A high-voltage spacecraft load control system applied to a distributed power supply

Abstract

This invention discloses a high-voltage spacecraft load control system applied to distributed power sources, comprising a fully regulated bus, a power supply control module, an intelligent management module, and high-voltage loads. The fully regulated bus outputs 400V to supply power to the power supply control module. The power supply control module includes multiple SSPC high-voltage control switches for performing load power supply on / off operations. The high-voltage loads include multiple 400V high-voltage loads, each connected one-to-one with the SSPC high-voltage control switches of the power supply control module. The intelligent management module is responsible for detecting the voltage of each power supply and issuing corresponding SSPC on / off commands according to the management strategy. This invention solves the safety control problem of high-voltage loads in spacecraft based on droop-controlled distributed power systems, ensuring the stable and safe operation of the distributed power bus. It is suitable for the output characteristics of droop-controlled distributed power systems and has advantages such as simple and reliable control logic, flexible intelligent control methods, fast system response, and good stability.

Description

Technical Field

[0001] This invention belongs to the field of spacecraft power technology, specifically relating to a high-voltage spacecraft load control system applied to distributed power sources. Background Technology

[0002] In a fully regulated distributed spacecraft power system employing droop control, control is typically performed in domains based on the bus voltage from highest to lowest: solar power regulation domain, grid-connected power regulation domain, charging power regulation domain, and discharging power regulation domain. The electrical loads are connected to the fully regulated bus and controlled by a power supply switch. Due to variations in conditions such as illumination, temperature, load, and the operating state of the power regulation circuit, the bus voltage of the spacecraft power system continuously changes. When the bus voltage falls below its normal value, it indicates that the power system's output power cannot meet the load demand, requiring categorized control of the energizing status of different types of loads. When the bus voltage returns to normal, categorized restoration of the energizing status of different loads is also necessary. Summary of the Invention

[0003] In view of this, the present invention provides a high-voltage spacecraft load control system for distributed power sources, which can overcome the shortcomings of existing load control functions being limited and lacking adaptability to the safety modes of spacecraft power systems based on droop control, and solves the problem of intelligent load safety control for spacecraft high-voltage buses based on droop control.

[0004] The technical solution for implementing the present invention is as follows:

[0005] A high-voltage spacecraft load control system for distributed power sources includes a fully regulated bus, a power supply control module, an intelligent management module, and a high-voltage load, wherein:

[0006] The fully adjustable bus outputs 400V voltage to supply the power supply control module. The 400V voltage is connected to the power supply control switches SSPC 1 to SSPC N.

[0007] The power supply control module consists of multiple SSPC control switches connected in parallel, used to execute load power supply on / off commands; the two ends of the power supply control switches SSPC 1 to SSPC N are respectively connected to the high-voltage load and the fully regulating bus.

[0008] The high-voltage load consists of high-voltage load 1 to high-voltage load N connected in parallel, and is connected one-to-one to the power supply control switches SSPC1 to SSPC N;

[0009] The intelligent management module is connected to the power supply control switches SSPC 1 to SSPC N; it collects the power supply voltage of each channel and issues switching commands to the power supply control switches SSPC 1 to SSPC N according to the predetermined domain control method.

[0010] Furthermore, the output voltage of the fully regulated bus is 400V to 405V; the bus voltage is divided into four droop control domains from high to low: solar power regulation domain, grid-connected power regulation domain, charging power regulation domain, and discharging power regulation domain; the bus voltage range of the solar power regulation domain is V7 to V8; the bus voltage range of the grid-connected power regulation domain is V5 to V6; the bus voltage range of the charging power regulation domain is V3 to V4; and the bus voltage range of the discharging power regulation domain is V1 to V2.

[0011] Furthermore, based on the order of importance from low to high, high-voltage loads are divided into three categories: general loads, important loads, and core loads.

