Bus power interaction power supply and distribution system based on minimum system on board

Abstract

The application discloses a bus power interaction power supply and distribution system based on an on-satellite minimum system, which comprises a main power supply controller, a minimum system power supply, an interconnected bus and a bus interconnection switch; the main power supply controller and the minimum system power supply are connected through the interconnected bus, and the bus interconnection switch is arranged on the interconnected bus; the main power supply controller is used for supplying power to other devices on the satellite except for minimum system envelope devices; the minimum system power supply is used for supplying power to the minimum system envelope devices; and the bus interconnection switch is used for controlling the on-off between the main power supply controller and the minimum system power supply, so as to realize power interaction. The bus power interaction power supply and distribution system based on the on-satellite minimum system improves the reliability of the satellite and avoids the influence of single-point bus failure on the safety of the whole satellite.

Description

TECHNICAL FIELD

[0001] The application belongs to the technical field of satellite power supply and distribution, and particularly relates to a bus power interactive power supply and distribution system based on an on-orbit minimum system. BACKGROUND

[0002] The power supply and distribution subsystem is an important component of a satellite, and is mainly responsible for providing and distributing power for a payload and a platform in each flight phase of the satellite.

[0003] Currently, high-orbit large-power GEO communication satellites generally adopt a single-bus power supply and distribution system, and only one power conditioning unit (PCU) is configured, which is a single-point device. In order to ensure the safety of the PCU and the bus power supply, the PCU has undergone multiple rounds of rigorous verification and inspection in design, process and production process. The single-bus power supply and distribution system has low adaptability to large-power scenarios, and the system has no reconstruction capability. For important loads, except for the difference in under-voltage protection value, no special configuration is made in the power distribution mode, so the system has insufficient fault tolerance capability for single-point faults of the PCU device such as bus output short circuit.

[0004] With the increase of the power level of the satellite, the power supply and distribution system architecture also needs to be adjusted. Currently, the reliability of the power supply and distribution system of a communication satellite is above 0.99 at the beginning of the life, and needs to reach above 0.96 at the end of the life. For the system, high reliability does not mean that the influence range after a fault is small. For example, although the power conditioning unit adopts a multi-module redundant configuration, if a bus short circuit fault occurs, it will cause serious consequences. Therefore, the multi-module redundant cross backup cannot completely eliminate the single-point failure influence caused by the parallel output of the power conditioning unit through the bus bar, and the fundamental solution still needs to be improved and optimized from the topology architecture of the power supply and distribution system. SUMMARY

[0005] The technical problem of the application is to overcome the shortcomings of the prior art, and to provide a bus power interactive power supply and distribution system based on an on-orbit minimum system, which aims to improve the reliability of the satellite and avoid the influence of single-point faults of the bus on the safety of the whole satellite.

[0006] In order to solve the above technical problems, the application discloses a bus power interactive power supply and distribution system based on an on-orbit minimum system, which comprises a main power conditioning unit, a minimum system power supply, an interconnected bus and a bus interconnection switch.

[0007] The main power conditioning unit is used to supply power to other devices on the satellite except the minimum system envelope devices.

[0008] a minimum system power supply for supplying power to the minimum system envelope device;

[0009] a bus interconnection switch for controlling the on-off between the main power supply controller and the minimum system power supply; wherein when the bus interconnection switch is in a closed state, the main power supply controller and the minimum system power supply are connected, realizing the power interaction between the main power supply controller and the minimum system power supply; when the bus interconnection switch is in an open state, the main power supply controller and the minimum system power supply are isolated.

[0010] In the above bus power interaction power supply and distribution system based on the minimum system on the satellite, the main power supply controller comprises: N solar modules, 2M battery charge and discharge adjustment modules, a capacitor module CPA1 and a backplane assembly A;

[0011] Each solar module is connected with a solar cell array for obtaining power input from the solar cell array;

[0012] Each battery charge and discharge adjustment module is connected with a battery pack for realizing the charge and discharge of the battery pack;

[0013] The capacitor module CPA1 is used for stabilizing the bus voltage;

[0014] The backplane assembly A is used for connecting the mechanical and circuit interfaces of all modules in the main power supply controller together.

