System and method for detecting abnormal wingtip extension of folding wingtip aircraft

Abstract

The invention provides a system and a method for detecting abnormal wingtip extension of a folding wingtip aircraft. The method includes executing, by an electronic controller of the aircraft, an extension command to rotate a wingtip of the wing to a flight position, the extension command being received by the electronic controller from a flight control computer. The method includes, in response to a first determination made by the electronic controller that rotation of the wingtip is stopped before the flight position during implementation of the extension command, sending a first notification signal from the electronic controller to the flight control computer to stop the aircraft and plan maintenance of the aircraft. The first notification signal includes one or more first error codes. In response to the electronic controller determining that a first particular angle of the wingtip relative to the main portion of the wing is within a lock pin interference range, the first notification signal causes the maintenance to include wingtip-to-lock pin drop maintenance.

Description

Technical Field

[0001] The present disclosure generally relates to detecting abnormal wingtip extension of a folding wingtip aircraft. Background Art

[0002] Generally, larger aircraft and aircraft with longer wingspans tend to be more efficient at transporting people, cargo, or both. For example, it is often more efficient to operate a larger aircraft (which can carry more passengers and payload) between two destinations than to fly several trips using a smaller aircraft. Some airports are able to accommodate large wingspan aircraft (e.g., F-type airports), however, most airports are built with taxiway spacing and parking stand locations that do not provide adequate spacing for aircraft with long wingspans.

[0003] In order to have a large wingspan and accommodate the wingspan restrictions associated with some airports (e.g., E-type airports), some aircraft are folding wingtip aircraft. Each wing of the aircraft includes a main portion coupled to the fuselage of the aircraft, a wingtip configured to fold (e.g., rotate) relative to the main portion, and a folding wingtip system configured to fold the wingtip relative to the main portion. When the wingtip is in the flying position, the aircraft has a larger wingspan to improve the flight efficiency of the aircraft, and when the wingtip is in the folded position, the aircraft has a smaller wingspan that meets the wingspan restrictions of the airport.

[0004] A folding wingtip system (i.e., one folding wingtip system for each wing of an aircraft) is designed to raise and lower the wingtips. Although the occurrence of abnormal operation of a folding wingtip system (e.g., due to human error, component failure, or both) is highly unlikely, it is desirable to detect if such an abnormal occurrence occurs and to provide instructions detailing an appropriate response. Summary of the invention

[0005] In a specific implementation, 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 implement an extension command received from a flight control computer to rotate the wingtip from a folded position to a flight position. The electronic controller is further configured to send a first notification signal to the flight control computer to ground the folding wingtip aircraft and schedule maintenance of the aircraft in response to determining that rotation of the wingtip stops before the flight position during implementation of the extension command. The first notification signal includes one or more first error codes. In response to the electronic controller making a determination indicating that a first specific angle of the wingtip relative to the main portion of the wing is within a latch pin interference range, the first notification signal causes maintenance including a wingtip-to-latch pin drop maintenance.

[0006] In another specific implementation, a method includes implementing an extension command via an electronic controller of an aircraft to rotate a wingtip of a wing from a folded position to a flight position, the extension command being received by the electronic controller from a flight control computer. The method includes, in response to a first determination at the electronic controller that rotation of the wingtip stops prior to the flight position during implementation of the extension 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. In response to the electronic controller making a determination indicating that a first particular angle of the wingtip relative to a main portion of the wing is within a locking pin interference range, the first notification signal causes maintenance including wingtip to locking pin lower maintenance.

[0007] In another specific implementation, a non-transitory computer-readable medium includes instructions executable by one or more processors of an electronic controller of an aircraft. The instructions are executable by the one or more processors to implement an extension command received from a flight control computer to rotate a wingtip of a wing 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 wingtip stops prior to the flight position during implementation of the extension command, send a first notification signal to the flight control computer to ground the aircraft and schedule maintenance for the aircraft. The first notification signal includes one or more first error codes. In response to the electronic controller making a determination indicating that a first specific angle of the wingtip relative to a main portion of the wing is within a locking pin interference range, the first notification signal causes maintenance to include wingtip to locking pin lower maintenance.

[0008] In a specific implementation, an aircraft includes a wing. The wing includes a main portion and a wingtip. The aircraft includes a folding wingtip system configured to rotate the wingtip relative to the main portion. The aircraft also includes a flight control computer. The flight control computer is configured to set an error code for the folding wingtip system in response to a first determination that a wingtip position of the wingtip is not in a folded position when a second determination indicates that a last completed command of the folding wingtip system is a fold command. The flight control computer is further configured to change a setting based on the error code to instruct the aircraft to ground.

[0009] In another specific implementation, a method includes: in response to determining that the last completed command of a folding wingtip system is a fold command, determining a wingtip position of a wingtip at a flight control computer of an aircraft. The method includes: in response to the wingtip position indicating that the wingtip is not in the folded position, setting a first error code for the folding wingtip system via the flight control computer. The method includes, in response to the wingtip position indicating that the wingtip is not in the folded position, changing a setting via the flight control computer to indicate that the aircraft is grounded. The method also includes: in response to the wingtip position indicating that the wingtip is not in the folded position, scheduling maintenance of the aircraft based on the first error code via the flight control computer.

