Aircraft onboard maintenance systems and methods for aircraft onboard maintenance

Abstract

The present application relates to an onboard maintenance system for an aircraft and a method for onboard maintenance of an aircraft. In one example, a method for onboard maintenance of an aircraft is described. The method includes measuring a pressure in a pipe associated with an engine of the aircraft by a pressure sensor. The method also includes determining, by a control system and based on the pressure measured by the pressure sensor, that the pipe is at least partially blocked by moisture. In addition, the method includes: in response to determining that the pipe is at least partially blocked by moisture, providing an alarm signal from the control system to a cockpit of the aircraft. The method also includes, in response to the alarm signal, manipulating an actuating switch at the cockpit to actuate a valve to an open state. The method further includes, in response to actuating the valve to an open state, supplying an inert gas from an inert gas supply to the pipe to expel moisture.

Description

Technical Field

[0001] The present disclosure relates generally to maintenance systems and methods for aircraft, and more particularly to systems and methods for mitigating moisture accumulation in aircraft. Background Art

[0002] Prior to takeoff, the aircraft may be evaluated to determine if any maintenance should be performed. In some cases, a condition may be identified and maintenance personnel may perform maintenance, repair, and / or overhaul operations to improve the condition of the aircraft. Typically, such maintenance, repair, and / or overhaul operations may be time consuming, which may result in delayed departure times and / or undesirably long downtime. Summary of the invention

[0003] In one example, an aircraft onboard maintenance system is described. The aircraft onboard maintenance system includes a pressure sensor configured to measure a pressure in a tube associated with an engine of the aircraft and to generate a sensor signal indicative of the pressure measured by the pressure sensor. The aircraft onboard maintenance system also includes a valve including an inlet coupled to an inert gas supply on the aircraft and an outlet coupled to a conduit extending to the tube, wherein the valve is actuatable in: (i) an open state, wherein the valve supplies inert gas from the inert gas supply to the tube through the conduit, and (ii) a closed state, wherein the valve inhibits the supply of inert gas.

[0004] The aircraft onboard maintenance system also includes a control system in communication with the pressure sensor and configured to receive the sensor signal. The control system is configured to: (i) determine, based on the sensor signal, that the tube is at least partially blocked by moisture, and (ii) provide, in response to determining that the tube is at least partially blocked by moisture, an alarm signal to be sent to a cockpit of the aircraft. The aircraft onboard maintenance system also includes an actuation switch at the cockpit, the actuation switch being operable to actuate the valve to an open state to supply an inert gas to the conduit and drain moisture from the tube.

[0005] In another example, a method for onboard maintenance of an aircraft is described. The method includes measuring a pressure in a tube associated with an engine of the aircraft by a pressure sensor. The method also includes determining, by a control system and based on the pressure measured by the pressure sensor, that the tube is at least partially blocked by moisture. In addition, the method includes: in response to determining that the tube is at least partially blocked by moisture, providing an alarm signal from the control system to a cockpit of the aircraft. The method further includes, in response to the alarm signal, operating an actuation switch at the cockpit to actuate a valve to an open state. The method also includes, in response to actuating the valve to an open state, supplying an inert gas from an inert gas supply to the tube via the valve and the conduit to expel moisture from the tube.

[0006] In another example, an aircraft onboard maintenance system is described. The aircraft onboard maintenance system includes a pressure sensor configured to measure a pressure in a tube associated with an engine of the aircraft and to generate a sensor signal indicative of the pressure measured by the pressure sensor. The aircraft onboard maintenance system also includes a valve including an inlet coupled to an onboard inert gas supply of the aircraft and an outlet coupled to a conduit extending to the tube. The valve is actuable in: (i) an open state, wherein the valve provides an inert gas from the inert gas supply to the tube through the conduit, and (ii) a closed state, wherein the valve inhibits the supply of the inert gas.

[0007] The aircraft onboard maintenance system also includes a moisture sensor configured to detect moisture in the tube and generate a moisture sensor signal indicating the presence of moisture in the tube. In addition, the aircraft onboard maintenance system includes a control system in communication with the moisture sensor and configured to receive the moisture sensor signal. The control system is configured to: (i) determine that the tube is at least partially blocked by moisture based on the moisture sensor signal, and (ii) in response to determining that the tube is at least partially blocked by moisture, issue an alarm signal to a cockpit of the aircraft. The aircraft onboard maintenance system also includes an actuation switch at the cockpit, the actuation switch being operable to actuate the valve to an open state to supply an inert gas to the conduit and drain moisture from the tube.

[0008] The features, functions, and advantages that have been discussed can be achieved independently in various embodiments or may be combined in yet other embodiments, further details of which may be seen with reference to the following description and drawings. BRIEF DESCRIPTION OF THE DRAWINGS

[0009] The novel features believed to be characteristic of the illustrative embodiments are set forth in the accompanying technical solutions. However, the illustrative embodiments and their preferred modes of use, further objects and description thereof will be best understood by reference to the following detailed description of illustrative embodiments of the present disclosure when read in conjunction with the accompanying drawings, wherein:

[0010] Figure 1 A simplified block diagram of an aircraft onboard maintenance system is shown in accordance with an example embodiment.

[0011] Figure 2 A simplified block diagram of an aircraft onboard maintenance system is shown in accordance with an example embodiment.

[0012] Figure 3 Depicted is a perspective view of tubes associated with an engine of an aircraft in accordance with an illustrative embodiment.

[0013] Figure 4 Describes an exemplary embodiment Figure 3 A partial cross-sectional view of the engine shown in FIG.

[0014] Figure 5A flow chart illustrating an example process for onboard maintenance of an aircraft in accordance with an example embodiment.

[0015] Figure 6 Show that it can be Figure 5 The process shown is used in conjunction with a flow chart of an example process for onboard maintenance of an aircraft.

[0016] Figure 7 Show that it can be Figure 5 The process shown is used in conjunction with a flow chart of an example process for onboard maintenance of an aircraft.

[0017] Figure 8 Show that it can be Figure 7 The process shown is used in conjunction with a flow chart of an example process for onboard maintenance of an aircraft.

