Patent Application
20250035499
This application claims the benefit of Great Britain Patent Application Number 2311349.1 filed on Jul. 24, 2023, the entire disclosure of which is incorporated herein by way of reference.
The present invention relates to a fuel system, an aircraft fuel storage system, an aircraft and a method of gauging fuel.
It may be desirable to gauge fuel stored within a chamber of a fuel system.
According to a first aspect, there is provided a fuel system comprising: a chamber for storing a fuel; an optical differential pressure sensor; and one or more processors in communication with the optical differential pressure sensor, wherein the optical differential pressure sensor is fluidically connected to the chamber and is configured to, when the fuel is stored in the chamber, output a signal indicative of a pressure difference in the optical differential pressure sensor to the one or more processors.
The use of an optical differential pressure sensor may reduce the total number of electrical connections in proximity of the chamber compared to the use of, for example, a capacitive differential pressure sensor. As only a non-current carrying element (such as an optical fiber) of the optical differential pressure sensor may need to be near the diaphragm, any current carrying electronics (such as an optical interrogator connected to the optical fiber) can be positioned away from the chamber. This may help to reduce a likelihood of electrical arcing occurring close to the chamber. The optical differential pressure sensor may be configured to determine a pressure difference by measuring an optical path difference to determine deflection of the diaphragm. As the optical pressure sensor may use light to measure deflection of the diaphragm, the optical differential pressure sensor may be less susceptible to magnetic fields compared to, for example, a capacitive differential pressure sensor. This may increase accuracy and/or consistency of measurements made by the optical differential pressure sensor.
The one or more processors may be configured to gauge fuel stored within the chamber based on the signal output by the optical differential pressure sensor. The one or more processors may be in communication with the optical differential pressure sensor via an electrical or optical connection. The electrical connection may be a hard-wired connection between the optical differential pressure sensor and the one or more processors. The one or more processors may be in communication with the optical differential pressure sensor via a wireless connection. The wireless connection may comprise any suitable standard of wireless communication, such as Bluetooth or WiFi. The wireless connection may allow the one or more processors to be located remote from the chamber without requiring wiring between the one or more processors and the optical differential pressure sensor. This may reduce space taken up by wiring within the fuel system. This may allow electrical current carrying components to be located away from the chamber, which may reduce a likelihood of arcing occurring close to the chamber.
The one or more processors may be configured to determine a weight of fuel within the chamber. The one or more processors may be configured to determine a depth of fuel within the chamber. The weight of the fuel and/or the depth of the fuel may be indicative of an amount of fuel within the chamber. Using the optical differential pressure sensor to gauge the fuel within the chamber may be more accurate than using other means, such as a float, as the measurement is affected less by motion of the fuel within the chamber.
The one or more processors may be in communication with an aircraft controller, wherein the aircraft controller may be operable to control one or more systems of an aircraft (such as a warning system, a navigation system or an aircraft flight control system). The aircraft controller may be configured to control operation of the one or more systems of the aircraft in response to a signal received from the one or more processors (which may be based on a signal received from the optical differential pressure sensor).
The fuel system may comprise a memory, and the optical differential pressure sensor may be configured to output the signal indicative of the pressure differential across the diaphragm to the memory to be stored thereon. Storing data indicative of the pressure differential across the diaphragm on the memory may allow the data to be analyzed at a later point in time. When the fuel system is installed on an aircraft, this may allow the data to be analyzed after flight. The data may be stored as a message which is output on a post-flight report. The data may also be used to further improve the accuracy of gauging of the fuel stored in the chamber.
The one or more processors may be configured to cause an indication to be output to an operator, based on the signal received from the differential pressure sensor. The indication may take the form of a light in a cockpit of an aircraft (when the fuel system is installed on an aircraft). Alternatively or additionally, an indication may be shown on a screen within the cockpit, to inform a flight crew of a level of fuel stored within the chamber. This may allow the flight crew to be informed of the level of fuel and take any necessary action (such as arranging for refueling or adjusting course). The indication may be that the fuel has fallen below a predetermined threshold. The predetermined threshold may correspond to an amount of fuel that is required to reach a target destination.
