Method of determining operating condition of a valve of an aircraft system

Abstract

A method of determining an operating condition of a valve of an aircraft system is disclosed. The method includes obtaining a first time period associated with actuating the valve and a second time period associated with actuating the valve. The method includes providing an indication of a modified operating condition associated with actuation of the valve based on the first time period and the second time period.

Description

Technical Field

[0001] This invention relates to a method for determining the operating status of valves in an aircraft system, and to an aircraft system. Background Technology

[0002] Aircraft systems may include valves for controlling fluid flow between different components of the aircraft system. For example, an aircraft fuel system may include multiple fuel storage tanks, and fuel can move between the fuel storage tanks during flight to maintain or achieve desired flight characteristics, such as trimming the aircraft to achieve a desired attitude. Thus, fuel storage tanks typically have valves that control the inflow and outflow of fluid. Summary of the Invention

[0003] A first aspect of the present invention provides a method for determining the operating status of a valve in an aircraft system, the method comprising: obtaining a first time period associated with an actuated valve and a second time period associated with an actuated valve; and providing an indication of a modified operating status associated with actuation of the valve based on the first time period and the second time period.

[0004] The first time period can be associated with the first actuation of the valve, and the second time period can be associated with the second actuation of the valve, which is different from the first actuation of the valve.

[0005] The valve can be actuated between a first position and a second position. A first time period can be associated with a first actuation of the valve from the first position to the second position or from the second position to the first position, and a second time period can be associated with a second actuation of the valve from the first position to the second position or from the second position to the first position.

[0006] The method may include: comparing each of a first time period and a second time period with a threshold, and, if each of the first time period and the second time period exceeds the threshold, providing an indication of a modified operating condition associated with valve actuation.

[0007] The first time period can be associated with the actuation of the valve during a first flight using the aircraft system, and the second time period can be associated with the actuation of the valve during a second flight using the aircraft system, which is different from the first flight.

[0008] The method may include providing an indication of altered operating conditions associated with valve actuation if the first flight and the second flight occur within a predetermined time window.

[0009] The valve can be actuated multiple times during a first flight, and the method may include: obtaining a first plurality of time periods, each corresponding to a corresponding actuation of the valve during the first flight, and selecting a first time period from the first plurality of time periods based on the length of each of the first plurality of time periods. The valve can be actuated multiple times during a second flight, and the method may include: obtaining a second plurality of time periods, each corresponding to a corresponding actuation of the valve during the second flight, and selecting a second time period from the second plurality of time periods based on the length of each of the second plurality of time periods.

[0010] The method may include: obtaining at least four distinct time periods associated with an actuation valve, each time period being associated with actuating the valve during a different corresponding flight period in multiple flights; comparing each time period with a corresponding threshold; and, if each time period exceeds the threshold and multiple flights occur within a predetermined time window, providing an indication of a modified operating condition associated with the actuation of the valve.

[0011] The valve can move from a first position to a second position in response to a command. The first time period includes the time taken for the valve to move from the first position to the second position, and the second time period includes the time taken from issuing or receiving the command to the valve reaching the second position.

[0012] The first time period may include the time taken for the valve to move from the first position to the second position. The second time period may include the time taken from issuing or receiving a command to the valve reaching the second position.

[0013] The first and second time periods can be associated with the same valve movement.

[0014] The method may include: performing a comparison of a first time period with parameters, and providing an indication of a modified operating condition associated with valve actuation based on the comparison.

[0015] The method may include: performing a second time period and another comparison with another parameter, and providing an indication of a modified operating condition associated with valve actuation based on the comparison and the other comparison.

[0016] This parameter may include the nominal time it takes for the valve to move from the first position to the second position, and the other parameter may include the nominal time it takes from issuing or receiving a command to the valve reaching the second position.

[0017] The method may include: providing an indication of a first modified operating condition associated with valve actuation when a first time period exceeds the parameter and a second time period exceeds the other parameter; providing an indication of a second modified operating condition associated with valve actuation when the first time period exceeds the parameter and the second time period does not exceed the other parameter, the second modified operating condition being different from the first modified operating condition associated with valve actuation; and providing an indication of a third modified operating condition associated with valve actuation when the first time period does not exceed the parameter and the second time period exceeds the other parameter, the third modified operating condition being different from the first and second modified operating conditions of the valve.