[0018] Fig. 9 Show that it can be Figure 5 The process shown is used in conjunction with a flow chart of an example process for in-flight maintenance of an aircraft.

[0019] Fig.10 Show that it can be Figure 5 The process shown is used in conjunction with a flow chart of an example process for in-flight maintenance of an aircraft. DETAILED DESCRIPTION

[0020] The disclosed embodiments will now be described more fully hereinafter with reference to the accompanying drawings, in which some, but not all, disclosed embodiments are shown. Indeed, several different embodiments may be described, and they should not be construed as limited to the embodiments set forth herein. Rather, these embodiments are described so that this disclosure will be thorough and complete, and will fully convey the scope of the disclosure to those skilled in the art.

[0021] As described above, the maintenance operations performed by maintenance personnel may be time-consuming and cause flight delays and / or excessive downtime. In some cases, moisture may accumulate in the tubes associated with the aircraft engine. The accumulated moisture may at least partially block the tubes, and maintenance personnel may perform maintenance operations to clear the obstruction from the tubes before takeoff. Typically, the maintenance operation to clear the obstruction in the pipe may involve: (i) driving an aviation truck to the aircraft, (ii) disconnecting one or more pipes on the aircraft, (iii) reconnecting the pipes to the aviation truck, (iv) delivering air from the aviation truck to the pipes to clear the obstruction, (v) disconnecting the pipes from the aviation truck, and (vi) reconnecting the pipes to the aircraft. This process may be particularly time-consuming. In addition, in the case of an obstruction found during taxiing, the aircraft usually has to return to the gate to resolve the obstruction. This further exacerbates the time required to clear the obstruction.

[0022] The example systems and methods described herein can beneficially address at least some of the shortcomings of existing aircraft maintenance systems and processes. In an example, an aircraft onboard maintenance system is described. The aircraft onboard maintenance system can determine when a blockage occurs in a pipe and responsively clear the blockage by providing an inert gas to the pipe from an inert gas supply. The aircraft onboard maintenance system can include a valve that can be manually and / or automatically operated to supply an inert gas to the pipe in response to determining that the pipe is at least partially blocked. Thus, the aircraft onboard maintenance system can clear blockages in the pipe more quickly and more efficiently than existing systems and processes.

[0023] Reference now Figure 1 , a simplified block diagram of an aircraft onboard maintenance system 100 is shown in accordance with an example embodiment. Figure 1 In the embodiment of the present invention, the aircraft onboard maintenance system 100 may be onboard an aircraft 110. In an example, the aircraft 110 may be an airplane, a helicopter, and / or an unmanned aerial vehicle (UAV). More generally, the aircraft 110 may be any aircraft including an engine 112 that may provide propulsion for the aircraft. The engine 112 may be, for example, a piston engine, a gas turbine engine (e.g., a turboprop engine, a turboshaft engine, and / or a jet engine), and / or a reaction engine (e.g., a turbojet engine, a turbojet engine, and / or a pulsejet engine).

[0024] like Figure 1 As shown, the aircraft onboard maintenance system 100 includes a pressure sensor 114 that can measure pressure in a tube 116 associated with an engine 112 of the aircraft 110 and generate a sensor signal indicative of the pressure measured by the pressure sensor 114. In one example, the tube 116 can be arranged to receive air into the tube 116 at the inlet of the engine 112 to facilitate the pressure sensor 114 to measure the engine inlet pressure (e.g., the tube 116 and the pressure sensor 114 can be arranged as a P20 probe).

[0025] In some cases, moisture can accumulate in tube 116 before, during, or after flight of aircraft 110. As an example, moisture can accumulate when aircraft 110 is flying in clouds and / or due to condensation when aircraft 110 is on the ground. Depending on the ambient temperature, the accumulated moisture can remain in liquid or freeze into ice structures within tube 116. In either case, the accumulated moisture can form at least a partial blockage in tube 116. Thus, in some cases, blockage of tube 116 by accumulated moisture can affect the pressure measured by pressure sensor 114.

[0026] like Figure 1 As shown, the aircraft onboard maintenance system 100 may also include an inert gas supply 118 on the aircraft 110. The inert gas supply 118 may contain an inert gas, such as nitrogen. Figure 1In the example, valve 120 may include an inlet 122 coupled to an inert gas supply 118 on aircraft 110 and an outlet 124 coupled to a conduit 126 extending to tube 116 associated with engine 112. In an example, valve 120 is actuatable between: (i) an open state, in which valve 120 supplies inert gas from inert gas supply 118 to tube 116 via conduit 126, and (ii) a closed state, in which valve 120 prohibits the supply of inert gas from inert gas supply 118 to conduit 126. Further, in an example, valve 120 may be a one-way valve such that, in the open state, valve 120 is closed along the inert gas supply 118. Figure 1 Inert gas is supplied in the direction indicated by arrow 127 (ie, from the inert gas supply 118 toward the tube 116 ), and gas and / or fluid flow in the opposite direction (ie, from the tube 116 toward the inert gas supply 118 ) is prevented.

[0027] In this arrangement, inert gas supply 118 can supply inert gas to tube 116 via valve 120 and conduit 126 to remove moisture from tube 116. In one embodiment, inert gas supply 118 is configured to supply inert gas along conduit 126 at a pressure of at least about 40 pounds per square inch (PSI).

[0028] like Figure 1 As shown, the aircraft onboard maintenance system 100 may also include a control system 130 in communication with the pressure sensor 114. As such, the control system 130 may receive a sensor signal indicative of the pressure measured by the pressure sensor 114.

[0029] In an example, the control system 130 may determine that the tube is at least partially blocked by moisture based on the sensor signal. For example, in one embodiment, to determine that the tube is at least partially blocked by moisture, the control system 130 may compare the pressure measured by the pressure sensor 114 with a threshold range, and based on the comparison, determine that the pressure measured by the pressure sensor 114 is outside the threshold range. The threshold range may be related to the pressure range expected during normal operation of the aircraft 110. As an example, the threshold may be based on the size of the tube 116 and / or the state of the aircraft (e.g., a power-on state, a pre-flight state, an engine start state, an in-door state, a taxiing state, a takeoff state, a climb state, a cruise state, a descending state, an approach state, a pushback state, a taxiing state, a go-around state, an engine shutdown state, and / or a maintenance state). Then, in response to determining that the pressure measured by the pressure sensor 114 is outside the threshold range, the control system 130 may determine that the tube 116 is at least partially blocked by moisture.

