Space high-voltage power supply system based on silicon-based device

Abstract

The invention relates to a space high-voltage power supply system based on a silicon-based device, which is characterized in that based on a low-voltage silicon-based MOS (Metal Oxide Semiconductor) device capable of meeting a space environment, a two-stage capacitance voltage division bridge circuit is provided to bear 400V high-voltage stress, the bridge circuit is adopted at a low-voltage end, and charge and discharge management of a storage battery pack is realized through bidirectional synchronous rectification; aiming at the power regulation of the high-voltage solar cell array, the problem of high voltage resistance of an MOS (Metal Oxide Semiconductor) tube is ingeniously solved through a solar cell array middle tapping mode, and a space 400V high-voltage power supply system is realized. The storage battery pack charging and discharging management unit adopts an isolation circuit, a load bus is designed to be an unadjusted bus so as to be separated from a platform full-adjusted bus, when a load is a pulse type load, an isolation type BCDR can block the influence of the load on platform equipment, and meanwhile the weight and the size of a power supply controller are reduced; and high-voltage and low-voltage double buses are designed, so that the reliability of the power supply system is improved. The system has expansibility and is realized by adjusting the number of modules formed by high-voltage end full bridges and voltage dividing capacitors.

Description

Technical Field

[0001] The invention relates to a space high voltage power supply system based on silicon-based devices, which is applied to the field of space high voltage power supply. Background Art

[0002] As the power of spacecraft continues to increase, the demand for high-voltage bus power supply is becoming increasingly strong. The American Institute of Aeronautics and Astronautics (AIAA) analyzed that if the voltage of the satellite power bus is increased from 100V to a high-voltage bus of 300-400V, the power supply and propulsion system of the electric propulsion platform will be reduced by 20%. The system power supply power of the 300-400V bus high-voltage satellite planned by ESA will be increased from 20kW to 100kW. The spacecraft bus voltage has several levels such as 28V, 42V and 100V. At present, there is a lack of space power systems with higher voltage levels internationally and domestically.

[0003] According to the 0.6 times derating requirement for aerospace components, if the bus voltage is 400V, the switch device must be able to withstand at least 667V. Due to the influence of the space environment, new high-voltage (greater than 300V) semiconductor devices such as SiC and GaN are difficult to withstand the impact of single-particle effects and cannot be used in high-reliability satellite power systems. At present, aerospace-grade silicon-based devices can withstand a maximum of 500V.

[0004] In addition, high-voltage, high-power spacecraft will have multiple different power generation sources and coexistence of high / low voltage power supply systems. Therefore, when designing a high-voltage power supply system in space, it is necessary to consider the grid-connected power supply of power supply systems with different voltages. Summary of the invention

[0005] The technical problem solved by the present invention is: to overcome the deficiencies of the prior art, to provide a space high-voltage power supply system based on silicon-based devices, and to realize the space high-voltage power supply system by utilizing low-voltage aerospace-grade silicon-based switching devices through the innovation of topological architecture.

[0006] The technical solution of the present invention is:

[0007] A space high-voltage power supply system based on silicon-based devices, comprising: a high-voltage solar cell array, a high-voltage shunt regulator, a high-voltage battery group charge and discharge regulator, a low-voltage solar cell array, a low-voltage shunt regulator, a low-voltage battery group charge and discharge regulator, a low-voltage battery group, a grid-connected power distribution device, a high-voltage bus, a low-voltage bus, a high-voltage MEA / BEA controller and a low-voltage MEA / BEA controller;

[0008] Among them, the high-voltage shunt regulator regulates and controls the electric energy generated by the high-voltage solar cell array to ensure the stability of the high-voltage bus voltage. The high-voltage battery group charge and discharge regulator controls the low-voltage battery group to charge and discharge and exchange electric energy with the high-voltage bus. The high-voltage battery group charge and discharge regulator is jointly controlled by the high-voltage MEA controller and the high-voltage BEA controller. The high-voltage shunt regulator is controlled and regulated by the high-voltage MEA controller.

[0009] The low-voltage shunt regulator regulates and controls the electric energy generated by the low-voltage solar cell array to ensure the stability of the low-voltage bus voltage. The low-voltage battery charge and discharge regulator controls the low-voltage battery group to charge and discharge and exchange electric energy with the low-voltage bus. The low-voltage battery charge and discharge regulator is jointly controlled by the low-voltage MEA controller and the low-voltage BEA controller. The low-voltage shunt regulator is controlled and regulated by the low-voltage MEA controller.

[0010] The high-voltage busbar supplies power to the high-voltage loads, and the low-voltage busbar supplies power to the low-voltage loads on the platform. At the same time, the high-voltage busbar is connected to the low-voltage busbar through a grid-connected distribution device to jointly supply power to the low-voltage loads on the platform.

[0011] Furthermore, the high-voltage bus and the low-voltage platform bus are fully adjustable bus, both adopting the S3R fully adjustable architecture, wherein the operating voltage range of the high-voltage bus is 400V±4V.

[0012] Furthermore, it also includes a load bus for supplying power to the load; the load bus is an unregulated bus directly led out from the root of the low-voltage battery group; the low-voltage battery group selects the number of battery groups in series according to the low-voltage bus voltage and the load bus voltage range.