[0015] In the above bus power interaction power supply and distribution system based on the minimum system on the satellite, each solar module comprises a 3-way sequential switch shunt regulation circuit for realizing the power regulation of the solar cell array in the light period, so as to stabilize the bus voltage at a set value.

[0016] In the above bus power interaction power supply and distribution system based on the minimum system on the satellite, M and N are positive integers, and 4≤N≤10 and 6≤M≤18; the set value is 100V.

[0017] In the above bus power interaction power supply and distribution system based on the minimum system on the satellite, the minimum system power supply comprises: a solar module SUN N+1 , a battery charge and discharge adjustment module BCDR (M+1)A , a battery charge and discharge adjustment module BCDR (M+1)B , a capacitor module CPA2 and a backplane assembly B;

[0018] The solar module SUN N+1 is connected with a solar cell array for obtaining power input from the solar cell array;

[0019] The battery charge and discharge adjustment module BCDR (M+1)A and the battery charge and discharge adjustment module BCDR (M+1)BRespectively connected with the battery pack, used to realize the charge and discharge of the battery pack;

[0020] The capacitor module CPA2 is used for stabilizing the bus voltage;

[0021] The back plate assembly B is used for connecting the mechanical and circuit interfaces of all modules in the minimum system power supply together.

[0022] In the above-mentioned bus power interactive power supply and distribution system based on the minimum system on the satellite, the solar module SUN N+1 Comprises a 3-way sequential switch shunt regulating circuit, used for realizing the power regulation of the solar cell array in the illumination period, so that the bus voltage is stabilized at the set value.

[0023] In the above-mentioned bus power interactive power supply and distribution system based on the minimum system on the satellite, the minimum system power supply is a module separated from the main power supply controller.

[0024] In the above-mentioned bus power interactive power supply and distribution system based on the minimum system on the satellite, the minimum system refers to a system which can guarantee the safety of the satellite and can complete the normal operation of the minimum load function.

[0025] In the above-mentioned bus power interactive power supply and distribution system based on the minimum system on the satellite, the minimum system envelope device comprises important loads and important payloads of the satellite.

[0026] In the above-mentioned bus power interactive power supply and distribution system based on the minimum system on the satellite, the power range of the minimum system power supply is greater than the total power of the minimum system envelope device.

[0027] The present application has the following advantages:

[0028] (1) The present application discloses a bus power interactive power supply and distribution system based on the minimum system on the satellite, which is decomposed reasonably on the basis of the original PCU, and the minimum system power supply is added to guarantee the uninterrupted operation of the minimum system of the satellite, has the flexible reconstruction ability, avoids the influence of the single point fault of the bus on the safety of the whole satellite, and improves the reliability of the satellite

[0029] (2) The present application discloses a bus power interactive power supply and distribution system based on the minimum system on the satellite, which is good in adaptability to the high-power (more than 20kW) communication satellite, avoids the single point problem caused by the single bus and single PCU, and truly realizes the continuous service on the satellite and guarantees the safety of the whole satellite. BRIEF DESCRIPTION OF DRAWINGS

[0030] Figure 1 It is a composition block diagram of a bus power interactive power supply and distribution system based on the minimum system on the satellite in the embodiment of the present application. DETAILED DESCRIPTION

[0031] In order to make the objects, technical solutions and advantages of the present application clearer, the disclosed embodiments of the present application will be further described in detail below with reference to the drawings.

[0032] As Figure 1 In the embodiment, the bus power interaction power supply system based on the minimum system on the satellite comprises a main power controller, a minimum system power supply, an interconnected bus and a bus interconnection switch, wherein the main power controller and the minimum system power supply are connected through the interconnected bus, and the bus interconnection switch is arranged on the interconnected bus.

[0033] The main power controller is used for supplying power to other devices on the satellite except for the minimum system envelope devices.

[0034] In the embodiment, the minimum system refers to a system that can ensure the safety of the satellite and complete the normal operation of the minimum payload. The minimum system envelope devices generally include important payloads of the satellite (i.e. a series of payloads with the lowest under-voltage value in the under-voltage protection design, such as a central computer, a control system hub, an attitude and orbit control system hub and an actuator), and in order to meet the normal operation of the minimum function, part of the important payloads also need to be listed as the envelope of the minimum system.