[0030] In addition, in response to determining that the tube 116 is at least partially blocked by moisture, the control system 130 may provide an alert signal to a cockpit 132 of the aircraft 110. The cockpit 132 may include a plurality of input devices 134 and output devices 136 for operating the aircraft 110. For example, the input devices 134 may include one or more buttons, joysticks, levers, switches, yokes, and / or pedals for operating the aircraft 110. In addition, for example, the output devices 136 may include one or more displays, instruments, commands, indicator lights, and / or speakers to provide information and / or generate notifications to the pilots in the cockpit 132.

[0031] like Figure 1 As shown, the aircraft onboard maintenance system 100 may include an actuation switch 138 at the cockpit 132, which is operable to actuate the valve 120 to an open state to supply inert gas to the conduit 126 and drain moisture in the tube 116. In one example, the output device 136 may include an output device 140 at the cockpit 132, which may communicate with the control system 130. The output device 140 may generate a notification at the cockpit 132 in response to an alarm signal from the control system 130. In an example, the notification may include at least one of an audible notification, a visual notification, and a tactile notification indicating that the tube 116 is at least partially blocked. The input device 134 may include an actuation input device 142 operable to actuate the actuation switch 138. In this arrangement, in response to the output device 140 generating the notification, the actuation input device 142 may be operated to actuate the actuation switch 138, which in turn actuates the valve 120 from the closed state to the open state. Thus, in this example, the actuation switch 138 may be manually operated in response to a notification generated by the output device 140 .

[0032] In one embodiment, aircraft onboard maintenance system 100 may be configured to inhibit actuation of valve 120 to an open state without control system 130 detecting that tube 116 is at least partially blocked. Figure 1 In the embodiment of the present invention, the aircraft onboard maintenance system 100 may include a lock switch 144 in communication with the control system 130 and the actuation switch 138. The lock switch 144 may be configured to (i) disable the actuation switch 138 before the cockpit 132 receives an alarm signal from the control system 130, and (ii) actuate the actuation switch 138 in response to the cockpit 132 receiving the alarm signal from the control system 130. The lock switch 144 may advantageously help mitigate accidental actuation of the valve 120 and the supply of inert gas from the inert gas supply 118 to the tube 116.

[0033] In another example, the aircraft onboard maintenance system 100 may additionally or alternatively provide for automatic actuation of the valve 120 in response to the control system 130 detecting at least a partial obstruction of the tube 116. For example, the aircraft onboard maintenance system 100 may include a processor 146 at the cockpit 132 that is configured to automatically operate the actuation switch 138 in response to an alarm signal received from the control system 130. This may advantageously provide for clearing the obstruction in the tube 116 more quickly and / or reducing the workload of the pilots of the aircraft 110.

[0034] Additionally, in an example, the aircraft onboard maintenance system 100 may determine when the obstruction is cleared from the tube 116. In an example, the pressure sensor 114 may measure a second pressure in the tube 116 and generate a second sensor signal indicative of the second pressure measured by the pressure sensor 114. Additionally, the control system 130 may (i) perform a second comparison of the second pressure indicated by the second sensor signal with a threshold range, (ii) determine, based on the second comparison, that the second pressure indicated by the second sensor signal is within the threshold range, and (iii) determine that there is no moisture in the tube 116 in response to determining that the second pressure is within the threshold range.

[0035] In one example, in response to the control system 130 determining that the tube 116 has been cleared of moisture, the control system 130 may provide a clear obstruction signal to the cockpit 132, and in response to the clear obstruction signal, the valve 120 may be actuated from an open state to a closed state. In this way, the aircraft onboard maintenance system 100 may be configured to stop supplying inert gas from the inert gas supply 118 to the tube 116 when the obstruction is cleared. This may help conserve and more efficiently use the inert gas within the inert gas supply.

[0036] In one embodiment, in response to the clear obstruction signal, the processor 146 at the cockpit 132 may actuate the valve 120 to a closed state in response to the clear obstruction signal. In one embodiment, in response to the clear obstruction signal, the output device 140 may generate a second notification to indicate that moisture has been cleared from the tube 116. For example, the second notification may include at least one of an audible notification, a visual notification, and a tactile notification indicating that the tube 116 has been cleared of obstruction. In embodiments where the actuation switch 138 is manually operable, the second notification may indicate that the pilot may stop the operation of the actuation switch 138.

[0037] As described above, the control system 130 can control the operation of the aircraft onboard maintenance system 100. In an example, the control system 130 can be implemented using hardware, software, and / or firmware. For example, the control system 130 may include one or more processors and a non-volatile computer-readable medium (e.g., volatile and / or non-volatile memory) storing machine language instructions or other executable instructions. When executed by the one or more processors, the instructions cause the aircraft onboard maintenance system 100 to perform the various operations described herein. Thus, the control system 130 can receive data and also store the data in memory.

[0038] Likewise, in the example, Figure 1 As shown, control system 130 may additionally perform other operations of aircraft 110. For example, Figure 1 As shown, control system 130 may include an electronic engine controller (EEC) 148 that communicates with an aircraft control system 150 .

[0039] In an example, the EEC 148 may be a full authority digital engine control (FADEC), or the EEC 148 may provide a manual override for certain operations. In general, the EEC 148 may be operable to perform engine performance control and monitoring operations. For example, the EEC 148 may receive inputs from a plurality of sensors (including the pressure sensor 114) of the aircraft 110 that may detect conditions related to the operation and performance of the engine 112. As examples, the sensors may detect and the EEC 148 may receive parameters related to air density, throttle lever position, ambient temperature, air speed and altitude, exhaust temperature, oil temperature, high pressure turbine shroud temperature, engine fuel flow, core speed, engine inlet pressure (P0) and engine inlet temperature (T12) measured at the engine inlet at the fan, compressor exhaust temperature (T3) and compressor exhaust pressure (P3) measured downstream of the engine high pressure compressor, turbine exhaust pressure, fan speed, and / or other engine parameters. Based on input from the sensors, the EEC 148 may generate command signals to operate one or more engine actuators, such as a hydraulic-mechanical unit (not shown) that meters fuel flow to the engine 112 .