[0013] Furthermore, the high-voltage solar cell array is divided into two series-connected parts S1 and S2, wherein the output voltage of the series-connected cell array in the S2 part is less than 200V; isolation diodes are designed at the output ends of both S1 and S2.

[0014] Furthermore, the high-voltage solar array uses a 32% efficient triple-junction GaAs solar cell, 224 cells are connected in series to ensure that the voltage is not less than 405V at the end of the eight-year life, and the cell is plated with an electrostatic charge dissipation film to avoid the accumulation of space charge on the surface of the solar array.

[0015] Furthermore, the high-voltage shunt regulator adopts a low-voltage withstand voltage silicon-based MOS tube, and is connected to the high-voltage shunt regulator through a lead wire when the high-voltage solar array is less than 200V to achieve sequential shunt control. The MOS tube only needs to withstand a voltage drop of less than 200V to meet the first-level derating requirements of the space power supply.

[0016] Furthermore, the high-voltage shunt regulator includes MOS tubes Q1 and Q2 connected in series; wherein Q1 is sequentially switched on and off by a high-voltage MEA controller in accordance with a three-domain control method; Q2 is controlled by a hard-wired instruction of a satellite service computer. When a short circuit fault occurs in Q1 or a control circuit fault occurs in the MOS tubes Q1 and Q2, in order to ensure that the power of the solar cell array is not lost, an instruction is directly sent to keep Q2 in a long open circuit state.

[0017] Furthermore, the high-voltage battery pack charge and discharge regulator adopts an isolated bidirectional converter to realize the unified architecture management of battery pack charging and discharging; at the high-voltage end, two-stage capacitor voltage division is used to reduce the electrical stress of the MOS tube, and each stage adopts a bridge topology; at the low-voltage end, a one-stage bridge topology is used to realize the battery pack charge and discharge control.

[0018] Furthermore, the high-voltage battery pack charge and discharge regulator includes three symmetrical H bridges, pressure-bearing capacitors C3 and C4, an auxiliary inductor L1 and a transformer with a transformation ratio of n:1;

[0019] Each bridge arm in the H-bridge is composed of a low-voltage silicon-based MOS tube, a diode and a filter capacitor in parallel. The diode can reduce the complex synchronous rectification control caused by the on-off of the MOS switch during the secondary side rectification. Two-stage pressure-bearing capacitors C3 and C4 are connected in parallel to withstand and divide the high voltage stress at the high-voltage end of the busbar. The full bridges H1 and H2 are connected in series behind the capacitors C3 and C4 respectively to ensure that the voltage pressure borne by the MOS tubes in the full bridges H1 and H2 is ≤200V. The MOS tubes in the full bridges H1 and H2 are synchronously controlled by the same signal.

[0020] A full-bridge H0 circuit is used at the low voltage end;

[0021] In each control cycle, the switch tubes at both ends of the auxiliary inductor L are controlled to realize charging and discharging of the auxiliary inductor L, thereby realizing conversion and transmission of electric energy.

[0022] The high-voltage battery pack charge and discharge regulator adopts extended phase shift control, that is, the charging state and discharging state of the battery pack are controlled by controlling the phase of the switch tube drive signal; when the phase shift angle between the low-voltage end input and the high-voltage end output is greater than 0, the battery pack is in the discharging state; when the phase shift angle is less than 0, the battery pack is in the charging state;

[0023] The low-voltage end voltage is ≤100V, and it can adapt to low-voltage busbars of different voltage levels by changing the transformer ratio n:1 and the duty cycle of the full-bridge H1 and H2 switches.

[0024] Furthermore, the grid-connected power distribution device includes two H-bridges composed of MOS tubes, filter capacitors and diodes, a rectifier full bridge composed of diodes, resonant capacitors C0 and C1, resonant inductors L1 and L2, pressure-bearing capacitors C3 and C4 and a transformer;

[0025] In the H-bridge, each bridge arm is composed of a low-voltage silicon-based MOS tube and a diode in parallel. Two-stage pressure-bearing capacitors C3 and C4 are used to bear the electrical stress of the high-voltage bus. The full bridges H1 and H2 are connected in series behind the capacitors C3 and C4 respectively to ensure that the voltage pressure borne by the MOS tubes in the full bridges H1 and H2 is ≤200V.

[0026] The MOS tubes in the full bridge H1 and H2 are synchronously controlled by the same signal;

[0027] The low-voltage end uses a rectifier full-bridge for rectification, which serves as the inverter circuit at the rear end of the transformer and also prevents the low-voltage bus power from flowing back. The resonant circuit composed of resonant capacitors C0, C1 and resonant inductors L1 and L2 is set between the full bridges H1, H2 and the rectifier full bridge. The capacitance values ​​of C0 and C1 are set to be consistent, and the inductance values ​​of L1 and L2 are set to be consistent.

