This disclosure relates generally to aircraft batteries and, more particularly, to systems and methods for controlling an aircraft battery including a main battery strings and reserve battery strings electrically connected in parallel.
Aircraft may include one or more batteries for supplying electrical power for an electrical distribution system of the aircraft and/or its propulsion system(s). The electrical connection of the battery to the electrical distribution system may, under some conditions, be controlled supplement the electrical power of the battery which is available to supply to the electrical distribution system. Various systems and methods for controlling aircraft batteries are known in the art. While these known systems and methods have various advantages, there is still room in the art for improvement.
It should be understood that any or all of the features or embodiments described herein can be used or combined in any combination with each and every other feature or embodiment described herein unless expressly noted otherwise.
According to an aspect of the present disclosure, an assembly for an aircraft includes an aircraft electrical distribution bus, a battery, and a battery monitoring system. The battery includes a plurality of battery strings. Each battery string is configured to be selectively electrically connected to the aircraft electrical distribution bus to direct electrical power to the aircraft electrical distribution bus. The plurality of battery strings is configured as a main subset of the plurality of battery strings and a reserve subset of the plurality of battery strings. Each of the main subset and the reserve subset include at least one battery string of the plurality of battery strings. The battery monitoring system includes a plurality of sensors. The plurality of sensors are configured to measure a bus voltage of the aircraft electrical distribution bus and a battery string voltage of each battery string. The battery monitoring system further includes a processor in communication with a non-transitory memory storing instructions, which instructions when executed by the processor, cause the processor to electrically connect the reserve subset of the plurality of battery strings to the aircraft electrical distribution bus by: determining the bus voltage and the battery string voltage of each battery string of the reserve subset of the plurality of battery strings with the plurality of sensors with at least one battery string of the main subset of the plurality of battery strings electrically connected to the aircraft electrical distribution bus, identifying a threshold voltage range of the reserve subset of the plurality of battery strings for electrically connecting the reserve subset of the plurality of battery strings to the aircraft electrical distribution bus, where identifying the threshold voltage range is based at least on the bus voltage, and electrically connecting at least one battery string of the reserve subset of the plurality of battery strings to the aircraft electrical distribution bus with the bus voltage within the identified threshold voltage range.
In any of the aspects or embodiments described above and herein, the plurality of battery strings may be configured to be selectively electrically connected in parallel.
In any of the aspects or embodiments described above and herein, each battery string of the plurality of battery strings may include a plurality of battery modules electrically connected in series.
In any of the aspects or embodiments described above and herein, each battery string may include a string contactor. The string contactor may be positionable in a closed string position or an open string position. The string contactor in the closed string position may be configured to direct electrical power from the respective battery string to the aircraft electrical distribution bus. The string contactor in the open string position may be configured to electrically isolate the respective battery string from the aircraft electrical distribution bus.
In any of the aspects or embodiments described above and herein, the at least one battery module of each battery string of the main subset of the plurality of battery strings may have a first battery chemistry configuration. The at least one battery module of each battery string of the reserve subset of the plurality of battery strings may have a second battery chemistry configuration. The first battery chemistry configuration may be different than the second battery chemistry configuration.
In any of the aspects or embodiments described above and herein, the at least one battery module of each battery string of the main subset of the plurality of battery strings may be rechargeable. The at least one battery module of each battery string of the reserve subset of the plurality of battery strings may be non-rechargeable.
In any of the aspects or embodiments described above and herein, the instructions when executed by the processor, may further cause the processor to electrically connect the reserve subset of the plurality of battery strings to the aircraft electrical distribution bus by electrically connecting the at least one battery string of the reserve subset of the plurality of battery strings to the aircraft electrical distribution bus with the battery string voltage of the at least one battery string of the reserve subset of the plurality of battery strings greater than the battery string voltage of the at least one battery string of the main subset of the plurality of battery strings.
In any of the aspects or embodiments described above and herein, the reserve subset of the plurality of battery strings may include at least a first reserve battery string and a second reserve battery string. The instructions when executed by the processor, may further cause the processor to electrically connect the reserve subset of the plurality of battery strings to the aircraft electrical distribution bus by determining the respective voltage range of the first reserve battery string and the second reserve battery string.