The optical differential pressure sensor may be located outside of the chamber. The optical differential pressure sensor being located outside of the chamber may reduce the likelihood of gases condensing within the optical differential pressure sensor, as the optical differential pressure sensor is less likely to come into contact with, and be cooled by, the cryogenic fuel. The optical differential pressure sensor may also be easier to maintain and/or replace as access into the chamber may not be required. Alternatively, the optical differential pressure sensor may be located within the chamber.
The optical differential pressure sensor may be positioned such that, when the fuel is stored in the chamber, the differential pressure sensor is located above a plane defined by a surface of the cryogenic fuel. As the optical differential pressure sensor is located above the surface of the fuel, any condensation within the optical differential pressure sensor may flow back toward the chamber rather than toward the optical differential pressure sensor.
The optical differential pressure sensor may be located in a vacuum. The vacuum may provide thermal insulation to the optical differential pressure sensor to reduce thermal ingress into the optical differential pressure sensor. This may reduce the likelihood of temperature variations within the optical differential pressure sensor, which may therefore increase accuracy of measurements by the optical differential pressure sensor. The vacuum may be a medium vacuum. The vacuum may have a pressure of between 100 Pa and 0.1 Pa. The optical differential pressure sensor may be located in a capsule area located outside of the chamber. The capsule area may be held at a medium vacuum, such as at a pressure of between 100 Pa and 0.1 Pa. The vacuum may provide thermal insulation to any components located within the capsule area.
The optical differential pressure sensor may be operable in a temperature range of between approximately 10K and 360K, such as between approximately 10K and 100K. This may allow the optical differential pressure sensor to operate in different climate and/or environments. As such, when the fuel system is installed in an aircraft, the optical differential pressure sensor may be capable of operating at differing temperatures while at altitude and while on the ground.
The optical differential pressure sensor may comprise a diaphragm, and the optical differential pressure sensor may be fluidically connected to the chamber such that, when the fuel is stored in the chamber, a gas is located on both sides of the diaphragm. Deflection of the diaphragm of the optical differential pressure sensor may be indicative of a pressure difference such that the deflection of the diaphragm may be measured to determine the differential pressure. As a gas is located on both sides of the diaphragm of the optical differential pressure sensor, this may reduce the likelihood of a liquid that is present on one or both sides of the diaphragm affecting the accuracy of measurements by the optical differential pressure sensor. Moreover, a gas being located on both sides of the diaphragm may result in the optical differential pressure sensor being less impacted by thermal transfer compared to if there was a liquid on one side of the diaphragm. This may reduce interference due to thermal transfer across the diaphragm where a lower temperature of the liquid may cause the gas to condense (at least temporarily), and a higher temperature of the gas may cause the liquid to evaporate.
When the fuel is stored in the chamber, the chamber may comprise a head space which is substantially free of fuel in a liquid state and a liquid space in which the fuel in the liquid state is located, and a first side of the diaphragm may be fluidically connected to the head space and a second side of the diaphragm is fluidically connected to the liquid space.
The optical differential pressure sensor may be configured to sense a pressure differential between the head space and the liquid space. This may allow a single optical differential pressure sensor to be used to determine the pressure differential between the head space and the liquid space. A weight of the fuel stored within the chamber may be determined based on the pressure differential between the head space and the liquid space.
The optical differential pressure sensor may be located in the head space of the chamber. This may reduce the likelihood of the optical differential pressure sensor being immersed in the fuel.
The cryogenic fuel storage system may comprise a first feed pipe and a second feed pipe, wherein the first side of the diaphragm is fluidically connected to the head space by the first feed pipe and the second side of the diaphragm is fluidically connected to the liquid space by the second feed pipe. The first and second feed pipes may allow the optical differential pressure sensor to be positioned away from the chamber. As such, the optical differential pressure sensor may be located away from the low temperatures of the fuel, which may reduce the likelihood of condensation and/or evaporation within the differential pressure sensor, improving accuracy and/or consistency of measurements.