[0018] This parameter may include a second time period, and / or the other parameter may include a first time period.

[0019] The valve may include a first actuator and a second actuator, a first time period may be associated with actuation of the valve by the first actuator and the second actuator at a first time point, a second time period may be associated with actuation of the valve by the first actuator and the second actuator at a second time point different from the first time point, and if the second time period is longer than the first time period, the method may include: providing an indication of a modified operating condition of at least one of the first actuator and the second actuator.

[0020] Aircraft systems may include aircraft fuel supply systems.

[0021] A second aspect of the invention provides a data carrier including machine-readable instructions for operating one or more processors of a controller of an aircraft system to obtain a first time period associated with an actuated valve and a second time period associated with the actuated valve, and to provide an indication of a modified operating condition associated with the actuation of the valve based on the first and second time periods.

[0022] The controller can be configured to perform any of the optional actions described above with respect to the first aspect of the invention.

[0023] A third aspect of the invention provides an aircraft system comprising: a valve; a controller configured to obtain a first time period associated with an actuation valve and a second time period associated with an actuation valve; and an indicator configured to provide an indication of a modified operating condition associated with actuation of the valve based on the first and second time periods.

[0024] The controller can be configured to perform any of the optional actions described above with respect to the first aspect of the invention.

[0025] A fourth aspect of the invention provides an aircraft fuel system comprising: a fuel tank; a conduit in fluid communication with the fuel tank; a valve located within the conduit for selectively enabling fuel to be delivered to and / or from the fuel tank; a controller; and an indicator configured to: monitor a plurality of time periods associated with actuation of the valve between an open position and a closed position or between a closed position and an open position, each of the plurality of time periods being acquired during different flights of the aircraft including the aircraft fuel system; and to compare each of the plurality of time periods with a corresponding parameter, and the indicator being configured to provide an indication based on the comparison of valve operation under modified operating conditions relative to the valve's normal operating conditions.

[0026] A fifth aspect of the present invention provides an aircraft comprising the aircraft system of the third aspect of the present invention or the aircraft fuel system of the fourth aspect of the present invention. Attached Figure Description

[0027] Embodiments of the invention will now be described by way of example only with reference to the accompanying drawings, in which:

[0028] Figure 1 A schematic diagram of the first aircraft's fuel system is shown;

[0029] Figure 2 It shows Figure 1 The actuation of the valves in the first aircraft's fuel system;

[0030] Figure 3 The determination is shown Figure 1 The method of altering the operating conditions of the valves in the first aircraft's fuel system;

[0031] Figure 4 It shows the comparison with Figure 1 The first diagram shows the time period associated with the actuation of the valves in the first aircraft's fuel system;

[0032] Figure 5 It shows the comparison with Figure 1 The second figure shows the time period associated with the actuation of the valves in the first aircraft's fuel system;

[0033] Figure 6 A schematic diagram of the second aircraft's fuel system is shown;

[0034] Figure 7 It shows including Figure 1 First aircraft fuel system or Figure 6 A schematic diagram of the second aircraft fuel system; and

[0035] Figure 8A schematic diagram of the data carrier is shown. Detailed Implementation

[0036] exist Figure 1 The diagram schematically illustrates an aircraft system in the form of an aircraft fuel system typically designated as 10.

[0037] The aircraft fuel system 10 includes a fuel storage tank 12, a conduit 14, a valve 16, a valve actuator 17, a controller 18, and an indicator 20.

[0038] Fuel storage tank 12 is any suitable fuel storage tank for an aircraft and includes a container for holding fuel during use. It should be understood that there may be many such fuel storage tanks 12 located on any single aircraft. Similarly, conduit 14 is any suitable conduit for an aircraft, and conduit 14 defines both the inlet and outlet of fuel storage tank 12. In other examples, conduit 14 may define only one of the inlet or outlet of fuel storage tank 12, wherein the other of the inlet and outlet of fuel storage tank 12 is provided by another conduit of fuel storage tank 12.