[0040] The aircraft control system 150 may perform aircraft and flight control operations. For example, the aircraft control system 150 may perform operations related to a flight data network, an electronic flight bag, a mode control panel on the cockpit 132 of the aircraft 110, a primary flight display at the cockpit 132, a navigation display at the cockpit 132, a flight management system, and / or flight controls. Also, as described in further detail below, the aircraft control system 150 may receive information from the EEC 148 and provide alerts to the cockpit 132 (e.g., information and / or alerts related to conditions detected by sensors in communication with the EEC 148).

[0041] In one embodiment, the EEC 148 may (i) receive an indication of the pressure measured by the pressure sensor 114, (ii) determine that the tube 116 is at least partially blocked by moisture based on the pressure measured by the pressure sensor 114, and (iii) generate an obstruction detection signal in response to determining that the tube 116 is at least partially blocked by moisture. The aircraft control system 150 may receive the signal that an obstacle is detected from the EEC 148 and provide an alert signal to the cockpit 132 in response to the signal that an obstacle is detected.

[0042] The EEC 148 and / or the aircraft control system 150 may be implemented using hardware, software, and / or firmware. For example, the EEC 148 and / or the aircraft control system 150 may include one or more processors and a non-volatile computer-readable medium (e.g., volatile and / or non-volatile memory) storing machine language instructions or other executable instructions. When executed by the one or more processors, the instructions cause the EEC 148 and / or the aircraft control system 150 to perform the various operations described herein. Thus, the EEC 148 and / or the aircraft control system 150 may receive data and also store the data in memory.

[0043] Likewise, in an example, the aircraft onboard maintenance system 100 may include a fitting 152 that couples the first portion 116A of the tube 116, the second portion 116B of the tube 116, and the conduit 126. The pressure sensor 114 may measure the pressure in the first portion 116A of the tube 116. The fitting 152 may direct the inert gas from the conduit 126 to the first portion 116A of the tube 116. For example, the fitting 152 may be a T-shaped fitting. In this arrangement, the fitting 152 may help direct the inert gas to the moisture accumulated in the first portion 116A of the tube 116, where the pressure sensor 114 measures the pressure.

[0044] Reference now Figure 2 , an aircraft onboard maintenance system 200 is shown according to another example embodiment. Figure 2 The aircraft onboard maintenance system 200 is substantially similar to Figure 1 The aircraft onboard maintenance system 100 is shown. For example, the aircraft onboard maintenance system 200 includes the pressure sensor 114, valve 120, control system 130, and actuation switch 138 onboard the aircraft 110 as described above. In addition, for example, as described above, the aircraft onboard maintenance system 200 may include one or more input devices 134 and / or output devices 136 at the cockpit 132, the lock switch 144, the processor 146, the EEC 148, the aircraft control system 150, and / or the accessories 152.

[0045] Pressure sensor 114 may measure pressure in tube 116 associated with engine 112 of aircraft 110 and generate a sensor signal indicative of the pressure measured by pressure sensor 114. Valve 120 includes an inlet 122 coupled to an inert gas supply 118 on the aircraft and an outlet 124 coupled to a conduit 126 extending to tube 116. In addition, valve 120 is actuable between: (i) an open state, in which valve 120 supplies inert gas from inert gas supply 118 to tube 116 through conduit 126, and (ii) a closed state, in which valve 120 prohibits the supply of inert gas.

[0046] like Figure 2 As shown, the aircraft onboard maintenance system 200 also includes a moisture sensor 254, which can detect moisture in the tube 116 and generate a moisture sensor signal indicating the presence of moisture in the tube 116. The control system 130 is in communication with the moisture sensor 254 and is configured to receive the moisture sensor signal. The control system 130 can determine that the tube 116 is at least partially blocked by moisture based on the moisture sensor signal. In one example, the moisture sensor 254 can generate the moisture sensor signal in response to the moisture sensor 254 detecting at least a threshold amount of moisture in the tube 116. As an example, the moisture sensor 254 can include an optical moisture sensor (e.g., a laser-based sensor).

[0047] The control system 130 may also provide an alarm signal to a cockpit 132 of the aircraft 110 in response to determining that the tube 116 is at least partially blocked by moisture. An actuation switch 138 at the cockpit 132 may be operable to actuate the valve 120 to an open state to supply inert gas to the conduit 126 and drain moisture from the tube 116. In an example, as described above, the actuation switch 138 may be manually and / or automatically operated to an open state. For example, the processor 146 at the cockpit 132 may automatically operate the actuation switch 138 in response to an alarm signal received from the control system 130.

[0048] Additionally or alternatively, for example, the output device 140 may provide a notification at the cockpit 132 in response to an alarm signal from the control system 130. In an example, the notification may include at least one of an audible notification, a visual notification, and a tactile notification indicating that the tube 116 is at least partially blocked. The input device 134 may include an actuation input device 142 operable to actuate the actuation switch 138. In this arrangement, in response to the output device 140 generating the notification, the actuation input device 142 may be operated to the actuation switch 138, which in turn actuates the valve 120 from a closed state to an open state. Thus, in this example, the actuation switch 138 may be manually operated in response to the notification generated by the output device 140.

[0049] Additionally, in an example, moisture sensor 254 may detect when moisture is purged from tube 116 and provide a moisture purge signal to cockpit 132 indicating that moisture is not present in tube 116. In response to cockpit 132 receiving the moisture purge signal, output device 140 may provide a second notification indicating that moisture has been drained from tube 116.

[0050] Reference now Figure 3-4 , shows example locations of tube 116 and catheter 126 according to an example embodiment. In particular, Figure 3 depicts a perspective view of an engine 312 of an aircraft 310 according to an example embodiment, and Figure 4 A partial cross-sectional view of engine 312 is depicted in accordance with an example embodiment. Figure 3 As shown, at least a portion of the tube 116 may extend from a cowling 356 of the engine 312 at the engine inlet 358. Figure 4 As shown, the duct 126 may extend from the wing 360 of the aircraft 310 along the pylon 362 and along the engine 312 to the Figure 3 Tube 116 is shown in the position.