The second feed pipe may extend into the chamber such that, when the fuel is stored within the chamber, the second feed pipe is at least partly submerged in the fuel. The fuel may assert a pressure on gas within the second pipe, which deflects the diaphragm of the optical differential pressure sensor. As such, the pressure applied to the diaphragm is representative of pressure of the fuel. The second feed pipe may the positioned such that it extends vertically through the chamber. The second feed pipe may extend through the head space and into the liquid space such that any fluid within the second feed pipe is guided into the liquid space. This may help to guide fluid away from the optical differential pressure sensor.
The first feed pipe and the second feed pipe may be thermally insulated. This may help to reduce heat transfer into and between the feed pipes, which may help to increase the accuracy of measurements of the pressure differential. The first feed pipe and the second feed pipe may be twisted together. At least one of the first feed pipe and the second feed pipe may be wrapped around the other of the second feed pipe and the first feed pipe. The first feed pipe and the second feed pipe may each comprise a substantially helical shape and may be intertwined about a common axis. This may help to equalize heat transfer between the feed pipes.
The fuel system may comprise multiple optical differential pressure sensors. This may provide redundancy in the event that one of the optical differential pressure sensors fails to operate correctly.
The fuel system may be pressurized. The fuel system may be pressurized to a least 1 bar (100 kPa), such as at least 2 bar (200 kPa), at least 3 bar (300 kPa) or at least 4 bar (400 kPa). The use of the optical differential pressure sensor in a pressurized fuel system may reduce or negate the effect of pressurization compared to the use of absolute pressure sensors. As the pressurization may be the same for the whole system, the pressurization may be equal on both sides of the diaphragm. As the pressurization may be equal on both sides of the diaphragm, the pressurization may not itself cause a differential pressure across the diaphragm, meaning that the differential pressure sensed by the differential pressure sensor may not be influenced by the pressurization. The use of the differential pressure sensor may therefore provide more accurate measurements compared to the use of absolute pressure sensors.
The fuel system may comprise a temperature sensor configured to determine a temperature of gas within the optical differential pressure sensor. Determining the temperature of gases within the optical differential pressure sensor may allow for a more accurate determination of the differential pressure. The temperature sensor may be located within the optical differential pressure sensor. The fuel system may comprise more than one temperature sensor, such as two, three or four temperature sensors. The fuel system may comprise a first temperature sensor located on the first side of the diaphragm and a second temperature sensor located on the second side of the diaphragm. This may allow the temperature of the gas on both sides of the diaphragm to be individually measured.
The fuel may comprise aviation fuel, such as avgas or kerosene. When the fuel is kerosene, gas being located on both sides of the diaphragm reduces likelihood of water contaminating the fuel becoming frozen and blocking the optical differential pressure sensor and/or the feed pipes when exposed to low temperatures. The chamber may comprise a cryogenic chamber for storing cryogenic fuel. The fuel may comprise a cryogenic fuel, such as liquid hydrogen. The fuel system may be configured to store the cryogenic fuel at between approximately 15K and 100K. This may help to maintain the cryogenic fuel in a liquid state.
According to a second aspect, there is provided an aircraft fuel system comprising the fuel system according to the first aspect.
According to a third aspect, there is provided an aircraft comprising the fuel system according to the first aspect or the aircraft fuel system according to the second aspect.
The chamber of the fuel system may be located within at least one of a wing of the aircraft and a tail section of the aircraft.
According to a fourth aspect, there is provided a method of gauging a fuel stored within a chamber, the method comprising: measuring a differential pressure in the chamber using an optical differential pressure sensor; outputting, by the optical differential pressure sensor, a signal indicative of the differential pressure; receiving, at one or more processors, the signal output by the differential pressure sensor; and based on the received signal, gauging the fuel stored within the chamber using the one or more processors.
The use of an optical differential pressure sensor may reduce the total number of electrical connections in proximity of the chamber compared to the use of an electrical differential pressure sensor, such as a capacitive differential pressure sensor. As only a non-current carrying element (such as an optical fiber) of the optical differential pressure sensor may need to be near the diaphragm, any current carrying electronics (such as an optical interrogator connected to the optical fiber) may be positioned away from the chamber. This may help to reduce a likelihood of electrical arcing occurring close to the chamber. The optical differential pressure sensor may be configured to determine a pressure difference by measuring an optical path difference to determine deflection of the diaphragm.