[0039] Valve 16 is located within conduit 14 and includes a ball valve. Valve 16 includes a valve drive spindle 27 connected to a generally spherical body 22, in which an orifice 24 is formed. The body 22 is located within a valve seat of conduit 14 such that the body 22 and therefore the orifice 24 can be rotated relative to conduit 14 via valve drive spindle 27. The body 22 can be rotated within conduit 14 at an angle of approximately 90 degrees, such that the body 22 is in a first position in which the body 22 interrupts the flow of fluid through conduit 14, or in a second position in which the orifice 24 is positioned such that fluid can pass through the orifice 24 and enter or exit fuel storage tank 12 through conduit 14. The first position may be referred to as the closed position of valve 16, and the second position may be referred to as the open position of valve 16.

[0040] Valve actuator 17 includes a shaft 26 and a motor 28. Shaft 26 is connected to the body 22 of valve 16 via a valve drive spindle 27, and motor 28 is operable in response to a command issued by controller 18 to rotate shaft 26 and thus the valve drive spindle 27, thereby moving body 22 between a first position and a second position (i.e., the closed and open positions discussed above). Motor 28 can be considered as a driver for valve 16. Shaft 26 is provided with a protrusion 30, and a first microswitch 32 and a second microswitch 34 are located near shaft 26. Protrusion 30 contacts the first microswitch 32 when the body 22 of valve 16 is in the first closed position, such that the first microswitch 32 is closed when the body 22 of valve 16 is in the closed position, and protrusion 30 contacts the second microswitch 34 when the body 22 of valve 16 is in the second open position, such that the second microswitch 34 is closed when the body 22 of valve 16 is in the open position.

[0041] The first microswitch 32 and the second microswitch 34 are connected to the controller 18, so that the controller 18 knows when the body 22 of the valve 16 is in the first closed position and the second open position, or when it is in the transition between the first closed position and the second open position.

[0042] Controller 18 includes a processor and is configured to provide commands to motor 28 to actuate the body 22 of valve 16 between a first closed position and a second open position. In some examples, controller 18 may derive commands based on input received from other systems of the aircraft on which the aircraft fuel system 10 is installed. Controller 18 includes a clock or counter that may be used to monitor the actuation of valve 16, as will be described in more detail below. Controller 18 may transmit details of the actuation of valve 16 to an indicator.

[0043] Indicator 20 can take various forms as described below and is capable of providing indication of the operating status or altered operating status of valve 16. Figure 1 In the example, indicator 20 is depicted as part of the aircraft fuel system 10, but it should be understood that other examples are also conceivable, in which the indicator forms part of a wider portion of the aircraft or is positioned away from the aircraft, such as at a ground location. Figure 1 The indicator 20 is depicted as being coupled to the controller 18, but it should be understood that in some examples, the controller 18 itself may provide an indication of the operating status or altered operating status of the valve 16 by means of data generated or output by the controller 18.

[0044] exist Figure 2 The actuation of valve 16 between the closed and open positions is schematically shown.

[0045] The controller 18 provides a command signal 36 to actuate the motor 28 to rotate the shaft 26, thereby driving the main shaft 27 to open or close the valve 16 via the valve, wherein the command signal 36 can vary between a logic high state indicating a valve closing command and a logic low state indicating a valve opening command.

[0046] The first microswitch 32 provides a "closed" feedback signal 38 to the controller 18, wherein the closed feedback signal 38 can vary between a logic low state in the first closed position of the indicating valve 16 and a logic high state in the non-closed position of the indicating valve 16. A logic low state of the closed feedback signal 38 is provided when the protrusion 30 contacts the first microswitch 32, and a logic high state of the closed feedback signal 38 is provided when the protrusion 30 does not contact the first microswitch 32.

