System and method to detect anomalous wingtip extension for folding wing tip aircraft

Abstract

To detect anomalous wingtip extension for a folding wing tip aircraft.SOLUTION: A method includes, in response to a first determination in an electronic controller 316A that rotation of a wingtip 344 stopped before a flight position during implementation of an extend command, sending a first notification signal to a flight control computer from the electronic controller 316A to cause the aircraft to be grounded and to schedule maintenance of the aircraft. The first notification signal includes one or more first error codes. The first notification signal causes the maintenance to include drop maintenance from the wingtip 344 to a latch pin 358 in response to a determination of the electronic controller 316A indicating that a first particular angle of the wingtip 344 relative to a primary portion of the wing is in a latch pin interference range.SELECTED DRAWING: Figure 3

Description

[Technical field]

[0001]

[0001] This disclosure relates generally to detecting abnormal wing tip extension on folding wing tip aircraft. [Background technology]

[0002]

[0002] In general, larger aircraft and aircraft with wider wingspans tend to be more efficient for transporting people, cargo, or both. For example, it is generally more efficient to operate larger aircraft that can carry more passengers and cargo than to fly multiple smaller aircraft between two destinations. While some airports (e.g., Type F airports) can accommodate aircraft with larger wingspans, most airport taxiway spacing and gate locations have been designed without sufficient spacing for aircraft with wider wingspans.

[0003]

[0003] To have a large wingspan and comply with the wingspan limitations associated with some airports (e.g., Type E airports), some aircraft are folding wingtip aircraft. Each wing of the aircraft includes a main section connected to the fuselage of the aircraft, a wingtip configured to fold (e.g., rotate) relative to the main section, and a folding wingtip system configured to fold the wingtip relative to the main section. When the wingtip is in a flying position, the aircraft has a large wingspan to improve the flight efficiency of the aircraft, and when the wingtip is in a folded position, the aircraft has a smaller wingspan that complies with the airport's wingspan limitations.

[0004]

[0004] Folding wingtip systems (i.e., one folding wingtip system for each wing of an aircraft) are designed to raise and lower the wingtips. Although the likelihood of abnormal operation of a folding wingtip system occurring (due to human error, component failure, or both) is highly unlikely, it is desirable to detect if such an abnormality occurs and provide an indication detailing an appropriate response. Summary of the Invention

[0005] In a particular embodiment, an aircraft includes a wing. The wing includes a main portion and a wingtip. The aircraft also includes a folding wingtip system configured to rotate the wingtip relative to the main portion. The folding wingtip system includes an electronic controller. The electronic controller is configured to execute an extend command received from a flight control computer to rotate the wingtip from a folded position to a flight position. The electronic controller is also configured, in response to a determination that the rotation of the wingtip stops before the flight position during execution of the extend command, to send a first notification signal to the flight control computer to ground the folding wingtip aircraft and schedule maintenance of the aircraft. The first notification signal includes one or more first error codes. The first notification signal, in response to the electronic controller's determination indicating that a first particular angle of the wingtip relative to the main portion of the wing is within a latch pin interference range, causes the maintenance to include wingtip-to-latch pin drop maintenance.

[0006] In another particular embodiment, a method includes executing, via an electronic controller of an aircraft, an extend command received by the electronic controller from a flight control computer to rotate a wing tip from a folded position to a flight position. The method includes, in response to a first determination in the electronic controller that rotation of the wing tip has stopped before the flight position during execution of the extend command, sending a first notification signal from the electronic controller to the flight control computer to ground the aircraft and schedule maintenance of the aircraft. The first notification signal includes one or more first error codes. The first notification signal, in response to a determination by the electronic controller indicating that a first particular angle of the wing tip relative to a main portion of the wing is within a latch pin interference range, causes the maintenance to include wingtip-to-latch pin drop maintenance.

[0007] In another particular embodiment, a non-transitory computer readable medium includes instructions executable by one or more processors of an aircraft electronic controller. The instructions are executable by the one or more processors to execute an extend command received from a flight control computer to rotate a wing tip from a folded position to a flight position. The instructions are also executable by the one or more processors to, in response to a first determination that rotation of the wing tip has stopped before the flight position during execution of the extend command, send a first notification signal to the flight control computer to ground the aircraft and schedule maintenance of the aircraft. The first notification signal includes one or more first error codes. The first notification signal, in response to a determination by the electronic controller indicating that a first particular angle of the wing tip relative to a main portion of the wing is within a latch pin interference range, causes the maintenance to include a down-maintenance from the wing tip to the latch pin.

[0008]

[0008] The features, functions, and advantages described herein may be realized alone in various embodiments or may be combined in yet other implementations, further details of which may be understood by reference to the following specification and accompanying drawings. [Brief description of the drawings]

[0009] [Figure 1A]

[0009] A diagram of a folding wingtip aircraft including a wingtip extension anomaly detector is shown with the wingtip in a flying position. [Figure 1B]

[0010] FIG. 1B shows a diagram of the folding wingtip aircraft of FIG. 1A with the wingtips in a folded position. [Diagram 2]

[0011] FIG. 1 is a block diagram of a folding wingtip aircraft including a wingtip extension anomaly detector. [Diagram 3]

[0012] FIG. 1 is a diagram of a folding wingtip system for a folding wingtip aircraft including a wingtip extension anomaly detector. [Figure 4]

[0013] 1 is a flow chart illustrating an implementation of a first method of using a folding wingtip system for an aircraft including wingtip extension anomaly detection. [Diagram 5]

[0014] 11 is a flow chart illustrating a second method of using a folding wingtip system for an aircraft including wingtip extension anomaly detection. [Figure 6]

[0015] 11 is a flow chart illustrating a third method of using a folding wingtip system on an aircraft including wingtip extension anomaly detection. [Figure 7]

[0016] 11 is a flow chart illustrating a fourth method of using a folding wingtip system on an aircraft including wingtip extension anomaly detection. [Figure 8]

[0017] 1B is a flowchart illustrating the life cycle of an aircraft including the wingtip extension anomaly detector of FIG. 1A. [Figure 9]

[0018] FIG. 1 is a block diagram of an aircraft. [Figure 10]

[0019] FIG. 1 is a block diagram of a computing environment including a computing device configured to support aspects of the computer-implemented methods and computer-executable program instructions (or code) according to the present disclosure. DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS

[0010]

[0020] A folding wingtip aircraft includes a folding wingtip system for each wing of the aircraft that allows rotation of the wing from a flying position to a folded position and vice versa, the folding wingtip system receiving commands from a flight control computer to engage the folding wingtip system.

[0011]

[0021] The folding wingtip system is designed such that the movement of the wingtip is controlled and held in place by a brake system when the wingtip is in the folded position and by a latch pin system when the wingtip is in the flight position. If the folding wingtip system of the aircraft does not operate correctly to execute commands to change the wingtip from a first position (e.g., folded position) to a second position (e.g., flight position) based on data provided by sensors monitoring the folding wingtip system, the aircraft will remain on the ground and be scheduled for maintenance. Fault isolation manuals, aircraft maintenance manuals, and information provided by the aircraft's flight control computer are used by maintenance personnel to determine the cause of a folding wingtip system failure, to function the folding wingtip system, to address and correct problems caused by the failure, or a combination thereof.

[0012]

[0022] Although highly unlikely, it is possible for a wing tip to fall out of its folded position or when a folding tip system is being used to change the position of the wing tip. A wing tip drop could result from human error (e.g., improper maintenance), failure of one or more components of the folding tip system (e.g., failure of a torque tube that supports the wing tip as it rotates from one position to another), other causes, or a combination of these. If a wing tip were to fall out, the tip lugs of the wing tip could contact stops in the main portion of the wing that limit the stopping of the rotation of the wing tip, which could cause damage to one or more of the tip lugs, one or more of the stops, or both, or the tip lugs of one or more of the wing tips could contact one or more latch pins of the latch pin system, which could cause damage to one or more of the tip lugs, one or more latch pins, or both.

[0013]

[0023] The present disclosure describes systems and methods that enable the determination of abnormal wingtip extension, such as when a wingtip falls off, and the determination of the type of maintenance required to return the aircraft to service. A technical advantage of the present disclosure is that scheduled maintenance on an aircraft as a result of a folding wingtip system failure, including specific maintenance to address the possible cause of the folding wingtip system failure, improves efficiency, reduces the time that a folding wingtip aircraft is out of service for maintenance, and reduces the costs associated with the maintenance. The scheduled maintenance on the aircraft includes specific maintenance performed to address the possible cause of failure of the folding wingtip system identified based on sensor data acquired during use of the folding wingtip system. Another technical advantage is that scheduled maintenance on an aircraft identifies whether a wingtip has fallen off, which may improve efficiency as maintenance personnel do not need to determine whether a wingtip has fallen off. If a scheduled maintenance on an aircraft indicates that a wingtip has been dropped, certain components of the folding wingtip system (e.g., one or more latch pins, one or more wingtip lugs, etc.) that are identified based on the sensor data as possibly being damaged by the wingtip being dropped can be identified and inspected for invisible damage instead of inspecting for invisible damage on all components that may have been damaged by the drop, which may improve efficiencies and reduce the time that an aircraft with folding wingtips is out of service, thereby reducing costs associated with maintenance.

[0014]

[0024] The drawings and the following description show specific exemplary embodiments. Although not explicitly described or illustrated herein, those skilled in the art will recognize that various configurations can be devised that embody the principles described herein and are included in the scope of the claims following the description of the specification. Furthermore, any examples described herein should be understood to be intended to aid in understanding the principles of the disclosure and are not intended to be limiting. As a result, the disclosure is not limited to the specific embodiments or examples described below, but is limited by the claims and their equivalents.

[0015]

[0025] Certain embodiments are described herein with reference to the drawings. In the description, common features are given common reference numbers throughout the drawings. In some drawings, multiple instances of a particular type of feature are used. Although these features are physically and / or logically different, the same reference number is used for each, and the different instances are distinguished by adding a letter to the reference number. When features as a group or type are referred to herein (e.g., when no particular one of the features is referred to), the reference number is used without a distinguishing letter. However, when a particular feature of one of multiple features of the same type is referred to herein, the reference number is used with a distinguishing letter. For example, referring to FIG. 3, multiple electronic controllers are illustrated and are associated with reference numbers 316A and 316B. When referring to a particular one of these electronic controllers (e.g., electronic controller 316A), the distinguishing letter "A" is used. However, when referring to any one of these electronic controllers or these electronic controllers as a group, the reference number 316 is used without a distinguishing letter.

[0016]

[0026] The present disclosure is directed to folding wingtip aircraft. As used herein, the term "aircraft" refers to a folding wingtip aircraft. Various terms are used herein only to describe particular embodiments and are not intended to be limiting. For example, the singular forms "a," "an," and "the" are intended to include the plural, unless the context clearly indicates otherwise. Additionally, some features described herein are in the singular in some embodiments and in the plural in other embodiments. For purposes of illustration, FIG. 2 shows a flight control computer 202 that includes one or more processors ("one or more processors" 216 in FIG. 2). In some embodiments, the flight control computer 202 includes a single processor 216, and in other embodiments, the flight control computer 202 includes multiple processors 216. For ease of reference herein, such features are generally introduced as "one or more" features and hereafter referred to as singular, unless aspects relating to multiple features are described.

[0017]

[0027] Additionally, the terms "comprise, comprise, and comprising" are used interchangeably with "include, includes, and including." Additionally, the term "wherein" is used interchangeably with the term "where." As used herein, the term "exemplary" indicates an embodiment and / or aspect and should not be construed as limiting or indicating a preferred or preferred embodiment. As used herein, ordinal terms (e.g., "first," "second," "third," etc.) modifying an element, such as a structure, component, operation, etc., do not themselves indicate any priority or order of said element relative to other elements, but merely distinguish other elements of the same name (apart from the use of the ordinal term). As used herein, the term "set" refers to a grouping of one or more elements, and the term "plurality" refers to a plurality of elements. As used herein, A "and / or" B may mean that either "A and B," "A or B," or both "A and B" and "A or B" are applicable or acceptable.