The optical pressure sensor may use light to measure deflection of the diaphragm, such that the optical differential pressure sensor may be less susceptible to magnetic fields compared to, for example, a capacitive differential pressure sensor. This may increase the accuracy and/or consistency of measurements made by the optical differential pressure sensor.
The method may comprise causing an indication to be output based on the received signal. The indication may take the form of a light in a cockpit of an aircraft (when the chamber is located on an aircraft). Alternatively or additionally, an indication may be shown on a screen within the cockpit, to inform a flight crew of a level of fuel stored within the chamber. This may allow the flight crew to be informed of the level of fuel and take any necessary action (such as arranging for refueling or adjusting course). The indication may be that the fuel has fallen below a predetermined threshold. The predetermined threshold may correspond to an amount of fuel that is required to reach a target destination.
Gauging the fuel stored in the chamber may comprise determining a weight of the fuel within the chamber. The gauging the fuel may comprise determining a depth of the fuel within the chamber. The weight of the fuel and/or the depth of the fuel may be indicative of an amount of fuel within the chamber. Using the optical differential pressure sensor to gauge the fuel within the chamber may be more accurate than using other means, such as a float connected to a rotary position sensor, as the measurement is affected less by motion of the fuel within the chamber.
The method may comprise gauging the fuel stored within the chamber based on the received signal using the one or more processors. This may allow the one or more processors to gauge the fuel without the use of external processing.
The method may comprise storing information indicative of the differential pressure across the diaphragm on a memory. Storing data indicative of the differential pressure across the diaphragm on the memory may allow the data to be analyzed at a later point in time. When the chamber is installed on an aircraft, this may allow the data to be analyzed after flight. The data may be stored as a message which is output on a post-flight report. The data may also be used to further improve the accuracy of gauging of the fuel stored in the chamber.
Embodiments of the invention will now be described, by way of example only, with reference to the accompanying drawings, in which:
The chamber 12 comprises an upper wall 30, a lower wall 32, side walls 34 (two of which are shown in
The controller 22 comprises one or more processors 56 and a transceiver 58. The one or more processors 56 are in communication with the optical differential pressure sensor 14 via an electrical connection 60. The transceiver 58 is in communication with the one or more processors 56 and receives from the one or more processors 56 information indicative of a signal output by the optical differential pressure sensor 14. The transceiver 58 can then, if required, transmit the information received from the one or more processors 56 to a receiver at a different geographical location to the fuel system 10, such as to a control center or an operations center located at an airport.
The optical differential pressure sensor 14 is located outside of the chamber 12 and is installed within the capsule area 26. The capsule area 26 is hermetically sealed and is evacuated to a pressure of less than approximately 100 Pa. As such, the optical differential pressure sensor 14 is located within a medium vacuum inside the capsule area 26. As well as being located outside of the chamber 12, the optical differential pressure sensor 14 is also positioned such that the head space 36 is between the optical differential pressure sensor 14 and the liquid space 40. As such, the optical differential pressure sensor 14 is above a surface 43 of the fuel 28 stored within the chamber 12. In particular, the optical differential pressure sensor 14 is positioned above a plane defined by the surface 43 of the fuel 28 stored within the chamber 12.
The first feed pipe 16 extends from a first side 44 of the optical differential pressure sensor 14 to the head space 36 of the chamber 12. The second feed pipe 18 extends from a second, opposite side 46 of the optical differential pressure sensor 14 through the head space 36 of the chamber 12 into the liquid space 40. The first feed pipe 16 and the second feed pipe 18 comprise the same material and have the same inner diameter as each other.
The first feed pipe 16 comprises a first end 48 and a second end 50. The first end 48 of the first feed pipe 16 is fluidically connected to the first side 44 of the optical differential pressure sensor 14 and the second end 50 of the first feed pipe 16 is fluidically connected to the head space 36 of the chamber 12. The second feed pipe 18 also comprises a first end 52 and a second end 54. The first end 52 of the second feed pipe 18 is fluidically connected to the second side 46 of the optical differential pressure sensor 14 and the second end 54 of the second feed pipe 18 is submerged in the fuel 28 stored within the chamber 12.