[0047] The second microswitch 34 provides an "on" feedback signal 40 to the controller 18, wherein the on feedback signal 40 can vary between a logic low state in the second open position of the indicating valve 16 and a logic high state in the non-open position of the indicating valve 16. The logic low state of the on feedback signal 40 is provided when the protrusion 30 contacts the second microswitch 34, and the logic high state of the on feedback signal 40 is provided when the protrusion 30 is not in contact with the first microswitch 32.

[0048] It should be understood that, if necessary, the functions of the logical high state and logical low state discussed above can be reversed.

[0049] It can be seen that, Figure 2 In the example, valve 16 transitions from a first closed position to a second open position.

[0050] At time T0, the command signal 36 provided by controller 18 transitions from its logic high state to its logic low state, indicating that valve 16 is expected to open to allow fuel to flow into or out of fuel storage tank 12. Given a delay in processing, the signal reaches motor 28, and motor 28 is energized. At a later time T1, shaft 26 is rotated such that protrusion 30 is no longer in contact with the first microswitch 32. Therefore, at time T1, the closure feedback signal 38 transitions from its logic low state to its logic high state, indicating that valve 16 is not closed. At time T1, the opening feedback signal 40 remains in its logic high state, indicating that valve 16 is not open.

[0051] At a later time T2, shaft 26 has rotated to move the body 22 of valve 16 from its first closed position to its second open position, and protrusion 30 contacts the second microswitch 34. Therefore, at T2, the open feedback signal 40 transitions from its logic high state to its logic low state, indicating that valve 16 is open.

[0052] Controller 18 monitors times T0, T1, and T2, and these times can be used to determine altered operating conditions of valve 16. Alternative operating conditions associated with valve 16 actuation may include situations where the valve operates unexpectedly, such as due to motor wear, friction, or other altered operating conditions. Alternative operating conditions associated with valve actuation may include situations where the time taken for the valve to open or close exceeds a predetermined nominal acceptable time. It should be understood that, in the case where valve 16 is closed instead of open, T1 and T2 may also refer to the transition of the opening feedback signal 40 from its logic low state to its logic high state and the transition of the closing feedback signal 38 from its logic high state to its logic low state, respectively.

[0053] Method 100 for determining the operating condition of valve 16 Figure 3 The diagram schematically illustrates and includes obtaining a first time period associated with actuating valve 16 and a second time period associated with actuating valve 16, and providing an indication of the modified operating condition associated with actuation of valve 16 based on the first and second time periods.

[0054] It should be understood that the first time period and the second time period can be used in different ways, as will be described below.

[0055] For example, a first time period 42 from T1 to T2 can be measured and used, and assuming that it depends on feedback from both the first microswitch 32 and the second microswitch 34, the first time period 42 can be referred to as the feedback-to-feedback period. The first time period 42 typically includes the time period during which the body 22 of the indicator valve 16 rotates between its first closed position and its second open position or between its second open position and its first closed position.

[0056] The second time period 44 from T0 to T2 can be additionally or alternatively measured and used, and it is assumed that the second time period 44 can be referred to as the command-to-feedback period, depending on the command to open or close the valve 16 provided by the controller 18 and the feedback from the second microswitch 34 or the first microswitch 32 depending on whether the valve 16 is open or closed.

[0057] In one example, a first time period 42 may be used to determine the altered operating condition associated with the actuation of valve 16. During a single flight of the aircraft 300 equipped with the aircraft fuel system 10, the controller 18 monitors the first time period 42 each time valve 16 is actuated (i.e., opened or closed). The controller 18 stores the first time period 42, which has a maximum value for that flight, in the memory of the aircraft 300, or transfers it to a remote memory location and stores it there. In some examples, every occurrence of the first time period 42 may be recorded; however, it should be understood that this may require a larger memory capacity.

[0058] This process is repeated during multiple flights of the aircraft 300, wherein each first time period 42 having a maximum value for a given flight is stored in the memory of the aircraft 300, or transferred to a remote memory location and stored there. Each stored value of the first time period 42 is compared with a threshold indicating the normal operating condition of the valve 16. The threshold can be selected to be below a value that would cause a warning of abnormal operating condition during flight to be provided. If a predetermined number of first time periods 42 exceed the threshold within a predetermined time window, an indication of a modified operating condition associated with the actuation of the valve 16 is provided.