[0018]

[0028] As used herein, "generating," "calculating," "using," "selecting," "accessing," and "determining" are interchangeable unless the context indicates otherwise. For example, "generating," "calculating," or "determining" a parameter (or signal) may refer to actively generating, calculating, or determining a parameter (or signal), or may refer to using, selecting, or accessing a parameter (or signal) that has already been generated, for example, by another component or device. As used herein, "coupled" may include "communicatively connected," "electrically connected," or "physically connected," and further (or alternatively) may include any combination thereof. Two devices (or components) may be directly or indirectly connected (communicatively connected, electrically connected, or physically connected) via one or more other devices, components, wires, buses, networks (e.g., wired networks, wireless networks, or combinations thereof), etc. Two devices (or components) that are electrically connected can be included in the same device or different devices, and can be connected via electronic devices, one or more connectors, or inductive coupling, as illustrative, non-limiting examples. In some embodiments, two devices (or components) that are communicatively connected, such as by electrical communication, can send and receive electrical signals (digital or analog signals) directly or indirectly via one or more wires, buses, networks, etc. In this specification, the phrase "directly coupled" is used to describe two devices that are connected (e.g., communicatively connected, electrically connected, or physically connected) without any intervening components.

[0019]

[0029] FIG. 1A shows a diagram of the folding wingtip aircraft 100 with the wingtip 102 of the aircraft 100 in a flying position. FIG. 1B shows a diagram of the aircraft 100 with the wingtip 102 in a folded position. Each wing 104 of the aircraft 100 includes a main section 106 connected to a fuselage 108 of the aircraft 100 and a wingtip 102. The folding wingtip system of the aircraft 100 can rotate the wingtip 102 from a flying position to a folded position and vice versa. In one embodiment, the horizontal length of the wingtip 102 from the end of the wingtip to the hinge axis is about 11 feet. In other embodiments, the horizontal length of the wingtip 102 may be shorter or longer. In some embodiments, the end of the wingtip 102 may include a winglet.

[0020]

[0030] Sensor data associated with one or more components of the folding wingtip system is processed by wingtip extension anomaly detector 110 to determine if the folding wingtip system has operated correctly to position wingtip 102 in an appropriate position (e.g., a folded or flight position). In Figures 1A and 1B, wingtip extension anomaly detector 110 is shown using dashed lines to indicate that it is not normally visible from outside the aircraft 100. An example of the operation of wingtip extension anomaly detector 110 is described below with reference to Figures 2-7.

[0021]

[0031] 2 illustrates a block diagram of an aircraft 100. The aircraft 100 includes wings 104, flight control computers 202, input devices 204 (e.g., steering yokes, side sticks, levers, buttons, dials, keyboards, touch screens, etc.) for receiving data, commands, and other information from the flight crew and external sources, output devices 206 (e.g., displays, gauges, speakers, headphones, haptic devices, etc.) for providing information to the flight crew and external sources about operational conditions associated with the aircraft 100, engines 208 for powering the aircraft 100, an operating system 210, and a sensor system 212 for enabling the flight control computer 202, the operating system 210, or both, to determine operational conditions associated with the aircraft 100, and other components. Each wing 104 includes a main portion 106 and a wing tip 102 configured to rotate relative to the main portion 106 about a hinge axis 214.

[0022]

[0032] Flight control computer 202 controls the operation of aircraft 100 based on inputs received from the crew and external sources and on the conditions of use. Flight control computer 202 includes one or more processors 216 and memory 218. Memory 218 stores data 220 related to the operation of aircraft 100 and instructions 222 executable by processor 216 to perform the operations. Instructions 222 may include flight instructions 224 for operating aircraft 100, a warning system 226 for indicating that one or more abnormal conditions have occurred, a maintenance scheduler 228 for scheduling maintenance of aircraft 100, wingtip extension anomaly detector 110A, other applications, or combinations thereof. Maintenance scheduled by maintenance scheduler 228 may include routine maintenance, specific maintenance to address issues detected by flight control computer 202, or combinations thereof.

[0023]

[0033] Operating system 210 is configured to execute control commands sent by flight control computer 202, control commands provided by the crew via input devices 204, or both. Operating system 210 includes folding wingtip systems 230, navigation systems, communication systems, and other systems utilized during use of aircraft 100. Each folding wingtip system 230 is associated with a wing 104 and is configured to rotate a wing tip 102 of the wing 104 relative to the main wing portion 106 from a folded position to a flying position and vice versa. Each folding wingtip system 230 is also configured to secure the wing tip 102 in the flying and folded positions.

[0024]

[0034] Flight instructions 224 control the use of folding wing tip system 230. Flight instructions 224 include logic that determines when folding wing tip system 230 is available for use. For example, if aircraft 100 is in the takeoff or flight phase and prevents flight control computer 202 from sending a fold command during landing, flight instructions 224 prohibit flight control computer 202 from sending a fold command to fold wing tips 102 from the flight position to the folded position until aircraft 100 lands on the ground and is traveling at a speed below a threshold speed. The threshold speed is less than the speed required for aircraft 100 to resume flight. In some implementations, the threshold speed is a taxi speed. As another example, when the aircraft 100 is not in flight but is in the taxi-in phase, taxi-out phase, or is positioned at a stand (e.g., a gate), the flight instructions 224 prohibit the flight control computer 202 from sending an extend command to extend the wingtips 102 from a folded position to a flight position based on a comparison of the current position of the aircraft 100 to the wingspan limit data for the aircraft 100.

[0025]

[0035] Wingtip expansion anomaly detector 110A may represent a portion of wingtip expansion anomaly detector 110 implemented in flight control computer 202 and operating based on inputs from sensor system 212, folding wingtip system 230, or both. Wingtip expansion anomaly detector 110A receives notification signals regarding operation of folding wingtip system 230 in response to commands sent from flight control computer 202 to folding wingtip system 230. If the received notification signal includes one or more error codes, wingtip expansion anomaly detector 110A is configured to change settings to indicate that aircraft 100 will remain on the ground, is configured to provide information to warning system 226 so that the crew can be notified of one or more issues with folding wingtip system 230 and notified that the aircraft will remain on the ground, and is configured to provide one or more error codes to maintenance scheduler 228 so that specific maintenance can be performed to address the one or more issues.

[0026]

[0036] Flight control computer 202 may determine that the last command completed by folding wingtip system 230 was a fold command. This may occur when aircraft 100 transitions from an idle or low power state to a powered state, periodically, when flight control computer 202 determines to execute one or more extend commands to move wingtip 102 from a folded position to a flying position, or combinations thereof. For example, wingtip extension anomaly detector 110A sends a request for the position of wingtip 102 to folding wingtip system 230 and determines from data 220 the last executed command of folding wingtip system 230 before one or more extend commands are sent to folding wingtip system 230. If the wing tip 102 is in the folded position and the response to the wing tip position request indicates that the last command issued by the folding wing tip system 230 was a fold command, the wing tip extension anomaly detector 110A determines that there is no anomaly and sends one or more extend commands to the folding wing tip system 230.

[0027]

[0037] If one or both of the wing tips 102 are not in the folded position and the wing tip extension anomaly detector 110A determines that the last command executed by the folding wing tip system was a fold command, the wing tip extension anomaly detector 110A determines that there is an anomaly. The wing tip extension anomaly detector 110A configures the aircraft 100 to remain on the ground and sets an error code associated with the anomaly. The error codes include one or more codes used by the maintenance scheduler 228 to specify the particular maintenance to be performed in order to return the aircraft 100 to service. The error codes include a code indicating a problem with a braking system (e.g., braking system 308 in FIG. 3 ) configured to maintain the wing tips 102 in the folded position and prevent the wing tips 102 from unintentionally moving out of the folded position, an error code associated with a wing tip actuation system (e.g., wing tip actuation system 304 in FIG. 3 ) of the folding wing tip system 230, and an error code associated with the position of the wing tips 102 not in the folded position. For example, if one of the wing tips 102 is in or near the flight position, an error code associated with the position of the wing tip 102 may cause the maintenance scheduler 228 to designate a specific maintenance to address an issue associated with the wing tip 102 dropping from the folded position to the flight position (e.g., a drop maintenance from the wing tip to the stop).

[0028]

[0038] 3 is a block diagram of a folding wing tip system 230 for a wing 104 of an aircraft 100. The folding wing tip system 230 includes a control system 302, a wing tip actuation system 304 for rotating the wing tip 102 between a folded position and a flight position, a latch pin system 306 for locking the wing tip 102 in a flight position, a brake system 308 for locking the wing tip 102 in a folded position, portions of the sensor system 212 (e.g., hinge line sensor 310, drive train actuator position sensor 312, and drive train position sensor 314), other components, or combinations thereof.

[0029]

[0039] Control system 302 includes an electronic controller 316A, a hydraulic controller 318A connected to electronic controller 316A, a redundant electronic controller 316B, a redundant hydraulic controller 318B connected to electronic controller 310B, and a shutoff valve 320 communicatively connected to electronic controller 316. Electronic controller 316 is communicatively connected to flight control computer 202.

[0030]

[0040] In some implementations, the electronic controllers 316A, 316B are shared by the folding wingtip systems 230 of the wings 104 of the other aircraft 100 such that both folding wingtip systems 230 can be controlled simultaneously via one of the electronic controllers 310A, 310B in response to commands received from the flight control computer 202. Sharing the electronic controllers 316A, 316B by the folding wingtip systems 230 allows the folding wingtip aircraft 100 to have two electronic controllers 316A, 316B instead of four electronic controllers 316A, 316B, such as when each folding wingtip system 230 includes its own electronic controller 316A, 316B. Similarly, in some implementations, the hydraulic controllers 318A, 318B are shared by the folding wingtip systems 230 of the wings 104 of the other aircraft 100. Spacing of components and coupling systems (e.g., wiring for electronic controller 316 and hydraulic lines for hydraulic controller 318) and system weight considerations may be considerations during the design of aircraft 100 that are used in determining whether to use two electronic controllers 316A, 316B or four electronic controllers 316A, 316B and whether to use two hydraulic controllers 318A, 318B or four hydraulic controllers 318A, 318B.

[0031]

[0041] Each electronic controller 316 includes one or more processors 322 and memory 324. The memory 324 is configured to store data and instructions. The instructions include extend instructions 326, fold instructions 328, and wing tip extension anomaly detector 110B. When a particular electronic controller 316 receives an extend command from flight control computer 202, the one or more processors 322 execute the extend instructions 326 to cause the folding wing tip system 230 to rotate the wing tip 102 from a folded position to a flight position and secure the wing tip 102 in the flight position. When a particular electronic controller 316 receives a fold command from flight control computer 202, the one or more processors 322 execute the fold instructions 328 to cause the folding wing tip system 230 to rotate the wing tip 102 from a flight position to a folded position and secure the wing tip 102 in the folded position.

[0032]

[0042] Wingtip extension anomaly detector 110B may represent a portion of wingtip extension anomaly detector 110 implemented in electronic controller 316 that monitors execution of specific commands received from flight control computer 202 via extend instructions 326 or fold instructions 328. If the commands are executed correctly, wingtip extension anomaly detector 110B provides a notification to wingtip extension anomaly detector 110A of flight control computer 202 indicating that the received command was executed successfully. If wingtip extension anomaly detector 110B detects, based on the sensor data, that execution of the received command is stopped prior to completion, wingtip extension anomaly detector 110B may stop further execution of the instruction (e.g., extend instruction 326 or fold instruction 328), close shutoff valve 320, set one or more error codes associated with folding wingtip system 230, send a notification signal including one or more error codes to wingtip extension anomaly detector 110A, or perform a combination thereof.