[0012] Furthermore, the energization and de-energization of general loads adopt hysteresis control method 1. When the intelligent management module detects the bus voltage V... BUS Reduce to V YL When the intelligent management module issues a command to disconnect the power supply control switch for general loads, and the bus voltage V... BUS Rise to V YH At this time, the power supply control switch for general loads is turned on; where V YL <V1, the shutdown voltage is lower than the lower limit of the normal voltage; V7 <V YH <V8, the on-state voltage is within the solar power regulation range.

[0013] Furthermore, the hysteresis control method 2 is used to control the power-on and power-off of critical loads. When the intelligent management module detects that the bus voltage V... BUS Reduce to V ZL When the intelligent management module issues a command to disconnect the power supply control switch for critical loads, and the bus voltage V... BUS Rise to V ZH At that time, the power supply control switch for the important load is turned on; where V ZL <V1, the shutdown voltage is lower than the lower limit of the normal voltage; V5 <V ZH <V6, the on-state voltage is within the grid-connected power regulation range.

[0014] Furthermore, the power-on and power-off of the core load adopts hysteresis control method 3. When the intelligent management module detects the bus voltage V BUS Reduce to V HL When the intelligent management module issues a command to disconnect the power supply control switch of the core load, and the bus voltage V... BUS Rise to V HH At that time, the power supply control switch of the core load is turned on; where V HL <V1, the shutdown voltage is lower than the lower limit of the normal voltage, V1 < V HH <V2, the on-state voltage is within the discharge power regulation range.

[0015] Furthermore, the turn-off voltage V of hysteresis control methods 1, 2, and 3... YL <V ZL <V HL <V1, and V YL With V ZL The voltage difference between them is not less than 1V; V ZL With V HL The voltage difference between them is not less than 1V, V HL The voltage difference between V1 and V1 is not less than 1V.

[0016] Furthermore, the on-state voltage V1 < V for hysteresis control methods 1, 2, and 3. HH <V5<V ZH <V7<V YH <V8, V HH The voltage difference between V1 and V2 is not less than 0.3V. ZH The voltage difference between V5 and V6 is not less than 0.3V. YH The voltage difference between V7 and V8 is not less than 0.3V.

[0017] Furthermore, the power supply control voltage in the power supply control module is 400V.

[0018] Beneficial effects:

[0019] The advantages of this invention compared to the prior art are:

[0020] (1) Compared with the prior art, this invention proposes a high-voltage spacecraft load control system for distributed power supply, which solves the problem of intelligent and safe power supply of the load of the high-voltage spacecraft power system bus. The system has the advantages of fast response speed, good stability and good matching with the output characteristics of the droop power system.

[0021] (2) Compared with the prior art, the present invention realizes the intelligent load control function of 400V spacecraft power system based on droop control. Control strategies are set for general load, important load and core load respectively, and classified control is carried out. The turn-off voltage of general load, important load and core load is less than the minimum voltage of discharge power regulation domain, and the turn-on voltage is in the solar power regulation domain, grid power regulation domain and discharge power regulation domain respectively.

[0022] (3) Compared with the prior art, the power supply control module of the present invention has a high control voltage, good versatility, and strong scalability. It can be applied to various spacecraft power systems that adopt droop control, such as on-orbit reconfigurable satellite platforms, nuclear-powered spacecraft, high-power communication satellites, and lunar bases.

[0023] (4) Compared with the prior art, the system control logic of the present invention is simple and reliable. Attached Figure Description

[0024] Figure 1 This is a connection diagram of a high-voltage spacecraft load control system applied to a distributed power source according to the present invention.

[0025] Figure 2 This is a schematic diagram of a control strategy for a high-voltage spacecraft load control system applied to a distributed power source, according to the present invention.

[0026] Figure 3 This is a schematic diagram of the bus voltage domain division of a high-voltage spacecraft load control system applied to a distributed power source according to the present invention. Detailed Implementation

[0027] The present invention will now be described in detail with reference to the accompanying drawings and embodiments.

[0028] This invention addresses the shortcomings of existing high-voltage bus control systems, such as low bus voltage, limited load control functionality, and insufficient adaptability to droop-controlled spacecraft power systems. It designs a high-voltage spacecraft load control system for distributed power supplies, solving the problem of intelligent and safe load control for droop-controlled spacecraft high-voltage buses. The invention will now be described in detail with reference to the accompanying drawings.