[0059] exist Figure 4 The diagram illustrates an example of a stored first time period 42, where each point corresponds to the first time period 42. Here, a threshold for the first time period 42 is shown as X. In some examples, X is in the range of six to fourteen seconds, for example, about ten seconds. If the stored first time period 42 exceeds the threshold X for a predetermined number of flights, an indication of a modified operating condition associated with the actuation of valve 16 is provided, for example, within... Figure 4 The number of flights between two and fifty flights within the time window marked as Y. This situation occurs in... Figure 4 The circled area in the graph is shown. The time window Y can range from ten to fifty days, for example, about thirty days. In some examples, the scheduled number of flights could be about five of the most recent fifty flights.

[0060] As will be understood, the indication can take many forms. For example, where the controller 18 stores the first time period 42 in the local memory of the aircraft 300, when the first time period 42 that causes the aforementioned criteria to be met is determined, the indicator 20 can provide the aircraft crew with a visual indication, in the form of a lighting or on-screen message, that a modified operating condition associated with the actuation of valve 16 has been determined. In such a case, the aircraft crew can log the indication in the log and / or mark the indication to ground maintenance personnel, so that valve 16 and / or valve actuator 17 can be inspected and replaced as needed.

[0061] In some examples, the comparison step may be performed by controller 18, wherein an indication of the altered operating condition associated with the actuation of valve 16 is transmitted from controller 18 to method indicator 20 for display by indicator 20. For example, the comparison and / or calculation step may be performed by controller 18, wherein remote indicator 20 is used to display the indication to ground maintenance personnel. Indications in such examples may include lighting or on-screen messages, or such as... Figure 4 The visual representation of the image.

[0062] In some examples, where controller 18 transmits a first time period 42 for storage in remote memory and indicator 20 is positioned remotely from aircraft 300, comparison and / or calculation steps can be performed remotely from aircraft 300 based on data transmitted by controller 18, wherein indicator 20 transmits an indication of a modified operating condition associated with the actuation of valve 16 to ground maintenance personnel. Indications in such examples may include lighting or on-screen messages, or such as... Figure 4 The visual representation of the image.

[0063] While visual indications have been described above, it should be understood that other forms of indications, such as auditory indications, are also conceivable. Furthermore, it should be understood that, assuming the modified operating conditions can be derived from the original data values, the original data values ​​of the first time period 42 itself (e.g., original data values ​​indicating the length, start, or end of the first time period 42) can be considered as indications of the modified operating conditions associated with the actuation of valve 16.

[0064] In other examples, both the first time period 42 and the second time period 44 can be used to determine the altered operating conditions associated with the actuation of valve 16.

[0065] During a single flight of the aircraft 300 equipped with the aircraft fuel system 10, the controller 18 monitors a first time period 42 and a second time period 44 each time the valve 16 is actuated (i.e., opened or closed). The controller 18 stores the first time period 42 having the maximum value for that flight and the second time period 44 having the maximum value for that flight, and / or the second time period 44 having the maximum value for that flight and its corresponding first time period 42, in the memory of the aircraft 300, or transfers it to a remote memory location and stores it there. In some examples, each occurrence of the first time period 42 and each occurrence of the second time period 44 may be recorded; however, it should be understood that this may require a larger memory capacity.

[0066] It has been found that the comparison between the first time period 42 and the second time period 44 can be used to distinguish the different modified operating modes of valve 16.

[0067] For example, when both the first time period 42 and the second time period 44 are higher than their corresponding thresholds, valve 16 may include an operating condition in which the time taken for valve 16 to open and / or close is longer than the nominal time taken during normal operation. The higher values ​​of both the first time period 42 and the second time period 44 compared to the nominal normal operating condition may indicate a greater amount of friction during the movement of shaft 26 and / or the movement of valve 16 body 22.