[0051] Referring now to Figure 500, a flow chart of a process 500 for onboard maintenance is shown in accordance with an exemplary embodiment. Figure 5 As shown, at box 510, process 500 includes measuring the pressure in a tube associated with an engine of an aircraft by a pressure sensor. At box 512, process 500 includes determining, by a control system and based on the pressure measured by the pressure sensor, that the tube is at least partially blocked by moisture. In response to determining at box 512 that the tube is at least partially blocked by moisture, process 500 includes providing an alarm signal from the control system to the cockpit of the aircraft at box 514. In response to the alarm signal at box 514, process 500 includes operating an actuation switch at the cockpit at box 516 to actuate the valve to an open state. In response to actuating the valve to an open state at box 516, process 500 includes supplying an inert gas to the tube from an inert gas supply via a valve and a conduit to expel moisture from the tube at box 518.

[0052] Figure 6-10 Other aspects of process 500 are described according to other examples. Figure 6 As shown, the process 500 may also include: before providing an alarm signal from the control system to the cockpit at box 514, disabling the operation of the actuation switch that actuates the valve to the open state to lock the valve in the closed state at box 520. Figure 6 In the process 500 , after providing the warning signal from the control system to the cockpit at block 514 , enabling operation of the actuation switch to allow actuation of the valve from the closed state to the open state at block 522 .

[0053] like Figure 7 As shown, determining at box 512 that the tube is at least partially blocked by moisture may include: (i) comparing the pressure measured by the pressure sensor with a threshold range at box 524, (ii) determining at box 526 that the pressure measured by the pressure sensor is outside the threshold range based on the comparison result, and (iii) in response to determining at box 526 that the pressure measured by the pressure sensor is outside the threshold range, determining at box 528 that the tube is at least partially blocked by moisture.

[0054] like Figure 8 As shown, at block 518, after supplying the inert gas from the inert gas supply to the tube, process 500 may include a number of operations. Figure 8 In the process 500, the process 500 may include measuring a second pressure in the tube by the pressure sensor at box 530. At box 532, the process 500 may include generating a second sensor signal indicating the second pressure measured by the pressure sensor. At box 534, the process 500 may include performing, by the control system, a second comparison of the second pressure indicated by the second sensor signal with a threshold range. At box 536, the process may include determining, based on the second comparison, that the second pressure indicated by the second sensor signal is within the threshold range. In response to determining, at box 536, that the second pressure indicated by the second sensor signal is within the threshold range, the process 500 may include determining, at box 538, that there is no moisture in the tube.

[0055] like Fig. 9 As shown, process 500 may also include receiving an alarm signal at the cockpit at block 540. In response to receiving the alarm signal at the cockpit at block 540, process 500 may include generating a notification at the cockpit via an output device at block 542. The notification may include at least one of an audible notification, a visual notification, and a tactile notification. Furthermore, Fig. 9 , operating the actuation switch at block 516 may include manually operating the actuation switch at block 544 in response to a notification generated by the output device at block 542 .

[0056] like Fig.10 As shown, process 500 may include detecting the presence of moisture in the tube by a moisture sensor at block 546. Fig.10 In block 512 , determining that the tube is at least partially blocked by moisture may include determining, at block 548 , that the tube is at least partially blocked by moisture based on a pressure measured by a pressure sensor and a presence of moisture detected by a moisture sensor.

[0057] Figure 6-Figure 10One or more boxes shown in can represent a module, segment or part of a program code, including one or more instructions, which can be executed by a processor for implementing a specific logical function or step in a process. The program code can be stored on any type of computer-readable medium or data storage, for example, a storage device including a disk or hard drive. In addition, the program code can be encoded on a computer-readable storage medium or on other non-transitory media or products in a machine-readable format. The computer-readable medium may include a non-transitory computer-readable medium or memory, for example, a computer-readable medium that can store data in a short time, such as a register memory, a processor cache, and a random access memory (RAM). The computer-readable medium may also include a non-transitory medium, such as a secondary or permanent long-term storage, such as a read-only memory (ROM), an optical disk or a disk, and a CD-ROM read-only memory (CD-ROM). The computer-readable medium may also be any other volatile or non-volatile storage system. For example, a computer-readable medium may be considered to be a tangible computer-readable storage medium.

[0058] In some instances, components of the devices and / or systems described herein may be configured to perform a function, such that the components are actually configured and constructed (with hardware and / or software) to achieve such performance. Then, the exemplary configuration includes one or more processors that execute instructions to cause the system to perform the function. Similarly, components of the devices and / or systems may be configured to be arranged or adapted to be capable of or suitable for performing a function, such as when operating in a particular manner.

[0059] Furthermore, the present disclosure includes embodiments according to the following clauses:

[0060] Clause 1. An aircraft onboard maintenance system (100), comprising:

[0061] a pressure sensor (114) configured to measure pressure in a tube (116) associated with an engine (112, 312) of an aircraft (110, 310) and to generate a sensor signal indicative of the pressure measured by the pressure sensor (114);

[0062] A valve (120) comprising an inlet (122) coupled to an inert gas supply (118) on an aircraft (110, 310) and an outlet (124) coupled to a conduit (126) extending to a tube (116), wherein the valve (120) is actuatable between: (i) an open state, wherein the valve (120) supplies inert gas from the inert gas supply (118) to the tube (116) through the conduit (126), and (ii) a closed state, wherein the valve (120) prohibits the supply of inert gas;

[0063] The control system (130) is in communication with the pressure sensor (114) and is configured to receive the sensor signal, wherein the control system (130) is configured to:

[0064] determining based on the sensor signal that the tube (116) is at least partially blocked by moisture, and

[0065] In response to determining that the tube (116) is at least partially blocked by moisture, providing a warning signal to a cockpit (132) of the aircraft (110, 310); and

[0066] An actuation switch at the cockpit (132) is operable to actuate the valve (120) to an open state to supply inert gas to the conduit (126) and to drain moisture from the tube (116).