In any of the aspects or embodiments described above and herein, the instructions when executed by the processor, may further cause the processor to electrically connect the reserve subset of the plurality of battery strings to the aircraft electrical distribution bus by electrically connecting the at least one battery string of the reserve subset of the plurality of battery strings, including the first reserve battery string, to the aircraft electrical distribution bus while maintaining the second reserve battery string electrically disconnected from the aircraft electrical distribution bus.
In any of the aspects or embodiments described above and herein, the assembly may further include an aircraft propulsion system including a rotational assembly. The rotational assembly may include a propeller, a rotatable shaft and an electric motor. The electrical motor may be electrically connected to the aircraft electrical distribution bus. The electric motor may be configured to selectively drive the rotatable shaft and the propeller.
In any of the aspects or embodiments described above and herein, the plurality of sensors may be further configured to measure a temperature of the at least one battery module of each battery string. Identifying the threshold voltage range of the reserve subset of the plurality of battery strings for electrically connecting the reserve subset of the plurality of battery strings to the aircraft electrical distribution bus may be further based on the measured temperature.
According to another aspect of the present disclosure, a method for operating a battery assembly for an aircraft is provided. The method includes supplying electrical power to an aircraft electrical distribution bus with a battery. The battery includes a plurality of battery strings. Each battery string includes at least one battery module. The plurality of battery strings are configured as a main subset of the plurality of battery strings and a reserve subset of the plurality of battery strings. Each of the main subset of the plurality of battery strings and the reserve subset of the plurality of battery strings include at least one battery string of the plurality of battery strings. The main subset of the plurality of battery strings is electrically connected to the aircraft electrical distribution bus. The reserve subset of the plurality of battery strings is electrically disconnected from the aircraft electrical distribution bus. The method further includes electrically connecting the reserve subset of the plurality of battery strings to the aircraft electrical distribution bus by determining a bus voltage of the aircraft electrical distribution bus and a battery string voltage of each battery string of the reserve subset of the plurality of battery strings, identifying a threshold voltage range between the aircraft electrical distribution bus and the reserve subset of the plurality of battery strings for electrically connecting the reserve subset of the plurality of battery strings to the aircraft electrical distribution bus, and electrically connecting at least one battery string of the reserve subset of the plurality of battery strings to the aircraft electrical distribution bus with a voltage range between the bus voltage and the at least one battery string of the reserve subset of the plurality of battery strings within the identified threshold voltage range.
In any of the aspects or embodiments described above and herein, the plurality of battery strings may be configured to be selectively electrically connected in parallel.
In any of the aspects or embodiments described above and herein, the threshold voltage range may be a predetermined value.
In any of the aspects or embodiments described above and herein, the threshold voltage range may be dynamically determined based on at least the bus voltage.
According to another aspect of the present disclosure, an assembly for an aircraft includes an aircraft electrical distribution bus, an aircraft propulsion system, a battery, and a battery monitoring system. The aircraft propulsion system includes a rotational assembly. The rotational assembly includes a rotatable shaft and an electric motor. The electric motor is electrically connected to the aircraft electrical distribution bus. The electric motor is configured to selectively drive the rotatable shaft. The battery includes a plurality of battery strings configured to be selectively electrically connected in parallel. Each battery string is configured to be selectively electrically connected to the aircraft electrical distribution bus to direct electrical power to the aircraft electrical distribution bus. The plurality of battery strings is configured as a main subset of the plurality of battery strings and a reserve subset of the plurality of battery strings. The battery monitoring system includes a plurality of sensors. The plurality of sensors are configured to measure a bus voltage of the aircraft electrical distribution bus and a battery string voltage of each battery string. The battery monitoring system further includes a processor in communication with a non-transitory memory storing instructions, which instructions when executed by the processor, cause the processor to electrically connect the reserve subset of the plurality of battery strings to the aircraft electrical distribution bus by determining the bus voltage and the battery string voltage of each battery string of the reserve subset of the plurality of battery strings with the plurality of sensors with at least one battery string of the main subset of the plurality of battery strings electrically connected to the aircraft electrical distribution bus, identifying a threshold voltage range of the reserve subset of the plurality of battery strings for electrically connecting the reserve subset of the plurality of battery strings to the aircraft electrical distribution bus, where identifying the threshold voltage range is based at least on the bus voltage, and electrically connecting at least one battery string of the reserve subset of the plurality of battery strings to the aircraft electrical distribution bus with the bus voltage within the identified threshold voltage range.