[0028] Furthermore, the grid-connected power distribution device is connected to the high-voltage line by setting a MOS tube Q12 at the low-voltage bus terminal, and its control logic is specifically as follows:

[0029] Detect the magnitude of the low-voltage bus voltage U0 and the direction of the low-voltage bus current I1. When I1 flows to the platform load or U0 is less than 100.2V, Q12 is closed, which is the initial state; when I1 does not flow to the platform load or U0 is greater than or equal to 100.3V, Q12 is disconnected;

[0030] The MOS tube Q12 is provided to control the grid connection of the low-voltage bus and reduce the power loss of the low-voltage bus to the platform load.

[0031] Furthermore, the grid-connected power distribution device adopts dual closed-loop droop control of voltage and current, and adapts to low-voltage buses of different voltage levels by changing the transformer ratio n:1 and the duty cycle of the H1 and H2 switches;

[0032] The real-time input of droop control includes the low-voltage bus voltage U0 and the low-voltage current I o , the droop control reference voltage U is calculated by the following expression: ref :

[0033] U ref =U std -I o R v

[0034] Where: R v For droop control virtual impedance, U std The open circuit voltage of the designed device;

[0035] U refThe low-voltage bus voltage U0 is used as the input of the voltage loop control and then input into the comparison amplifier PI after comparison; the output of the voltage loop is i ref and low voltage terminal current I o As the input of the current loop, it is input into the comparison amplifier PI after comparison; the current loop output signal is sent to the PWM control as the control of the grid-connected distributor.

[0036] Furthermore, the high-voltage MEA controller adopts three-domain control. When it is in the charging domain during the illumination period, it controls the high-voltage battery pack charge and discharge regulator to charge the battery pack. On the premise of meeting the battery pack charging and bus load power requirements, that is, when entering the shunt domain, the high-voltage shunt regulator controls the high-voltage solar array output power to adjust; in the shadow area or when the load power demand is large, the high-voltage MEA controller enters the discharge domain and controls the high-voltage battery pack charge and discharge regulator to discharge the battery pack.

[0037] Furthermore, the high-voltage BEA controller collects the feedback battery charging current and battery charging voltage, obtains the BEA output control signal through the integrating operational amplifier, controls the high-voltage battery pack charging and discharging regulator, and realizes the battery charging management.

[0038] Furthermore, the low-voltage solar array, low-voltage shunt regulator, low-voltage battery pack charge and discharge regulator, low-voltage MEA controller, and low-voltage BEA controller all adopt a traditional S3R topology architecture, which serves as a backup for the satellite power supply system.

[0039] Furthermore, the number of series connections of the low-voltage battery pack is determined by the low-voltage bus voltage. If the low-voltage bus is 100V, 22 battery packs are configured; if 42V is selected, 9 battery packs are configured; if 30.5V is selected, 7 battery packs are configured; the capacity of the battery pack is determined by the load power, mission duration and track, and the specific calculation formula is as follows:

[0040]

[0041] Where, R is the ampere-hour of the battery pack; P 常 is the constant power of the spacecraft; t 地影 is the orbital shadow time; P 载荷 is the load power; t 任务 is the load working time; 3.6V is the median power of a single battery pack; K is the number of battery packs in series; A is the allowable discharge depth of the battery pack, usually 30% for the low rail and 80% for the high rail.

[0042] The beneficial effects of the present invention compared with the prior art are:

[0043] (1) Based on low-voltage silicon-based MOS devices that can meet the space environment, a two-stage capacitor voltage-dividing bridge circuit is proposed to withstand 400V high-voltage stress. A bridge circuit is used at the low-voltage end, and the charging and discharging management of the battery group is realized through bidirectional synchronous rectification. In addition, for the power regulation of the high-voltage solar array, the problem of MOS tube high-voltage resistance is cleverly avoided by tapping the middle of the solar array. The 400V high-voltage power supply system in space can be realized through the traditional S3R sequential shunt technology. The un-shunted part of the solar array will not be in an open circuit state because it is directly connected to the busbar, and the high voltage of the solar array caused by low temperature just after leaving the earth's shadow will not occur.

[0044] (2) The battery pack charge and discharge management unit adopts an isolation circuit, and the load bus is designed as a non-regulated bus to separate it from the platform's fully regulated bus. When the load is a pulse load, the isolated BCDR can block its impact on the platform equipment, while reducing the weight and volume of the power controller;

[0045] (3) Design high-voltage and low-voltage dual busbars, and connect the two busbars together through a grid-connected controller. When a high-voltage or low-voltage busbar fails (especially the high-voltage busbar), the other busbar can directly take on the power supply of the entire satellite platform load, thereby improving the reliability of the power supply system.

[0046] (4) This module is scalable and can be modified by adjusting the number of modules consisting of the high-voltage full bridge and the voltage-dividing capacitor in the high-voltage battery pack charger and discharger according to the different bus voltages. BRIEF DESCRIPTION OF THE DRAWINGS

[0047] Figure 1 This is a schematic diagram of a space high voltage power supply system based on silicon-based devices according to the present invention;

[0048] Figure 2 It is a schematic diagram of a high-voltage shunt regulator of the present invention;

[0049] Figure 3 It is a schematic diagram of an isolated high-voltage battery pack charge and discharge regulator based on silicon-based devices of the present invention;

[0050] Figure 4 It is a schematic diagram of an isolated grid-connected power distribution device based on silicon-based devices of the present invention;

[0051] Figure 5 This is the droop control logic diagram of the grid-connected power distribution device of the present invention. DETAILED DESCRIPTION

[0052] The specific embodiments of the present invention are further described in detail below with reference to the accompanying drawings.