[0067] Clause 2. The aircraft onboard maintenance system (100) of clause 1, wherein the control system (130) comprises:

[0068] An electronic engine controller (EEC) (148) in communication with the pressure sensor (114), wherein the EEC (148) is configured to:

[0069] receiving an indication of a pressure measured by a pressure sensor (114),

[0070] determining, based on the pressure measured by the pressure sensor (114), that the tube (116) is at least partially blocked by moisture, and

[0071] In response to determining that the tube (116) is at least partially blocked by moisture, generating a blockage detected signal; and

[0072] An aircraft control system (150) in communication with the EEC (148) and configured to:

[0073] receiving a signal from the EEC (148) that a blockage has been detected, and

[0074] In response to detecting the obstruction signal, an alarm signal is provided to the cockpit (132).

[0075] Clause 3. The aircraft onboard maintenance system (100) of clause 1, wherein, in order to determine that the tube (116) is at least partially blocked by moisture, the control system (130) is configured to:

[0076] The pressure measured by the pressure sensor (114) is compared with a series of threshold values,

[0077] According to the comparison result, determining that the pressure measured by the pressure sensor (114) is outside the threshold range, and

[0078] In response to determining that the pressure measured by the pressure sensor (114) is outside of a threshold range, it is determined that the tube (116) is at least partially blocked by moisture.

[0079] Clause 4. The aircraft onboard maintenance system (100) of clause 3, wherein the pressure sensor (114) is configured to measure a second pressure in the tube (116) and to generate a second sensor signal indicative of the second pressure measured by the pressure sensor (114), and

[0080] Wherein, the control system (130) is configured as follows:

[0081] performing a second comparison between the second pressure indicated by the second sensor signal and the threshold range, and determining, based on the second comparison, that the second pressure indicated by the second sensor signal is within the threshold range, and

[0082] In response to determining that the second pressure is within the threshold range, it is determined that there is no moisture in the tube (116).

[0083] Clause 5. The aircraft onboard maintenance system (100) of clause 1, further comprising an output device (140) at the cockpit (132) and in communication with the control system (130),

[0084] wherein the output device (140) is configured to generate a notification in the cockpit (132) in response to the alarm signal,

[0085] wherein the notification includes at least one of an audible notification, a visual notification, and a tactile notification indicating that the tube (116) is at least partially blocked, and

[0086] Wherein the actuation switch is manually operable in response to a notification generated by an output device (140).

[0087] Clause 6. The aircraft onboard maintenance system (100) according to Clause 5 further includes a lock switch (144) configured to (i) disable the actuation switch before the cockpit (132) receives an alarm signal from the control system (130), and (ii) enable the actuation switch in response to the cockpit (132) receiving an alarm signal from the control system (130).

[0088] Clause 7. The aircraft onboard maintenance system (100) of clause 1, further comprising a processor (146) at the cockpit (132), the processor configured to automatically operate the actuation switch in response to an alarm signal received from the control system (130).

[0089] Clause 8. The aircraft onboard maintenance system (100) of clause 1, wherein the inert gas supply (118) is configured to supply the inert gas along the conduit (126) at a pressure of at least 40 pounds per square inch (PSI).

[0090] Clause 9. The aircraft onboard maintenance system (100) of clause 1, further comprising a fitting (152) coupling the first portion (116A) of the tube (116), the second portion (116B) of the tube (116), and the conduit (126),

[0091] wherein the pressure sensor (114) is configured to measure the pressure in the first portion (116A) of the tube (116), and

[0092] The fitting (152) is configured to direct the inert gas from the conduit (126) toward the first portion (116A) of the tube (116).

[0093] Clause 10. A method for onboard maintenance of an aircraft (110, 310), comprising:

[0094] measuring pressure in a pipe (116) associated with an engine (112, 312) of an aircraft (110, 310) by means of a pressure sensor (114);

[0095] determining, by the control system (130) and based on the pressure measured by the pressure sensor (114), that the tube (116) is at least partially blocked by moisture;

[0096] In response to determining that the tube (116) is at least partially blocked by moisture, providing a warning signal from the control system (130) to a cockpit (132) of the aircraft (110, 310); and

[0097] In response to the alarm signal, operating an actuation switch on the cockpit (132) to actuate the valve (120) to an open state; and

[0098] In response to actuating the valve (120) to an open state, an inert gas is supplied from the inert gas supply (118) to the tube (116) via the valve (120) and the conduit (126) to expel moisture from the tube (116).

[0099] Clause 11. The method according to clause 10, further comprising:

[0100] disabling operation of an actuating switch that actuates the valve (120) to an open state to lock the valve (120) in a closed state before providing an alarm signal from the control system (130) to the cockpit (132), and

[0101] After an alarm signal from a control system (130) is provided to a cockpit (132), an actuation switch is enabled to allow actuation of the valve (120) from a closed state to an open state.

[0102] Clause 12. The method of clause 10, wherein determining that the tube (116) is at least partially blocked by moisture comprises:

[0103] comparing a pressure measured by a pressure sensor (114) to a threshold range;

[0104] Based on the comparison, determining that the pressure measured by the pressure sensor (114) is outside a threshold range;

[0105] as well as

[0106] In response to determining that the pressure measured by the pressure sensor (114) is outside of a threshold range, it is determined that the tube (116) is at least partially blocked by moisture.

[0107] Clause 13. The method of clause 12, further comprising, after supplying the inert gas from the inert gas supply (118) to the tube (116):

[0108] measuring a second pressure in the tube (116) by means of a pressure sensor (114);

[0109] generating a second sensor signal indicative of a second pressure measured by the pressure sensor (114);

[0110] performing, by the control system (130), a second comparison of a second pressure indicated by a second sensor signal with a threshold range;

[0111] Based on the second comparison, determining that a second pressure indicated by the second sensor signal is within a threshold range; and

[0112] In response to determining that the second pressure indicated by the second sensor signal is within a threshold range, it is determined that there is no moisture in the tube (116).