The first feed pipe 16 and the second feed pipe 18 are both wrapped in thermally insulating material to thermally insulate the first feed pipe 16 and the second feed pipe 18 from each other and from an external environment. In some examples, not shown in the Figures, at least a part of the first feed pipe 16 and the second feed pipe 18 are twisted together. The respective parts of the first feed pipe 16 and the second feed pipe 18 each comprise a substantially helical shape and are intertwined about a common axis.
A schematic cross-sectional view of the optical differential pressure sensor 14 is shown in
As the optical differential pressure sensor 14 is located above the surface 43 of the fuel 28 stored in the chamber 12, the cavity 62 of the optical differential pressure sensor 14 is substantially free of any liquid fuel and gas is located on both sides of the diaphragm 64. This is because any liquid within the cavity will be encouraged by gravity away from the optical differential pressure sensor 14 and into the chamber 12.
As gas is located on both sides of the diaphragm 64 of the optical differential pressure sensor 14, this may reduce the likelihood of a liquid that is present on one or both sides of the diaphragm 64 affecting the accuracy of measurements by the optical differential pressure sensor 14. As the pressure differential may be larger, the optical differential pressure sensor 14 may be less sensitive than other sensors known in the art. Gas being located on both sides of the diaphragm 64 may also result in a reduction in the impact of a temperature differential across the diaphragm 64 compared to if there was a liquid on one side of the diaphragm 64. This may reduce interference due to thermal transfer across the diaphragm 64 where a lower temperature of the fuel 28 (in liquid form) may cause the gas to condense (at least temporarily), and a higher temperature of the gas may cause the fuel 28 to evaporate.
A pressure exerted on the first side 70 of the diaphragm 64 corresponds to the pressure in the head space 36 of the chamber 12 (also known as head pressure), while a pressure exerted on the second side 72 of the diaphragm 64 corresponds to a combination of the head pressure and the weight of the fuel 28 stored in the chamber 12. As such, the differential pressure between the first side 70 of the diaphragm 64 and the second side 72 of the diaphragm 64 corresponds to the weight of the fuel 28 within the chamber 12.
The optical fiber 66 extends into the optical differential pressure sensor 14 on the second side 46 of the optical differential pressure sensor 14. An optical interrogator 74 is attached to an end of the optical fiber 66 that is distal from the optical differential pressure sensor 14. The optical interrogator 74 injects light with known properties (such as amplitude and wavelength) into the optical fiber 66 and receives and analyses light reflected into the optical fiber 66. The optical fiber 66 is positioned such that light exiting the optical fiber 66 is incident on the diaphragm 64 and is reflected into the optical fiber 66. The optical interrogator 74 is in communication with the one or more processors 56 via an electrical connection and outputs a signal indicative of an amount the diaphragm 64 has deflected to the one or more processors 56.
The temperature sensor 68 is located on the first side 70 of the diaphragm 64 and comprises a thermocouple 76. In other examples, the temperature sensor 68 comprises another device capable of determining temperature, such as a thermistor. The temperature sensor 68 monitors a temperature of gas within the cavity 62 of the optical differential pressure sensor 14 and outputs a signal indicative of the temperature to the one or more processors 56. The temperature is then used by the one or more processors 56 when gauging the fuel within the chamber 12. Although only one temperature sensor 68 is shown in
The fuel system 10 discussed above in relation to
The chamber 12 of the fuel system 10 is located in the tail section 5 of the aircraft 1. The fuel system 10 is installed such that when the aircraft 1 is on the ground (or at level flight), the optical differential pressure sensor 14 remains above a plane defined by the surface 43 of the fuel 28 stored within the chamber 12. The second feed pipe 18 also arranged such that when the aircraft 1 is on the ground, the second feed pipe 18 extends vertically into the chamber 12 with respect to the ground. While in this example the chamber 12 of the fuel system 10 is located in the tail section 5 of the aircraft 1, in some examples the chamber 12 is alternatively or additionally located within at least one of the wings 4. In the example illustrated in
When there is a pressure difference between the first side 70 of the diaphragm 64 and the second side 72 of the diaphragm 64, the diaphragm 64 will deflect towards either the first side 44 of the optical differential pressure sensor 14 or the second side 46 of the optical differential pressure sensor 14. For example, if a pressure on the first side 70 of the diaphragm 64 is greater than on the second side 72 of the diaphragm 64, the diaphragm 64 will deflect towards the second side 46 of the optical differential pressure sensor 14 (as shown by dashed lines in
The optical differential pressure sensor 14 outputs a signal indicative of the amount the diaphragm 64 has deflected (which is indicative of the pressure difference across the diaphragm 64) to the one or more processors 56 of the controller 22. Based on the signal received from the optical differential pressure sensor 14, the one or more processors 56 gauge the fuel 28 stored with the chamber 12 to determine a weight of the fuel 28 within the chamber 12. The one or more processors 56 of the controller 22 subsequently cause an indication to be provided on the display of the cockpit 3. The indication is provided by the display within the cockpit 3 of the aircraft 1 to inform the flight crew of the weight of the fuel 28 stored within the chamber 12. The flight crew may then take action if required based on the indication, such as by requesting refueling or changing a route of the aircraft 1.