[0053] like Figure 1As shown, the present invention proposes a space high voltage power supply system based on silicon-based devices, including a 400V high voltage solar cell array, a high voltage shunt regulator (HV SR), a high voltage battery charge and discharge regulator (HV BCDR), a low voltage solar cell array, a low voltage shunt regulator (LV SR), a low voltage battery charge and discharge regulator (LV BCDR), a low voltage battery pack, a grid-connected power distribution device, a high voltage load, a load load, a low voltage load, a load bus, a high voltage MEA / BEA controller and a low voltage MEA / BEA controller, a high voltage bus and a low voltage platform bus.

[0054] Among them, the high-voltage shunt regulator regulates and controls the electric energy generated by the high-voltage solar cell array to ensure the stability of the high-voltage bus voltage. The high-voltage battery group charge and discharge regulator controls the low-voltage battery group to charge and discharge and exchange electric energy with the high-voltage bus. The high-voltage battery group charge and discharge regulator is jointly controlled by the high-voltage MEA controller and the high-voltage BEA controller. The high-voltage shunt regulator is controlled and regulated by the high-voltage MEA controller.

[0055] The low-voltage shunt regulator regulates and controls the electric energy generated by the low-voltage solar cell array to ensure the stability of the low-voltage bus voltage. The low-voltage battery charge and discharge regulator controls the low-voltage battery group to charge and discharge and exchange electric energy with the low-voltage bus. The low-voltage battery charge and discharge regulator is jointly controlled by the low-voltage MEA controller and the low-voltage BEA controller. The low-voltage shunt regulator is controlled and regulated by the low-voltage MEA controller.

[0056] The high-voltage busbar supplies power to the high-voltage loads, and the low-voltage busbar supplies power to the low-voltage loads on the platform. At the same time, the high-voltage busbar is connected to the low-voltage busbar through a grid-connected distribution device to jointly supply power to the low-voltage loads on the platform.

[0057] The high-voltage bus and low-voltage platform bus are fully adjustable bus, both adopt the S3R fully adjustable architecture, wherein the operating voltage range of the high-voltage bus is 400V±4V, the high-voltage bus supplies power to the high-voltage load, and the low-voltage bus supplies power to the platform low-voltage load. At the same time, the high-voltage bus is also connected to the low-voltage bus through a grid-connected distribution device to jointly supply power to the platform low-voltage load.

[0058] The load bus is used to supply power to the load; the load bus is an unregulated bus, which is directly led out from the root of the low-voltage battery pack; the low-voltage battery pack selects the number of battery packs in series according to the low-voltage bus voltage and the load bus voltage range; the high-voltage parts such as the high-voltage shunt regulator, high-voltage BCDR, and grid-connected distribution device all use traditional silicon-based semiconductor devices that are resistant to space radiation and are implemented through topology optimization.

[0059] Both high-voltage and low-voltage bus lines are designed with independent high / low-voltage solar cell arrays, high / low-voltage shunt regulators, high / low-voltage battery charge and discharge regulators and corresponding high / low-voltage MEA / BEA controllers. A unified low-voltage battery pack is used, and both high and low-voltage buses can operate independently. In addition, the unregulated bus is drawn from the root of the battery pack to directly supply power to pulse-type high-energy loads.

[0060] The high-voltage solar array uses 30mm×40mm 32% efficient triple-junction GaAs solar cells, and 220 cells are designed to be connected in series to ensure that the output voltage is not less than 405V at the end of the eight-year life of the spacecraft. In order to avoid discharge between strings and improve the space voltage resistance, modular battery layout and hybrid connection circuit layout are used to ensure that the voltage between strings is less than 75V. Conductive film is plated on the glass cover of the solar cell to simulate static electricity accumulation, and a direct dissipation channel between the glass cover and the battery circuit is designed to eliminate the formation of the three-combination electric field, fundamentally avoiding the occurrence of a discharge.

[0061] High voltage solar array circuit design Figure 2 As shown in the figure, the 400V high voltage solar array is divided into two series parts S1 and S2, where the output voltage of the S2 series array is less than 200V. In order to prevent the failure of a certain string of the battery array, causing the other strings to short-circuit and unable to output, isolation diodes are designed at the output ends of S1 and S2. The circuit structure of the 400V solar array can also be extended to solar arrays with higher voltages, and it is only necessary to ensure that the output voltage of circuit S2 is less than 200V.

[0062] The high voltage shunt regulator (HV SR) of the present invention is as follows Figure 2 As shown. The output voltage of the S2 end of the solar array is less than 200V, and a low-voltage silicon-based MOS tube can be selected to meet the first-level derating requirements of the space power supply. In the high-voltage shunt regulator, MOS tubes Q1 and Q2 are connected in series, where Q1 is sequentially switched by the high-voltage MEA controller in accordance with the three-domain control method; Q2 is controlled by the hard-wired instructions of the satellite computer. When Q1 short-circuit fault occurs or the control circuit of MOS tubes Q1 and Q2 fails, in order to ensure that the power of the solar array is not lost, a direct instruction is sent to keep Q2 in a long open state.