[0068] If the first time period 42 is below the corresponding threshold and the second time period 44 is above the corresponding threshold, valve 16 may include an operating condition where the time spent opening and / or closing valve 16 is longer than the nominal time spent during normal operation. The relatively high value of the second time period 44 and the relatively low value of the first time period 42 compared to the nominal normal operating condition can indicate a greater amount of static friction in shaft 26 and motor 28 or valve 16. This can be considered as time period T0 to T1, i.e., the time period from when the controller issues a command to when valve 16 moves away from the closed or open position, which is longer than the nominal corresponding time period for normal operation.

[0069] If the first time period 42 is above the corresponding threshold and the second time period 44 is below the corresponding threshold, this can indicate that the closed feedback signal 38 or the open feedback signal 40 changes state, while the state of the command signal 36 remains unchanged. For example, this could occur if the protrusion 30 of the shaft 36 moves out of contact with the corresponding microswitch 32, 34 without a command signal, if one of the microswitches 32, 34 experiences an abnormal operating condition, or if there is an unintentional alteration in the electrical connection or wiring.

[0070] In some examples, the threshold for each of the first time period 42 and the second time period 44 can be the same value.

[0071] While in some examples, a first time period 42 and a second time period 44 from a single flight can be used to determine abnormal operating conditions associated with the actuation of valve 16, in other examples, a first time period 42 and a second time period 44 from multiple flights can be used, similar to the examples discussed above, where the first time period 42 is used instead of the second time period 44.

[0072] Specifically, appropriate first time period 42 and second time period 44 for a given flight are stored in the memory of the aircraft 300, or transferred to a remote memory location and stored there. Each stored value of the first time period 42 and second time period 44 is compared with a threshold indicating the normal operating condition of the valve 16. The threshold can be selected to be lower than a value that would cause a warning of abnormal operating condition during flight to be provided. When a predetermined number of first time periods 42 and second time periods 44 have the above-described relationship with respect to the threshold within a predetermined time window (i.e., first time period 42 is high and second time period 44 is high, second time period 44 is high and first time period 42 is low, or first time period 42 is high and second time period 44 is low), an indication of the modified operating condition associated with the actuation of the valve 16 is provided.

[0073] exist Figure 5 The diagram shows an example of a stored first time period 42 and a second time period 44, where the first time period 42 and the second time period 44 appear in pairs, where the higher value in a pair is the second time period 44 and the lower value in the pair is the first time period 42.

[0074] As above Figure 4 Related examples, about Figure 5 The example indication can take various forms. For instance, where controller 18 stores the first time period 42 and the second time period 44 in the local memory of aircraft 300, when a relationship causing the aforementioned criteria to be met is determined, indicator 20 can provide the crew of aircraft 300 with a visual indication, in the form of a lighting or on-screen message, that a modified operating condition associated with the actuation of valve 16 has been determined. In such a case, the crew of aircraft 300 can log the indication in the log and / or mark the indication to ground maintenance personnel, so that valve 16 and / or valve actuator 17 can be inspected and replaced as needed.

[0075] In some examples, the comparison step may be performed by controller 18, wherein an indication of the altered operating condition associated with the actuation of valve 16 is transmitted from controller 18 to method indicator 20 for display by indicator 20. For example, the comparison and / or calculation step may be performed by controller 18, wherein remote indicator 20 is used to display the indication to ground maintenance personnel. Indications in such examples may include lighting or on-screen messages, or such as... Figure 5 The visual representation of the image.

[0076] In some examples, where controller 18 transmits a first time period 42 and a second time period 44 for storage in remote memory and indicator 20 is positioned remotely from aircraft 300, comparison and / or calculation steps can be performed remotely from aircraft 300 based on data transmitted by controller 18, wherein indicator 20 transmits an indication of a modified operating condition associated with the actuation of valve 16 to ground maintenance personnel. Indications in such examples may include lighting or on-screen messages, or other similar... Figure 5 The visual representation of the image.

