DE202023100648U1 - Self-sufficient battery module for a battery system and battery system - Google Patents

Abstract

Self-sufficiently operable battery module (10) for a battery system (100) of a satellite or spacecraft, with a carrier board (20) on which a plurality of battery cells (12) and operating components (88) for temperature control of the battery cells (12), for charge equalization between the battery cells (12) and for monitoring the battery cells (12) are arranged, wherein communication means (37) are also present on the carrier board (20) for communication with the battery system (100) and further battery modules (10) in the battery system (100), and connecting means (33) for electrical serial and/or parallel coupling with one or more further similar battery modules (10) are arranged on the carrier board (20).

Description

State of the art

The invention relates to an autonomously operable battery module for a battery system, in particular of a satellite or spacecraft, with a plurality of battery cells and to a battery system of a satellite or spacecraft, with at least one battery module.

Tried and tested technology is usually used in space applications. This means that components that are years or decades old are used. These are tried and tested and have proven to be flight-ready in many satellites for many years. However, these components are also simple and outdated. In the case of Li-ion battery cells, this means that there are already new generations with better power density. Electronic components in battery management have microcontrollers and circuits that enable more functionality. In larger space systems, analogue circuits are usually used for battery systems. In addition, only the total voltage and temperatures at a few points in the battery system are usually monitored.

In space travel, an increased level of qualification is also necessary to demonstrate the functionality of components, for example a battery system.

Disclosure of the invention

The object of the invention is to create a cost-effective, self-sufficient battery module for a battery system of a satellite or spacecraft with a plurality of battery cells.

A further task is to create a cost-effective battery system for a satellite or spacecraft with at least two autonomously operable battery modules.

A further object is to provide a method for operating a cost-effective battery system of a satellite or spacecraft with at least two autonomously operable battery modules.

The objects are achieved by the features of the independent claims. Favorable embodiments and advantages of the invention emerge from the further claims, the description and the drawing.

According to one aspect of the invention, a battery module for a battery system of a satellite or spacecraft that can be operated independently is proposed, with a carrier board on which a plurality of battery cells and operating components for controlling the temperature of the battery cells, for balancing the charge between the battery cells and for monitoring the battery cells are arranged. Furthermore, communication means are present on the carrier board for communication with the battery system and other battery modules in the battery system. Connection means for electrical serial and/or parallel coupling with one or more other similar battery modules are arranged on the carrier board.

The proposed autonomously operable battery module advantageously enables the implementation of battery systems, in particular for space applications such as satellites, with commercial components, also known as so-called commercial off-the-shelf (COTS) components. The battery module forms in particular a base module from which, by adding further, preferably identical battery modules, different battery systems with greater electrical power and/or greater electrical voltage and/or electrical capacity can be formed. The battery module can be qualified for use in a satellite or spacecraft. This means that further, usually very complex, qualification of battery systems constructed from such identical battery modules can be omitted.

The scalability of the proposed battery module makes it possible to create modular battery systems in which the battery modules can be connected in parallel and/or in series, so that voltage, and/or current, and/or capacity can be easily adapted for each space mission. Such battery modules can be connected together in a suitable manner and form battery systems with different voltage levels, and/or different power, and/or different energy content. For this purpose, the battery modules have the necessary connecting means for parallel and serial connection as well as communication means for communication with other battery modules or the battery system. Connecting means can be, for example, the connectors of the positive power connection and ground connection as well as connectors for data lines for controlling charge equalization of the battery cells.

A control and regulation device as well as a unit for monitoring and/or balancing the charge between the battery cells can advantageously enable the collection of data from each individual battery cell and the processing of the data with algorithms in the battery module itself. lichen. But the communication of data to the earth is also possible. In addition, some operating parameters, such as heating and charge balancing, can be adjusted during operation. Adaptive charge balancing, in which the end-of-charge voltage can be changed, is particularly important for the operation of satellites or spacecraft. Here, a lower end-of-charge voltage can initially increase the service life of the battery cells. Later in the life cycle of the satellite or spacecraft, a higher end-of-charge voltage can increase the operating time of the satellite or spacecraft by providing more energy.

Monitoring the battery cells using the monitoring and/or charge balancing unit and processing the data in the control and/or regulating device makes it possible to use complex algorithms to determine the state of charge (SOC) and the state of health (SOH) of the battery cells. SOC and SOH give the operator, for example of the satellite, insight into the state of the battery cells and the entire battery system. The operator thus receives detailed information about which charge is still available for current operation and for what period the satellite can still be operated safely. This also makes it possible to qualify more complex circuits for space travel with reasonable effort.

The carrier board, for example a standard circuit board, serves as the basis of the battery module. The electronic components are arranged on the carrier board. The board has connection points for battery cells, power supply, ground, communication, sensors and interconnection with other battery modules or with a battery system.

The electronic components jointly perform tasks such as monitoring the battery module and the battery cells, for example with voltage, current, temperature. The battery module can also be analyzed, for example calculating the SOC and SOH of the battery cells, and/or comparing the values with set limits. The battery module can be managed by controlling the charge balance and heating the battery cells. The electronic components also handle external data communication and processing commands from outside. The components ensure that the electronics and the battery cells are protected from errors and/or short circuits in semiconductors caused by radiation from space, so-called single event effects, and can also correct such errors under certain circumstances.

The carrier board can also have holding devices for holding the battery cells, thus also serving as a structural component for the battery cells. In addition, the carrier board can also have operating components for monitoring and controlling the thermal balance of the battery cells. In this way, the carrier board ensures mechanical and thermal stability of the battery module.

Advantageously, the battery modules can be stackable, for example, thus enabling the construction of a compact battery system with expandable current and capacity.

According to a favorable design of the battery module, the carrier board can have first and second holding devices. The battery cells can be clamped between a first and a second holding device. The first and second holding devices can advantageously encompass the battery cells at opposite ends on their circumference, at least in some areas. In this way, round cells in particular can be accommodated safely and in a mechanically stable manner. Vibration requirements, such as those mandatory in space travel, can also be advantageously met in this way.