[0063] like Figure 3 As shown, the high-voltage battery pack charge and discharge regulator (high-voltage BCDR) adopts an isolated bidirectional converter to realize the unified architecture management of battery pack charging and discharging; at the high-voltage end, two-stage capacitor voltage division is used to reduce the MOS tube electrical stress, and each stage adopts a bridge topology; at the low-voltage end, a single-stage bridge topology is used to realize battery pack charge and discharge control.

[0064] The high-voltage BCDR includes three symmetrical H-bridges, pressure-bearing capacitors C3 and C4, auxiliary inductor L1 and a transformer with a transformation ratio of n:1. In each H-bridge, a low-voltage silicon-based MOS tube, a diode and a filter capacitor are connected in parallel. The diode can reduce the complex synchronous rectification control caused by the need to rely on the on-off of the MOS switch during the secondary rectification. Two-stage pressure-bearing capacitors C3 and C4 are connected in parallel to withstand and divide the high voltage stress at the high-voltage end of the busbar. The full bridges H1 and H2 are connected in series behind the capacitors C3 and C4 respectively to ensure that the voltage pressure borne by the MOS tubes in the full bridges H1 and H2 is ≤200V. The MOS tubes in the full bridges H1 and H2 are synchronously controlled by the same signal. H1 includes MOS tubes Q5~Q8, H2 includes MOS tubes Q9~Q12, Q6 and Q10, Q5 and Q9, Q8 and Q12, Q7 and Q11 are opened and closed synchronously.

[0065] A full-bridge H0 circuit is used at the low-voltage end.

[0066] In each control cycle, the switch tubes at both ends of the auxiliary inductor L are controlled to realize charging and discharging of the auxiliary inductor L, thereby realizing conversion and transmission of electric energy.

[0067] In addition, the converter is expandable when facing higher voltages. On this basis, the high-voltage end only needs to continue to connect the voltage-dividing capacitor Ci and the Hi full bridge in parallel, i=U / 200 (U is the high-voltage end voltage). This converter adopts extended phase shift control, that is, the converter is controlled in the battery pack charging and discharging state by controlling the phase of the switch tube drive signal. When the phase shift angle at the low-voltage end input and the high-voltage end output is greater than 0, it is the battery pack discharge state; when the phase shift angle is less than 0, it is the battery pack charging state. The low-voltage end voltage is ≤100V, which can adapt to low-voltage buses of different voltage levels such as 7 strings (bus voltage is 30.5V), 9 strings (bus voltage is 42V) and 22 strings (bus voltage is 100V), and adapt to different low-voltage bus voltage levels by changing the transformer ratio (n:1) and the duty cycle of the H1 and H2 switch tubes.

[0068] like Figure 4 As shown, the grid-connected distribution device uses two-stage capacitor voltage division at the high-voltage end to reduce the stress of the MOS tube, each stage uses a full-bridge topology, the low-voltage end uses a diode full-bridge rectification, and the control uses droop control to be flexibly connected to the low-voltage bus.

[0069] The isolated grid-connected power distribution device based on silicon-based devices includes two H-bridges composed of MOS tubes, filter capacitors and diodes, a rectifier full bridge composed of diodes, resonant capacitors C0 and C1, resonant inductors L1 and L2, pressure-bearing capacitors C3 and C4 and a transformer.

[0070] In the H-bridge, each bridge arm is composed of a low-voltage silicon-based MOS tube and a diode in parallel. Two-stage pressure-bearing capacitors C3 and C4 are used to bear the electrical stress of the high-voltage bus. The full bridges H1 and H2 are connected in series behind the capacitors C3 and C4 respectively to ensure that the voltage pressure borne by the MOS tubes in the full bridges H1 and H2 is ≤200V.

[0071] The MOS tubes in the full bridge H1 and H2 are synchronously controlled by the same signal. H1 includes MOS tubes Q5 to Q8, and H2 includes MOS tubes Q9 to Q12. Q6 and Q10, Q5 and Q9, Q8 and Q12, and Q7 and Q11 are synchronously disconnected.

[0072] The low-voltage end uses a rectifier full-bridge for rectification, which serves as the inverter circuit at the rear end of the transformer and also prevents the low-voltage bus power from flowing back. The resonant circuit composed of resonant capacitors C0, C1 and resonant inductors L1 and L2 is set between the full bridges H1, H2 and the rectifier full bridge. The capacitance values ​​of C0 and C1 are set to be consistent, and the inductance values ​​of L1 and L2 are set to be consistent.

[0073] The grid-connected power distribution device is connected to the high-voltage line by setting a MOS tube Q12 at the low-voltage bus end. Its control logic is as follows:

[0074] Detect the magnitude of the low-voltage bus voltage U0 and the direction of the low-voltage bus current I1. When I1 flows to the platform load or U0 is less than 100.2V, Q12 is closed, which is the initial state; when I1 does not flow to the platform load or U0 is greater than or equal to 100.3V, Q12 is disconnected;

[0075] The MOS tube Q12 is provided to control the grid connection of the low-voltage bus and reduce the power loss of the low-voltage bus to the platform load.