[0077] In the previously described example, the aircraft fuel system 10 has a valve 16 actuated by a single motor 28. In other examples, the valves of the aircraft fuel system may be actuated by more than one motor. Figure 6 Such an example is schematically shown, where the same reference numerals are used for clarity. Here, as previously described, the aircraft fuel system 200 includes a fuel storage tank 12, a conduit 14, a valve 16, a controller 18, and an indicator 20.

[0078] The aircraft fuel system 200 also includes a valve actuator 202, which is connected to... Figure 1 The valve actuator 17 in the example differs in that the valve actuator 202 includes a shaft 204, a first motor 206, a second motor 208, and a transmission 210. The shaft 204 is connected to the body 22 of the valve 16 via a valve drive spindle 27, and the first motor 206 and the second motor 208 are operable in response to commands issued by the controller 18 to rotate the shaft 204 via the transmission 210, thereby rotating the valve drive spindle 27 in a first position and a second position (i.e., as described above regarding...). Figure 1 The body 22 is moved between the closed and open positions discussed in the example. The first motor 206 and the second motor 208 can be considered as the first and second actuators of the valve 16, respectively. A shaft 204 is provided with a protrusion 212, and a first microswitch 214 and a second microswitch 216 are located near the shaft 204. The protrusion 212 contacts the first microswitch 214 when the body 22 of the valve 16 is in the first closed position, causing the first microswitch 214 to close when the body 22 of the valve 16 is in the closed position, and the protrusion 212 contacts the second microswitch 216 when the body 22 of the valve 16 is in the second open position, causing the second microswitch 216 to close when the body 22 of the valve 16 is in the open position.

[0079] Therefore, it should be understood that regarding Figure 1 The examples discussed regarding the first time period 42 and the second time period 44 can also be related to Figure 6 The fuel system 200 of the aircraft is obtained by actuation of valve 16.

[0080] It has been found that by monitoring the first time period 42 or the first time period 42 and the second time period 44 during multiple flights as previously described, altered operating conditions associated with the actuation of valve 16 can be determined, wherein the altered operating conditions are caused by altered operating conditions of at least one of the first motor 206 and the second motor 208. For example, if the first motor 206 experiences a greater load torque than under nominal operating conditions, opening and / or closing valve 16 may require a longer time, thus causing the first time period 42 and the second time period 44 to be longer. It should be understood that both the first time period 42 and the second time period 44 can also be envisioned for identifying and / or distinguishing from... Figure 6 An example of a modified operating condition associated with the actuation of valve 16 in the aircraft fuel system 200, similar to the above example regarding... Figure 1 Example of an aircraft fuel system discussed in section 10.

[0081] In the above example, it should be understood that the time period associated with the actuation of valve 16 can be used to determine the altered operating conditions associated with the actuation of valve 16.

[0082] exist Figure 7 The diagram schematically shows including Figure 1 The aircraft fuel system 12 or Figure 6 The aircraft fuel system of the 200 aircraft 300.

[0083] Data carrier 400 in Figure 8 The diagram is schematically shown and includes machine-readable instructions 402, which cause... Figure 1 The aircraft fuel system 10 or Figure 6 The processor of the aircraft fuel system 200 operates to obtain a time period associated with the actuation of valve 16, and provides an indication of the modified operating condition associated with the actuation of valve 16 based on the obtained time period.

[0084] Although this article describes aircraft fuel systems, it should be understood that the teachings can be applied more generally to any aircraft system that uses valves, including, for example, aircraft environmental control systems.

[0085] It should be noted that, unless otherwise expressly stated, the term “or” as used herein shall be interpreted as meaning “and / or”.

Claims

1. A method for determining the operating status of valves in an aircraft system, wherein, The valve is actuable between a first position and a second position, and the method includes: Obtain a first time period and a second time period, the first time period indicating the time taken for the valve to be actuated from the first position to the second position or from the second position to the first position during a first flight using the aircraft system, and the second time period indicating the time taken for the valve to be actuated from the first position to the second position or from the second position to the first position during a second flight using the aircraft system, the second flight being different from the first flight; and Indications of altered operating conditions associated with valve actuation are provided based on the first and second time periods.