According to a favorable design of the battery module, one of the first holding devices can be arranged on opposite side edges of the carrier board. Battery cells can thus be advantageously clamped between the first holding devices.

According to a favorable design of the battery module, the second holding devices can be arranged, in particular centrally, between the first holding devices. The second holding device can advantageously be designed to fix battery cells arranged on both sides of the second holding device. This advantageously saves installation space and weight.

According to a favorable design of the battery module, the battery cells can be arranged horizontally on the carrier board. In particular, the battery cells can be designed as round cells; round cells can be used inexpensively as commercial battery cells from mass production.

According to a favorable design of the battery module, the battery cells can be arranged next to each other and/or one behind the other with respect to their longitudinal axis, wherein the battery cells are electrically connected in parallel and/or in series on the carrier board. switched or interconnectable. This allows a modular design of the battery module with a variety of interconnection options. In this way, desired voltage levels can easily be achieved or capacity requirements can be met.

According to a favorable design of the battery module, structural elements can be arranged at least in some areas between adjacent battery cells, which are designed for passive temperature control of the battery cells. The structural elements can be adapted to an external shape of the battery cells at least in some areas. In particular, the structural elements can have a negative contour of the battery cells in some areas and nestle against the battery cells. Metallic structural elements can advantageously dissipate heat. In addition, heating elements, such as heating resistors, can advantageously be arranged on the structural elements or even integrated. This allows the thermal balance of the battery cells to be advantageously controlled.

If the battery module is designed in a favorable way, the structural elements can be integrated into the holding devices. This saves installation space and can also make the assembly of the battery modules easier.

According to a favorable design of the battery module, the carrier board can have one or more heating elements. In particular, one or more heating elements can be integrated into the structural elements. The heating elements can advantageously bring the battery cells to the necessary operating temperatures. This feature is particularly important for space applications when the satellite experiences cooling due to radiation losses in positions facing away from the sun.

According to a favorable design of the battery module, a heating element can be provided for simultaneously heating at least two adjacent battery cells on the carrier board. This advantageously reduces the number of components and thus the costs.

According to a favorable design of the battery module, the carrier board can have one or more temperature sensors, which are provided for thermal contact with the battery cells. In this way, the temperature of each battery cell can advantageously be determined and a detailed overview of the condition of the battery module can be obtained from this.

If the battery module is designed in a favorable way, the connection poles of the battery cells can be electrically connected to the current paths of the carrier board using cell connectors. The battery cells can thus be electrically contacted in the desired circuit in a flexible and simple manner.

According to an advantageous design of the battery module, the carrier board can have at least one unit for monitoring and charge balancing of the battery cells in at least one free space between the battery cells. In this way, the battery module can be monitored in detail for its condition. Charge balancing can be passive or active, depending on the electronic components used. With passive charge balancing, all battery cells of the battery module are set to the lowest voltage of a battery cell of the battery module by consuming excess electrical charge, for example in a resistor. With active charge balancing, electrical charge can be shifted from a battery cell with a higher voltage to a battery cell with a lower voltage. This makes it possible to set an average voltage of the battery cells of the battery module.

Advantageously, the unit for monitoring and balancing the charge of the battery cells can be designed to selectably set a final charge voltage for the battery cells. In this way, an adaptive charge balancing of the battery cells can be carried out, in which the final charge voltage can be changed. Here, for example, at the start of the mission, a lower final charge voltage can increase the service life of the battery cells. Later in the life cycle of the satellite, a higher final charge voltage can increase the operational time of the satellite by providing more energy.

According to a favorable embodiment of the battery module, the carrier board can have at least one regulating and control device, in particular a microcontroller, for controlling a charging and discharging operation of the battery cells in at least one free space between the battery cells.

In particular, the control and regulating device can be designed to determine a charge state and/or an aging state of the battery cells. In this way, the battery module can be monitored in detail and an overall state of the battery module can be determined with a forecast for the further service life of the battery cells.

According to a favorable design of the battery module, the carrier board can have at least one CAN transceiver in at least one free space between the battery cells for communication with other battery modules and/or the battery system. CAN networks are widely used communication applications, particularly in the automotive sector, which can also be used cost-effectively and very flexibly in the battery module.

According to a favorable design of the battery module, the first and second holding devices of the carrier board can be designed for mechanical connection to a carrier board of another battery module stacked above it and/or a terminal board. The holding devices as structural components of the battery module can conveniently accommodate other stacked battery modules and lead to a mechanically stable assembly.

According to a further aspect of the invention, a battery system of a satellite or spacecraft is proposed, with at least two battery modules that can be operated independently. The at least two battery modules are of identical construction and each have a carrier board on which a plurality of battery cells and operating components for controlling the temperature of the battery cells, for balancing the charge between the battery cells and for monitoring the battery cells are arranged.

Furthermore, there are communication means on the carrier board for communication with the battery system and the at least one further battery module in the battery system. The at least two battery modules are electrically coupled in series and/or in parallel by means of connecting means which are arranged on the carrier board.

In this case, a battery module forms in particular a base module from which different types of battery systems with greater electrical power and/or greater electrical voltage and/or electrical capacity can be formed by adding further, preferably identical battery modules. The battery module can be qualified for use in a satellite or spacecraft. This means that further, usually very complex, qualification of battery systems constructed from such identical battery modules can be omitted.

The proposed battery system for space applications such as satellites can advantageously be implemented with commercial components, also known as Commercial Off-The-Shelf (COTS) components.

The proposed battery system is modular and scalable, as it has battery modules that can be operated independently and can be connected in parallel and/or series. This means that the voltage and/or current and/or capacity of the battery system can be easily adapted for each space mission. The battery modules can be connected together in a suitable manner and form battery systems with different voltage levels and/or different power and/or different energy content.