[0076] In order to ensure flexible grid connection with the low-voltage bus, the grid-connected distribution device adopts dual closed-loop droop control of voltage and current, and adapts to low-voltage buses of different voltage levels by changing the transformer ratio n:1 and the duty cycle of the H1 and H2 switches; Figure 5 shown.

[0077] The real-time input of droop control includes the low-voltage bus voltage U0 and the low-voltage current I o , the droop control reference voltage U is calculated by the following expression: ref :

[0078] U ref =U std -I o R v

[0079] Where: R v For droop control virtual impedance, U stdis the designed open circuit voltage of the equipment; in order to ensure that the high voltage bus can output first than the low voltage bus, U std Set to 102V.

[0080] U ref The low-voltage bus voltage U0 is used as the input of the voltage loop control and then input into the comparison amplifier PI after comparison; the output of the voltage loop is i ref and low voltage terminal current I o As the input of the current loop, it is input into the comparison amplifier PI after comparison; the current loop output signal is sent to the PWM control as the control of the grid-connected distributor.

[0081] In addition, the grid-connected power distribution device is expandable when the voltage at the high-voltage end is higher. It only needs to connect the voltage-dividing capacitor Ci and Hi full bridge in parallel at the high-voltage end, i=U / 200 (U is the voltage at the high-voltage end).

[0082] The high-voltage MEA controller proposed in the present invention adopts three-domain control. When it is in the charging domain during the illumination period, it controls the high-voltage battery pack charge and discharge regulator to charge the battery pack. On the premise that the battery pack charging and bus load power requirements are met, that is, when entering the shunt domain, the high-voltage shunt regulator controls the high-voltage solar array output power to adjust; in the shadow area or when the load power demand is large, the high-voltage MEA controller enters the discharge domain, and controls the high-voltage battery pack charge and discharge regulator to discharge the battery pack.

[0083] The high-voltage BEA controller collects the feedback battery charging current and battery charging voltage, obtains the BEA output control signal through the integrating operational amplifier, controls the high-voltage battery pack charging and discharging regulator, and realizes battery charging management.

[0084] The low-voltage solar array, low-voltage shunt regulator, low-voltage battery pack charge and discharge regulator, low-voltage MEA controller, and low-voltage BEA controller all adopt the traditional S3R topology architecture, which serves as a backup for the satellite power supply system to enhance system reliability.

[0085] The number of series connections of low-voltage battery packs is determined by the voltage of the low-voltage bus. If the low-voltage bus is 100V, 22 battery packs are configured; if 42V is selected, 9 battery packs are configured; if 30.5V is selected, 7 battery packs are configured; the capacity of the battery pack is determined by the load power, mission duration and track. The specific calculation formula is as follows:

[0086]

[0087] Where, R is the ampere-hour of the battery pack; P 常 is the constant power of the spacecraft; t 地影 is the orbital shadow time; P 载荷 is the load power; t任务 is the load working time; 3.6V is the median power of a single battery pack; K is the number of battery packs in series; A is the allowable discharge depth of the battery pack, usually 30% for the low rail and 80% for the high rail.

[0088] The present invention is based on low-voltage silicon-based MOS devices that can meet the space environment, and proposes a two-stage capacitor voltage-dividing bridge circuit to withstand 400V high-voltage stress. A bridge circuit is used at the low-voltage end, and the charge and discharge management of the battery group is realized through bidirectional synchronous rectification; in addition, for the power regulation of the high-voltage solar cell array, the problem of MOS tube high-voltage resistance is cleverly avoided by tapping the middle of the solar cell array, and a 400V high-voltage power supply system in space is realized. The battery group charge and discharge management unit adopts an isolation circuit, and the load bus is designed as a non-adjustable bus to separate it from the platform full-adjustable bus. When the load is a pulse load, the isolated BCDR can block its influence on the platform equipment, while reducing the weight and volume of the power controller; a high-voltage and low-voltage double bus is designed, and the two busbars are connected together through a grid-connected controller. When the high-voltage or low-voltage busbar fails (especially the high-voltage busbar), the other busbar can directly bear the power supply of the entire satellite platform load, thereby improving the reliability of the power supply system. This module is scalable and can be realized by adjusting the number of modules consisting of the high-voltage full bridge and the voltage-dividing capacitor in the high-voltage battery pack charger and discharger according to the different bus voltages.

[0089] Parts of the present invention that are not described in detail belong to common knowledge among those skilled in the art.