2. The method according to claim 1, wherein, The method includes: comparing each of the first time period and the second time period with a threshold, and, if each of the first time period and the second time period exceeds the threshold, providing an indication of a modified operating condition associated with the actuation of the valve.

3. The method according to claim 1, wherein, The method includes providing an indication of a modified operating condition associated with the actuation of the valve, provided that the first flight and the second flight occur within a predetermined time window.

4. The method according to claim 1 or 3, wherein, The valve is actuated multiple times during the first flight, the method comprising: obtaining a first plurality of time periods, each corresponding to a corresponding actuation of the valve during the first flight, and selecting a first time period from the first plurality of time periods based on the length of each of the first plurality of time periods, wherein the valve is actuated multiple times during the second flight, the method comprising: obtaining a second plurality of time periods, each corresponding to a corresponding actuation of the valve during the second flight, and selecting a second time period from the second plurality of time periods based on the length of each of the second plurality of time periods.

5. The method according to claim 4, wherein, The step of selecting the first time period from the first plurality of time periods includes: selecting the first time period having the maximum value for the first flight; and The step of selecting the second time period from the second plurality of time periods includes: selecting the second time period that has the maximum value for the second flight.

6. The method according to any one of claims 1 to 3, wherein, The method includes: obtaining at least four distinct time periods, including the first time period and the second time period, the at least four distinct time periods indicating the time taken for the valve to be actuated from the first position to the second position or from the second position to the first position, each time period being associated with actuating the valve during different corresponding flight periods in multiple flights; comparing each time period with a corresponding threshold; and providing an indication of a modified operating condition associated with the actuation of the valve if each time period exceeds the corresponding threshold and the multiple flights occur within a predetermined time window.

7. The method according to claim 1, wherein, The valve is capable of moving from the first position to the second position in response to a command, and the method further includes: The command-to-feedback time period is the time taken from issuing or receiving the command to the valve reaching the second position, and the command-to-feedback time period and the first time period are associated with the same movement of the valve. Perform a comparison between the first time period and the parameters; Another comparison between the time interval from executing the command to receiving feedback and another parameter; and The comparison and the other comparison are also used to provide an indication of the modified operating conditions associated with the actuation of the valve.

8. The method according to claim 7, wherein, The parameter includes the nominal time taken for the valve to move from the first position to the second position, and the other parameter includes the nominal time taken from issuing or receiving the command to the valve reaching the second position.

9. The method according to claim 7 or 8, wherein, The method includes: If the first time period exceeds the parameter and the command-to-feedback time period exceeds the other parameter, an indication of a first altered operating condition associated with the actuation of the valve is provided; If the first time period exceeds the parameter and the command-to-feedback time period does not exceed the other parameter, an indication of a second modified operating condition associated with the actuation of the valve is provided, the second modified operating condition being different from the first modified operating condition associated with the actuation of the valve; and If the first time period does not exceed the parameter and the command-to-feedback time period exceeds the other parameter, an indication of a third modified operating condition associated with the actuation of the valve is provided, the third modified operating condition being different from the first modified operating condition and the second modified operating condition of the valve.

10. The method according to claim 7, wherein, The parameter is the time interval from the command to the feedback.

11. The method according to any one of claims 1 to 3, wherein, The aircraft system includes an aircraft fuel supply system.

12. An aircraft fuel system, comprising: A fuel storage tank; a conduit in fluid communication with the fuel storage tank; a valve located within the conduit for selectively allowing fuel to be delivered to and / or from the fuel storage tank; a controller; and an indicator configured to: monitor a plurality of time periods indicating the time taken for the valve to be actuated between an open and closed position or between a closed and open position, each of the plurality of time periods being acquired during different flights of the aircraft including the aircraft fuel system; and to compare each of the plurality of time periods with a corresponding parameter, and the indicator being configured to provide an indication of the valve's operation under modified operating conditions relative to the valve's normal operating conditions based on the comparison.

13. The aircraft fuel system according to claim 12, wherein, The indicator is located away from the aircraft.

14. An aircraft comprising an aircraft fuel system according to claim 12 or 13.

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