[0033]

[0043] Each electronic controller 316 is communicatively connected to a corresponding hydraulic controller 318. Each hydraulic controller 318 is connected by a hydraulic supply line to a shutoff valve 320 for receiving pressurized hydraulic fluid from a hydraulic fluid system 330. The hydraulic fluid system 330 may be a centralized system that supplies hydraulic fluid to the folding wingtip systems 230 of each wing 104 of the aircraft 100. Each hydraulic controller 318 is connected to a hydraulic return line that directs returning hydraulic fluid to the hydraulic fluid system 330. The hydraulic controller 318 includes a number of ports. The hydraulic supply and return lines are coupled to ports of the folding wingtip systems 230 and hydraulic units (e.g., power drive unit 332, latch pin actuator 334, brake system 308, etc.). When the electronic controller 316 is executing a first command (e.g., an extend command or a fold command), the electronic controller 316 sends an open signal to the shutoff valve 320 and sends various signals to the corresponding hydraulic controllers 318 during the execution of the first command, causing the hydraulic controllers 318 to direct pressurized hydraulic fluid to the appropriate hydraulic units at the appropriate times and to stop providing hydraulic fluid to particular units at particular times. The last or near last signal sent by the electronic controllers 316 during the execution of the first command is a close signal to close the shutoff valve 320, thereby stopping the functioning of the folding wingtip system 230 until one of the electronic controllers 316 receives a second command signal from the flight control computer 202 to engage the folding wingtip system 230 (e.g., a fold command or an extend command) and the electronic controller 316 sends a signal to open the shutoff valve 320 as part of the procedure for executing the second command.

[0034]

[0044] The shut-off valve 320 is associated with a first valve coil controlled by a first electronic controller 316A to open and close the shut-off valve 320, a second valve coil controlled by a second electronic controller 316B to open and close the shut-off valve 320, and one or more valve sensors configured to monitor the operation of the valve coils. Data from the valve sensors is used by the electronic controllers 316 to determine if a command to open or close the valve has been executed. When a particular electronic controller 316 executes a particular command (i.e., a command to open or close the valve) and the valve sensor data indicates that the particular command was not completed, a first shut-off valve error code associated with the particular controller is set and the particular electronic controller 316 causes the particular command to be executed by the other electronic controller 316. When the valve sensor data indicates that the particular command was completed by the other electronic controller 316, the notification signal sent to the flight control computer 202 includes the first shut-off valve error code. If the first shutoff valve error code is present in the notification signal without the presence of a second shutoff valve error code associated with another electronic controller 316, the flight control computer 202 may continue operating the aircraft and schedule maintenance on the aircraft 100 to address the problem with the particular electronic controller 316, the valve sensor associated with the particular electronic controller 316, or both.

[0035]

[0045] If the valve sensor data indicates that a particular command was also not completed by the other electronic controller 316, a second shut-off valve error code associated with the other electronic controller is set and a notification signal including the first shut-off valve error code and the second shut-off valve error code is sent to flight control computer 202. In response to the presence of the first shut-off valve error code and the second shut-off valve error code in the notification signal, flight control computer 202 causes a setting change to indicate that the aircraft 100 should remain on the ground and schedules maintenance to address one or more problems associated with the valve sensor, the shut-off valve 320, or both.

[0036]

[0046] The wing tip actuation system 304 includes a powered drive unit 332 that rotates a first torque tube 336, an angle gearbox 338 driven by the first torque tube 336, a second torque tube 340 driven by the angle gearbox 338, and a rotary fold actuator 342 driven by the second torque tube 340. The rotary fold actuator 342 is aligned on the hinge axis 214 and connected to a wing tip structure 344. Rotation of the second torque tube 340 causes the rotary fold actuator 342 to rotate about the hinge axis 214, which causes the wing tip 102 to rotate about the hinge axis 214. The powered drive unit 332 is connected to a main section structure 346 of the main section 106 of the wing 104. The powered drive unit 332 may be a hydraulic unit including a first unit configured to rotate a first torque tube 336 in a first direction to cause the wing tip 102 to rotate about the hinge axis 214 by the rotary fold actuator 342 towards the flight position, and a second unit configured to rotate the first torque tube 336 in a second direction to cause the wing tip 102 to rotate about the hinge axis 214 by the rotary fold actuator 342 towards the folded position in the second direction. The first and second units of the powered drive unit 332 are each coupled to the hydraulic controller 318 by a hydraulic supply line and a hydraulic return line.

[0037]

[0047] The latch pin system 306 includes a plurality of latch pin actuators 334, a drive train 348 connected to a drive shaft of a locking system 350 of the latch pin actuators 334, a drive train actuator 352 configured to rotate the drive train 348, a plurality of wing tip lugs 354 structurally connected to the wing tip structure 344 such that rotation of the rotary fold actuator 342 about the hinge axis 214 rotates the plurality of wing tip lugs 354, and a plurality of main portion lugs 356 that are part of the main portion structure 346. The lugs 354, 356 include support structures with openings sized to receive latch pins 358 of the latch pin actuators 334 when the openings are aligned and the wing tip 102 is in the flight position.

[0038]

[0048] The latch pin actuators 334 are connected to the main section structure 346 in communication with openings in the lugs 356 of the main section. The latch pin actuators may be the latch pin actuators shown and described in U.S. Pat. No. 5,427,329 or similar thereto. FIG. 3 shows four latch pin actuators 334. In other embodiments, each folding wingtip system 230 may include a different number of latch pin actuators 334. Each latch pin actuator 334 may be a hydraulic unit configured to extend a latch pin 358 of the latch pin actuator 334 through an opening in a lug 354, 356 associated with the latch pin actuator 334 to secure the wingtip 102 in the flight position. Each latch pin actuator 334 is also configured to retract the latch pin 358 from the opening in the lug 354, 356 to allow the wingtip actuation system 304 to rotate the wingtip 102 to the folded position.

[0039]

[0049] Each latch pin actuator 334 includes a first hydraulic fluid port, a second hydraulic fluid port, a latch pin 358, and a locking system 350. When hydraulic fluid is provided by one of the hydraulic controllers 318 through a first hydraulic line to the first hydraulic fluid port of the latch pin actuator 334, the hydraulic fluid fills and expands a first chamber of the latch pin actuator 334, causing the latch pin 358 to extend from the housing of the latch pin actuator 334. When the first chamber expands, the second chamber of the latch pin actuator 334 contracts. Hydraulic fluid from the second chamber flows through a second hydraulic port and a second hydraulic line to the hydraulic controller 318. When hydraulic fluid is provided by one of the hydraulic controllers 318 through a second hydraulic line to the second hydraulic fluid port, the hydraulic fluid fills and expands a second chamber of the latch pin actuator 334, causing the latch pin 358 to retract into the housing. When the second chamber expands, the first chamber contracts. Hydraulic fluid from the first chamber flows through a first hydraulic port and a first hydraulic line to a hydraulic controller 318 .

[0040]

[0050] The drive train actuator 352 is configured to rotate the drive train 348 in a first direction to a locked position, causing the locking system 350 to place a locking member in a position that prevents retraction of the latch pin 358 of the latch pin actuator 334, and to rotate the drive train 348 in a second direction to an unlocked position, causing the locking system 350 to move the locking member to a position where the latch pin 358 may be retracted into the housing of the latch pin actuator 334. The drive train actuator 352 may be a hydraulic unit or an electric drive unit.

[0041]

[0051] During execution of a command received by one of the electronic controllers 316 from the flight control computer 202 to employ the folding wingtip system 230, the electronic controller 316 executes an extend instruction 326 or a fold instruction 328 depending on the command. Upon executing the instruction 326 or the instruction 328, the electronic controller 316 sends a signal to employ the latch pin system 306. The signal includes a signal to the drive train actuator 352 to rotate the drive train 348 to an unlocked position or to idle the drive train actuator 352 to rotate the drive train 348 to a locked position. The wingtip extension anomaly detector 110B receives sensor data from a corresponding drive train actuator position sensor 312 and a corresponding drive train position sensor 314. The wingtip extension anomaly detector 110B analyzes the sensor data. If the analysis indicates that the latch pin system 306 did not function properly, the wingtip extension anomaly detector 110B stops execution of the procedure, sets one or more error codes, and sends a notification signal to the flight control computer 202 indicating a failure of the command. The notification signal includes the one or more error codes. In response to the notification signal, the flight control computer 202 may change settings to indicate that the aircraft 100 should remain on the ground and may schedule maintenance for the aircraft 100 based on the one or more error codes.

[0042]

[0052] For example, if the electronic controller 316A sends a signal to the drivetrain actuator 352 to cause the drivetrain actuator 352 to rotate the drivetrain 348 to a locked position, and data from the drivetrain actuator position sensor 312A indicates that the drivetrain 348 is idle and data from the drivetrain position sensor 314A associated with the electronic controller 316A indicates that the drivetrain 348 is not in a locked position, the notification signal sent by the wingtip extension anomaly detector 110B to the flight control computer 202 includes one or more first error codes (e.g., one or more numbers, one or more characteristics, or both) that cause scheduled maintenance for the aircraft 100 to include maintenance of the drivetrain actuator. As another example, if the electronic controller 316A sends a signal to the drivetrain actuator 352 to rotate the drivetrain 348 to an unlocked position and data from the drivetrain actuator position sensor 312A indicates that the drivetrain 348 is set to rotate the drivetrain 348 to an unlocked position, but data from the drivetrain position sensor 314A indicates that the drivetrain 348 is not within the unlocked position after a threshold time has elapsed, the notification signal causes scheduled maintenance of the aircraft 100 to include maintenance of the latch pin actuator and includes one or more second error codes identifying the one or more latch pin actuators 334 that are not functioning properly.

[0043]

[0053] The braking system 308 secures the wing tip 102 in the folded position. In some implementations, the braking system 308 is a hydraulic unit connected to an output of the powered drive unit 332. The braking system 308 includes a torque limiter and a clutch. When the braking system 308 is in the locked configuration, no hydraulic fluid is supplied to the braking system 308 and the torque limiter is biased against the output of the powered drive unit 332, securing the wing tip 102 in place and preventing movement of the wing tip 102. When hydraulic fluid is supplied to the braking system 308, the braking system 308 transitions to an unlocked configuration. The hydraulic fluid actuates the clutch and disengages the torque limiter, allowing the first torque tube 336 to be rotated by the powered drive unit 332 to rotate the wing tip 102.

[0044]

[0054] During use of the aircraft 100, the flight control computer 202 is configured to send a fold command to one or more electronic controllers 316 associated with the folding wingtip system 230 to rotate the wingtips 102 of the aircraft 100 from a flying position to a folded position. The fold command may be sent automatically based on one or more conditions associated with the operation of the aircraft 100 (e.g., a taxi-in flight phase after landing and a speed below a threshold speed) or may be sent in response to a crew input that does not violate one or more conditions associated with the use of the folding wingtip system 230 to move the wingtips 102 from a flying position to a folded position. If the crew input violates one or more conditions associated with the use of the folding wingtip system 230, the warning system 226 indicates any violation and the flight control computer 202 does not send a fold command to one of the electronic controllers 316.

[0045]

[0055] When the electronic controller 316 associated with the wing tip 102 receives the fold command, the electronic controller 316 sends an open signal to the shutoff valve 320. The electronic controller 316 sends a number of signals to the drive train actuator 352 and a hydraulic controller 318 associated with the electronic controller 316 to cause the latch pin 358 of the latch pin actuator 334 to retract from the main section lug 356 and the wing tip lug 354. If the sensor data received from the drive train actuator position sensor 312 and the drive train position sensor 314 associated with the electronic controller 316 indicates that the latch pin 358 is retracted, the electronic controller 316 sends a signal to the brake system 308 to change the brake system 308 from a locked configuration to an unlocked configuration and sends a signal to the hydraulic controller 318 to actuate the wing tip actuation system 304 to rotate the wing tip 102 to the folded position. When the electronic controller determines that the data from the hinge line sensor 310 indicates that the wing tip 102 is in the folded position, the electronic controller 316 sends signals to the hydraulic controller 318 to deactivate the drive train actuator 352 and rotate the drive train 348, change the brake system 308 from an unlocked configuration to a locked configuration, lock the wing tip 102 in the folded position, deactivate the powered drive unit 332, and deactivate the supply of hydraulic fluid to the latch pin actuator 334 that maintains the latch pin 358 in the retracted position. The wing tip extension anomaly detector 110B sends a notification signal to the flight control computer 202 indicating completion of the fold command. A close signal is sent to the shutoff valve 320.