In any of the aspects or embodiments described above and herein, the rotational assembly may further include a propeller. The electric motor may be configured to selectively drive the propeller via the rotatable shaft.
In any of the aspects or embodiments described above and herein, each battery string of the plurality of battery strings may include a plurality of battery modules electrically connected in series.
In any of the aspects or embodiments described above and herein, the plurality of battery modules of each battery string of the main subset of the plurality of battery strings may have a first battery chemistry configuration, the plurality of battery modules of each battery string of the reserve subset of the plurality of battery strings may have a second battery chemistry configuration, and the first battery chemistry configuration may be different than the second battery chemistry configuration.
In any of the aspects or embodiments described above and herein, the plurality of battery modules of each battery string of the main subset of the plurality of battery strings may be rechargeable and the plurality of battery modules of each battery string of the reserve subset of the plurality of battery strings may be non-rechargeable.
The present disclosure, and all its aspects, embodiments and advantages associated therewith will become more readily apparent in view of the detailed description provided below, including the accompanying drawings.
The gas turbine engine 22 of
Components of the gas turbine engine 22 of
The first rotational assembly 42 includes a first shaft 46, a bladed compressor rotor 48 for the compressor 28, and a bladed turbine rotor 50 for the high-pressure turbine 32. The first shaft 46 interconnects the bladed compressor rotor 48 and the bladed turbine rotor 50. The second rotational assembly 44 includes a second shaft 52, a bladed power turbine rotor 54 for the power turbine 34, and a propeller 56. The second shaft 52 is connected to the bladed power turbine rotor 54. The second shaft 52 may be directly or indirectly connected to the propeller 56. For example, the second shaft 52 may be configured to rotatably drive the propeller 56 via a reduction gear box (RGB) 58. The second rotation assembly 44 may include additional components (e.g., a propeller input shaft) for interconnecting the second shaft 52 with the bladed power turbine rotor 54 and the propeller 56. The RGB 58 may be configured to drive the propeller 56 at a reduced rotational speed relative to the second shaft 52. Alternatively, the second shaft 52 may directly interconnect the bladed power turbine rotor 54 and the propeller 56.
During operation of the gas turbine engine 22 of
The electrical distribution system 24 of
The electric motor 62 is configured to apply a rotational force to second rotational assembly 44. For example, the electric motor 62 may be directly or indirectly coupled to the second shaft 52 to drive the second shaft 52 by applying a rotational force to the second shaft 52. The electric motor 62 may further include a clutch configured to selectively couple the electric motor 62 to the second shaft 52 or to an intermediate component of the second rotational assembly 44. Accordingly, the electric motor 62 may be configured to apply a rotational force to the second rotational assembly 44 to facilitate rotation of the propeller 56 by the second rotational assembly 44. For example, the electric motor 62 in combination with the bladed power turbine rotor 54 may provide the rotational force for driving the propeller 56. The electric motor 62 may be selected to be sufficiently powerful to drive the propeller 56 during all flight conditions independent of the bladed power turbine rotor 54. Accordingly, the electric motor 62 may provide all of the rotational force for driving the propeller 56. The electric motor 62 is electrically connected to the electrical distribution bus 66 and configured to receive electrical power from the electrical distribution bus 66 for operation of the electric motor 62.