[0035] Taking a DFH-4E typical communication satellite as an example, the selection principle of the minimum system envelope devices is as follows: the devices with an under-voltage protection threshold lower than 60V (the normal bus voltage of the whole satellite is 100V), generally the central computer, the control system and the important single machines of the attitude and orbit control system. Further, in the communication satellite, the devices with an under-voltage protection threshold lower than 60V, which means that the bus voltage drops due to a sudden situation, still need to work normally to ensure the controllability of the whole satellite, and belong to the key devices of the whole satellite. These devices need to be included in the minimum system envelope. In addition, part of the important payloads, such as antennas, traveling wave tube amplifiers and frequency converters, which can support communication business, although the under-voltage protection threshold is all above 60V, a part of them can be selected according to the business level of the whole satellite to be included in the minimum system envelope, so as to ensure that the minimum system power supply can support the continuous operation of part of the business of the whole satellite.

[0036] Preferably, the main power controller can specifically comprise N solar modules, 2M battery charge and discharge adjustment modules, a capacitor module CPA1 and a backplane assembly A. The solar modules are respectively connected with the solar cell array, and are used for obtaining power input from the solar cell array. The battery charge and discharge adjustment modules are respectively connected with the battery pack, and are used for realizing the charge and discharge of the battery pack. The capacitor module CPA1 is used for stabilizing the bus voltage. The backplane assembly A is used for connecting the mechanical and circuit interfaces of all the modules in the main power controller together. Wherein, M and N are both positive integers, and 4≤N≤10 and 6≤M≤18.

[0037] Further, each solar module includes a 3-path sequential switch shunt regulation circuit for regulating the power of the solar cell array during the light period, so that the bus voltage is stabilized at a set value (e.g. 100V). Among the 3-path sequential switch shunt regulation circuits, only one is in the adjustment state, and the other two are in the state of supplying power to the bus or shunting to the ground. When the load is reduced, the 3-path sequential switch shunt regulation circuits enter the shunt state in turn; on the contrary, when the load is increased, the 3-path sequential switch shunt regulation circuits exit the shunt state in turn and turn to the state of supplying power to the bus. The solar cell array energy is shunted to the ground or supplied to the bus according to the load demand, and is adjusted through the intermediate stage to ensure the stability of the bus voltage.

[0038] A minimum system power supply for supplying power to the minimum system envelope device.

[0039] In the embodiment, the device in the minimum system is powered by the minimum system power supply. The minimum system power supply is a module separated from the main power supply controller. The separation strategy should ensure that the composition of the minimum system power supply is completely consistent with the basic structure of the main power supply controller. The minimum system power supply is completely independent of the main power supply controller in physical location and will not cause common cause failure.

[0040] Preferably, the minimum system power supply can specifically include: a solar module SUN N+1 , a battery charge-discharge regulation module BCDR (M+1)A , a battery charge-discharge regulation module BCDR (M+1)B , a capacitor module CPA2 and a backplane assembly B. Among them, the solar module SUN N+1 is connected to the solar cell array for obtaining power input from the solar cell array. The battery charge-discharge regulation module BCDR (M+1)A and the battery charge-discharge regulation module BCDR (M+1)B are connected to the battery pack respectively for realizing the charge-discharge of the battery pack. The capacitor module CPA2 is used for stabilizing the bus voltage. The backplane assembly B is used for connecting the mechanical and circuit interfaces of all modules in the minimum system power supply together. Further, like the solar module in the main power supply controller, the solar module SUN N+1 in the minimum system power supply also includes a 3-path sequential switch shunt regulation circuit, and the function is the same as that of the 3-path sequential switch shunt regulation circuit in the solar module SUN N+1 , which will not be described here.

[0041] During the earth shadow period, the battery group works, and the power is outputted through the battery charge-discharge adjustment module. During the light period, the solar cell array works, and the power is outputted through the solar module. Assuming that the output power of one battery charge-discharge adjustment module is 2kW, and the output power of one solar module is 5kW, the minimum system power output power during the earth shadow period is 4kW, and the minimum system power output power during the light period is 5kW. Considering that the minimum system power can be safely carried during the whole period, the power sum of the minimum system envelope device should be less than 4kW.