For this purpose, the battery modules have the respective interfaces for parallel and serial connections and for communication with other battery modules or the battery system. For this purpose, the battery modules have the necessary connection means for parallel and serial connections and communication means for communication with other battery modules or the battery system. Connection means can be, for example, the connectors for the positive power connection and ground connection as well as connectors for data lines for controlling charge equalization of the battery cells.

Advantageously, a control and regulation device and a unit for monitoring and/or charge balancing between the battery cells can advantageously enable the collection of data from each individual battery cell and the processing of the data with algorithms in the at least one battery module itself. However, communication of the data to Earth is also possible. In addition, some operating parameters, such as heating, charge balancing, can be adjusted during operation. Adaptive charge balancing, in which the end-of-charge voltage can be changed, is particularly important for the operation of satellites or spacecraft. Here, a lower end-of-charge voltage can initially increase the service life of the battery cells. Later in the life cycle of the satellite or spacecraft, a higher end-of-charge voltage can increase the operating time of the satellite or spacecraft by providing more energy.

Monitoring the battery cells using the monitoring and/or charge balancing unit and processing the data in the control and/or regulating device makes it possible to use complex algorithms to determine the state of charge (SOC) and the state of health (SOH) of the battery cells. SOC and SOH give the operator, for example of the satellite, insight into the state of the battery cells and the entire battery system. The operator thus conveniently receives detailed information on which charge is required for the current operation is still available or over what period the satellite can still be operated safely. This also makes it possible to qualify more complex circuits for space travel with reasonable effort.

The carrier board, for example a standard circuit board, serves as the basis of the battery module. The electronic components are arranged on the carrier board. The board has connection points for battery cells, power supply, ground, communication, sensors and interconnection with other battery modules or with the battery system.

The electronic components jointly perform tasks such as monitoring the battery system with its battery modules and their battery cells, for example with voltage, current, temperature. The battery module can also be analyzed, for example calculating the SOC and SOH of the battery cells, and/or comparing the values with set limits. The battery module can be managed by controlling the charge balance and heating the battery cells.

The electronic components also handle external data communication and processing commands from the outside. The components ensure that the electronics and battery cells are protected from errors and/or short circuits in semiconductors caused by radiation from space, so-called single event effects, and can also correct such errors under certain circumstances.

The carrier board can also have holding devices for holding the battery cells, thus also serving as a structural component for the battery cells. In addition, the carrier board can also have operating components for monitoring and controlling the thermal balance of the battery cells. In this way, the carrier board ensures mechanical and thermal stability of the battery module.

Advantageously, the battery modules in the battery system can be stackable, thus enabling the construction of a compact battery system with expandable current and capacity.

According to a favorable embodiment of the battery system, the at least two battery modules can be arranged in a battery housing. In particular, at least one of the battery modules can be closed with a termination board, which is arranged on a holding device of the at least one battery module. In particular, the uppermost battery module in a stacking direction can be closed with the termination board. Such a battery housing made of, for example, two housing parts can be assembled favorably. The termination board represents a cover for the uppermost battery module. This makes it easy to remove or replace the battery modules, for example in the event of a fault or to change the required connections.

According to a favorable embodiment of the battery system, the battery housing can have holders for fixing to a mounting plate, in particular to a mounting plate of the satellite or spacecraft. Alternatively or additionally, the battery housing can have at least one electrical connector for power supply and/or for transmitting data. The housing parts can thus be easily mounted on a platform of a satellite and electrically connected, for example.

According to a favorable embodiment of the battery system, the terminating board can have at least one electrical connection for an onboard data connection and/or an electrical connection for programming a control and regulation device, in particular a microcontroller. Electrical communication with the battery system can be carried out in a simple manner via the terminating board. In addition, configurations and programming can be carried out advantageously.

To operate a battery module that can be operated independently, the end-of-charge voltage of the battery cells can advantageously be selected according to operating parameters and/or set using a unit for monitoring and balancing the charge of battery cells. Adaptive charge balancing, in which the end-of-charge voltage can be changed, is particularly important for the operation of satellites. Here, a lower end-of-charge voltage can initially increase the service life of the battery cells. Later in the life cycle of the satellite, a higher end-of-charge voltage can increase the operating time of the satellite by providing more energy.

Advantageously, a charging and discharging operation of the battery cells can be controlled and/or regulated by means of at least one regulating and control device, in particular by means of a microcontroller. In particular, a charge state and/or an aging state of the battery cells can be determined by means of the regulating and control device. In particular, the regulating and control device can be designed to determine a charge state and/or an aging state of the battery cells. In this way At least one battery module can be monitored in detail and an overall condition of the battery system can be determined with a forecast for the further service life of the battery cells.

Advantageously, a battery module can communicate with other battery modules and/or a battery system using at least one CAN network. CAN networks are widely used communication applications, particularly in the automotive sector, and can also be used cost-effectively and very flexibly in the battery system.

Advantageously, operating parameters of the battery module, in particular a charge state and/or an aging state, can be exchanged with other battery modules. In this way, the battery system can be operated as economically as possible by adjusting the operating parameters of individual battery modules.

According to a further aspect of the invention, a method for operating a battery system with at least two independently operable battery modules is proposed, wherein final charge voltages of the battery cells of battery modules are selected according to operating parameters and/or are set by means of a unit for monitoring and charge balancing of battery cells of at least one battery module.

Adaptive charge balancing, where the end-of-charge voltage can be changed, is particularly important for satellite operation. Here, a lower end-of-charge voltage can initially increase the service life of the battery cells. Later in the satellite's life cycle, a higher end-of-charge voltage can increase the satellite's operating time by providing more energy.

According to a favorable embodiment of the method, external communication of the battery system and/or internal communication between the battery modules can be carried out via at least one CAN network. CAN networks are widely used communication applications, particularly in the automotive sector, which can also be used in the battery system in a cost-effective and very flexible manner.