[0029] like Figure 1 and Figure 2 As shown, this is a high-voltage spacecraft load control system applied to distributed power sources, including a fully adjustable bus, a power supply control module, an intelligent management module, and a high-voltage load, such as... Figure 3 The diagram shown is a schematic of the bus voltage domain division in a distributed power system.

[0030] The fully adjustable bus outputs 400V voltage to supply power to the power supply control module. The 400V bus is connected to the power supply control switches SSPC 1 to SSPC N.

[0031] The power supply control module consists of multiple parallel SSPC control switches used to perform load power supply switching operations. The two ends of power supply control switches SSPC 1 to SSPC N are connected to the high-voltage load and the fully regulated bus, respectively. The power supply control module uses SiC power transistors in its SSPC design and incorporates a freewheeling circuit. The input and output voltages are 400V, and expansion can be achieved by increasing the number of high-voltage power supply control modules.

[0032] The high-voltage load consists of high-voltage load 1 to high-voltage load N connected in parallel, and is connected one-to-one to the power supply control switches SSPC1 to SSPC N.

[0033] The intelligent management module is connected to the power supply control switches SSPC 1 to SSPC N; it employs a bus voltage domain control method to issue switching operation commands to the power supply control switches SSPC 1 to SSPC N. The intelligent management module of this invention is used to send switching commands to the SSPCs in the power supply control module. The hysteresis voltage value V of hysteresis control methods 1, 2, and 3 can be modified through design. YL V ZL V HL V YH V ZH and V HH .

[0034] The bus voltage is divided into four droop control domains from largest to smallest: solar power regulation domain, grid-connected power regulation domain, charging power regulation domain, and discharging power regulation domain. The bus voltage range of the solar power regulation domain is V7 to V8; the bus voltage range of the grid-connected power regulation domain is V5 to V6; the bus voltage range of the charging power regulation domain is V3 to V4; and the bus voltage range of the discharging power regulation domain is V1 to V2.

[0035] The bus voltage gradually decreases, when V BUS Below the normal range, reaching V YL At this time, the load is generally turned off; the bus voltage continues to decrease, when V BUS Reaching V ZL At that time, the important load is turned off; the bus voltage continues to decrease, when V BUS Reaching V HL At that time, the core load is shut down.

[0036] The bus voltage gradually increases, when V BUS Return to normal range, reaching V HH At that time, the core load is connected; the bus voltage continues to increase, when V BUS Reaching V ZH At that time, the important load is connected; the bus voltage continues to increase, when V BUS Reaching V HH At this time, the load is usually connected.

[0037] The control method for a general load involved in this invention employs hysteresis control method 1, when the bus voltage V BUS Reduce to V YL When the power supply control switch for general loads is disconnected, and the bus voltage V... BUS Rise to V YH At this time, the power supply control switch for general loads is turned on.

[0038] The control method for the critical load involved in this invention employs hysteresis control method 2, when the bus voltage V BUS Reduce to V ZLWhen the power supply control switch for the critical load is disconnected, and the bus voltage V... BUS Rise to V ZH When necessary, turn on the power supply control switch for important loads.

[0039] The core load control method involved in this invention employs hysteresis control method 3, when the bus voltage V BUS Reduce to V HL When the core load power supply control switch is disconnected, and the bus voltage V... BUS Rise to V HH At that time, turn on the power supply control switch for the core load.

[0040] V YL With V ZL The voltage difference between them is not less than 1V; V ZL With V HL The voltage difference between them is not less than 1V, V HL The voltage difference between V1 and V2 is not less than 1V; V YH The voltage difference between V7 and V1 is not less than 0.3V. ZH The voltage difference between V5 and V6 is not less than 0.3V. HH The voltage difference between V1 and V1 is not less than 0.3V.

[0041] The present invention provides a high-voltage spacecraft load control system applied to distributed power sources, which solves the problem of intelligent load safety control of high-voltage busbars in spacecraft based on distributed power sources.