[0042] The output bus of the minimum system power is connected to the backup of the determined minimum system envelope device; the minimum system power is configured with corresponding solar cells and battery groups according to the required power, so as to ensure uninterrupted power supply of the minimum system power during the whole period under normal working conditions.

[0043] The bus interconnection switch is used for controlling the on-off between the main power controller and the minimum system power.

[0044] In the embodiment, under normal circumstances, the bus interconnection switch is in the closed state, the main power controller and the minimum system power are connected, and the power is exchanged. When the main power controller has a single point fault such as bus short circuit, the bus interconnection switch detects the fault signal and automatically opens, so as to realize the isolation of the main power controller and the minimum system power, and ensure that the minimum system can work independently.

[0045] Based on the above embodiment, taking the high-orbit communication satellite of the DFH-4E typical platform as an example, N=7 and M=6, there are:

[0046] The main power controller comprises: solar modules SUN1-SUN7, battery charge-discharge adjustment modules BCDR 1A -BCDR 6A , battery charge-discharge adjustment modules BCDR 1B -BCDR 6B , a capacitor module CPA1 and a backplane assembly A. The minimum system power comprises: a solar module SUN8, a battery charge-discharge adjustment module BCDR 7A , a battery charge-discharge adjustment module BCDR 7B , a capacitor module CPA2 and a backplane assembly B.

[0047] For the high-orbit communication satellite of the DFH-4E typical platform: for the power consumption equipment on the satellite, the priority level of obtaining power is determined according to the functional properties and importance. Among them, the key equipment is the power consumption equipment necessary to ensure the safety of the satellite, the important equipment is the equipment necessary to ensure the continuous operation of the satellite, and the rest is the general equipment. According to the current configuration of the typical platform communication satellite, the equipment classification is shown in Table 1:

[0048]

[0049]

[0050] Table 1, on-board power equipment classification table

[0051] The minimum system envelope equipment can be determined by the under-voltage protection threshold <60V, that is, based on the above Table 1, the power of the whole-star key equipment and part of the important load equipment with the under-voltage protection threshold <60V is sorted out, and the minimum system envelope list is shown in Table 2:

[0052]

[0053] Table 2, minimum system envelope equipment

[0054] It can be seen that the power sum of the minimum system envelope equipment of the typical satellite is about 2150W.

[0055] The significance of introducing the minimum system is to separate the key and part of the important equipment of the whole satellite from the current single PCU power distribution mode, that is, to separate the functional modules (SUN module, BCDR module, CAP module, backplane) from the main PCU to form a minimum system power supply, to supply power to the backup of the minimum system envelope equipment, and to configure the corresponding solar cell array and battery pack interface to always provide uninterrupted power supply for the minimum system, and to ensure the safe and normal operation of the satellite basic functions.

[0056] Since the total power of the whole satellite is constant, two power supplies can be set, one is the master power controller, and the other is the minimum system power separated from the master power controller. The power range of the minimum system power needs to be greater than the total power of the minimum system envelope equipment. The output bus of the minimum system power is connected to the backup of the envelope equipment. The bus interconnection switch is set between the bus of the master power controller and the bus of the minimum system power, which is convenient for power interaction, and can realize fault isolation and system reconstruction at emergency time (fault working condition).

[0057] Fault working condition:

[0058] 1) Short circuit occurs: current telemetry is set on the bus interconnection switch, when the current telemetry value is greater than 1.5 times the power transmission capacity of the minimum system power (4kW / 100V*1.5=60A), it is considered that a short circuit fault occurs at some place, at this time, the bus interconnection switch should be quickly cut off to ensure that the master power controller and the minimum system power run independently and do not affect each other, switch the fault diffusion path, and complete system reconstruction.

[0059] 2) Single module output failure: When the output power is insufficient due to failure of other modules in the main power controller, power interaction can be performed through the interconnection channel (formed when the bus interconnection switch is closed) to ensure normal operation of the entire satellite.