According to a favorable embodiment of the method, charging and discharging of the battery cells can be controlled and/or regulated by means of distributed communication with control and regulation devices of the individual battery modules. In particular, a charge state and/or an aging state of the battery cells can be determined by means of the control and regulation devices of the individual battery modules. In this way, the battery system can be monitored in detail and the continued operation of the satellite over the service life of the battery system can be ensured as inexpensively as possible.

According to a favorable design of the method, a mutual check of the individual battery modules, in particular regarding a charge level and/or an aging level, can be carried out via the control and regulation devices of the battery modules. In this way, a favorable redundancy in the monitoring and control of the battery system can be achieved. This is particularly important in space applications, since failures of individual electronic components cannot be ruled out over the service life of the satellite due to the effects of the environment in space.

drawing

Further advantages emerge from the following description of the drawings. The figures show embodiments of the invention. The figures, the description and the claims contain numerous features in combination. The person skilled in the art will also expediently consider the features individually and combine them into further useful combinations.

• 1 eine schematische Seitenansicht eines stapelbaren Batteriemoduls für ein Batteriesystem, insbesondere eines Satelliten, nach einem Ausführungsbeispiel der Erfindung;
• 2 eine isometrische Ansicht eines stapelbaren Batteriemoduls mit einer Abschlussplatine nach einem Ausführungsbeispiel der Erfindung;
• 3 eine Seitenansicht des Batteriemoduls nach 2;
• 4 eine andere Seitenansicht des Batteriemoduls nach 2;
• 5 einen Querschnitt des Batteriemoduls entlang der Schnittlinie A-A nach 4;
• 6 eine isometrische Darstellung einer Trägerplatine eines Batteriemoduls nach einem Ausführungsbeispiel der Erfindung;
• 7 eine Draufsicht auf eine Oberseite der Trägerplatine nach 6;
• 8 eine Draufsicht auf eine Unterseite der Trägerplatine nach 6;
• 9 eine Seitenansicht der Trägerplatine nach 6;
• 10 eine isometrische Darstellung eines Batteriesystems für einen Satelliten mit zwei Batteriemodulen nach einem Ausführungsbeispiel der Erfindung;
• 11 eine Seitenansicht des Batteriesystems nach 10;
• 12 eine andere Seitenansicht des Batteriesystems nach 10;
• 13 einen Querschnitt des Batteriesystems entlang der Schnittlinie A-A nach 12;
• 14 eine elektrische Verschaltung von zwei Batteriemodulen nach einem Ausführungsbeispiel der Erfindung;
• 15 Schnittstellen von zwei Batteriemodulen in einem Batteriesystem nach einem Ausführungsbeispiel der Erfindung;
• 16 ein Funktionsdiagramm einer Regel- und Steuerungseinrichtung eines Batteriemoduls; und
• 17 ein Systemdiagramm eines Batteriemoduls nach einem Ausführungsbeispiel der Erfindung.

Examples include:

• 1 a schematic side view of a stackable battery module for a battery system, in particular a satellite, according to an embodiment of the invention;
• 2 an isometric view of a stackable battery module with a termination board according to an embodiment of the invention;
• 3 a side view of the battery module after 2 ;
• 4 another side view of the battery module 2 ;
• 5 a cross-section of the battery module along the section line AA to 4 ;
• 6 an isometric representation of a carrier board of a battery module according to an embodiment of the invention;
• 7 a top view of a top side of the carrier board after 6 ;
• 8th a top view of a bottom side of the carrier board after 6 ;
• 9 a side view of the carrier board after 6 ;
• 10 an isometric representation of a battery system for a satellite with two battery modules according to an embodiment of the invention;
• 11 a side view of the battery system after 10 ;
• 12 another side view of the battery system 10 ;
• 13 a cross-section of the battery system along the section line AA to 12 ;
• 14 an electrical connection of two battery modules according to an embodiment of the invention;
• 15 Interfaces of two battery modules in a battery system according to an embodiment of the invention;
• 16 a functional diagram of a control and regulation device of a battery module; and
• 17 a system diagram of a battery module according to an embodiment of the invention.

Embodiments of the invention

In the figures, components of the same type or with the same effect are numbered with the same reference symbols. The figures show only examples and are not to be understood as limiting.

Directional terminology used below with terms such as "left", "right", "top", "bottom", "before", "behind", "after" and the like is intended only to facilitate understanding of the figures and is in no way intended to limit the scope. The components and elements shown, their design and use may vary in accordance with the considerations of a person skilled in the art and may be adapted to the respective applications.

1 shows a schematic side view of a stackable battery module 10 for a battery system 100, in particular a satellite, according to an embodiment of the invention.

For the sake of clarity, reference symbols in the figures are only used as examples for individual components and not for all identical components.

The battery module 10 has a plurality of battery cells 12, which are arranged on a carrier board 20. Four of these battery cells 12 can be seen in the side view. The battery cells 12 in the embodiment shown are designed as round cells and are fixed horizontally on the carrier board 20. The battery cells 12 have connection poles 19 on the front sides, which are electrically connected to current paths of the carrier board 20 via cell connectors 32. The battery module 10 is closed off with a closure board 40 on the top side in the stacking direction 50.

The carrier board 20 has operating components 88 for controlling the temperature of the battery cells 12, for balancing the charge between the battery cells 12, for monitoring the battery cells 12 and communication means 37 ( 6 ) for communication with other battery modules 10 and/or the battery system 100.

Various electronic components 46 are arranged on the carrier board 20. Temperature sensors 30 are attached to each of the battery cells 12 and are thermally coupled directly to a housing of the battery cells 12.

Furthermore, connecting means 33 for electrical serial and/or parallel coupling with one or more other similar, in particular identical, battery modules 10 are arranged on the carrier board 20. Connecting means 33 can be, for example, the plug connectors 70, 74 of the positive power connection and ground connection as well as plug connectors 92 for data lines for controlling charge equalization of the battery cells.