The generator 64 is configured to supply electrical power to the electrical distribution system 24. The generator 64 of
Referring to
Each battery string 80 of
The plurality of battery strings 80 may be configured as a main subset 106 of the plurality of battery strings 80 (e.g., a main battery) and a reserve subset 108 of the plurality of battery strings 80 (e.g., a reserve battery). Each of the main subset 106 and the reserve subset 108 may include at least one battery string 80 of the plurality of battery strings 80. For example, the main subset 106 of
The battery 70 of
The battery monitoring system 72 of
The battery monitoring system 72 includes a plurality of sensors 104 to monitor operational parameters of the battery 70 including, but not limited to, voltage, current, and temperature. For example, the battery monitoring system 72 may include one or more of the sensors 104 at (e.g., on, adjacent, or proximate) each battery module 74 to monitor the health of each battery module 74 and or to monitor operational parameters of each battery module 74 such as, but not limited to, voltage, current, and temperature. The battery monitoring system 72 may additionally include one or more sensors 104 for monitoring voltage and current parameters for each battery string 80, for the battery 70 (e.g., at the battery terminals 86, 88), and/or for the charger 94.
The battery monitoring system 72 may be connected in electrical and/or electronic communication with the string contactors 90, 92. The battery monitoring system 72 may control the string contactors 90, 92 for positioning in their respective open positions or closed positions using a control signal (e.g., a control current, electronic signal, etc.). Similarly, the battery monitoring system 72 may be connected in electrical and/or electronic communication with the main charger contactors 96 and/or the main battery contactors 98 to control the main charger contactors 96 and/or the main battery contactors 98 in their respective open positions or closed positions. Alternatively, the main battery contactors 98 may be controlled independent of the battery monitoring system 72, for example, manually (e.g., by a pilot or other operator) or by another control system of the propulsion system 20 or the aircraft (see
Referring to
Step 502 includes supplying electrical power to the electrical distribution bus 66 with the battery 70. For example, as shown in
Step 504 includes determining a bus voltage of the electrical distribution bus 66 and/or battery string voltages of the battery strings 80 of the reserve subset 108. For example, the battery monitoring system 72 may determine the bus voltage of the electrical distribution bus 66 and the battery string voltage of each battery string 80 of the reserve subset 108 using the sensors 104. The battery strings 80 of the main subset 106 which are electrically connected to the electrical distribution bus 66 may have respective string voltages which are the same as or substantially the same as the bus voltage.
Step 506 includes identifying a threshold voltage range for the battery strings 80 of the reserve subset 108. For example, the battery monitoring system 72 may identify a threshold voltage range for each battery string 80 of the reserve subset 108. The threshold voltage range identifies a voltage range relative to the respective battery string of the reserve subset 108. With the bus voltage of the electrical distribution bus 66 within the threshold voltage range, the respective battery string 80 of the reserve subset 108 may be safely electrically connected to the electrical distribution bus 66. For example, the threshold voltage range identifies a voltage range within which a respective battery string 80 of the reserve subset 108 may be electrically connected to the electrical distribution bus 66 (e.g., by closing the respective string contactors 90, 92) so as to prevent or minimize the likelihood of damage to the respective battery string 80, the respective string contactors 90, 92, and/or other components of the battery assembly 68 which may be caused by high electrical current, high temperatures, electric arcs (e.g., arc discharge), or the like. All or a substantially portion of the identified threshold voltage range for a respective battery string 80 of the reserve subset 108 may be less than the battery string voltage for the respective battery string 80 (e.g., the battery string voltage may be a maximum point for the threshold voltage range). This is because upon electrically connecting the respective battery string 80 of the reserve subset 108 to the electrical distribution bus 66, the battery string voltage of the respective battery string 80 will be expected to decrease (e.g., because the battery string is experiencing electrical load) while the battery string voltages of the other battery strings 80 electrically connected to the electrical distribution bus 66 will be expected to increase (e.g., because the other battery strings 80 may experience a decrease in electrical load). Accordingly, the electrically-connected battery strings 80 of the main subset 106 and the reserve subset 108 may have substantially equalized battery string voltages as the battery strings 80 of the reserve subset 108 are electrically connected. The threshold voltage range may be a predetermined value (e.g., stored in memory 102). Alternatively, the threshold voltage range may be dynamically determined by the battery monitoring system 72 based on one or more factors such as, but not limited to, battery module 74 and/or battery string 80 energy capacity, battery module 74 chemistry configurations, battery module 74 temperatures, string contactor 90, 92 configurations and electrical current limits, and bus voltage of the electrical distribution bus 66. Routine experimentation may be performed by a person of ordinary skill in the art to determine a suitable threshold voltage range for electrically connecting battery strings 80 of the reserve subset 108 for a particular electrical distribution system 24 and battery assembly 68 in accordance with and as informed by one or more aspects of the present disclosure.