[0046]

[0056] If during execution of the fold instruction 328, the wingtip extension anomaly detector 110B determines that the fold command is not completed, the wingtip extension anomaly detector 110B stops further execution of the fold instruction 328 and sends a notification signal to the flight control computer 202 indicating a failure of the fold command. The notification signal includes one or more error codes that can be used by the maintenance scheduler 228 to schedule specific maintenance to address the possible cause of failure of the folding wingtip system 230 and repair the folding wingtip system 230 so that the aircraft 100 is airworthy.

[0047]

[0057] For example, if the wingtip extension anomaly detector 110B detects based on data from the hinge line sensor 310 associated with the electronic controller 116 that the wingtip 102 has first moved from a flying position to a folded position and then returned to the flying position, the wingtip extension anomaly detector 110B stops further execution of the fold command 328 and the notification signal sent to the flight control computer 202 includes an error code indicative of the wingtip 102 dropping. The error code includes one or more first codes that cause the aircraft 100 to schedule maintenance of the wingtip actuation system 304 to identify and repair one or more portions of the wingtip actuation system 304 that allowed the wingtip 102 to drop (e.g., first torque tube 336, second torque tube 340, etc.) and one or more second codes based on the position of the wingtip 102.

[0048]

[0058] If the position of the wing tip 102 is at or near the flight position, the one or more second codes include one or more specific codes that instruct the flight control computer 202 to schedule the aircraft for tip-to-stop drop maintenance. The tip-to-stop drop maintenance includes instructions to remove the tip lugs 354 and lug stops 360 of the main portion 106 that limit the rotation range of the wing tip 102 and replace the removed tip lugs 354 and lug stops 360. The first set of removed wing tip lugs 354 with visible damage (e.g., warping, cracks, etc.) are identified as scrap. The second set of removed wing tip lugs 354 without visible damage are subject to testing (e.g., x-ray imaging, ultrasonic imaging, or other non-destructive testing methods) to determine if the tip lugs 354 have non-visible damage. Tip lugs 354 with non-visible damage may be identified as scrap, and in some embodiments, tip lugs 354 without visible or non-visible damage may be recycled.

[0049]

[0059] If the position of the wing tip 102 is within the latch pin interference range, the one or more second codes include one or more codes instructing the flight control computer 202 to schedule the aircraft 100 for drop maintenance from the wing tip to the latch pin. The latch pin interference range corresponds to an angular range of the wing tip 102 relative to the main portion, as indicated by data from the hinge line sensor 310, over which one or more wing tip lugs 354 may contact one or more latch pins 358 of the latch pin actuator 334. The latch pin interference range may be a narrow range (e.g., 14 degrees to 15 degrees or other range) for latch pin systems 306 in which the central axes of the latch pins 358 are aligned with the hinge axis 214, or a wider range (e.g., 10 degrees to 20 degrees or other range) for latch pin systems 306 in which the central axes of the one or more latch pins 358 are not aligned with the hinge axis 214. The central axis of one or more latch pins 358 may not be aligned with the hinge axis 214 due to spacing limitations within the wing 104, and / or it may be possible to determine which particular latch pins 358 are contacted by one or more wing tip lugs 354 based on the angle of the wing tip 102.

[0050]

[0060] The tip-to-latch pin drop maintenance includes identifying one or more specific latch pins 358 contacted by one or more specific tip lugs 354 and instructions to replace each of the one or more specific latch pins 358 with a replacement latch pin 358. Replacing the latch pins 358 may involve removing the latch pins 358 from the latch pin actuator 334 and replacing the latch pins 358 with the replacement latch pins 358 or replacing the latch pin actuator 334 with another latch pin actuator 334. A first subset of the contacted latch pins 358 that have visible damage (e.g., dents or cracks) are identified as scrap. A second subset of the contacted latch pins 358 that do not include visible damage are subject to testing to determine if there is non-visible damage. Based on the testing, in some embodiments, the contacted latch pins 358 that are free of visible and non-visible damage may be reused. And, the contacted latch pins 358 that have visible or non-visible damage are identified as scrap.

[0051]

[0061] The tip-to-latch pin drop maintenance also includes identifying one or more specific tip lugs 354 that contacted the latch pin 358 and instructions to replace each of the one or more specific tip lugs 354 with a replacement tip lug 354. A first subset of the tip lugs 354 that contacted the latch pin 358 and include visible damage are identified as scrap. A second subset of the tip lugs 354 that contacted the latch pin 358 and do not include visible damage are subject to testing to determine if there is non-visible damage. Based on the testing, in some embodiments, the tip lugs 354 that are free of visible and non-visible damage may be reused. And, the tip lugs 354 that have visible or non-visible damage are identified as scrap.

[0052]

[0062] During use of the aircraft 100, flight control computer 202 is configured to transmit extend commands to one or more electronic controllers 316 associated with folding wingtip system 230 to move the wingtips 102 of the aircraft 100 from a folded position to a flight position. Flight control computer 202 may automatically transmit the extend commands based on the occurrence of one or more conditions (e.g., the position of the aircraft 100 is within an area permitted to have the wingtips 102 in a flight position, the flight phase of the aircraft 100 is taxiing out or taxiing in, etc.) or in response to crew input that, if executed, does not violate one or more conditions that prohibit having the wingtips 102 in a flight position.

[0053]

[0063] Prior to sending the extend command, the wingtip extension anomaly detector 110A of the flight control computer 202 determines whether the folding wingtip system 230 is functional based on data received from one or more of the electronic controllers 316 indicating the position of the wingtip 102. If the wingtip extension anomaly detector 110A determines that the folding wingtip system 230 is functional, the wingtip extension anomaly detector 110A sends an extend command to the one or more controllers 316.

[0054]

[0064] In response to the extend command, the electronic controller 316 executes the extend instruction 326 and sends an open signal to the shutoff valve 320. The electronic controller 316 sends a number of signals to the drive train actuator 352, the hydraulic controller 318 associated with the electronic controller 316, and the latch pin system 306 to retract the latch pin 358 of the latch pin actuator 334 so that the wing tip lug 354 can rotate into position relative to the main portion lug 356 without contacting any of the latch pins 358. If the sensor data received from the drive train actuator position sensor 312 and the drive train position sensor 314 associated with the electronic controller 316 indicates that the latch pin 358 is retracted, the electronic controller 316 sends a signal to change the brake system 308 from a locked configuration to an unlocked configuration and sends a signal to the hydraulic controller 318 to actuate the wing tip actuation system 304 to rotate the wing tip 102 to a flight position. When the electronic controller 316 determines that the data from the hinge line sensor 310 indicates that the wingtip 102 is in the flight position, the electronic controller 316 sends a signal to the drive train actuator 352 to rotate the drive train 348 towards the locked position, and sends a plurality of signals to the hydraulic controller 318 to the latch pin actuator 334 to extend the latch pin 358 through the openings in the main section lug 356 and the wingtip lug 354, stop operation of the powered drive unit 332, and change the brake system 308 from an unlocked configuration to a locked configuration. If the data from the drive train position sensor 314 indicates that the locking system 350 is fully locked, the wingtip extension anomaly detector 110B sends a notification signal to the flight control computer 202 indicating completion of the extend command. A close signal is sent to the shutoff valve 320.

[0055]

[0065] If the wingtip extension anomaly detector 110B determines that the extend command is stopped prior to completion, the wingtip extension anomaly detector 110B stops further execution of the extend instructions 326 and sends a notification signal to the flight control computer 202 indicating a failure of the extend command. The notification signal includes one or more error codes that can be used by the maintenance scheduler 228 to schedule specific maintenance to address the possible cause of the extend command failure and repair the aircraft 100.

[0056]

[0066] For example, if the wingtip extension anomaly detector 110B detects, based on data from a hinge line sensor 310 associated with the electronic controller 116, that the wingtip 102 initially moves from a folded position toward a flight position and stops before reaching the flight position, the wingtip extension anomaly detector 110B stops further execution of the extension instructions 328 and sends a notification signal to the flight control computer 202 with one or more specific error codes. The one or more specific error codes depend on the angle of the wingtip 102 relative to the main portion 106. If the angle of the wingtip 102 is not within the latch pin interference range, the one or more specific error signals include one or more first error codes that cause the flight control computer 202 to schedule maintenance of the aircraft 100, including testing of components of the wingtip actuation system 304, to determine the cause of the wingtip 102 motion being stopped and to repair the wingtip actuation system 304. If the angle of the wingtip 102 is within the latch pin interference range, the one or more particular error codes include one or more second error codes that cause the flight control computer 202 to determine if one or more wingtip lugs 354 have contacted a corresponding latch pin 358 and, if so, schedule maintenance of the aircraft 100, including performing drop maintenance from the wingtip to the latch pins. The one or more second error codes also include one or more error codes that, if there is no contact between the one or more wingtip lugs 354 and the corresponding latch pins 358, schedule maintenance to determine the cause of the wingtip 102 stopping motion and repair the wingtip actuation system 304.

[0057]

[0067] As another example, if wingtip extension anomaly detector 110B determines that wingtip 102 has arrived at or near the flight location within a time faster than the threshold time, the signal sent to flight control computer 202 includes one or more third error codes indicating that there has been a wingtip-to-stop drop. Based on the one or more third error codes, flight control computer 202 changes certain settings to indicate that aircraft 100 should remain on the ground to repair the wingtip actuation system and to schedule maintenance of aircraft 100, including the wingtip-to-stop drop and maintenance of the wingtip actuation system.

[0058]

[0068] 4 illustrates a flow chart of an embodiment of a first method 400 of using the folding wingtip system 230. The method 400 may be performed by the flight control computer 202, including the maintenance scheduler 228 and the wingtip extension anomaly detector 110A. The method 400 includes, at block 402, determining that the last command completed by the folding wingtip system 230 was a fold command. The determination may include checking that the last command executed by the folding wingtip system 230 was a fold command based on data 220 stored in the memory 218 of the flight control computer 202. The determination is made when the aircraft 100 transitions from an idle or unpowered state to a powered state. The determination may also be made periodically when the aircraft 100 is powered by the engines 208 of the aircraft 100 or by connection to an external power source.

[0059]

[0069] The determination may also be made in response to a determination to send an extend command to move the wingtips 102 from a folded position to a flight position using the folding wingtip system 230. The determination to use the folding wingtip system 230 may be made automatically based on the conditions of use of the aircraft 100 (e.g., the aircraft 100 is in a taxi-in phase and is not in a section of the airport where having the wingtips 102 in a flight position is prohibited) determined by the flight control computer 202 based on sensor data from the sensor system 212, input received from the flight crew to execute the extend command that does not violate one or more conditions associated with the change to the flight position, or a combination thereof. If the input from the flight crew does not violate one or more conditions, the warning system 226 provides an output to inform the flight crew of the issue associated with the extend command and the flight control computer 202 does not cause the extend command to be executed.

[0060]

[0070] The method 400 includes, at block 404, determining a tip position of the wing tip 102. Determining the wing tip position may include sending a wing tip position request to the folding wing tip system 230 and receiving position data from the hinge line sensor 310. The position data corresponds to an angle of the wing tip 102 relative to the main portion 106 of the wing 104.

[0061]

[0071] The method 400 determines whether the wing tip position is within a folded position at decision block 406. If the wing tip 102 is determined to be within a folded position at decision block 406 and the method 400 is performed based on a determination to send an extend command to the folding wing tip system 230, the method 400 includes, at optional block 408, sending an extend command to the electronic controller 316 of the folding wing tip system 230 associated with the wing tip 102, and the method 400 ends at block 410. If the wing tip 102 is determined to be within a folded position at decision block 406 and the method is not performed based on a determination to send an extend command to the folding wing tip system 230, the method 400 ends at block 410.

[0062]

[0072] If, at decision block 406, it is determined that the wing tip 102 is not in the folded position, the method 400 includes, at block 412, setting error codes for the folding wing tip system 230. The error codes include an error code associated with a failure of the braking system 308 and an error code associated with a failure of the wing tip actuation system 304. An error code associated with a failure of the braking system 308 causes the maintenance scheduler 228 of the flight control computer 202 to schedule brake system maintenance, determine why the braking system 308 failed, and repair the braking system 308. An error code associated with a failure of the wing tip actuation system 304 causes the maintenance scheduler 228 to schedule wing tip actuation system maintenance, determine which one or more components of the wing tip actuation system 304 failed causing the wing tip 102 to drop, and repair the wing tip actuation system 304.