On the one hand, battery modules 10 can be connected in parallel by connecting the connectors 70 of the positive power connection of each battery module and connecting the connectors 74 of the ground connection of each battery module 10.

Additionally, battery modules 10 may be connected in series by having the ground connector 74 of the first battery module act as the ground of the battery system 100. The positive power connector 70 of the first battery module 10 is then connected to the ground connector 74 of the next battery module 10, and so on. The positive power connector 70 of the last battery module 10 then serves as the positive power connector of the battery system. Additionally, when connected in series, the modules 10 communicate/synchronize the charge balance of the unit 34 for monitoring and/or charge balancing via the data line connectors 92.

Between the battery cells 12, but in thermal contact with them, structural elements 26 are arranged, which are used to dissipate heat from the battery cells 12 and to heat of the battery cells 12. For this purpose, heating elements 28 can be integrated into the structural elements 26, for example. The structural elements 26 are adapted to the external shape of the battery cells 12 and nestle against the battery cells 12.

In 2 is an isometric view of a battery module 10 with a termination board 40 according to an embodiment of the invention. 3 shows a side view of the battery module 10 after 2 , while in 4 another side view of the battery module 10 after 2 and in 5 a cross section of the battery module 10 along the section line AA according to 4 is shown.

The battery module 10 comprises eight battery cells 12, of which four battery cells 12 are arranged next to each other. The battery cells 12 are designed as round cells 12, which are arranged lying on the carrier board 20. As shown in particular in 4 As can be seen, the battery cells 12 are arranged next to one another and one behind the other with respect to a longitudinal axis 14. The battery cells 12 can be electrically connected in parallel or in series.

The carrier board 20 has first and second holding devices 22, 24, by means of which the battery cells 12 are fixed on the carrier board 20. The first holding devices are arranged on both side edges 16, 18 of the carrier board 20. A second holding device 24 in the middle of the battery module 10, as in 4 can be seen, is designed to fix battery cells 12 arranged on both sides of the holding device 24.

The holding devices 22, 24 encompass the battery cells 12 on opposite side edges 16, 18 of the carrier board 20 on their circumference at least in regions, so that the battery cells 12 are securely fixed on the carrier board 12.

Mounting holes 66 are arranged on the top side of the battery module 10 in the end plate 40, by means of which further battery modules 10 can be arranged stacked on top of one another. Slots can also be seen in the end plate 40 as a receptacle for cell connectors 32 for electrically contacting the battery cells 12.

The holding devices 22 arranged at the two ends of the battery module 10 have mounting holes 62 for mechanically connecting the battery module 10 to a housing part 110, 112 of a battery system 100 (see 10 ). To save weight, the holding devices 22 are perforated with recesses 60.

Such battery modules 10 can be interconnected in a suitable manner and form battery systems 100 with different voltage levels, different power, and/or different energy content.

As shown in the sectional view in 5 As can be seen, structural elements 26 are arranged on the carrier board 20 between adjacent battery cells 12 at least in some areas, which are designed to control the temperature of the battery cells 12, in particular to dissipate and supply heat. The structural elements 26 are adapted to an external shape of the battery cells 12 at least in some areas.

In particular, the structural elements 26 have a negative contour of the battery cells 12 in some areas and nestle against the battery cells 12. Holes 68 for receiving heating elements 28 can be seen in the structural elements 26.

6 shows an isometric view of a carrier board 20 of a battery module 10 according to an embodiment of the invention. In 7 a plan view of a top side of the carrier board 20 is shown, while 8th a plan view of a bottom side of the carrier board 20 and 9 shows a side view of the carrier board 20. The battery cells 12 of the battery module 10 are not shown.

In 6 In particular, the design of the first and second holding devices 22, 24 can be clearly seen. The holding devices 22, 24 are designed to accommodate the battery cells 12 according to the external shape of the battery cells 12, in the illustrated embodiments round cells, so that the battery cells 12 are firmly fixed by the holding devices 22, 24. The middle second holding device 24 accommodates battery cells 12 from both sides. The structural elements 26 arranged between the battery cells 12 for dissipating heat from the battery cells 12 and for heating the battery cells 12 are integrated into the holding devices 22, 24 and can simultaneously take on the function of fixing the battery cells 12.

The first and second holding devices 22, 24 of the carrier board 20 are designed for mechanical connection to a carrier board 20 of a further battery module 10 stacked above it and/or a terminal board 40. For this purpose, the holding devices 22, 24 each have mounting holes 66 on their upper side for receiving screw connections.

At the ends of the long side of the battery module 10, the holding devices 22, 24 also has mounting holes 62 for connection to the housing parts 110, 112 of a battery system 100.

To heat the battery cells 12, the carrier board 20 has several (schematically indicated) heating elements 28, which can be pressed onto the battery cells 12 for good heat transfer. Alternatively, the heating elements 28 can also be integrated into the structural elements 26, for example via holes 68.

Advantageously, one heating element 28 can be provided for simultaneously heating at least two battery cells 12 adjacent to one another on the carrier board 20. For example, four heating elements 28 can be arranged in the middle of the carrier board 20 between the battery cells 12 lying next to one another in order to heat the eight battery cells 12 arranged on the carrier board 20.

The carrier board 20 has eight temperature sensors 30, which are provided for thermal contact with the battery cells 12. One temperature sensor 30 can thus advantageously be attached to each battery cell 12.

Electronic operating components 88, which are arranged on the carrier board 20, jointly perform tasks such as monitoring the battery module 10 and the battery cells 12, for example with voltage, current, temperature. Furthermore, an analysis of the battery module 10 can be carried out, for example a calculation of SOC and SOH of the battery cells 12, and/or a comparison of the values with set limits.