[0060] The system reconstruction mode under several typical failure conditions is as follows:

[0061] 1) Failure of any solar module in the main power controller

[0062] The solar module contains 3-way sequential switch shunt regulation circuit. According to the circuit characteristics and protection design, single failure will only cause a certain S3R circuit to be always on. At this time, the solar cell array power corresponding to the S3R circuit will be sent to the bus. However, since all S3R circuits in the solar module are connected in parallel, the next stage S3R circuit will continue to participate in shunt regulation to maintain the bus voltage. At this time, the bus section switch remains closed, and the power supply of the entire satellite is not affected.

[0063] 2) Failure of any battery charge and discharge regulation module in the main power controller

[0064] Battery charge and discharge regulation module BCDR xA When the battery charge and discharge regulation module BCDR (x = 1 ~ 7) fails to work, the corresponding battery charge and discharge regulation module BCDR needs to be turned off. xB The two groups of battery packs connected to the main power controller are in the same charge and discharge state, ensuring the consistency of the service life of the two groups of battery packs. The battery charge and discharge regulation module of the entire satellite adopts a 14-to-12 design. At this time, there are 2 battery charge and discharge regulation modules in the main power controller that do not output power, but there are 2 battery charge and discharge regulation modules in the minimum system power supply. The power of the battery pack can be sent to the main power controller through the interconnection bus to ensure the normal function of the battery charge and discharge of the entire satellite. At this time, the bus interconnection switch remains closed, and the power supply of the entire satellite is not affected.

[0065] 3) Failure of solar module in minimum system power supply

[0066] This case is similar to the main power controller, only a certain S3R circuit is always on. There are 3 S3R circuits in a solar module, and the bus interconnection switch and the solar module in the main power controller also form an interconnection, ensuring that the S3R circuit in the next stage participates in shunt regulation to eliminate the influence of the always-on S3R circuit due to failure, ensuring that the bus voltage remains unchanged. At this time, the bus interconnection switch remains closed, and the power supply of the entire satellite is not affected.

[0067] 4) Failure of battery charge and discharge regulation module in minimum system power supply

[0068] When the battery charge and discharge regulation module in the minimum system power supply fails, the corresponding battery pack cannot output power to the bus. However, since there is an interconnected bus, the main power controller can deliver the battery pack power to the minimum system envelope device, and the bus interconnection switch remains closed, so that the power supply of the whole satellite is not affected.

[0069] 5) Bus short circuit failure in the main power controller

[0070] When a bus short circuit occurs in the main power controller, the bus interconnection switch detects a large current and is automatically disconnected, so that the minimum system power supply is not affected by the failure of the main power controller, and the problem is prevented from spreading. At this time, the minimum system power supply is working normally, and long-term support is provided for the key devices and important loads of the whole satellite platform. If it is determined through satellite telemetry state and other methods that the failure point has been restored and the conditions for re-connection of the main power controller are met, the bus interconnection switch can be closed again by sending a command.

[0071] 6) Bus short circuit failure in the minimum system power supply

[0072] When a bus short circuit occurs in the minimum system power supply, the bus interconnection switch is disconnected quickly, and the design of the main power controller can fully support all functions of the whole satellite for a long time. If it is determined through satellite telemetry state and other methods that the failure point has been restored and the conditions for connection of the minimum system power supply to the main bus are met, the bus interconnection switch can be closed again by sending a command.

[0073] Compared with the single-bus architecture, the bus power interaction power supply system based on the minimum system on the satellite proposed in the application divides the minimum system power supply from the main power controller by two, forms isolation in physical location, eliminates the single-point problem of the bus, has flexible reconfigurable capability, and is a highly reliable on-board power supply architecture.

[0074] It should be noted that in the present embodiment, S3R: Sequential Switching Shunt Regulator, sequential switching shunt regulator; BCDR: Battery Charge and Discharge Regulator, battery charge and discharge regulation; CAP: Capacitance, capacitance.

[0075] Although the application has been disclosed with reference to the preferred embodiments above, it is not intended to limit the application, and any person skilled in the art can make possible changes and modifications to the technical solutions of the application by using the disclosed methods and technical contents without departing from the spirit and scope of the application. Therefore, any simple modification, equivalent change and modification made to the above embodiments according to the technical essence of the application, which does not deviate from the technical solutions of the application, belongs to the protection scope of the technical solutions of the application.