Claims

1. A space high voltage power supply system based on silicon-based devices, characterized in that include: High-voltage solar cell array, high-voltage shunt regulator, high-voltage battery charge and discharge regulator, low-voltage solar cell array, low-voltage shunt regulator, low-voltage battery charge and discharge regulator, low-voltage battery, grid-connected power distribution device, high-voltage bus, low-voltage bus, high-voltage MEA / BEA controller and low-voltage MEA / BEA controller; Among them, the high-voltage shunt regulator regulates and controls the electric energy generated by the high-voltage solar cell array to ensure the stability of the high-voltage bus voltage. The high-voltage battery group charge and discharge regulator controls the low-voltage battery group to charge and discharge and exchange electric energy with the high-voltage bus. The high-voltage battery group charge and discharge regulator is jointly controlled by the high-voltage MEA controller and the high-voltage BEA controller. The high-voltage shunt regulator is controlled and regulated by the high-voltage MEA controller. The low-voltage shunt regulator regulates and controls the electric energy generated by the low-voltage solar cell array to ensure the stability of the low-voltage bus voltage. The low-voltage battery charge and discharge regulator controls the low-voltage battery group to charge and discharge and exchange electric energy with the low-voltage bus. The low-voltage battery charge and discharge regulator is jointly controlled by the low-voltage MEA controller and the low-voltage BEA controller. The low-voltage shunt regulator is controlled and regulated by the low-voltage MEA controller. The high-voltage busbar supplies power to the high-voltage loads, and the low-voltage busbar supplies power to the low-voltage loads on the platform. At the same time, the high-voltage busbar is connected to the low-voltage busbar through a grid-connected distribution device to jointly supply power to the low-voltage loads on the platform.

2. A space high voltage power supply system based on silicon-based devices according to claim 1, characterized in that: The high-voltage bus and the low-voltage platform bus are fully adjustable bus, both adopting the S3R fully adjustable architecture, wherein the operating voltage range of the high-voltage bus is 400V±4V.

3. The space high voltage power supply system based on silicon-based devices according to claim 1, characterized in that: It also includes a load bus for supplying power to the load; the load bus is an unregulated bus directly drawn from the root of the low-voltage battery group; the low-voltage battery group selects the number of battery groups connected in series according to the low-voltage bus voltage and the load bus voltage range.

4. The space high voltage power supply system based on silicon-based devices according to claim 1, characterized in that: The high-voltage solar cell array is divided into two series-connected parts S1 and S2, wherein the output voltage of the S2 series-connected cell array is <200V; isolation diodes are designed at the output ends of S1 and S2.

5. The space high voltage power supply system based on silicon-based devices according to claim 4 is characterized in that: The high-voltage solar array uses a 32% efficient triple-junction GaAs solar cell. 224 cells are connected in series to ensure that the voltage is not less than 405V at the end of an eight-year lifespan. The cell is plated with an electrostatic charge dissipation film to avoid the accumulation of space charge on the surface of the solar array.

6. The space high voltage power supply system based on silicon-based devices according to claim 1, characterized in that: The high-voltage shunt regulator adopts a low-voltage withstand voltage silicon-based MOS tube, which is connected to the high-voltage shunt regulator through a lead wire when the high-voltage solar array is less than 200V to achieve sequential shunt control. The MOS tube only needs to withstand a voltage drop of less than 200V, meeting the first-level derating requirements of the space power supply.

7. The space high voltage power supply system based on silicon-based devices according to claim 6 is characterized in that: The high-voltage shunt regulator includes MOS tubes Q1 and Q2 connected in series; Q1 is controlled by the high-voltage MEA controller in a three-domain control mode to achieve sequential switching shunt; Q2 is controlled by the hard-wired instructions of the satellite computer. When Q1 short-circuit fault occurs or the control circuit of MOS tubes Q1 and Q2 fails, in order to ensure that the power of the solar cell array is not lost, a direct instruction is sent to keep Q2 in a long open circuit state.

8. The space high voltage power supply system based on silicon-based devices according to claim 1, characterized in that: The high-voltage battery pack charge and discharge regulator adopts an isolated bidirectional converter to achieve unified architecture management of battery pack charging and discharging; at the high-voltage end, two-stage capacitor voltage division is used to reduce the electrical stress of the MOS tube, and each stage adopts a bridge topology; at the low-voltage end, a single-stage bridge topology is used to realize battery pack charge and discharge control.

9. The space high voltage power supply system based on silicon-based devices according to claim 8, characterized in that: The high-voltage battery pack charge and discharge regulator includes three symmetrical H bridges, pressure-bearing capacitors C3 and C4, an auxiliary inductor L1 and a transformer with a transformation ratio of n:1; Each bridge arm in the H-bridge is composed of a low-voltage silicon-based MOS tube, a diode and a filter capacitor in parallel. The diode can reduce the complex synchronous rectification control caused by the on-off of the MOS switch during the secondary side rectification. Two-stage pressure-bearing capacitors C3 and C4 are connected in parallel to withstand and divide the high voltage stress at the high-voltage end of the busbar. The full bridges H1 and H2 are connected in series behind the capacitors C3 and C4 respectively to ensure that the voltage pressure borne by the MOS tubes in the full bridges H1 and H2 is ≤200V. The MOS tubes in the full bridges H1 and H2 are synchronously controlled by the same signal. A full-bridge H0 circuit is used at the low voltage end; In each control cycle, the switch tubes at both ends of the auxiliary inductor L are controlled to realize charging and discharging of the auxiliary inductor L, thereby realizing conversion and transmission of electric energy. The high-voltage battery pack charge and discharge regulator adopts extended phase shift control, that is, the charging state and discharging state of the battery pack are controlled by controlling the phase of the switch tube drive signal; when the phase shift angle between the low-voltage end input and the high-voltage end output is greater than 0, the battery pack is in the discharging state; when the phase shift angle is less than 0, the battery pack is in the charging state; The low-voltage end voltage is ≤100V, and it can adapt to low-voltage busbars of different voltage levels by changing the transformer ratio n:1 and the duty cycle of the full-bridge H1 and H2 switches.