[0113] Clause 14. The method according to clause 10, further comprising:

[0114] Receiving an alarm signal at a cockpit (132);

[0115] In response to receiving the alert signal in the cockpit (132), generating a notification in the cockpit (132) by an output device (140), wherein the notification includes at least one of an audible notification, a visual notification, and a tactile notification; and

[0116] Wherein operating the activation switch comprises manually operating the activation switch in response to a notification generated by an output device (140).

[0117] Clause 15. The method according to Clause 10, further comprising:

[0118] The presence of moisture in the tube (116) is detected by a moisture sensor (254); and wherein determining that the tube (116) is at least partially blocked by moisture includes determining that the tube (116) is at least partially blocked by moisture based on the pressure measured by the pressure sensor (114) and the presence of moisture detected by the moisture sensor (254).

[0119] Clause 16. An aircraft onboard maintenance system (200), comprising:

[0120] a pressure sensor (114) configured to measure pressure in a tube (116) associated with an engine (112, 312) of an aircraft (110, 310) and to generate a sensor signal indicative of the pressure measured by the pressure sensor (114);

[0121] A valve (120) comprising an inlet (122) coupled to an inert gas supply (118) on an aircraft (110, 310) and an outlet (124) coupled to a conduit (126) extending to a tube (116), wherein the valve (120) is actuatable between: (i) an open state, wherein the valve (120) supplies inert gas from the inert gas supply (118) to the tube (116) through the conduit (126), and (ii) a closed state, wherein the valve (120) prohibits the supply of inert gas;

[0122] a moisture sensor (254) configured to detect moisture in the tube (116) and generate a moisture sensor signal indicating the presence of moisture in the tube (116);

[0123] A control system (130) in communication with the moisture sensor (254) and configured to receive a moisture sensor signal, wherein the control system (130) is configured to:

[0124] determining that the tube (116) is at least partially blocked by moisture based on the moisture sensor signal, and

[0125] In response to determining that the tube (116) is at least partially blocked by moisture, providing a warning signal to a cockpit (132) of the aircraft (110, 310); and

[0126] There is an actuation switch at the cockpit (132) operable to actuate the valve (120) to an open state to supply inert gas to the conduit (126) and to drain moisture from the tube (116).

[0127] Clause 17. The aircraft onboard maintenance system (200) of clause 16, comprising an output device (136) located in the cockpit (132) and in communication with the control system (130),

[0128] wherein the output device (136) is configured to generate a notification in the cockpit (132) in response to the alarm signal,

[0129] wherein the notification includes at least one of an audible notification, a visual notification, and a tactile notification indicating that the tube (116) is at least partially blocked, and

[0130] Wherein the actuation switch (138) is manually operable in response to a notification generated by the output device (136).

[0131] Clause 18. The aircraft onboard maintenance system (200) according to clause 16, further comprising a processor (146) located in the cockpit (132), the processor being configured to automatically operate the actuation switch in response to an alarm signal received from the control system (130).

[0132] Clause 19. The aircraft onboard maintenance system (200) of clause 16, further comprising an output device (140) configured to provide a notification at the cockpit (132), wherein the notification comprises at least one of an audible notification, a visual notification, and a tactile notification, and

[0133] wherein the moisture sensor (254) is configured to detect when moisture is purged from the tube (116) and provide a purged moisture signal to the cockpit (132) indicating the absence of moisture in the tube (116), and

[0134] The output device (140) is configured to provide a notification indicating that moisture has been drained from the tube (116) in response to the cockpit (132) receiving the signal that moisture has been cleared.

[0135] Clause 20. The aircraft onboard maintenance system (200) of clause 16, further comprising a fitting (152) coupling the first portion (116A) of the tube (116), the second portion (116B) of the tube (116), and the conduit (126),

[0136] wherein the moisture sensor (254) is configured to detect moisture in the first portion (116A) of the tube (116); and

[0137] The fitting (152) is configured to direct the inert gas from the conduit (126) toward the first portion (116A) of the tube (116).

[0138] The description of different advantageous arrangements has been given for the purpose of illustration and description, and is not intended to be exhaustive or limited to the embodiments in the disclosed form. Many modifications and variations will be apparent to those of ordinary skill in the art. In addition, different advantageous embodiments may describe different advantages compared to other advantageous embodiments. The selected one or more embodiments are selected and described to explain the principles of the embodiments, practical applications, and to enable others of ordinary skill in the art to understand the disclosure of various embodiments with various modifications that are suitable for the intended specific use.

Claims

1. An aircraft onboard maintenance system (100), comprising: a pressure sensor (114) configured to measure pressure in a tube (116) associated with an engine (112, 312) of an aircraft (110, 310) and to generate a sensor signal indicative of the pressure measured by the pressure sensor (114), wherein the tube (116) is arranged to receive air into the tube (116) at an inlet of the engine when the tube (116) is not blocked by moisture, such that the pressure sensor (114) is configured to measure the pressure as an indication of the engine inlet pressure, wherein the pressure sensor (114) is located in the tube (116); A valve (120) comprising an inlet (122) coupled to an inert gas supply (118) on the aircraft (110, 310) and an outlet (124) coupled to a conduit (126) extending to the tube (116), wherein the valve (120) is actuatable between: an open state, wherein the valve (120) supplies inert gas from the inert gas supply (118) to the tube (116) through the conduit (126); and a closed state, wherein the valve (120) inhibits the supply of the inert gas, wherein the conduit (126) extends from a wing of the aircraft along a pylon and along the engine to the tube (116); The control system (130) is in communication with the pressure sensor (114) and is configured to receive the sensor signal, wherein the control system (130) is configured to: determining, based on the sensor signal, that the tube (116) is at least partially blocked by moisture, and In response to determining that the tube (116) is at least partially blocked by moisture, providing a warning signal to a cockpit (132) of the aircraft (110, 310); an actuation switch at the cockpit (132) operable to actuate the valve (120) to the open state to supply the inert gas to the conduit (126) and drain the moisture in the tube (116); and a lock switch (144) in communication with the control system, The lock switch (144) is configured to disable the actuation switch before the cockpit receives the alarm signal from the control system, and to enable the actuation switch in response to the cockpit receiving the alarm signal from the control system.