[0010] In another specific implementation, a non-transitory computer readable medium includes instructions executable by one or more processors of an aircraft. The instructions are executable by the one or more processors to determine a wingtip position of a wingtip of the aircraft in response to determining that the last completed command of a folding wingtip system was a fold command. The instructions are executable by the one or more processors to set a first error code for the folding wingtip system in response to the wingtip position indicating that the wingtip is not in a folded position. The instructions are executable by the one or more processors to change a setting based on the first error code to indicate that the aircraft is grounded. The instructions are also executable by the one or more processors to schedule maintenance for the aircraft based on the first error code.

[0011] The features, functions, and advantages described herein can be achieved independently in various embodiments or may be combined in yet other implementations further details of which can be found with reference to the following description and drawings. BRIEF DESCRIPTION OF THE DRAWINGS

[0012] Figure 1A An illustration of a folding wingtip aircraft including a wingtip extension anomaly detector is depicted, wherein the wingtip is in a flight position.

[0013] Figure 1B Depicted Figure 1A Illustration of a folding wingtip aircraft with the wingtips in a folded position.

[0014] Figure 2 is a block diagram of a folding wingtip aircraft including a wingtip extension anomaly detector.

[0015] Figure 3 is an illustration of a folding wingtip system for a folding wingtip aircraft including a wingtip extension anomaly detector.

[0016] Figure 4 is a flow chart of an embodiment of a first method of using a folding wingtip system for an aircraft including wingtip extension anomaly detection.

[0017] Figure 5is a flow chart of an implementation of a second method for using a folding wingtip system of an aircraft including wingtip extension anomaly detection.

[0018] Figure 6 is a flow chart of an implementation of a third method for using a folding wingtip system of an aircraft including wingtip extension anomaly detection.

[0019] Figure 7 is a flow chart of an embodiment of a fourth method of using a folding wingtip system for an aircraft including wingtip extension anomaly detection.

[0020] Figure 8 It shows that Figure 1A Flowchart of the life cycle of an aircraft of the wingtip extension anomaly detector.

[0021] Fig. 9 This is a block diagram of an aircraft.

[0022] Fig.10 is a block diagram of a computing environment including a computing device configured to support aspects of computer-implemented methods and computer-executable program instructions (or code) according to the present disclosure. DETAILED DESCRIPTION

[0023] A folding wingtip aircraft includes a folding wingtip system for each wing of the aircraft. The folding wingtip system enables the wing to rotate from a flying position to a folded position and vice versa. The folding wingtip system receives a command from a flight control computer to use the folding wingtip system.

[0024] The folding wingtip system is designed so that the movement of the wingtip is controlled and the wingtip is secured in position by a braking system when the wingtip is in the folded position, and by a locking pin system when the wingtip is in the flight position. When the folding wingtip system of the aircraft fails to operate properly to implement a command 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 is grounded and scheduled for maintenance. The fault isolation manual, aircraft maintenance manual, and information provided by the aircraft's flight control computer are used by maintenance personnel performing maintenance to determine why the folding wingtip system failed, to enable the folding wingtip system, to troubleshoot and correct the problem caused by the failure, or a combination thereof.

[0025] Although it is highly unlikely, the wingtip may drop from the folded position or when the folding wingtip system is used to change the position of the wingtip. The wingtip may drop due to human error (e.g., improper maintenance), due to failure of one or more components of the folding wingtip system (e.g., failure of a torque tube that supports the wingtip as it rotates from one position to another), other reasons, or a combination thereof. If the wingtip drops, the wingtip lugs of the wingtip may contact stops of the main portion of the wing that provide end limits for the rotation of the wingtip, which may cause damage to one or more of the wingtip lugs, one or more of the stops, or both; or one or more of the wingtip lugs of the wingtip may contact one or more locking pins of the locking pin system, which may cause damage to one or more of the wingtip lugs, one or more locking pins, or both.

[0026] The present disclosure describes systems and methods that are capable of determining abnormal wingtip extension (such as when the wingtip is down) and determining the type of maintenance required to return an aircraft to service. The technical advantages of the present disclosure are that maintenance scheduled for an aircraft due to a folding wingtip system failure (including specific maintenance to address the possible cause of the folding wingtip system failure) improves efficiency, reduces the time a folding wingtip aircraft is out of service for maintenance, and reduces costs associated with maintenance. The maintenance scheduled for the aircraft includes specific maintenance to be performed to address the possible cause of the failure of the folding wingtip system identified based on sensor data obtained during use of the folding wingtip system. Other technical advantages are that the maintenance scheduled for the aircraft identifies whether the wingtip is down, which can improve efficiency by eliminating the need for maintenance personnel to determine whether the wingtip is down. If the maintenance scheduled for the aircraft indicates a wingtip down, specific components of the folding wingtip system (e.g., one or more locking pins, one or more wingtip lugs, etc.) that are identified based on the sensor data as possibly being damaged by the wingtip down can be identified and inspected for non-visible damage, rather than inspecting all components that may have been damaged by the down, which also improves efficiency, reduces the time a folding wingtip aircraft is out of service, and reduces costs associated with maintenance.

