Discharge module and spacecraft high-reliability battery pack power connection / disconnection control method

Abstract

The present invention provides a discharge module and a power connection / disconnection control method for a spacecraft high-reliability battery pack, which are used to realize the connection / disconnection control of a spacecraft high-reliability battery pack and reduce the weight of the power supply system. The power supply controller is connected between the battery pack and the bus, and is used to control the connection and disconnection of the battery pack. It is characterized in that it includes a discharge regulation circuit, an input power switch, an output power switch, and an auxiliary power supply, wherein the positive electrode of the battery pack is connected to the input power switch, the discharge regulation circuit, the output power switch, and the positive electrode of the bus in sequence, the negative electrode of the battery pack is connected to the discharge regulation circuit and the negative electrode of the bus in sequence, and the auxiliary power supply is connected to the input power switch and the output power switch to control their on and off.

Description

Technical Field

[0001] The invention relates to a discharge module and a power connection / disconnection control method for a spacecraft high-reliability storage battery pack, and is suitable for designing a spacecraft power supply system in which a storage battery pack is configured as an energy storage device. Background Art

[0002] The battery pack is a key device in the spacecraft power subsystem, used to provide power to the satellite during the satellite's eclipse period or when the light power is insufficient. According to the characteristics of the satellite mission, the power output of the satellite battery pack to the bus power control requirements are different at different stages: during the ground satellite test phase, the battery pack is required to achieve reliable power access and disconnection control, meet the satellite electrical measurement requirements when connected, and achieve reliable power off of the satellite when disconnected to ensure the safety of the satellite and personnel; from the launch of the satellite to the in-orbit operation phase, the battery pack is required to have reliable power access, and no power disconnection working mode is allowed, otherwise it may cause the entire satellite to lose power and affect the satellite's energy security.

[0003] In the traditional satellite power system design, the power connection / disconnection control of the battery pack as an energy storage device is implemented by a separate electronic stand-alone machine - the battery pack connection relay box. The connection / disconnection of the relay is controlled by commands in the ground phase, and the reliable connection of the battery pack power to the bus is ensured by prohibiting or canceling the relay disconnection command in the on-orbit phase. However, in theory, it is impossible to completely avoid the interference caused by the space environment, which may cause the relay or other switching devices to malfunction, causing some or all relays in the power path to disconnect. Although this is a low-probability event, once it occurs, it will affect the power supply reliability of the battery pack and the safety of the entire satellite, resulting in catastrophic consequences. In addition, the battery pack connection relay box needs to be configured separately, and it is usually implemented by multiple power relays in parallel. As the satellite power increases, the weight also increases, which will occupy the volume, weight and other resources of the satellite platform. Summary of the invention

[0004] Based on this background, the present invention proposes a spacecraft battery pack power controller and a method of using the same, which completely eliminates the power disconnection failure mode of the on-orbit battery pack, further improves the power supply safety and reliability of the satellite, and reduces the weight of the power system.

[0005] The present invention provides a discharge module, which is connected between a battery pack and a busbar and is used to control the connection and disconnection of the battery pack. The module is characterized in that it comprises a discharge regulation circuit, an input power switch, an output power switch and an auxiliary power supply, wherein the positive pole of the battery pack is connected to the input power switch, the discharge regulation circuit, the output power switch and the positive pole of the busbar in sequence, the negative pole of the battery pack is connected to the discharge regulation circuit and the negative pole of the busbar in sequence, and the auxiliary power supply is connected to the input power switch and the output power switch to control their connection and disconnection.

[0006] Furthermore, the power controller also includes an on-off control circuit, which is connected to the auxiliary power supply and outputs a TC_ISO_BAT signal to the auxiliary power supply. When the TC_ISO_BAT signal is low, the battery pack is disconnected from the bus channel. When the TC_ISO_BAT signal is high impedance, the battery pack is connected to the bus channel.

[0007] Furthermore, the access and disconnection control circuit is mainly composed of two relays connected in series, and the control line package of the relay is led out for the access / disconnection command interface. After the two relay contact ends are connected in series, the upper end is output to the auxiliary power supply control end of the discharge regulation module through the isolation diode, and the lower end leads out the STRAP signal, which is not connected to the bus return line BUS_RET.

[0008] The present invention also provides a method for using a spacecraft battery pack power controller. A method for controlling power connection / disconnection of a spacecraft high-reliability battery pack is characterized in that the power controller is used, specifically:

[0009] During the satellite ground phase, STRAP and RET are maintained in a short-circuited state through off-satellite equipment / cables, and the connection / disconnection control of the battery group power to the bus output is achieved by sending connection / disconnection commands;

[0010] During the satellite launch phase, after the satellite and rocket separate, the physical connection between the STRAP signal and the RET signal is disconnected, the TC_ISO_BAT signal is high impedance, and the battery pack power is stably and reliably output to the bus.