The battery module 10 can be managed by controlling the charge balance and heating the battery cells 12. Electronic communication means 37 also handle external data communication and processing commands from the outside. The operating components 88 ensure that the electronics and the battery cells 12 are protected from errors and/or short circuits in semiconductors caused by radiation from space, so-called single event effects, and can also correct such errors under certain circumstances. Because the electronic operating components 88 are partially arranged under the battery cells 12, they can also be protected from cosmic radiation.

The carrier board 20 thus has, for example, in a free space 25 between the battery cells 12, at least one unit 34 for monitoring and balancing the charge of the battery cells 12. The unit 34 can advantageously be designed for selectable setting of a final charging voltage of the battery cells 12.

Furthermore, the carrier board 20 has at least one regulating and control device 36, in particular a microcontroller, for controlling a charging and discharging operation of the battery cells 12 in a free space 25 between the battery cells 12. The regulating and control device 36 can be designed in particular to determine a state of charge and/or an aging state of the battery cells 12.

The carrier board 20 also has at least one CAN transceiver 38 in a free space 25 between the battery cells 12 for communication with other battery modules 10 and/or the battery system 100.

Furthermore, operating components 88 such as a current sensor 72, switching components such as a MOSFET 78 for a heating element 28, a MOSFET 80 for charge equalization, various integrated circuits 82, 84 for protecting the electronics, temperature sensors 76 and power converters 90 are arranged on the carrier board 20.

A connector 70 for the positive power connection of the battery module 10, a connector 74 for the ground connection, a connector 92 for data lines, and a connector 94 for so-called in-system programming (ISP) are also arranged on the top of the carrier board 20. During in-system programming, software is loaded, for example flashed, onto the microcontroller of the control device 36.

On the 8th For example, charge balancing ICs 98 are arranged on the rear side of the carrier board 20 shown, which take over balancing if the smart balancing ICs 34 fail. The resistor 96 is then used for charge balancing. A transient voltage suppressor (TVS) diode 99 is also located on the rear side of the carrier board 20 and protects the lines of the power supply 158, 162, 92 and programming 94. The TVS diode 99 acts on the one hand as a surge arrester for transient voltages and on the other hand as protection against electrostatic discharge.

10 shows an isometric view of a battery system 100 for a satellite with two battery modules 10 according to an embodiment of the invention. In 11 a side view of the battery system 100 is shown, while in 12 another side view of the battery system tems 100 and in 13 a cross section of the battery system 100 along the section line AA according to 12 is shown.

The battery system 100 comprises a battery housing 110 with two housing parts 111, 112 for accommodating the battery modules 10. The two housing parts 110, 112 are designed to accommodate two battery modules 10 stacked on top of one another. The uppermost battery module 10 in the stacking direction 50 is closed off with a closing plate 40, which is arranged on the holding devices 22, 24 of the uppermost battery module 10.

The battery modules 10 are each mechanically connected to the holding devices 22 of the carrier boards 20 with the two housing parts 110, 112 via screw connections 120.

The housing parts 110, 112 have holders 114 for fixing to a mounting plate, in particular to a mounting plate of the satellite. Electrical connectors 116, 118 for supplying power and/or transmitting data are arranged on at least one of the two housing parts 110, 112.

The termination board 40 has an electrical connection 42 for an onboard data connection and/or an electrical connection 44 for programming the control device 36 of the battery modules 10, in particular a microcontroller.

The two battery modules 20 can be connected in parallel or in series by means of connecting means 33, depending on the desired voltage level, and/or power, and/or capacity of the battery system 100. Connecting means 33 can be, for example, the connectors 70, 74 of the positive power connection and ground connection as well as connectors 92 for data lines for controlling charge equalization of the battery cells.

On the one hand, battery modules 10 can be connected in parallel by connecting the connectors 70 of the positive power connection of each battery module and connecting the connectors 74 of the ground connection of each battery module 10.

Additionally, battery modules 10 may be connected in series by having the ground connector 74 of the first battery module 10 serve as the ground of the battery system 100. The positive power connector 70 of the first battery module is then connected to the ground connector 74 of the next battery module 10, and so on. The positive power connector 70 of the last battery module 10 then serves as the positive power connector of the battery system. Additionally, when connected in series, the modules communicate/synchronize the charge balance of the unit 34 for monitoring and/or charge balancing via the data line connectors 92.

The voltage of the battery system 100 is equal to the voltage of a battery module 10 multiplied by the number of battery modules connected in series.

The maximum current and capacity of the battery system 100 is equal to the current or capacity of a battery module 10 multiplied by the number of battery modules 10 connected in parallel.

The voltage or current and capacity can then be increased together using a combination of parallel and serial connections.

14 shows an electrical connection of two battery modules 10 of a battery system 100 according to an embodiment of the invention.

The two battery modules 10 are connected in parallel to supply voltages or data lines. For example, a non-regulated voltage supply (24V - 34 V) is supplied. The two battery modules 10 are also connected to a CAN line 132, an inter-integrated circuit line 130 (12C line) and to separate 28 V voltage supplies 158, 162. The 12C line 130 is used for the electrical coupling of additional temperature sensors, which can be read directly from the outside, for example by satellite computers, in the event of a fault in the system.

In 15 Interfaces of two battery modules 10 in a battery system 10 according to an embodiment of the invention are shown.

In this schematic representation, two battery modules 10 are connected to housing parts 110, 112 of the battery system 100 via mechanical and thermal interfaces, which are symbolically shown as arrows.

The battery system 100 has connectors 116, 118 for power supply and for data. Corresponding power connection lines 154 and ground lines 156 are connected to corresponding connectors 70, 74 of the battery modules 10.

The data connector 118 leads 28 V lines 158, 162 and ground lines 160 separately to data connectors 92 of the battery modules 10, while the CAN line 132 and 12C line 130 are fed to the battery modules 10 in parallel.

16 shows a functional diagram of a control device 36 of a battery module 10.

As previously shown, the battery module 10 has an interface 134 for supplying voltage. The battery module 10 also has an interface 197 of the cell string, wherein the cell string is understood to be a combination of serial and parallel connection of the battery cells 12.