10. The space high voltage power supply system based on silicon-based devices according to claim 1, characterized in that: The grid-connected power distribution device includes two H-bridges composed of MOS tubes, filter capacitors and diodes, a rectifier full bridge composed of diodes, resonant capacitors C0 and C1, resonant inductors L1 and L2, pressure-bearing capacitors C3 and C4 and a transformer; In the H-bridge, each bridge arm is composed of a low-voltage silicon-based MOS tube and a diode in parallel. Two-stage pressure-bearing capacitors C3 and C4 are used to bear the electrical stress of the high-voltage bus. The full bridges H1 and H2 are connected in series behind the capacitors C3 and C4 respectively to ensure that the voltage pressure borne by the MOS tubes in the full bridges H1 and H2 is ≤200V. The MOS tubes in the full bridge H1 and H2 are synchronously controlled by the same signal; The low-voltage end uses a rectifier full-bridge for rectification, which serves as the inverter circuit at the rear end of the transformer and also prevents the low-voltage bus power from flowing back. The resonant circuit composed of resonant capacitors C0, C1 and resonant inductors L1 and L2 is set between the full bridges H1, H2 and the rectifier full bridge. The capacitance values ​​of C0 and C1 are set to be consistent, and the inductance values ​​of L1 and L2 are set to be consistent.

11. The space high voltage power supply system based on silicon-based devices according to claim 10, characterized in that: The grid-connected power distribution device is connected to the high-voltage line by setting a MOS tube Q12 at the low-voltage bus terminal, and its control logic is specifically as follows: Detect the magnitude of the low-voltage bus voltage U0 and the direction of the low-voltage bus current I1. When I1 flows to the platform load or U0 is less than 100.2V, Q12 is closed, which is the initial state; when I1 does not flow to the platform load or U0 is greater than or equal to 100.3V, Q12 is disconnected; The MOS tube Q12 is provided to control the grid connection of the low-voltage bus and reduce the power loss of the low-voltage bus to the platform load.

12. The space high voltage power supply system based on silicon-based devices according to claim 10 or 11, characterized in that: The grid-connected power distribution device adopts dual closed-loop droop control of voltage and current, and adapts to low-voltage buses of different voltage levels by changing the transformer ratio n:1 and the duty cycle of the H1 and H2 switch tubes; The real-time input of droop control includes the low-voltage bus voltage U0 and the low-voltage current I o , the droop control reference voltage U is calculated by the following expression: ref : U ref =U std -I o R v Where: R v For droop control virtual impedance, U std The open circuit voltage of the designed device; U ref The low-voltage bus voltage U0 is used as the input of the voltage loop control and then input into the comparison amplifier PI after comparison; the output of the voltage loop is i ref and low voltage terminal current I o As the input of the current loop, it is input into the comparison amplifier PI after comparison; the current loop output signal is sent to the PWM control as the control of the grid-connected distributor.

13. The space high voltage power supply system based on silicon-based devices according to claim 1, characterized in that: The high-voltage MEA controller adopts three-domain control. When it is in the charging domain during the illumination period, it controls the high-voltage battery pack charge and discharge regulator to charge the battery pack. On the premise that the battery pack charging and bus load power requirements are met, that is, when entering the shunt domain, the high-voltage shunt regulator controls the high-voltage solar array output power to adjust; in the shadow area or when the load power demand is large, the high-voltage MEA controller enters the discharge domain and controls the high-voltage battery pack charge and discharge regulator to discharge the battery pack.

14. The space high voltage power supply system based on silicon-based devices according to claim 1, characterized in that: The high-voltage BEA controller collects the feedback battery charging current and battery charging voltage, obtains the BEA output control signal through the integrating operational amplifier, controls the high-voltage battery pack charging and discharging regulator, and realizes the battery charging management.

15. The space high voltage power supply system based on silicon-based devices according to claim 1, characterized in that: The low-voltage solar cell array, low-voltage shunt regulator, low-voltage battery pack charge and discharge regulator, low-voltage MEA controller, and low-voltage BEA controller all adopt a traditional S3R topology architecture, which serves as a backup for the satellite power supply system.

16. The space high voltage power supply system based on silicon-based devices according to claim 1, characterized in that: The number of series connections of the low-voltage battery pack is determined by the low-voltage bus voltage. If the low-voltage bus is 100V, 22 battery packs are configured; if 42V is selected, 9 battery packs are configured; if 30.5V is selected, 7 battery packs are configured; the battery pack capacity is determined by the load power, mission duration and track, and the specific calculation formula is as follows: Where, R is the ampere-hour of the battery pack; P 常 is the constant power of the spacecraft; t 地影 is the orbital shadow time; P 载荷 is the load power; t 任务 is the load working time; 3.6V is the median power of a single battery pack; K is the number of batteries in series; A is the allowable discharge depth of the battery pack, usually 30% for the low rail and 80% for the high rail.

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