[0063]

[0073] The error code also includes one or more additional error codes that depend on the angle of the wing tip 102 determined based on the position data. For example, if the angle of the wing tip 102 is within the latch pin interference range, the error code includes one or more additional error codes indicating that the wing tip 102 may have dropped and contacted the latch pin 358, and the maintenance would include drop maintenance from the wing tip to the latch pin. And, if the wing tip is in flight position or substantially in flight position (e.g., within 1 degree, 2 degrees, or other small number of degrees), the error code includes one or more additional error codes indicating that the wing tip 102 has dropped, and the maintenance would include drop maintenance from the wing tip to the stop.

[0064]

[0074] Method 400 includes, at block 414, changing a setting to indicate that aircraft 100 should remain on the ground, which causes flight control computer 202 to not allow aircraft 100 to fly. Method 400 also includes, at block 416, scheduling maintenance on aircraft 100. The type of maintenance scheduled for the aircraft is based on the error code. Method 400 then ends at 410.

[0065]

[0075] 5 shows a flow chart of an embodiment of a second method 500 of using the folding wing tip system 230. The method 500 may be performed by the flight control computer 202. The method 500 includes, at block 502, sending a command to a first electronic controller 316A of the folding wing tip system 230 to move the wing tip 102 from a first position to a second position. The command may be a fold command to move the wing tip 102 from a flight position to a folded position, or the command may be an extend command to move the wing tip 102 from a folded position to a flight position.

[0066]

[0076] The method 500 includes, at block 504, receiving a first notification signal from the first electronic controller 316A regarding executing the command. The method 500 includes, at decision block 506, determining whether the command completed successfully based on content of the notification. If, at decision block 506, it is determined that the command completed successfully, the method 500 ends at block 508. If, at decision block 506, it is determined that the command did not complete successfully, the method 500 includes, at block 510, changing a setting to indicate that the aircraft 100 should remain on the ground. The method 500 includes, at block 512, scheduling maintenance on the aircraft 100, the type of maintenance based on one or more error codes included in the first notification signal.

[0067]

[0077] If, at decision block 506, it is determined that the command did not complete successfully, then the problem with the folding wingtip system 230 may be a problem with one or more sensors associated with the first electronic controller 316A and not a problem with the mechanics of the folding wingtip system 230. The redundant control system 316B of the folding wingtip system 230 may be used to determine if the problem with the folding wingtip system 230 is a problem with one or more of the sensors associated with the first electronic controller 316A. If the problem is a problem with one or more sensors, the aircraft 100 does not need to remain on the ground for maintenance, but maintenance can be scheduled on the sensors associated with the electronic controller 316A at a convenient time, and the aircraft 100 may be used for one or more additional flights.

[0068]

[0078] In conjunction with determining whether the command did not complete successfully due to one or more sensors associated with the first electronic controller 316A, the method 500 includes sending the command to the second electronic controller 316B, at block 514. The method 500 includes receiving a second notification signal from the second controller 316B regarding executing the command, at block 516.

[0069]

[0079] The method 500 includes, at decision block 518, determining whether the command completed successfully based on content of the second notification. When the command is determined to have completed successfully at decision block 518, the method 500 includes, at block 520, modifying a setting to indicate that the aircraft 100 is not to remain on the ground. The method 500 includes, at block 522, modifying the scheduled maintenance to include servicing of a sensor system associated with the first electronic controller 316A. The method 500 then ends at 508.

[0070]

[0080] If, at decision block 518, it is determined that the command did not complete successfully, the method 500 includes determining whether the error codes in the notification signals are the same, at decision block 524. If, at decision block 518, it is determined that the notification signals include the same error codes, the method 500 ends at 508. If, at decision block 524, it is determined that the notification signals include different error codes, at block 526, the method 500 includes modifying the maintenance scheduled for the aircraft to include maintenance based on all error codes in the notification signals. The method 500 then ends at 508.

[0071]

[0081] 6 illustrates a flow chart of an embodiment of a third method 600 of using the folding wingtip system 230 to execute an extend command. The method 600 may be used to change the position of the wingtip 102 from a folded position to a flying position. The method 600 may be performed by one of the electronic controllers 316 in response to receiving an extend command from the flight control computer 202. The method 600 includes using the extend indication 326 and the wingtip extension anomaly detector 110B. The method 600 includes sending an open signal to the isolation valve 320 at block 602. Opening the isolation valve enables hydraulic powered components of the folding wingtip system 230 to function when supplied with hydraulic fluid from a hydraulic controller 318 associated with the electronic controller 316.

[0072]

[0082] Method 600 determines whether shutoff valve 320 is open at decision block 604. The determination is based on data from the valve sensor. If it is determined at decision block 604 that the shutoff valve was not open, method 600 includes setting a shutoff valve error code at block 606. Method 600 includes sending a notification signal to flight control computer 202 at block 608. The notification signal includes the shutoff valve error code, which causes aircraft 100 to be grounded and scheduled for maintenance to fix one or more problems associated with the shutoff valve, the valve sensor, or both. Method 600 ends at block 610.

[0073]

[0083] If, at decision block 604, it is determined that the shutoff valve 320 is open, the method 600 includes, at block 612, sending a first series of signals to fully retract the latch pin 358 of the latch pin actuator 334. The first signals may include a signal to the hydraulic controller 318 to supply hydraulic fluid to the latch pin system 306 and a signal to the drivetrain actuator 352 to rotate the drivetrain 348.

[0074]

[0084] The method 600 determines whether the locking system 350 of the latch pin actuator 334 operated correctly at decision block 614. The determination may be based on sensor data from the drivetrain actuator position sensor 312 and the drivetrain position sensor 314. If it is determined at decision block 614 that the locking system 350 did not operate correctly, the method 600 includes closing the isolation valve 320 by sending a close signal to the isolation valve 320 at block 616.

[0075]

[0085] The method 600 determines at decision block 618 whether the shutoff valve 320 was operated correctly to close the shutoff valve 320. If it is determined at decision block 618 that the shutoff valve 320 was not operated correctly, the method includes setting one or more shutoff valve error codes at block 620. The method 600 includes setting one or more error codes at block 622. Also, if it is determined at decision block 618 that the shutoff valve was operated correctly to close the shutoff valve 320, the method 600 moves to block 622 and sets one or more error codes. The error codes may indicate that one or more of the locking systems 350 did not function correctly. The method 600 proceeds to block 608 and sends a notification signal to the flight control computer 202. The notification signal includes the error codes, any shutoff valve error codes, and indicates a failure of the extended command. The method 600 then ends at block 610.

[0076]

[0086] If, at decision block 614, it is determined that the locking system 350 operated correctly, the method 600 includes, at block 624, sending a second series of signals to change the braking system 308 from a locked configuration to an unlocked configuration and actuate the wing tip actuation system 304 to move the wing tip 102 from the folded position to the flight position.

[0077]

[0087] The method 600 determines whether the wing tip 102 has reached a flying position at decision block 626. The determination may be based on hinge line sensor data from the hinge line sensor 310, which indicates the angle of the wing tip 102 relative to the main portion 106 of the wing 104.

[0078]

[0088] If at decision block 626 it is determined that the wing tip 102 has not reached the flight position, the method 600 proceeds to block 616 and then to decision block 618. After execution of decision block 618 or decision blocks 618 and 620, the method 600 returns to block 622 to set one or more error codes. The one or more error codes may include a specific error code based on an analysis of the hinge line sensor data, the clock data, or both. If the hinge line sensor data indicates that the wing tip 102 has not moved from the folded position, a specific error code is set that indicates a problem associated with the braking system 308 and the wing tip actuation system 304.

[0079]

[0089] If the hinge line sensor data indicates that the wing tip 102 has stopped at a position outside the latch pin interference range, a specific error code is set indicating a problem associated with the wing tip actuation system 304. If the hinge line sensor data indicates that the wing tip 102 has stopped within the latch pin interference range, a specific error code is set indicating the occurrence of a wing tip to latch pin drop. If the wing tip 102 has stopped within the latch pin interference range due to a failure of the wing tip actuation system 304 without contacting one or more of the latch pins 358, if the wing tip actuation system 304 has failed and the wing tip lugs 354 have dropped and may contact one or more of the latch pins 358, or if the wing tip actuation system 304 has not failed and one or more of the wing tip lugs 354 have been driven by the wing tip actuation system 304 against one or more of the latch pins 358, the specific error code allows for scheduled maintenance to determine and address the problem that may have occurred.

[0080]

[0090] If the clock data indicates that the wingtip reached a flight position or near a position too quickly (e.g., faster than a threshold time), a specific error code indicates that a tip-to-stop drop has occurred. The error code allows for scheduled maintenance to address issues with the wingtip actuation system 304 that may have caused the wingtip 102 to drop, and to address damage that may have occurred as a result of the wingtip 102 dropping.

[0081]

[0091] If, at decision block 626, it is determined that the wing tip 102 has reached the flight position, the method 600 includes, at block 628, sending a third series of signals to deactivate the wing tip actuation system 304 and provide hydraulic fluid to the latch pin actuator 334 to extend the latch pin 358 through the wing tip lug 354 and the main section lug, and change the brake system 308 to a locked configuration. Once the latch pin 358 is extended through the wing tip lug and the main section lug, the wing tip is secured to the main section 106 and the aircraft 100 is configured for flight.

[0082]

[0092] The method 600 includes determining whether the action based on the third series of signals was completed successfully at decision block 630. If it is determined at block 630 that the action based on the third series of signals was not completed successfully, the method 600 proceeds to block 616 and then to decision block 618. From decision block 618, or from decision block 618 and block 620, the method 600 proceeds to block 622 to set one or more error codes. For example, if data from drivetrain position sensor 314 indicates that drivetrain 348 did not reach a fully locked position, the one or more error signals may include a particular error code indicative of a fault in locking system 150, drivetrain 348, or both.

[0083]

[0093] If, at decision block 630, it is determined that the action based on the third series of signals was completed successfully, then the method 600 includes, at block 632, closing the shut-off valve 320. The method 600 determines, at decision block 634, whether the shut-off valve was closed. If, at decision block 634, it is determined that the shut-off valve 320 was not closed, then the method 600 includes, at block 636, setting a shut-off valve error code. The method proceeds to block 608, where it sends a notification signal to the flight control computer 202, and the method 600 ends at block 610. The notification signal indicates that the extended command failed and includes the shut-off valve error code. The flight control computer 202 grounds the aircraft 100 and schedules appropriate maintenance to address the issue with the shut-off valve 320 in response to the notification signal.

[0084]

[0094] If, at decision block 634, it is determined that the shut-off valve 320 is closed, the method 600 includes, at block 638, sending a notification signal to the flight control computer 202 indicating completion of the extended command. The method then ends at block 610. The notification signal sent to the flight control computer 202 at block 638 may include one or more shut-off valve error codes that indicate a problem with one or more valve sensors if the open signal sent to the shut-off valve 320 at block 602, the close signal sent to the shut-off valve at block 632, or both, were executed by the redundant electronic controller 316 rather than by the electronic controller 316 executing the extended instructions 326. In response to the presence of at least one shut-off valve error code in the notification signal indicating completion of the extended command, the flight control computer 202 schedules maintenance to address the problem with the valve sensor.

[0085]

[0095] 7 shows a flow chart of an embodiment of a fourth method 700 of using folding wingtip system 230 to execute a fold command. Method 700 may be used to change the position of wingtip 102 from a flying position to a folded position. Method 700 may be performed by one of electronic controllers 316 in response to receiving a fold command from flight control computer 202. Method 700 includes using fold indication 328 and wingtip extension anomaly detector 110B. Method 700 includes sending an open signal to shutoff valve 320 at block 702.