The control and regulating device 36 processes information from the temperature sensors 30, which are supplied in the form of a single-wire temperature sensor 195 via a single-wire communication 196.

The unit 34 for monitoring and/or charge balancing is integrated via the communication interface 194. In this case, an SPI message is decoded via a so-called serial peripheral interface communication 179 (SPI communication) in the function 177, which is fed as string current 174, string voltage 175, individual cell voltages 176 to a central function 180 for estimating a battery status and monitoring limits.

In the central function 180, monitoring limits for voltage, current and temperature are determined in function 181, and a SOC per string is determined in function 182. Furthermore, voltage limits per string are tested in function 183, temperature limits per string are tested in function 184, and current limits per string are tested in function 185.

From the functions 183, 184, 185, a target voltage for the charge equalization per battery cell 12 is defined in function 190, which is again encoded as an SPI message in a function 178 and is passed to the SPI communication 179 of the unit 34 for monitoring and/or voltage equalization.

Further information for a function 187 of an error management of a function 186 of a heating control system is derived from the central function 180. This error management 187 flows further as input into a state machine 188, which derives a general status message from it in function 189. Information from the state machine 199 also flows into the definition of the target voltages for the charge equalization in function 190.

The status message from function 189 can be sent via a CAN line 132 to a CAN transceiver 38 of the CAN communication 170, which is controlled by a CAN transceiver module 171. A decoder 172 of received CAN messages is connected to the CAN transceiver 38 via a CAN line 132.

Furthermore, the control device 36 comprises a general function 191 for initialization and configuration, an interrupt handling 192 and a watchdog 193.

17 shows a system diagram of a battery module 10 according to an embodiment of the invention.

The battery module 10 has a connector 92 for data lines 130, 132 and a connector 70 for the positive power connection 154.

The string voltage 175 of the battery cells 12 is fed in parallel to a 3.3 V supply unit 52, to the unit 34 for monitoring and/or charge equalization, to a MOSFET 78 for a heating element 28, and to a current sensor 72.

The 3.3 V line is led from the 3.3 V supply unit 52 to the temperature measuring unit 58, to the temperature sensor 76 and to the current sensor 72.

The 12C line 130 goes from the connector 92 to the temperature sensor 76. The CAN line 132 leads to the CAN transceiver 38 and from there to the central microprocessor of the control device 36.

The control and regulation device 36 is connected via an SPI communication 165 to the unit 34 for monitoring and/or charge balancing, which includes units for voltage measurement 54 and for charge balancing 56. The voltage measurement 54 is connected directly to the battery cells 12 via the FET control 142 for charge balancing. A line 146 for measuring the individual cell voltage leads from the battery cells 12 back to the charge balancing function 56.

A line 174 for the current signal of the current through the cell string also leads from the current sensor 72 to the charge balancing function 56.

The MOSFET 78 for the heating is controlled by the control and regulation device 36 via the line 140. A bus line 138 leads from the control and regulation device 36 to the temperature measuring unit 58. The temperature sensors 76 receive their signal of the individual cell temperatures via the line 148, as does the temperature measuring unit 58.

The MOSFET 80 for charge equalization receives a signal via the single cell connection 152 and is in turn connected to the battery cells 12 via a series resistor 150.

Advantageously, in the proposed battery module 10, a final charging voltage of the battery cells 12 can be selected according to operating parameters and/or set by means of the unit 34 for monitoring and balancing the charge of battery cells 12.

A charging and discharging operation of the battery cells 12 can be controlled and/or regulated by means of at least the regulating and control device 36, in particular by means of a microcontroller. In particular, a charge state and/or an aging state of the battery cells 12 can be determined by means of the regulating and control device 36.

It is advantageous to communicate with other battery modules 10 and/or a battery system 100 using a CAN network. Operating parameters of the battery module 10, in particular a charge state and/or an aging state, can also be exchanged with other battery modules.

In a battery system 100, both external communication of the battery system 100 and internal communication between the battery modules 10 can be carried out via the CAN network.

The charging and discharging operation of the battery cells 12 of the battery system 100 can be controlled and/or regulated by means of distributed communication with the regulating and control devices 36 of the individual battery modules 10. In particular, a charge state and/or an aging state of the battery cells 12 can be determined by means of the regulating and control devices 36 of the individual battery modules 10.

In the battery system 100, a mutual check of the individual battery modules 10, in particular regarding a state of charge and/or an aging state, can advantageously be carried out via the regulating and control devices 36 of the battery modules 10.