Step 508 includes electrically connecting one or more of the battery strings 80 of the reserve subset 108 to the electrical distribution bus 66. For example, each battery string 80 of the reserve subset 108 may be electrically connected to the electrical distribution bus 66 by the battery monitoring system 72 when the bus voltage for the electrical distribution bus 66 has decreased to within the threshold voltage range for each respective battery string 80 of the reserve subset 108 (see
While the principles of the disclosure have been described above in connection with specific apparatuses and methods, it is to be clearly understood that this description is made only by way of example and not as limitation on the scope of the disclosure. Specific details are given in the above description to provide a thorough understanding of the embodiments. However, it is understood that the embodiments may be practiced without these specific details.
It is noted that the embodiments may be described as a process which is depicted as a flowchart, a flow diagram, a block diagram, etc. Although any one of these structures may describe the operations as a sequential process, many of the operations can be performed in parallel or concurrently. In addition, the order of the operations may be rearranged. A process may correspond to a method, a function, a procedure, a subroutine, a subprogram, etc.
The singular forms “a,” “an,” and “the” refer to one or more than one, unless the context clearly dictates otherwise. For example, the term “comprising a specimen” includes single or plural specimens and is considered equivalent to the phrase “comprising at least one specimen.” The term “or” refers to a single element of stated alternative elements or a combination of two or more elements unless the context clearly indicates otherwise. As used herein, “comprises” means “includes.” Thus, “comprising A or B,” means “including A or B, or A and B,” without excluding additional elements.
It is noted that various connections are set forth between elements in the present description and drawings (the contents of which are included in this disclosure by way of reference). It is noted that these connections are general and, unless specified otherwise, may be direct or indirect and that this specification is not intended to be limiting in this respect. Any reference to attached, fixed, connected, or the like may include permanent, removable, temporary, partial, full and/or any other possible attachment option.
No element, component, or method step in the present disclosure is intended to be dedicated to the public regardless of whether the element, component, or method step is explicitly recited in the claims. No claim element herein is to be construed under the provisions of 35 U.S.C. 112 (f) unless the element is expressly recited using the phrase “means for.” As used herein, the terms “comprise”, “comprising”, or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus.
While various inventive aspects, concepts and features of the disclosures may be described and illustrated herein as embodied in combination in the exemplary embodiments, these various aspects, concepts, and features may be used in many alternative embodiments, either individually or in various combinations and sub-combinations thereof. Unless expressly excluded herein all such combinations and sub-combinations are intended to be within the scope of the present application. Still further, while various alternative embodiments as to the various aspects, concepts, and features of the disclosures—such as alternative materials, structures, configurations, methods, devices, and components, and so on—may be described herein, such descriptions are not intended to be a complete or exhaustive list of available alternative embodiments, whether presently known or later developed. Those skilled in the art may readily adopt one or more of the inventive aspects, concepts, or features into additional embodiments and uses within the scope of the present application even if such embodiments are not expressly disclosed herein. For example, in the exemplary embodiments described above within the Detailed Description portion of the present specification, elements may be described as individual units and shown as independent of one another to facilitate the description. In alternative embodiments, such elements may be configured as combined elements.
This application claims priority to U.S. Patent Appln. No. 63/443,883 filed Feb. 7, 2023, which is hereby incorporated herein by reference in its entirety.
Number | Date | Country | |
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63443883 | Feb 2023 | US |