whether the divided voltage of the load is less than the reference signal transmitted by the triangular wave transmitter; The loop is disconnected, the first loop and the third loop are turned on, the charging solar array and the battery pack supply power to the load at the same time; if not, that is, the partial voltage of the load is greater than the reference signal, then judge for the second time whether the partial voltage of the battery pack is not is less than the reference signal; if it is, that is, the partial voltage of the load is greater than the reference signal, and the partial voltage of the battery pack is less than the reference signal, then the fourth loop is disconnected, the second loop is turned on, and the charging solar array supplies power to the battery pack; if no , that is, the partial voltage of the load and the battery pack is greater than the reference signal, the fourth loop is turned on, and the electric energy of the charging solar array is directly shunted.
综上所述，本发明一种用于航天器的多路充电分流控制系统，解决了传统S4R型电路的结构复杂，且放电效率损耗高的问题，通过设置多路充电分流控制电路和充电切换开关，利用充电太阳阵和蓄电池组共同对负载充电，节省了器件，降低了成本，且保证了放电的利用率，降低了放电损耗，提高了能量的利用率和航天器的性能。To sum up, the present invention is a multi-channel charging shunt control system for spacecraft, which solves the problems of complex structure and high discharge efficiency loss of the traditional S 4 R type circuit. The charging switch uses the charging solar array and the battery pack to jointly charge the load, which saves components, reduces costs, ensures the utilization rate of discharge, reduces discharge loss, and improves the utilization rate of energy and the performance of the spacecraft.
尽管本发明的内容已经通过上述优选实施例作了详细介绍，但应当认识到上述的描述不应被认为是对本发明的限制。在本领域技术人员阅读了上述内容后，对于本发明的多种修改和替代都将是显而易见的。因此，本发明的保护范围应由所附的权利要求来限定。While the content of the present invention has been described in detail by way of the above preferred embodiments, it should be appreciated that the above description should not be construed as limiting the present invention. Various modifications and alternatives to the present invention will be apparent to those skilled in the art upon reading the foregoing. Accordingly, the scope of protection of the present invention should be defined by the appended claims.
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114285132A (en) * | 2021-12-30 | 2022-04-05 | 中北大学 | A low-power energy harvesting circuit |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106134502B (en) * | 2009-08-20 | 2013-01-23 | 北京卫星制造厂 | A kind of solar cell divides battle array parallel regulator |
| RU2492124C1 (en) * | 2012-04-17 | 2013-09-10 | Федеральное государственное унитарное предприятие "Научно-производственное объединение им. С.А. Лавочкина" | Space solar electric station and independent photo emitting panel |
| CN103326445A (en) * | 2013-07-11 | 2013-09-25 | 上海空间电源研究所 | Lithium battery control system in non-regulated bus mode |
| CN103337892A (en) * | 2013-07-10 | 2013-10-02 | 上海空间电源研究所 | Independent dormancy awakening control system of satellite power source |
| CN105429182A (en) * | 2015-12-30 | 2016-03-23 | 哈尔滨工业大学 | Power source MPPT control system for satellite |
| CN110474389A (en) * | 2019-08-06 | 2019-11-19 | 中国电子科技集团公司第十八研究所 | A kind of control topological circuit of LEO satellite power supply |
| CN111030181A (en) * | 2019-12-26 | 2020-04-17 | 北京空间飞行器总体设计部 | Intelligent power building blocks and distributed space power system based on intelligent power building blocks |
-
2020
- 2020-07-02 CN CN202010633613.4A patent/CN111697681B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106134502B (en) * | 2009-08-20 | 2013-01-23 | 北京卫星制造厂 | A kind of solar cell divides battle array parallel regulator |
| RU2492124C1 (en) * | 2012-04-17 | 2013-09-10 | Федеральное государственное унитарное предприятие "Научно-производственное объединение им. С.А. Лавочкина" | Space solar electric station and independent photo emitting panel |
| CN103337892A (en) * | 2013-07-10 | 2013-10-02 | 上海空间电源研究所 | Independent dormancy awakening control system of satellite power source |
| CN103326445A (en) * | 2013-07-11 | 2013-09-25 | 上海空间电源研究所 | Lithium battery control system in non-regulated bus mode |
| CN105429182A (en) * | 2015-12-30 | 2016-03-23 | 哈尔滨工业大学 | Power source MPPT control system for satellite |
| CN110474389A (en) * | 2019-08-06 | 2019-11-19 | 中国电子科技集团公司第十八研究所 | A kind of control topological circuit of LEO satellite power supply |
| CN111030181A (en) * | 2019-12-26 | 2020-04-17 | 北京空间飞行器总体设计部 | Intelligent power building blocks and distributed space power system based on intelligent power building blocks |
Non-Patent Citations (2)
| Title |
|---|
| LEI WANG等: ""Design and Research of High Voltage Power Conversion System for Space Solar Power Station"", 《2018 IEEE INTERNATIONAL POWER ELECTRONICS AND APPLICATION CONFERENCE AND EXPOSITION (PEAC)》 * |
| 刘志强: ""适用于载人航天器的低压大功率电源系统的设计"", 《中国优秀硕士学位论文全文数据库 工程科技II辑》 * |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114285132A (en) * | 2021-12-30 | 2022-04-05 | 中北大学 | A low-power energy harvesting circuit |
| CN114285132B (en) * | 2021-12-30 | 2023-08-29 | 中北大学 | A low power consumption energy harvesting circuit |
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