[0076] That which is not specifically described in the specification of the present application is within the knowledge of the skilled person.

Claims

1. A power exchange and distribution system based on the minimum system bus power on board, characterized in that, The system comprises: a main power controller, a minimum system power supply, an interconnection bus, and a bus interconnection switch; the main power controller and the minimum system power supply are connected through the interconnection bus, and the bus interconnection switch is arranged on the interconnection bus; the main power controller is used for supplying power to devices other than the minimum system envelope devices on the satellite; the minimum system power supply is used for supplying power to the minimum system envelope devices; the bus interconnection switch is used for controlling the on-off between the main power controller and the minimum system power supply; under normal conditions, the bus interconnection switch is in a closed state, the main power controller and the minimum system power supply are connected, and power interaction between the main power controller and the minimum system power supply is realized; under fault conditions, the bus interconnection switch is controlled to be in an open or closed state, fault isolation and system reconstruction are realized; the fault conditions include: 1) short circuit: a current telemetry is arranged on the bus interconnection switch, when it is detected that the current telemetry value is greater than 1.5 times the power transmission capacity of the minimum system power supply, it is considered that a short circuit fault occurs, the bus interconnection switch is cut off, the main power controller and the minimum system power supply are ensured to operate independently and not to affect each other, the fault diffusion path is cut off, and system reconstruction is completed; 2) single module output fault: when a single module fault in the main power controller causes insufficient output power or the minimum system power supply fails to output power, the bus interconnection switch is closed, and the interconnection channel is used for power interaction, so that the power supply of the whole satellite is not affected; the minimum system refers to a system that ensures the safety of the satellite and can normally operate the minimum load; the minimum system envelope devices include important loads and important payloads of the satellite; the minimum system power supply is a module separated from the main power controller; the minimum system power supply and the main power controller are completely independent in physical position and will not cause common cause failure.

2. The on-board minimum system based bus power interaction power distribution system according to claim 1, wherein, The main power controller comprises N solar modules, 2M battery charge-discharge adjustment modules, a capacitor module CPA1, and a backplane assembly A; each solar module is connected with a solar cell array and is used for obtaining power input from the solar cell array; each battery charge-discharge adjustment module is connected with a battery pack and is used for realizing charge and discharge of the battery pack; the capacitor module CPA1 is used for stabilizing the bus voltage; the backplane assembly A is used for connecting mechanical and circuit interfaces of all modules in the main power controller.

3. The on-board minimum system based bus power interaction power distribution system of claim 2, wherein, Each solar module comprises a 3-way sequential switch shunt adjustment circuit, which is used for realizing power adjustment of the solar cell array during the light period, so that the bus voltage is stabilized at a set value.

4. The on-board minimum system based bus power trading system of claim 3, wherein, M and N are positive integers, and 4≤N≤10 and 6≤M≤18; the set value is 100V.

5. The on-board minimum system based bus power trading system of claim 1, wherein, Minimum system power supply, comprising: a solar module SUN N+1 , a battery charge-discharge regulation module BCDR (M+1)A , a battery charge-discharge regulation module BCDR (M+1)B , a capacitor module CPA2 and a backplane assembly B; Solar module SUN N+1 connected to the solar cell array for obtaining a supply input from the solar cell array; Battery charge-discharge regulation module BCDR (M+1)A and battery charge-discharge regulation module BCDR (M+1)B are respectively connected with the battery pack for realizing charge-discharge of the battery pack; The capacitor module CPA2 is used for stabilizing the bus voltage; the backplane assembly B is used for connecting mechanical and circuit interfaces of all modules in the minimum system power supply.

6. The on-board minimum system based bus power trading system of claim 5, wherein, Solar module SUN N+1 The circuit includes a 3-way sequential switch shunt regulation circuit for regulating the power of the solar cell array during the light period, so that the bus voltage is stabilized at a set value.

7. The on-board minimum system based bus power trading system of claim 1, wherein, The power range of the minimum system power supply is greater than the total power of the minimum system envelope devices.

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