Reference symbols

10

Battery module

12

Battery cell

14

Longitudinal axis

16

End, front side

18

End, front side

19

Connection pole

20

Carrier board

22

Holding device

24

Holding device

25

free space

26

Structural element

28

Heating element

30

Temperature sensor

32

Cell connectors

33

Connecting elements

34

Unit for monitoring and/or charge balancing

36

Control and regulation device

37

Means of communication

38

CAN transceiver

40

End plate

42

electrical connection onboard data connection

44

electrical connection programming

46

Electronic component

48

Battery cell recess

50

Stacking direction

52

3.3V supply

54

Voltage measurement

56

Load balancing

58

Temperature measuring unit

60

Recess

62

Mounting hole

64

Cell connector holder

66

Mounting hole

68

Hole for heating element

70

Connector power connection positive

72

Current sensor

74

Connector Power connection Ground

76

Temperature sensor

78

MOSFET heater

80

MOSFET charge balancing

82

Protection IC

84

Protection IC

88

Operational component

90

Power converter

92

Connectors Data cables

94

ISP connectors

96

Resistance for charge equalization

98

Redundant charge balancing IC

99

TVS Diode

100

Battery system

110

Battery housing

111

Housing part

112

Housing part

114

bracket

116

Connector power supply

118

Connector data

120

Screw connection holding device

130

I2C

132

CAN

134

Power supply

136

3.3V line

138

Bus line

140

FET control heating

142

FET control charge balancing

146

Measurement of single cell voltage

148

Individual cell temperature

150

Series resistor

152

Single cell connection

154

Power connection

156

Ground connection

158

28V

160

Ground line

162

28V

164

Ground line

165

SPI communication

170

CAN Transceiver

171

CAN transmit-receive module

172

Decoder for CAN messages

173

Cell temperature

174

String current

175

Phase voltage

176

Cell voltage

177

Decode SPI message

178

Encoding SPI message

179

SPI communication

180

Estimate battery status & monitoring limits

181

Calculate monitoring limits

182

Determine SOC per strand

183

Test voltage limit per strand

184

Test temperature limit per strand

185

Test current limit per string

186

Heating control

187

Error management

188

State machine

189

Generate status message

190

Define target voltage per cell for charge balancing

191

Initialize & Configure

192

Interrupt handling

193

Watchdog

194

Communication with charge balancing unit

195

Single-wire temperature sensor

196

Single-wire communication

197

Cell strand interface

Claims (20)

Autonomously operable battery module (10) for a battery system (100) of a satellite or spacecraft, with a carrier board (20) on which a plurality of battery cells (12) and operating components (88) for controlling the temperature of the battery cells (12), for balancing the charge between the battery cells (12) and for monitoring the battery cells (12) are arranged, wherein communication means (37) are also present on the carrier board (20) for communication with the battery system (100) and other battery modules (10) in the battery system (100), and connection means (33) for electrical serial and/or parallel coupling with one or more other similar battery modules (10) are arranged on the carrier board (20). Battery module after Claim 1 , wherein the carrier board (20) has first and second holding devices (22, 24) and the battery cells (12) are clamped between a first and a second holding device (22, 24). Battery module after Claim 1 or 2 , wherein one of the first holding devices (22) is arranged on opposite side edges (16, 18) of the carrier board (20). Battery module according to one of the preceding claims, wherein the second holding devices (24) are arranged, in particular centrally, between the first holding devices (22). Battery module according to one of the preceding claims, wherein the battery cells (12) are arranged horizontally on the carrier board (20), in particular wherein the battery cells (12) are designed as round cells (12). Battery module according to one of the preceding claims, wherein the battery cells (12) are arranged next to one another and/or one behind the other with respect to their longitudinal axis (14), wherein the battery cells (12) on the carrier board (20) are or can be connected electrically in parallel and/or in series. Battery module according to one of the preceding claims, wherein structural elements (26) are arranged at least in regions between adjacent battery cells (12), which are designed for passive temperature control of the battery cells (12), wherein the structural elements (26) are at least partially adapted to an external shape of the battery cells (12), in particular partially having a negative contour of the battery cells (12), and nestling against the battery cells (12). Battery module after Claim 7 , wherein the structural elements (26) are integrated into the holding devices (22, 24). Battery module after Claim 7 or 8th , wherein the carrier board (20) has one or more heating elements (28), in particular wherein one or more heating elements (28) are integrated into the structural elements (26). Battery module after Claim 9 , wherein a heating element (28) is provided for simultaneously heating at least two battery cells (12) adjacent to one another on the carrier board (20). Battery module according to one of the preceding claims, wherein the carrier board (20) has one or more temperature sensors (30) which are provided for thermally contacting the battery cells (12). Battery module according to one of the preceding claims, wherein connection poles (19) of the battery cells (12) are electrically connected to current paths of the carrier board (20) by means of cell connectors (32). Battery module according to one of the preceding claims, wherein the carrier board (20) has at least one unit (34) for monitoring and charge balancing of the battery cells (12) in at least one free space (25) between the battery cells (12). Battery module according to one of the preceding claims, wherein the carrier board (20) has at least one regulating and control device (36), in particular a microcontroller, for controlling a charging and discharging operation of the battery cells (12) in at least one free space (25) between the battery cells (12), in particular wherein the regulating and control device (36) is designed to determine a state of charge and/or an aging state of the battery cells (12). Battery module according to one of the preceding claims, wherein the carrier board (20) has at least one CAN transceiver (38) for communication with other battery modules (10) and/or the battery system (100) in at least one free space (25) between the battery cells (12). Battery module according to one of the Claims 2 until 15 , wherein the first and second holding devices (22, 24) of the carrier board (20) are designed for mechanical connection to a carrier board (20) of a further battery module (10) stacked above it and/or a termination board (40). Battery system (100) of a satellite or spacecraft, with at least two autonomously operable battery modules (10) according to one of the preceding claims, wherein the at least two battery modules (10) are of identical construction and each have a carrier board (20) on which a plurality of battery cells (12) and operating components (88) for controlling the temperature of the battery cells (12), for balancing the charge between the battery cells (12) and for monitoring the battery cells (12) are arranged, wherein furthermore communication means (37) are arranged on the carrier board (20) for communication with the battery system (100) and the at least one further battery module (10) in the battery system (100). wherein the at least two battery modules (10) are electrically coupled in series and/or in parallel by means of connecting means (33) which are arranged on the carrier board (20). Battery system according to Claim 17 , wherein the at least two battery modules (10) are arranged in a battery housing (110), in particular wherein at least one of the battery modules (10) is closed with a termination board (40) which is arranged on a holding device (22, 24) of the at least one battery module (10), in particular wherein the uppermost battery module (10) in a stacking direction (50) is closed with the termination board (40). Battery system according to Claim 17 or 18 , wherein the battery housing (110) each has holders (114) for fixing to a mounting plate, in particular to a mounting plate of the satellite or spacecraft, and/or wherein the battery housing (110) has at least one electrical connector (116, 118) for power supply and/or for transmitting data. Battery system according to Claim 18 or 19 , wherein the terminating board (40) has at least one electrical connection (42) for an onboard data connection and/or an electrical connection (44) for programming a control and regulating device (36), in particular a microcontroller.

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