[0042] In summary, the above are merely preferred embodiments of the present invention and are not intended to limit the scope of protection of the present invention. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the scope of protection of the present invention.

Claims

1. A high-voltage spacecraft load control system for distributed power sources, comprising a fully adjustable bus, a power supply control module, an intelligent management module, and a high-voltage load, wherein: The fully adjustable bus outputs 400V voltage to supply the power supply control module. The 400V voltage is connected to the power supply control switches SSPC1 to SSPC N. The power supply control module consists of multiple SSPC control switches connected in parallel, used to execute load power supply on / off commands; the two ends of the power supply control switches SSPC 1 to SSPC N are respectively connected to the high-voltage load and the fully regulating bus. The high-voltage load consists of high-voltage load 1 to high-voltage load N connected in parallel, and is connected one-to-one to the power supply control switches SSPC 1 to SSPC N; The intelligent management module is connected to the power supply control switches SSPC 1 to SSPC N; it collects the power supply voltage of each channel and issues switching commands to the power supply control switches SSPC 1 to SSPC N according to the predetermined domain control method. Based on the order of importance from low to high, high-voltage loads are divided into three categories: general loads, important loads, and core loads. The power on / off of general loads adopts hysteresis control method 1. When the intelligent management module detects the bus voltage V BUS Reduce to V YL When the intelligent management module issues a command to disconnect the power supply control switch for general loads, and the bus voltage V... BUS Rise to V YH At this time, the power supply control switch for general loads is turned on; where V YL <V1, the shutdown voltage is lower than the lower limit of the normal voltage; V7 <V YH <V8, the switching voltage is within the solar power regulation range; The hysteresis control method 2 is used to control the power on and off of critical loads. When the intelligent management module detects that the bus voltage V... BUS Reduce to V ZL When the intelligent management module issues a command to disconnect the power supply control switch for critical loads, and the bus voltage V... BUS Rise to V ZH At that time, the power supply control switch for the important load is turned on; where V ZL <V1, the shutdown voltage is lower than the lower limit of the normal voltage; V5 <V ZH <V6, the on-state voltage is within the grid-connected power regulation range; The core load's power-on / off operation employs hysteresis control method 3. When the intelligent management module detects the bus voltage V... BUS Reduce to V HL When the intelligent management module issues a command to disconnect the power supply control switch of the core load, and the bus voltage V... BUS Rise to V HH At that time, the power supply control switch of the core load is turned on; where V HL <V1, the shutdown voltage is lower than the lower limit of the normal voltage, V1 < V HH <V2, the on-state voltage is within the discharge power regulation range.

2. The high-voltage spacecraft load control system applied to distributed power sources according to claim 1, characterized in that: The output voltage of the fully regulated bus is 400V~405V; the bus voltage is divided into four droop control domains from high to low: solar power regulation domain, grid-connected power regulation domain, charging power regulation domain, and discharging power regulation domain; the bus voltage range of the solar power regulation domain is V7~V8; the bus voltage range of the grid-connected power regulation domain is V5~V6; the bus voltage range of the charging power regulation domain is V3~V4; and the bus voltage range of the discharging power regulation domain is V1~V2.

3. A high-voltage spacecraft load control system for distributed power sources according to claim 1, characterized in that: Turn-off voltage V for hysteresis control methods 1, 2, and 3 YL <V ZL <V HL <V1, and V YL With V ZL The voltage difference between them is not less than 1V; V ZL With V HL The voltage difference between them is not less than 1V, V HL The voltage difference between V1 and V1 is not less than 1V.

4. A high-voltage spacecraft load control system for distributed power sources according to claim 1, characterized in that: The on-state voltage V1 < V for hysteresis control methods 1, 2, and 3 HH <V5<V ZH <V7<V YH <V8, V HH The voltage difference between V1 and V2 is not less than 0.3V. ZH The voltage difference between V5 and V6 is not less than 0.3V. YH The voltage difference between V7 and V8 is not less than 0.3V.

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