[0086]

[0096] Method 700 determines, at decision block 704, whether shut-off valve 320 was open. The determination is based on data from the valve sensor. If, at decision block 704, it is determined that the shut-off valve was not open, method 700 includes setting a shut-off valve error code, at block 706. Method 700 includes sending a notification signal, at block 708, to flight control computer 202. The notification signal includes the shut-off valve error code, which causes aircraft 100 to be grounded and / or scheduled for maintenance to fix one or more problems associated with the shut-off valve, the valve sensor, or both. Method 700 ends at 710.

[0087]

[0097] If, at decision block 704, it is determined that the shutoff valve is open, the method 700 includes, at block 712, placing the brake system 308 in an unlocked configuration and sending a first series of signals to the latch pin system 306 to retract the latch pin 358 from the openings in the tip lugs 354 and the main section lugs 356. The signals may include signals from the electronic controller 316 to the corresponding hydraulic controllers 318 and signals to the drive train actuators 352 to rotate the drive train 348.

[0088]

[0098] The method 700 determines whether the locking system 350 of the latch pin actuator 334 operated correctly at decision block 714. The determination may be based on sensor data from the drivetrain actuator position sensor 312 and the drivetrain position sensor 314. If it is determined at decision block 714 that the locking system 350 did not operate correctly, the method 700 includes closing the isolation valve 320 at block 716.

[0089]

[0099] The method 700 determines at decision block 718 whether the shut-off valve 320 was operated correctly to close the shut-off valve 320. If it is determined at decision block 718 that the shut-off valve 320 was not operated correctly, the method includes setting one or more shut-off valve error codes at block 720. The method 700 includes setting one or more error codes at block 722. Also, if it is determined at decision block 718 that the shut-off valve was operated correctly to close the shut-off valve 320, the method 700 moves to block 722 and sets one or more error codes. The error codes may indicate that one or more of the locking systems 350 did not function correctly. The method 700 proceeds to block 708 and sends a notification signal to the flight control computer 202. The notification signal includes the error codes, any shut-off valve error codes, and indicates failure of the fold command. The error code notifies flight control computer 202 to ground aircraft 100, allowing flight control computer 202 to schedule appropriate maintenance for aircraft 100 and allowing aircraft 100 to return to service. Method 700 ends at block 710.

[0090]

[0100] If, at decision block 714, it is determined that the locking system 350 operated correctly, then the method 700 includes, at block 724, sending a second series of signals to the wing tip actuation system 304 to move the wing tip 102 to the folded position. At decision block 726, the method 700 determines whether the wing tip 102 has reached the folded position. The determination may be based on hinge line sensor data from the hinge line sensor 310 indicative of the angle of the wing tip 102 relative to the main portion 106 of the wing 104.

[0091]

[0101] If at decision block 726 it is determined that the wing tip 102 did not reach the folded position, the method 700 proceeds to block 716 and then to decision block 718. From decision block 718, or from blocks 718 and 720, the method 700 proceeds to block 722 to set one or more error codes. For example, the one or more specific error codes may be based on an analysis of the hinge line sensor data. If the hinge line sensor data indicates that the wing tip 102 did not lift, the specific error code may include one or more error codes indicative of a problem with one or more of the torque tubes 336, 340 of the wing tip actuation system 304. If the hinge line sensor data indicates that the wing tip 102 initially lifted and stopped at a particular angle, the specific error code may be one or more error codes indicative of a problem with the power drive unit 332, the angle gearbox 338, the rotary fold actuator 342, or a combination thereof. If the wing tip 102 first rises and then drops back down to or near the line position, the specific error codes may be an error code indicating a problem with one or more of the torque tubes 336, 340 of the wing tip actuation system 304 and an error code indicating a tip-to-latch drop of the wing tip 102 has occurred. If the wing tip 102 first rises and then drops to a stop within the latch pin interference range, the specific error codes may be an error code indicating a problem with the torque tubes 336, 340 of the wing tip actuation system 304 and an error code indicating a tip-to-latch pin drop has occurred. Additional error codes could be set based on hinge line sensor data or other sensor data.

[0092]

[0102] If, at decision block 726, it is determined that the wing tip 102 has reached the folded position, the method 700 includes, at block 728, sending a third series of signals to stop the hydraulic fluid supply, retract the latch pin 358, stop operation of the wing tip actuation system 304, and set the braking system 308 to a locked configuration. The method 700 proceeds to decision block 730 to determine whether the actions executed by the third set of signals were completed successfully.

[0093]

[0103] If at decision block 730 it is determined that the actions performed by the third set of instructions were not completed successfully, the method 700 proceeds to block 716 and then to decision block 718. From decision block 618, or from decision block and block 720, the method 700 proceeds to block 722 and sets one or more error codes after decision block 718. For example, if data from the brake system sensors indicates that the brake system 308 was not changed to a locked configuration, a particular error code is set to indicate a problem with the brake system 308 or a brake system sensor.

[0094]

[0104] If, at decision block 730, it is determined that the action based on the third series of signals was completed successfully, then the method 700 includes, at block 732, closing the shut-off valve 320. The method 700 determines, at decision block 734, whether the shut-off valve 320 was closed. If, at decision block 734, it is determined that the shut-off valve 320 was not closed, then the method 700 includes, at block 736, setting a shut-off valve error code. The method proceeds to block 708, where it sends a notification signal to the flight control computer 202, and the method 700 ends at block 710. The notification signal indicates that the extended command failed and includes the shut-off valve error code. The flight control computer 202 grounds the aircraft 100 and schedules appropriate maintenance to address the issue with the shut-off valve 320 in response to the notification signal.

[0095]

[0105] If, at decision block 734, it is determined that the shut-off valve 320 is closed, the method 700 includes, at block 738, sending a notification signal to the flight control computer 202 indicating completion of the fold command. The method then ends at block 710. The notification signal sent to the flight control computer 202 at block 738 may include one or more shut-off valve error codes that indicate a problem with one or more valve sensors if the open signal sent to the shut-off valve 320 at block 702, the close signal sent to the shut-off valve at block 732, or both, were executed by the redundant electronic controller 316 rather than by the electronic controller 316 executing the fold instructions 328. In response to the presence of at least one shut-off valve error code in the notification signal indicating completion of the fold command, the flight control computer 202 schedules maintenance to address the problem with the valve sensor.

[0096]

[0106] FIG. 8 is a flow chart illustrating a method 800 illustrating a life cycle of an aircraft including a flight control computer 202 with a wingtip extension anomaly detector 110A and the folding wingtip system 230 of FIG. 2. The folding wingtip system 230 includes (or is otherwise connected to) the wingtip extension anomaly detector 110B. During a pre-production stage, the example method 800 includes, at 802, a specification and design of an aircraft, such as the aircraft 100 described with reference to FIGS. 1A-3. During the specification and design of the aircraft, the method 800 may include a specification and design of the flight control computer 202 and the folding wingtip system 230. At block 804, the method 800 includes sourcing materials. The sourcing of materials may include sourcing components of the flight control computer 202 and the folding wingtip system 230.

[0097]

[0107] During the production phase, method 800 includes, at block 806, manufacturing of components and subassemblies, and, at block 808, system integration of the aircraft. For example, method 800 may include manufacturing components and subassemblies of flight control computer 202 and folding wing tip system 230. Method 800 may include, at block 810, certification and delivery of the aircraft, and, at block 812, placing the aircraft into service. Certification and delivery may include certification of flight control computer 202 and folding wing tip system 230 to place the flight control computer 202 and folding wing tip system 230 into service. While in service by the customer, the aircraft may be scheduled for routine maintenance and service, which may also include modifications, reconfigurations, refurbishments, etc. In block 814, method 800 includes performing maintenance and service on the aircraft. Maintenance and service may include performing maintenance and service on flight control computer 202 and folding wing tip system 230.

[0098]

[0108] Each of the processes of method 800 may be performed or implemented by a system integrator, a third party, and / or an operator (e.g., a customer). For purposes of this specification, a system integrator may include, but is not limited to, any number of aircraft manufacturers and subcontractors of major systems, a third party may include, but is not limited to, any number of vendors, subcontractors, and suppliers, and an operator may be an airline, a leasing company, a military entity, a service organization, etc.

[0099]

[0109] Aspects of the disclosure may be described in the context of an embodiment of an aircraft. A specific example of the aircraft 100 of FIGS.

[0100]

[0110] In the example of Figure 9, aircraft 100 includes an airframe 902 that includes a number of systems 904 and an interior 906. Examples of the number of systems 904 include one or more of a propulsion system 908, an electrical system 910, an environmental system 912, and a hydraulic system 914. Any number of other systems may be included. In the example shown in Figure 9, electrical system 910 includes some components of folding wing tip system 230 of Figure 2, and hydraulic system 914 includes other components of folding wing tip system 230. Electrical system 910 includes flight control computer 202 of Figure 2.

[0101]

[0111] 10 illustrates a block diagram of a computing environment 1000 including a computing device 1002 configured to support embodiments of computer-implemented methods and computer-executable program instructions (or codes) according to the present disclosure. For example, the computing device 1002, or portions thereof, may execute instructions to perform or cause an apparatus to perform the processes described with reference to FIGS. 2-9. In embodiments, the computing device 1002 is, or is a component of, the aircraft 100, flight control computer 202, folding wingtip system 230, and electrical controller 316 of FIGS. 1A-3.

[0102]

[0112] The computing device 1002 includes one or more processors 1004. The processor 1004 communicates with a system memory 1006, one or more storage devices 1008, one or more input / output interfaces 1010, one or more communication interfaces 1012, or a combination thereof. The system memory 1006 includes a non-transitory computer-readable medium, which may include volatile memory devices (e.g., random access memory (RAM) devices), non-volatile memory devices (e.g., read-only memory (ROM) devices, programmable read-only memory, and flash memory), or both. The system memory 1006 includes an operating system 1014, which may include a basic input / output system for booting the computing device 1002, as well as a full operating system for allowing the computing device 1002 to interact with a user, other programs, and other devices. The system memory 1006 includes one or more applications 1016 (e.g., instructions) executable by the processor 1004. For example, when the computing device 1002 is a flight control computer 202, the one or more applications 1016 include flight instructions 224, warning system 226, maintenance scheduler 228, and wing tip extension anomaly detector 110A, and when the computing device is an electronic controller 316, the one or more applications 1016 include extension instructions 326, fold instructions 328, and wing tip extension anomaly detector 110B.

[0103]

[0113] In some configurations, the processor 1004 communicates with one or more storage devices 1008. For example, the storage devices 1008 include non-transitory computer-readable media, which may include non-volatile storage devices, such as magnetic disks, optical disks, flash memory devices, etc. The storage devices 1008 may include both removable and non-removable memory devices. The storage devices 1008 may be configured to store an operating system, operating system images, applications, and program data. In certain implementations, the system memory 1006, the storage devices 1008, or both include tangible computer-readable media that are embedded in hardware and are not signals.

[0104]

[0114] In some configurations, the processor 1004 communicates with one or more input / output interfaces 1010 that enable the computing device 1002 to communicate with one or more input / output devices 1018 to facilitate interaction with a user. The input / output interfaces 1010 include serial interfaces (e.g., Universal Serial Bus (USB) interfaces or Institute of Electrical and Electronics Engineers (IEEE) interfaces), parallel interfaces, display adapters, audio adapters, and other interfaces ("IEEE" is a registered trademark of the Institute of Electrical and Electronics Engineers, Piscataway, NJ). The input / output devices 1018 include keyboards, pointing devices, displays (e.g., one or more monitors, one or more gauges, etc.), speakers, microphones, touch screens, rotary selectors, levers, knobs, slides, switches, and other devices. The processor 1004 detects an interaction event based on a user input received via the input / output interface 1010. In addition, the processor 1004 transmits a display to a display device via the input / output interface 1010.

[0105]

[0115] In some configurations, the processor 1004 may communicate with one or more devices 1020 via one or more communication interfaces 1012. The one or more devices 1020 may include external computing devices connected via a communication network, and controllers, sensors, and other devices connected to the computing device 1002 via a wired or wireless local connection. For example, when the computing device 1002 is the electronic controller 316 of FIG. 3, the computing device 1002 is configured to communicate with the flight control computer 202 and certain sensors of the folding wing tip system 230 of FIG. 2 via the interface 1012. The one or more communication interfaces 1012 may include a wired Ethernet interface, an IEEE 802 wireless interface, other wireless communication interface, one or more converters for converting analog signals to digital signals and electrical signals to optical signals, one or more converters for converting received optical signals to electrical signals, or other network interfaces.