[0011] The beneficial effects of the present invention are that the reliability of the power supply path of the battery pack is increased, while achieving power system topology optimization and system weight reduction of more than 10Kg (satellites with power levels above 10kW), with good effects, good economic benefits and promotion value. BRIEF DESCRIPTION OF THE DRAWINGS

[0012] Figure 1 The power controller battery pack access / disconnection control circuit and interface of the present invention;

[0013] Figure 2 The connection diagram for the battery pack access / disconnection control during satellite ground testing (excluding the launch area at the launch site);

[0014] Figure 3 The connection diagram for the battery pack access / disconnection control in the launch area of ​​the satellite launch site;

[0015] Figure 4 This is the connection diagram for the battery pack connection / disconnection control after rocket-satellite separation to on-orbit operation. DETAILED DESCRIPTION

[0016] 1) Internal design of the power controller, the battery pack power connection / disconnection control circuit is used to control the auxiliary power output state (+13V) of the input and output power tube drive signal of the discharge regulation module in the power controller, thereby realizing the battery pack connection / disconnection power control, see Figure 1 ;

[0017] 2) During the satellite electrical test phase, the ground umbilical cable leads the STRAP-ISO signal and RET signal from the X2F of the entire satellite to the ground test equipment, and a switch is set in the test equipment to control the on / off of the STRAP-ISO signal and the RET signal. When the STRAP-ISO signal and the RET signal are connected, the battery pack power can be connected / disconnected by sending instructions to control the status of relays K1 and K2 to meet the test requirements of the entire satellite, see Figure 2 ;

[0018] 3) During the satellite electrical test phase, the onboard cable network leads the STRAP-ISO signal and RET signal to the satellite table plug X10B to meet the need for emergency power off of the satellite when the umbilical cable is disconnected during the AIT test of the entire satellite. The dedicated power off control device can be connected to X10B to send commands, see Figure 2 ;

[0019] 4) In the launch area stage of the launch site, the STRAP-ISO signal and the RET signal are directly short-circuited on the X2F(T) side of the satellite cable in the rocket, and the ground equipment sends commands to control the states of relays K1 and K2 to achieve the connection and disconnection control of the battery pack, see Figure 3 ;

[0020] 5) During the launch area phase of the launch site, the STRAP-ISO signal and the RET signal are led out to the EXB plug on the third-stage surface of the rocket through the intra-satellite cable network - the intra-satellite cable in the rocket. In order to deal with the emergency situation before the launch after the rocket is unplugged and the satellite needs to be powered off, the dedicated power-off control device can be connected to the EXB plug to send a command to realize the emergency power-off of the satellite to ensure the safety of the satellite. Figure 3 ;

[0021] 6) After the satellite is launched and before the rocket and satellite are separated, the separation plug is separated, the short-circuit between the STRAP-ISO signal and the RET signal is disconnected, the battery pack power is permanently connected to the power controller, and the connection / disconnection of the battery will no longer be controlled by the status of relays K1 and K2;

[0022] The satellite is fixed until the end of its life, the STRAP-ISO signal and the RET signal remain disconnected, the battery pack power is permanently connected to the power controller, and the connection / disconnection of the battery will no longer be controlled by the status of relays K1 and K2, so that the battery pack can be reliably powered.

Claims

1. A discharge module, connected between a battery pack and a bus bar, used to control the connection and disconnection of the battery pack, characterized in that: It includes a discharge regulating circuit, an input power switch, an output power switch, and an auxiliary power supply, wherein the positive electrode of the battery pack is connected to the input power switch, the discharge regulating circuit, the output power switch, and the positive electrode of the busbar in sequence, the negative electrode of the battery pack is connected to the discharge regulating circuit and the negative electrode of the busbar in sequence, and the auxiliary power supply is connected to the input power switch and the output power switch to control their on and off; It also includes an on-off control circuit, which is connected to the auxiliary power supply and outputs a TC_ISO_BAT signal to the auxiliary power supply. When the TC_ISO_BAT signal is low, the battery pack is disconnected from the bus path. When the TC_ISO_BAT signal is high impedance, the battery pack is connected to the bus path. The access and disconnection control circuit is mainly composed of two relays connected in series. The control line package of the relay is led out for the access / disconnection command interface. After the two relay contact ends are connected in series, the upper end is output to the auxiliary power supply control end of the discharge regulation module through the isolation diode, and the lower end leads out the STRAP signal, which is not connected to the bus return line BUS_RET.

2. A spacecraft high-reliability battery pack power connection / disconnection control method, characterized in that: The discharge module according to claim 1 is used, specifically: During the satellite ground phase, STRAP and RET are maintained in a short-circuited state through off-satellite equipment / cables, and the connection / disconnection control of the battery group power to the bus output is achieved by sending connection / disconnection commands; During the satellite launch phase, after the satellite and rocket separate, the physical connection between the STRAP signal and the RET signal is disconnected, the TC_ISO_BAT signal is high impedance, and the battery pack power is stably and reliably output to the bus.

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