The use of an optical differential pressure sensor 14 to gauge the fuel 28 may reduce the total number of electrical connections with current running through them in proximity of the chamber 12 compared to the use of, for example, a capacitive differential pressure sensor. As only the optical fiber 66 needs to be near the diaphragm 64, the optical interrogator 74 (and any associated current carrying electronics) can be positioned away from the chamber 12.
While in the example shown in
The method 100 further comprises receiving 106, at the one or more processors 56, the signal output by the differential pressure sensor 14 and, based on the received signal, gauging 108 the fuel 28 stored within the chamber 12 to determine a weight of the fuel 28 within the chamber 12. In other examples, the gauging 108 comprises determining another property of the fuel 28, such as a depth of fuel 28 within the chamber 12. The gauging 108 is carried out by the one or more processors 56.
After the fuel 28 has been gauged, the method 100 comprises causing an indication to be output 110 based on the result of gauging 108 the fuel 28. The indication is provided by the display in the cockpit 3 of the aircraft 1 and informs the flight crew of the weight of the fuel 28 within the chamber 12.
The method 100 also comprises storing 112 information indicative of the differential pressure across the diaphragm 64 of the optical differential pressure sensor 14 on the memory 6.
In some examples, one or more of the steps of causing or outputting 110 an indication or storing 112 information indicative of the differential pressure may be omitted from the method 100.
Although in the examples described herein the one or more processors 56 are in communication with the optical differential pressure sensor 14 via an electrical connection 60, in other examples the one or more processors 56 are in communication with the optical differential pressure sensor 14 via wireless communication, such as WiFi, Bluetooth or other suitable wireless standard.
While the examples discussed above utilize an optical differential pressure sensor 14, it is understood that an arrangement where gas is located on both sides of a diaphragm may also be beneficial to other types of differential pressure sensor, such as capacitive differential pressure sensors. As gas is located on both sides of the diaphragm of the differential pressure sensor, this may reduce the likelihood of a liquid that is present on one or both sides of the diaphragm affecting the accuracy of measurements by the differential pressure sensor. Gas being located on both sides of the diaphragm may also result in the differential pressure sensor being less impacted by thermal transfer compared to if there was a liquid on one side of the diaphragm. This may reduce interference due to thermal transfer across the diaphragm where a lower temperature of the fuel (in liquid form) may cause the gas to condense (at least temporarily), and a higher temperature of the gas may cause the fuel to evaporate. Although a single optical differential pressure sensor 14 is shown in the fuel system 10 discussed above, in some examples a plurality of optical differential pressure sensors 14 are used with a single chamber 12.
While in the examples discussed above, the fuel 28 is liquid nitrogen, it is understood that the use of an optical differential pressure sensor to gauge fuel may be beneficial for other types of fuel, such as kerosene or avgas (aviation gasoline). The use of the optical differential pressure sensor may reduce the total number of electrical connections in proximity of the chamber compared to the use of, for example, a capacitive differential pressure sensor. As only a non-current carrying element (such as an optical fiber 66) of the optical differential pressure sensor may need to be near the diaphragm, any current carrying electronics (such as the optical interrogator 74 connected to the optical fiber 66) can be positioned away from the chamber. This may help to reduce a likelihood of electrical arcing occurring close to the chamber.