[0106]

[0116] In some implementations, a non-transitory computer-readable medium stores instructions that, when executed by one or more processors, cause the one or more processors to initiate, execute, or control operations to perform some or all of the functionality described above. For example, the instructions may be executable to implement one or more of the operations or methods of FIGS. 1A-10. In some implementations, some or all of one or more of the operations or methods associated with FIGS. 1A-10 may be performed by one or more processors (e.g., one or more central processing units (CPUs), one or more graphics processing units (GPUs), one or more digital signal processors (DSPs)) executing instructions via dedicated hardware circuitry, or any combination thereof.

[0107]

[0117] Certain aspects of the present disclosure are described in the following series of interrelated examples.

[0108]

[0118] According to Example 1, an aircraft includes a wing including a main portion and a wing tip, and a folding wing tip system configured to rotate the wing tip relative to the main portion, the folding wing tip system including an electronic controller, the electronic controller configured to execute an extend command received from a flight control computer to rotate the wing tip from a folded position to a flight position, and in response to a determination during execution of the extend command that the rotation of the wing tip has stopped before the flight position, send a first signal to the flight control computer to ground the folding wing tip aircraft and schedule maintenance of the folding wing tip aircraft, the first signal indicating that the maintenance includes drop maintenance from the wing tip to the latch pin in response to a determination by the control unit that a first particular angle of the wing tip relative to the main portion is within a latch pin interference range.

[0109]

[0119] Example 2 includes the aircraft of example 1, where the wingtip-to-latch pin drop maintenance includes instructions to identify one or more specific latch pins contacted by one or more specific lugs on the wingtip, replace the one or more specific latch pins, identify a first subset of the one or more specific latch pins with visible damage as scrap, and subject a second subset of the one or more specific latch pins without visible damage to testing for non-visible damage.

[0110]

[0120] Example 3 includes the aircraft of example 2, wherein the drop maintenance from the wing tip to the latch pin further includes instructions to replace one or more of the wing tip lugs, identify a first subset of the wing tip lugs having visible damage as scrap, and subject a second subset of the wing tip lugs without visible damage to testing for non-visible damage.

[0111]

[0121] Example 4 includes the aircraft of any one of examples 1 to 3, wherein the first signal also causes a flight control computer to schedule maintenance of a wingtip actuation system of the aircraft.

[0112]

[0122] Example 5 includes the aircraft of any one of examples 1 to 4, wherein if a determination by the electronic controller indicates that the first particular angle is not within the latch pin interference range, the first signal indicates that the maintenance includes maintenance of a wingtip actuator.

[0113]

[0123] Example 6 includes the aircraft of any one of Examples 1 to 5, wherein the electronic controller is further configured to: receive a request from the flight control computer for position data related to an angle of the wing tip relative to the main portion; and transmit the position data to the flight control computer based on the data received from the hinge line sensor, wherein when a position of the wing tip indicated by the position data is not within the folded position, the flight control computer transmits the position data to ground the aircraft and schedule maintenance of the aircraft.

[0114]

[0124] Example 7 includes the aircraft of example 6, wherein the maintenance includes a brake system maintenance of the brake system configured to maintain the wing tips in the folded position.

[0115]

[0125] Example 8 is the aircraft of example 6 or example 7, wherein the maintenance includes drop maintenance from the wing tip to the latch pin when the angle of the wing tip relative to the main portion is within the latch pin interference range.

[0116]

[0126] Example 9 is the aircraft of example 6 or example 7, wherein the servicing includes drop servicing from the wing tip to the stop when the wing tip is in or near the flight position.

[0117]

[0127] Example 10 includes the aircraft of example 9, wherein the tip-to-stop drop maintenance includes replacing the tip lugs, replacing the lug stops at the main section, identifying a first subset of the tip lugs having visible damage for scrap, and subjecting a second subset of the tip lugs without visible damage to testing for non-visible damage.

[0118]

[0128] According to Example 11, a method includes executing an extend command received from a flight control computer by an electronic controller via an electronic controller of a folding wingtip system of the aircraft to rotate a wing tip from a folded position to a flight position; and in response to a first determination in the electronic controller that rotation of the wing tip has stopped before the flight position during execution of the extend command, sending a first notification signal from the electronic controller to the flight control computer to ground the aircraft and schedule maintenance of the aircraft, the first notification signal including one or more first error codes, and in response to a determination by the electronic controller indicating that a first particular angle of the wing tip relative to a main portion of the wing is within a latch pin interference range, sending a first notification signal to cause the maintenance to include drop maintenance from the wing tip to the latch pin.

[0119]

[0129] Example 12 includes the method of example 11, configured to, in response to a second determination that an execution time of the extended command from a start of execution of the extended command to a completion of execution of the extended command, as indicated when rotation of the wingtip relative to the main portion stops in a flight position, is less than a threshold execution time, wherein one or more first error codes indicate a wingtip-to-stop drop, and the one or more first error codes cause maintenance of the aircraft to include a wingtip-to-stop drop maintenance.

[0120]

[0130] Example 13 includes the method of example 11 or example 12, further including detecting, in the control unit, that the aircraft has transitioned from a power-down state to a power-up state; determining, in the control unit, a particular angle of the wing tip relative to the main portion; determining, in the control unit, that a last executed command to the folding wing tip system positioned the wing tip in a folded position; and if the particular angle differs from a first angle associated with the folded position, sending a signal to the flight computer to ground the aircraft and schedule maintenance on the aircraft.

[0121]

[0131] Example 14 includes the method of example 13, wherein the specified servicing includes drop servicing from the wing tip to the latch pin when the wing tip position data indicates that the wing tip is at a particular angle within the latch pin interference range.

[0122]

[0132] Example 15 includes the method of example 13, wherein servicing includes drop servicing from the wing tip to the stop when the wing tip position data indicates the wing tip is in or substantially in a flying position.

[0123]

[0133] Example 16 includes a method according to any one of examples 11 to 15, further including receiving at the control unit from the flight control computer a second command to transition the wingtip from the first position to the second position; sending control signals to the drivetrain actuator, the hydraulic control module, or both to execute the second command; and in response to a determination by the control unit that a locking system of the latch pin actuator has not functioned properly based on the drivetrain actuator data from the drivetrain actuator sensor and the drivetrain position data from the drivetrain position sensor, sending a specific notification signal to the flight control computer, the specific notification signal including one or more specific error codes associated with a locking system failure, the specific notification signal grounding the aircraft and scheduling specific maintenance of the aircraft, the specific maintenance including maintenance of the latch pin system.

[0124]

[0134] According to Example 17, the device includes a memory configured to store instructions and a processor configured to execute the instructions to perform a method described in any one of Examples 11 to 16.

[0125]

[0135] According to Example 18, a non-transitory computer-readable medium stores instructions that, when executed by a processor, cause the processor to perform a method according to any one of Examples 11 to 16.

[0126]

[0136] According to Example 19, the apparatus comprises means for carrying out the method according to any one of Examples 11 to 16.

[0127]

[0137] According to Example 20, a non-transitory computer-readable medium includes instructions executable by one or more processors of an aircraft electronic controller to execute an extend command received from a flight control computer to rotate a wing tip about a hinge axis from a folded position to a flight position, and in response to a first determination that rotation of the wing tip has stopped before the flight position during execution of the extend command, sending a first signal to the flight control computer to ground the aircraft and schedule aircraft servicing of the folded wing tip, the first signal being in response to a second determination indicating a first particular angle of the wing tip relative to a main portion of the wing is within a latch pin interference range, the first signal causing the servicing to include drop servicing from the wing tip to the latch pin.

[0128]

[0138] Example 21 includes the non-transitory computer-readable medium of example 20, wherein the instructions are further executable by one or more processors to: execute a fold command to transition the wing tips from a flying position to a folded position; determine that a position of the wing tips relative to the main portion is not in a folded position upon completion of execution of the fold command; and send a second notification signal to the flight control computer, the second notification signal including one or more second error codes related to the position, and based on the one or more second error codes, send a second notification signal to ground the aircraft and schedule certain maintenance of the aircraft.

[0129]

[0139] Example 22 includes the non-transitory computer readable medium of example 21, wherein the specific servicing includes drop servicing from the wing tip to the latch pin when the position is within the latch pin interference range.

[0130]

[0140] Example 23 includes the non-transitory computer readable medium of example 21, wherein servicing includes drop servicing from the wing tip to a stop when the location is in or near the flight position.

[0131]

[0141] According to Example 24, an aircraft comprises a wing including a main portion and a wing tip, a folding wing tip system configured to rotate the wing tip relative to the main portion, and a flight control computer, the flight control computer configured to perform the following in response to a first determination that the wing tip position of the wing tip is not within a folded position when a second determination indicates that the last completed command by the folding wing tip system was a fold command: set a first error code of the folding wing tip system; and change the setting to indicate that the aircraft will remain on the ground based on the first error code.

[0132]

[0142] Example 25 includes the aircraft of example 24, wherein the flight control computer is further configured to schedule maintenance for the aircraft based on the first error code.

[0133]

[0143] Example 26 includes the aircraft of example 25, wherein the maintenance includes maintenance of the braking system configured to maintain the wing tips in the folded position.

[0134]

[0144] Example 27 includes the aircraft of example 25 or example 26, wherein the maintenance includes maintenance of a wingtip actuation system.

[0135]

[0145] Example 28 includes the aircraft of any one of examples 25 to 27, wherein the maintenance includes drop maintenance from the wingtip to the latch pin in response to a third determination that the wingtip position is within the latch pin interference range.

[0136]

[0146] Example 29 includes the aircraft of example 28, wherein the wingtip-to-latch pin drop maintenance includes instructions to: identify one or more specific latch pins contacted by one or more specific lugs on the wingtip; replace the one or more specific latch pins; identify a first subset of the one or more specific latch pins with visible damage as scrap; and subject a second subset of the one or more specific latch pins without visible damage to testing for non-visible damage.

[0137]

[0147] Example 30 includes the aircraft of example 29, wherein the wingtip-to-latch pin drop maintenance further includes instructions to: replace one or more wingtip lugs; identify a first subset of the wingtip lugs having visible damage as scrap; and subject a second subset of the wingtip lugs without visible damage to testing for non-visible damage.

[0138]

[0148] Example 31 includes the aircraft of any one of examples 25 to 27, where in response to a third determination that the wingtip position is at or near the flight position, the maintenance includes drop maintenance from the wingtip to the stop.

[0139]

[0149] Example 32 includes the aircraft of example 31, wherein the wingtip-to-stop drop maintenance includes instructions to: replace the wingtip lugs; replace the main section lug stops; identify a first subset of the wingtip lugs having visible damage for scrap; and subject a second subset of the wingtip lugs without visible damage to testing for non-visible damage.

[0140]

[0150] Example 33 includes the aircraft of any one of examples 24 to 32, wherein the flight control computer is further configured to send an extend command to the folding wingtip system electronic controller in response to determining that the wingtip position indicates that the wingtip is in a folded position and to send an extend command to move the wingtip from the folded position to a flight position.

[0141]

[0151] Example 34 includes the aircraft of any one of Examples 24 to 33, wherein the flight control computer is further configured to: send a first extend command to the first electronic controller to change the wingtip position from a folded position to a flight position; receive a first notification signal from the first electronic controller indicating that the first extend command has failed; change a setting to indicate that the aircraft will remain on the ground based on the first notification signal; and schedule maintenance of the aircraft based on one or more second error codes included in the first notification signal.

[0142]

[0152] Example 35 includes the aircraft of example 34, wherein the flight control computer is further configured to: send a second extended command to the second electronic controller in response to the first notification signal; receive a second notification signal from the second electronic controller indicating successful completion of the second extended command; change a setting to indicate that the aircraft is not grounded based on the second notification signal; and change a type of maintenance scheduled for the aircraft based on the second notification signal.

