Patent Application
20180138555
The present invention relates generally to a vehicle battery and more particularly to a self-switching, dual voltage battery suitable for use in an aircraft.
Contemporary business aircraft have generally standardized on a 28 volt direct current (28 VDC) power supply (e.g., battery) to power the various navigation, flight control, and other systems used on board an aircraft. Historically, as aircraft power demands have increased, many aircraft manufacturers elected to generate higher voltage alternating current power supplies (e.g., 115 VAC) for routing power throughout the aircraft fuselage, and converting down to 28 VDC locally to power aircraft systems. Additionally, by generating a higher voltage for transmission throughout the aircraft fuselage, a lower current is required to provide a given power level as will be appreciated by those skilled in the art (i.e., Ohm's law). By reducing current requirements, a higher gauge (i.e., smaller diameter) wire can be used, which affords a substantial weight reduction given the miles of wire that are used in an aircraft.
Currently, in an effort to further reduce wire weight, some aircraft manufacturers have begun generating power at even higher voltages (e.g., 235 VAC or 270 VDC) that is converted by dedicated transformer rectifier units to 28 VDC and re-distributed to power aircraft systems. While down-converting of higher voltage power to 28 VDC is generally efficient, no power-converting system is 100% efficient and some power is lost as heat during the voltage conversion process. When the aircraft is parked without connection to ground power sources, it is dependent upon batteries to continue to provide time-limited power to some aircraft systems that remain powered when the aircraft is not in use (e.g., security system, cellular connections). Even a 1%-2% loss during the conversion from a high voltage direct current battery to nominal 28 VDC would drain the battery after a few days due to the heat lost during the conversion. Carrying a dedicated 28 VDC battery to power these systems without the need for conversion adds weight, cost, and additional wiring that is undesirable.
Accordingly, it is desirable to provide a power source (i.e., battery) that can provide a high-voltage direct current power source to reduce wire weight and also provides a 28 VDC power source without voltage conversion loss. It is further desirable that the 28 VDC power source have an extended capacity for use on aircraft over a long period of time. Furthermore, other desirable features and characteristics will become apparent from the subsequent detailed description and the appended claims, taken in conjunction with the accompanying drawings and the foregoing technical field and background.
Various non-limiting embodiments of a self-switching dual voltage battery and a method of operating a self-switching dual voltage battery are disclosed herein.
In a first non-limiting embodiment, the self-switching dual voltage battery system includes, but is not limited to, a plurality of battery cell groups connected in series to provide a first voltage between a negative terminal and a first positive terminal. The self-switching dual voltage battery system also includes, but is not limited to, a switch matrix coupled to each of the plurality of battery cell groups and to a second positive terminal. The self-switching dual voltage battery system also includes, but is not limited to, a controller coupled to the switch matrix for controlling the switch matrix to couple a selected battery cell group of the plurality of battery cell groups to the second terminal to provide a second voltage. The controller is also coupled to each of the plurality of battery cell groups for monitoring a charge level associated with each of the plurality of battery cell groups. In this way, when the controller determines that the charge level associated with the selected battery cell group falls below a threshold, the controller causes the switch matrix to select another battery cell group from the plurality of battery cell groups to provide the second voltage.
In another non-limiting embodiment, a method of operating a self-switching dual voltage battery system includes, but is not limited to, providing a first voltage between a negative terminal and a first positive terminal from a plurality of battery cell groups connected in series. The method further includes, but is not limited to, monitoring, via a controller, a charge level associated with each of the plurality of battery cell groups. The method further includes, but is not limited to, controlling a switch matrix to select one of the plurality of battery cell groups to provide a selected battery cell group between the negative terminal and the second positive terminal. The method further includes, but is not limited to, determining when the charge level associated with the selected battery cell group falls below a threshold. The method further includes, but is not limited to, controlling the switch matrix to select another battery cell group from the plurality of battery cell groups to provide the second voltage when the charge level associated with the selected battery cell group falls below the threshold.
The present invention will hereinafter be described in conjunction with the following drawing figures, wherein like numerals denote like elements, and
As used herein, the word “exemplary” means “serving as an example, instance, or illustration.” The following detailed description is merely exemplary in nature and is not intended to limit application and uses. Any embodiment described herein as “exemplary” is not necessarily to be construed as preferred or advantageous over other embodiments. All of the embodiments described in this Detailed Description are exemplary embodiments provided to enable persons skilled in the art to make or use the embodiment and not to limit the scope that is defined by the claims.
A self-switching dual voltage battery is disclosed herein. The self-switching dual voltage battery of the present disclosure provides a first (high-voltage) output by serially coupling a plurality of battery cells or groups of cells. A second (28 VDC) output is also provided by selectively coupling one of the plurality of battery cell groups to a second (28 VDC) terminal. While the self-switching, dual voltage battery of the present disclosure is described as affording an advantage in an aircraft application, it will be appreciated that the present disclosure may be advantageously employed in other applications, including but not limited to, batteries for ground based vehicles, watercraft and spacecraft without departing from the teachings of the present disclosure.
A greater understanding of the self-switching, dual voltage battery and of the method of operating a self-switching, dual voltage battery may be obtained through a review of the illustrations accompanying this application together with a review of the detailed description that follows.
As illustrated in
In operation, the controller 204 selects one of the plurality of battery cell groups 202 to provide a selected battery cell group that the switch matrix 210 couples to the second positive terminal 212. As the selected battery cell group powers the circuit or systems coupled to the second positive terminal 212, the controller 204 monitors the charge level associated with the selected battery cell group that will gradually be reduced under the load drawing power from the selected battery cell group. When the controller 204 determines that the charge level associated with the selected battery cell group drops below a threshold, the controller 204 causes the switch matrix to couple another of the plurality of battery cell groups to the second positive terminal 212. In some embodiments, the threshold used by the controller 204 to determine when to switch to another of the plurality of battery cell groups is fifty percent (50%) of the battery capacity of the selected battery cell group. As used herein, the “capacity” of a battery cell group means the amount of charge available in the battery cell group expressed in ampere-hours (or amp-hours). This process can continue throughout the plurality of battery cell groups providing a prolonged 28 VDC power supply to power select circuits of the aircraft.
As a non-limiting example, if each battery cell group 202 is rated to provide twenty amp-hours, then the battery 200 of
With continuing reference to
While at least one exemplary embodiment has been presented in the foregoing detailed description of the invention, it should be appreciated that a vast number of variations exist. It should also be appreciated that the exemplary embodiment or exemplary embodiments are only examples, and are not intended to limit the scope, applicability, or configuration of the invention in any way. Rather, the foregoing detailed description will provide those skilled in the art with a convenient road map for implementing an exemplary embodiment of the invention. It being understood that various changes may be made in the function and arrangement of elements described in an exemplary embodiment without departing from the scope of the invention as set forth in the appended claims.