It is to be noted that the term “or” as used herein is to be interpreted to mean “and/or”, unless expressly stated otherwise.
The systems and devices described herein may include a controller or a computing device comprising a processing and a memory which has stored therein computer-executable instructions for implementing the processes described herein. The processing unit may comprise any suitable devices configured to cause a series of steps to be performed so as to implement the method such that instructions, when executed by the computing device or other programmable apparatus, may cause the functions/acts/steps specified in the methods described herein to be executed. The processing unit may comprise, for example, any type of general-purpose microprocessor or microcontroller, a digital signal processing (DSP) processor, a central processing unit (CPU), an integrated circuit, a field programmable gate array (FPGA), a reconfigurable processor, other suitably programmed or programmable logic circuits, or any combination thereof.
The memory may be any suitable known or other machine-readable storage medium. The memory may comprise non-transitory computer readable storage medium such as, for example, but not limited to, an electronic, magnetic, optical, electromagnetic, infrared, or semiconductor system, apparatus, or device, or any suitable combination of the foregoing. The memory may include a suitable combination of any type of computer memory that is located either internally or externally to the device such as, for example, random-access memory (RAM), read-only memory (ROM), compact disc read-only memory (CDROM), electro-optical memory, magneto-optical memory, erasable programmable read-only memory (EPROM), and electrically-erasable programmable read-only memory (EEPROM), Ferroelectric RAM (FRAM) or the like. The memory may comprise any storage means (e.g., devices) suitable for retrievably storing the computer-executable instructions executable by processing unit.
The methods and systems described herein may be implemented in a high-level procedural or object-oriented programming or scripting language, or a combination thereof, to communicate with or assist in the operation of the controller or computing device. Alternatively, the methods and systems described herein may be implemented in assembly or machine language. The language may be a compiled or interpreted language. Program code for implementing the methods and systems described herein may be stored on the storage media or the device, for example a ROM, a magnetic disk, an optical disc, a flash drive, or any other suitable storage media or device. The program code may be readable by a general or special-purpose programmable computer for configuring and operating the computer when the storage media or device is read by the computer to perform the procedures described herein.
Computer-executable instructions may be in many forms, including modules, executed by one or more computers or other devices. Generally, modules include routines, programs, objects, components, data structures, etc., that perform particular tasks or implement particular abstract data types. Typically, the functionality of the modules may be combined or distributed as desired in various embodiments.
It will be appreciated that the systems and devices and components thereof may utilize communication through any of various network protocols such as TCP/IP, Ethernet, FTP, HTTP and the like, and/or through various wireless communication technologies such as GSM, CDMA, Wi-Fi, and WiMAX, is and the various computing devices described herein may be configured to communicate using any of these network protocols or technologies.
The above embodiments are to be understood as illustrative examples of the invention. Further embodiments of the invention are envisaged. It is to be understood that any feature described in relation to any one embodiment may be used alone, or in combination with other features described, and may also be used in combination with one or more features of any other of the embodiments, or any combination of any other of the embodiments. Furthermore, equivalents and modifications not described above may also be employed without departing from the scope of the invention, which is defined in the accompanying claims.
While at least one exemplary embodiment of the present invention(s) is disclosed herein, it should be understood that modifications, substitutions and alternatives may be apparent to one of ordinary skill in the art and can be made without departing from the scope of this disclosure. This disclosure is intended to cover any adaptations or variations of the exemplary embodiment(s). In addition, in this disclosure, the terms “comprise” or “comprising” do not exclude other elements or steps, the terms “a” or “one” do not exclude a plural number, and the term “or” means either or both. Furthermore, characteristics or steps which have been described may also be used in combination with other characteristics or steps and in any order unless the disclosure or context suggests otherwise. This disclosure hereby incorporates by reference the complete disclosure of any patent or application from which it claims benefit or priority.
| Number | Date | Country | Kind |
|---|---|---|---|
| 2311349.1 | Jul 2023 | GB | national |