[0143]

[0153] Example 36 includes the aircraft of example 34, wherein the flight control computer is further configured to: send a second extended command to the second electronic controller in response to the first notification signal; receive a second notification signal from the second electronic controller indicating a failure of the second extended command; and modify maintenance scheduled for the aircraft to include the additional maintenance in response to the second notification signal including one or more additional error codes not included in the first notification signal.

[0144]

[0154] According to Example 37, the method includes, in a flight control computer of the aircraft, determining a wing tip position of the wing tip in response to determining that the last completed command by the folding wing tip system was a fold command, setting, via the flight control computer, a first error code for the folding wing tip system in response to the wing tip position indicating the wing tip is not in a folded position, changing, via the flight control computer, the setting to indicate the aircraft should remain on the ground, and scheduling maintenance of the aircraft based on the first error code.

[0145]

[0155] Example 38 includes the method of example 37, wherein determining a wing tip position of the wing tip is performed in response to an aircraft transitioning from an idle or low powered condition to a powered condition.

[0146]

[0156] Example 39 includes the method of example 37, wherein determining a wing tip position of the folding wing tip is performed in response to making a particular decision to send an extend command to a folding wing tip system.

[0147]

[0157] According to Example 40, the device includes a memory configured to store instructions and a processor configured to execute the instructions to perform a method described in any one of Examples 37 to 39.

[0148]

[0158] According to Example 41, a non-transitory computer-readable medium stores instructions that, when executed by a processor, cause the processor to perform a method according to any one of Examples 37 to 39.

[0149]

[0159] According to Example 42, the apparatus comprises means for carrying out the method according to any one of Examples 37 to 39.

[0150]

[0160] According to Example 43, a non-transitory computer readable medium includes instructions executable by one or more processors to: determine a wing tip position of a wing tip of the aircraft in response to determining that the last command completed by the folding wing tip system was a fold command; set a first error code of the folding wing tip system in response to the wing tip position indicating the wing tip is not in a folded position; change the setting to indicate the aircraft shall remain on the ground; and schedule maintenance of the aircraft based on the first error code.

[0151]

[0161] Example 44 includes the non-transitory computer readable medium of example 42, wherein the instructions are further executable by one or more processors to: send a first extend command to the first electronic controller to change the wingtip position from the flight position to the folded position; receive a first notification signal from the first electronic controller indicating that the first extend command failed; change a setting to indicate the aircraft will remain on the ground based on the first notification signal; and schedule maintenance of the aircraft based on one or more second error codes in the first notification signal.

[0152]

[0162] Example 45 includes the non-transitory computer readable medium of example 44, wherein the instructions are executable by one or more processors to: send a second fold command to a second electronic controller in response to the first notification signal; receive a second second notification signal from the electronic controller indicating successful completion of the second fold command; change a setting to indicate that the aircraft will not remain grounded based on the second notification signal; and change a type of maintenance scheduled for the aircraft based on the second notification signal.

[0153]

[0163] Example 46 includes the non-transitory computer-readable medium of example 44, wherein the instructions are executable by one or more processors to: in response to the first notification signal, send a second fold command to the second electronic controller; receive a second notification signal from the second electronic controller indicating a failure of the second fold command; and in response to the second notification signal including one or more additional error codes not included in the first notification signal, modify maintenance scheduled for the aircraft to include the additional maintenance.

[0154]

[0164] The illustrations of the embodiments described herein are intended to provide a general understanding of the structure of the various embodiments. These illustrations are not intended to exhaustively describe all elements and features of the apparatus and systems that utilize the structures or methods described herein. Many other embodiments may become apparent to those skilled in the art upon review of the present disclosure. Other embodiments may be utilized and derived from the present disclosure, such that structural and logical substitutions and changes may be made without departing from the scope of the present disclosure. For example, the method steps may be performed in a different order than shown in the figures, or one or more method steps may be omitted. Correspondingly, the present disclosure and the figures should be considered illustrative rather than restrictive.

[0155]

[0165] Moreover, although specific examples have been illustrated and described herein, it should be understood that any subsequent configurations designed to achieve the same or similar results may be substituted for the specific embodiment shown. The present disclosure is intended to cover any subsequent adaptations or variations of the various embodiments. Combinations of the above embodiments, as well as other embodiments not specifically described herein, will be apparent to those of skill in the art upon review of the description herein.

[0156]

[0166] The Abstract of the Disclosure is submitted with the understanding that it will not be used to interpret or limit the scope or meaning of the claims. In addition, in the above detailed description, various features may be grouped together or described as one embodiment for the purpose of brevity of the disclosure. The above examples illustrate the disclosure, but do not limit it. It should also be understood that numerous modifications and variations are possible in accordance with the principles of the disclosure. As reflected in the following claims, the subject matter of the claimed invention may be directed to less than all features of any of the disclosed embodiments. Correspondingly, the scope of the disclosure is defined by the following claims and their equivalents.

Claims

1. An aircraft (100), an airfoil (104) including a main portion (106) and a tip (102); a folding wingtip system (230) configured to rotate the wing tip relative to the main section, the folding wingtip system including an electronic controller (316); said electronic controller (316) Executing extension commands (604-632) received from a flight control computer (202) to rotate the wing tips from a folded position to a flying position; and In response to determining that the wingtip rotation has stopped prior to the flight position during execution of the extension command (620), sending a first notification signal (614) to the flight control computer to keep the aircraft on the ground and schedule maintenance for the aircraft. the first notification signal includes one or more first error codes (612), and the first notification signal, in response to the electronic controller determining that a first particular angle of the wing tip relative to the main portion of the wing is within a latch pin interference range, causes the maintenance to include drop maintenance from the wing tip to a latch pin.

2. The drop maintenance from the wing tip to the latch pin is identifying one or more particular latch pins (358) contacted by one or more particular lugs (354) of said wing tip; replacing said one or more particular latch pins; identifying a first subset of the one or more particular latch pins having visible damage as scrap; subjecting a second subset of the one or more particular latch pins free of visible damage to testing for non-visible damage; The aircraft of claim 1 including instructions to perform the steps of:

3. The wing tip to latch pin drop maintenance further comprises: Replacing one or more wing tip lugs (354); identifying a first subset of the one or more wing tip lugs having visible damage as scrap; testing a second subset of the one or more wingtip lugs free of visible damage for non-visible damage; and The aircraft of claim 2 including instructions to perform the following:

4. 2. The aircraft of claim 1, wherein the first notification signal also causes the flight control computer to schedule maintenance of a wingtip actuation system of the aircraft.

5. 2. The aircraft of claim 1, wherein the first notification signal indicates that the maintenance includes maintenance of a wingtip actuator when the determination by the electronic controller indicates that the first particular angle is not within the latch pin interference range.

6. The electronic controller further comprises: receiving (404) a request for position data from the flight control computer relating to an angle of the wing tip relative to the main portion; transmitting the position data to the flight control computer based on data received from a hinge line sensor (310), wherein when the position of the wing tips indicated by the position data is not within the folded position, the flight control computer grounds (414) the aircraft and schedules (416) maintenance of the aircraft; and 2. The aircraft of claim 1, configured to execute the

7. 7. The aircraft of claim 6, wherein the maintenance comprises brake system maintenance of a brake system (308) configured to maintain the wing tips in the folded position.

8. 7. The aircraft of claim 6, wherein the servicing includes drop servicing from the wing tip to a latch pin when the angle of the wing tip relative to the main portion is within the latch pin interference range.

9. 7. The aircraft of claim 6, wherein the servicing includes drop servicing from the wing tip to a stop when the wing tip is in or near the flight position.

10. The drop maintenance from the wing tip to the stopper is replacing a tip lug of the wing tip; replacing the lug fasteners (360) of said main section; identifying a first subset of the wingtip lugs having visible damage as scrap; testing a second subset of said wingtip lugs without visible damage for non-visible damage; 10. The aircraft of claim 9, further comprising instructions to perform the steps of:

11. 1. A method comprising: executing (604-632) an extension command received by an electronic controller (316) of a folding wingtip system (230) of the aircraft (100) from the flight control computer (202) via said electronic controller to rotate the wing tips from a folded position to a flying position; in response to a first determination in the electronic controller that rotation of the wingtip has stopped before the flight position during execution of the extension command (620), sending a first notification signal (614) from the electronic controller to the flight control computer to keep the aircraft on the ground and schedule maintenance of the aircraft; the first notification signal includes one or more first error codes, and the first notification signal includes drop servicing from the wing tip to a latch pin in response to the electronic controller determining that a first particular angle of the wing tip relative to a main portion of the wing is within a latch pin interference range.

12. 12. The method of claim 11, wherein in response to a second determination that an execution time of the extend command from a start of execution of the extend command to a completion of execution of the extend command, as indicated when rotation of the wingtip relative to the main portion stops in the flight position, is less than a threshold execution time, the one or more first error codes are indicative of a tip-to-stop drop, and the one or more first error codes are configured to cause the maintenance of the aircraft to include a tip-to-stop drop maintenance.

13. 12. The method of claim 11, further comprising providing wingtip position data to the flight control computer in response to the wingtip position request (404), the flight control computer being configured to change a setting to indicate the aircraft remain on the ground (414) and schedule certain maintenance for the aircraft based on a first determination that the wing tips are not in a folded position (416) and based on a second determination that the last executed command by the folding wingtip system was a fold command.

14. 14. The method of claim 13, wherein the particular maintenance comprises drop maintenance from the wing tip to a latch pin when the wing tip position data indicates that the wing tip is at a particular angle within the latch pin interference range.

15. 14. The method of claim 13, wherein the particular maintenance comprises drop maintenance from the wing tip to a stop when the wing tip position data indicates that the wing tip is at or substantially at the flight position.

16. moreover, receiving at the electronic controller from the flight control computer a second command to transition the wingtip from a first position to a second position (602, 702); sending control signals to a drive train actuator, a hydraulic control module, or both to execute the second command (606, 706); sending a particular notification signal to said flight control computer in response to a determination by the electronic controller that a latch pin actuator locking system has failed (608, 708) based on drivetrain actuator data from a drivetrain actuator sensor and drivetrain position data from a drivetrain position sensor; 12. The method of claim 11 , wherein the specific notification signal includes one or more specific error codes related to a locking system failure, and wherein the specific notification signal causes the aircraft to be grounded and specific maintenance scheduled for the aircraft, the specific maintenance including maintenance to a latch pin system.

17. A non-transitory computer readable medium (1006), the computer readable medium (1006) comprising: executing extension commands (604-632) received from the flight control computer (202) to rotate the wing tips (102) of the wings (104) about the hinge axes (214) from a folded position to a flying position; in response to a first determination that rotation of the wingtip has stopped before the flight position during execution of the extension command (620), sending a first notification signal (614) to the flight control computer to keep the aircraft on the ground and schedule maintenance for the aircraft; a first notification signal including one or more first error codes, the first notification signal including one or more first error codes, the notification signal including a drop maintenance from the wing tip to a latch pin in response to a determination by the electronic controller indicating that a first particular angle of the wing tip relative to a main portion of the wing is within a latch pin interference range, the first notification signal including one or more first error codes, the notification signal including a drop maintenance from the wing tip to a latch pin in response to a determination by the electronic controller indicating that a first particular angle of the wing tip relative to a main portion of the wing is within a latch pin interference range.

18. The instructions further include: executing fold commands (704-732) to transition the wing tips from the flying position to the folded position; determining that a position of the wing tip relative to the main portion is not in the folded position at the end of execution of the fold command; transmitting a second notification signal to the flight control computer, the second notification signal including one or more second error codes associated with the location, the second notification signal causing the aircraft to be grounded and to schedule specific maintenance of the aircraft based on the one or more second error codes; 20. The aircraft of claim 17, wherein the one or more processors are executable to perform the steps of:

19. 20. The aircraft of claim 18, wherein the particular maintenance comprises drop maintenance from a wingtip to a latch pin when the location is within the latch pin interference range.

20. 20. The aircraft of claim 18, wherein the servicing includes drop servicing from a wingtip to a stop when the location is in or near the flight position.

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