2. The aircraft onboard maintenance system (100) according to claim 1, wherein: The control system (130) comprises: An electronic engine controller (148) in communication with the pressure sensor (114), wherein the electronic engine controller (148) is configured to: receiving an indication of the pressure measured by the pressure sensor (114), determining, based on the pressure measured by the pressure sensor (114), that the tube (116) is at least partially blocked by the moisture, and In response to determining that the tube (116) is at least partially blocked by the moisture, generating a blockage detected signal; and An aircraft control system (150) in communication with the electronic engine controller (148) and configured to: receiving the detected obstruction signal from the electronic engine controller (148), and In response to the signal that a blockage is detected, the alarm signal is provided to the cockpit (132).

3. The aircraft onboard maintenance system (100) according to claim 1 or 2, wherein: In order to determine that the tube (116) is at least partially blocked by the moisture, the control system (130) is configured to: performing a comparison of the pressure measured by the pressure sensor (114) with a series of threshold values, determining, based on the comparison result, that the pressure measured by the pressure sensor (114) is outside a threshold range, and In response to determining that the pressure measured by the pressure sensor (114) is outside the threshold range, it is determined that the tube (116) is at least partially blocked by the moisture.

4. The aircraft onboard maintenance system (100) according to claim 3, wherein: The pressure sensor (114) is configured to measure a second pressure in the tube (116) and to generate a second sensor signal indicative of the second pressure measured by the pressure sensor (114), and Wherein, the control system (130) is configured as follows: performing a second comparison of the second pressure indicated by the second sensor signal with the threshold range, determining, based on the second comparison, that the second pressure indicated by the second sensor signal is within the threshold range, and In response to determining that the second pressure is within the threshold range, it is determined that the tube (116) is free of the moisture.

5. The aircraft onboard maintenance system (100) according to claim 1 or 2, further comprising an output device (140) at the cockpit (132) and in communication with the control system (130), in, The output device (140) is configured to generate a notification in the cockpit (132) in response to the alarm signal, wherein the notification includes at least one of an audible notification, a visual notification, and a tactile notification indicating that the tube (116) is at least partially blocked, and wherein the actuation switch is manually operable in response to the notification generated by the output device (140).

6. The aircraft onboard maintenance system (100) of claim 1 or 2, further comprising a processor (146) at the cockpit (132), the processor configured to automatically operate the actuation switch in response to the alarm signal received from the control system (130).

7. The aircraft onboard maintenance system (100) according to claim 1 or 2, wherein: The inert gas supply (118) is configured to supply the inert gas along the conduit (126) at a pressure of at least 40 psig.

8. The aircraft onboard maintenance system (100) according to claim 1 or 2, further comprising a fitting (152) coupling the first portion (116A) of the tube (116), the second portion (116B) of the tube (116), and the conduit (126), in, The pressure sensor (114) is configured to measure the pressure in the first portion (116A) of the tube (116), and wherein the fitting (152) is configured to direct the inert gas from the conduit (126) toward the first portion (116A) of the tube (116).

9. A method for onboard maintenance of an aircraft (110, 310), comprising: measuring, by means of a pressure sensor (114), a pressure in a pipe (116) associated with an engine (112, 312) of an aircraft (110, 310); determining, by a control system (130) and based on the pressure measured by the pressure sensor (114), that the tube (116) is at least partially blocked by moisture; In response to determining that the tube (116) is at least partially blocked by the moisture, providing a warning signal from the control system (130) to a cockpit (132) of the aircraft (110, 310); as well as in response to the cockpit receiving the alarm signal from the control system, enabling an actuation switch by a lock switch in communication with the control system, wherein the lock switch is configured to disable the actuation switch before the cockpit receives the alarm signal from the control system and to enable the actuation switch in response to the cockpit receiving the alarm signal from the control system; In response to the lock switch activating the actuation switch, operating the actuation switch at the cockpit (132) to actuate the valve (120) to an open state; and In response to actuating the valve (120) to the open state, inert gas is supplied from an inert gas supply (118) to the tube (116) via the valve (120) and a conduit (126) to expel the moisture from the tube (116).

10. The method according to claim 9, further comprising: disabling operation of the actuating switch that actuates the valve (120) to the open state to lock the valve (120) in the closed state before providing the alarm signal from the control system (130) to the cockpit (132), and After the alarm signal from the control system (130) is provided to the cockpit (132), the actuation switch is enabled to allow actuation of the valve (120) from the closed state to the open state.

11. The method according to claim 9 or 10, wherein: Determining that the tube (116) is at least partially blocked by the moisture includes: performing a comparison of the pressure measured by the pressure sensor (114) with a threshold range; Based on the comparison, determining that the pressure measured by the pressure sensor (114) is outside the threshold range; and In response to determining that the pressure measured by the pressure sensor (114) is outside the threshold range, it is determined that the tube (116) is at least partially blocked by the moisture.

12. The method of claim 11, further comprising, after supplying the inert gas from the inert gas supply (118) to the tube (116): measuring a second pressure in the tube (116) by means of the pressure sensor (114); generating a second sensor signal indicative of the second pressure measured by the pressure sensor (114); performing, by the control system (130), a second comparison of the second pressure indicated by the second sensor signal with the threshold range; determining, based on the second comparison, that the second pressure indicated by the second sensor signal is within a threshold range; as well as In response to determining that the second pressure indicated by the second sensor signal is within the threshold range, it is determined that the tube (116) is free of the moisture.

13. The method according to claim 9 or 10, further comprising: Receiving the alarm signal at the cockpit (132); In response to receiving the alert signal in the cockpit (132), generating a notification in the cockpit (132) by an output device (140), wherein the notification includes at least one of an audible notification, a visual notification, and a tactile notification; and Wherein operating the actuation switch comprises manually operating the actuation switch in response to the notification generated by the output device (140).

14. The method according to claim 9 or 10, further comprising: detecting whether the moisture exists in the tube (116) by means of a moisture sensor (254); as well as Wherein, determining that the tube (116) is at least partially blocked by the moisture includes determining that the tube (116) is at least partially blocked by the moisture based on the pressure measured by the pressure sensor (114) and the presence of the moisture detected by the moisture sensor (254).

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