[0027] The accompanying drawings and the following description illustrate specific exemplary implementations. It should be understood that those skilled in the art will be able to design various arrangements that, although not explicitly described or shown herein, embody the principles described herein and are included within the scope of the claims following this description. In addition, any embodiments described herein are intended to aid in understanding the principles of the present disclosure and are to be interpreted as not limiting. Therefore, the present disclosure is not limited to the specific embodiments or embodiments described below, but is defined by the claims and their equivalents.

[0028] Specific implementations are described herein with reference to the accompanying drawings. In the description, common features are represented by common reference numerals throughout the drawings. In some of the drawings, multiple embodiments of a particular type of feature are used. Although the features are physically and / or logically different, the same reference numerals are used for each, and different embodiments are distinguished by adding letters to the reference numerals. When features are referred to herein as a group or type (for example, when a specific one of the features is not mentioned), the reference numerals are used without distinguishing letters. However, when a specific feature among multiple features of the same type is referred to herein, the reference numeral is used with a distinguishing letter. For example, reference numerals are used in conjunction with distinguishing letters. Figure 3 , a plurality of electronic controllers are shown and are associated with reference numerals 316A and 316B. When referring to a specific one of these electronic controllers (such as electronic controller 316A), a distinguishing letter "A" is used. However, when referring to any one of these electronic controllers or these electronic controllers as a group, reference numeral 316 is used without a distinguishing letter.

[0029] The present disclosure relates to folding wingtip aircraft. As used herein, the term "aircraft" refers to a folding wingtip aircraft. As used herein, various terms are used only for the purpose of describing a particular implementation and are not intended to be limiting. For example, the singular forms "a," "an," and "the" are intended to include the plural forms as well, unless the context clearly indicates otherwise. Further, some features described herein are singular in some implementations and plural in other implementations. For illustration, Figure 2 Describes a system comprising one or more processors ( Figure 2 216), which means that 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 are subsequently referred to in the singular unless aspects related to multiple features are being described.

[0030] The terms "comprise", "comprises" and "comprising" are used interchangeably with "include", "includes" or "including". In addition, the term "wherein" is used interchangeably with the term "wherein". As used herein, "exemplary" indicates an embodiment, implementation and / or aspect, and should not be interpreted as limiting or indicating a preference or preferred implementation. As used herein, ordinal terms (e.g., "first", "second", "third", etc.) used to modify an element (such as a structure, component, operation, etc.) do not themselves indicate any priority or order of the element relative to another element, but only distinguish the element from another element with the same name (but for the use of ordinal terms). 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 "A and B", or "A or B", or both "A and B" and "A or B" are applicable or acceptable.

[0031] As used herein, "generate", "calculate", "use", "select", "access" and "determine" are interchangeable unless the context indicates otherwise. For example, "generate", "calculate" or "determine" a parameter (or signal) may refer to actively generating, calculating or determining the parameter (or signal) or may refer to using, selecting or accessing the parameter (or signal) that has been generated, such as by another component or device. As used herein, "connection" may include "communication connection", "electrical connection" or "physical connection", and may also (or alternatively) include any combination thereof. Two devices (or components) may be directly or indirectly coupled (e.g., communicatively coupled, electrically coupled or physically coupled) via one or more other devices, components, wires, buses, networks (e.g., wired networks, wireless networks, or combinations thereof), etc. Two electrically coupled devices (or components) may be included in the same device or in different devices, and may be connected via electronic devices, one or more connectors, or inductive coupling, as illustrative, non-limiting embodiments. In some embodiments, two devices (or components) that are communicatively coupled (e.g., in electrical communication) may directly or indirectly send and receive electrical signals (digital or analog), for example, via one or more wires, buses, networks, etc. As used herein, "directly coupled" is used to describe two devices that are coupled (e.g., communicatively coupled, electrically coupled, or physically coupled) without intermediary components.

[0032] Figure 1A An illustration of a folding wingtip aircraft 100 is depicted, wherein wingtips 102 of the aircraft 100 are in a flight position. Figure 1BAn illustration of an aircraft 100 with wingtips 102 in a folded position is depicted. Each wing 104 of the aircraft 100 includes a main portion 106 coupled to a fuselage 108 of the aircraft 100 and a wingtip 102. The folding wingtip system of the aircraft 100 is capable of rotating the wingtip 102 from a flight position to a folded position and vice versa. In an embodiment, the horizontal length of the wingtip 102 from the wingtip end to the hinge axis is approximately 11 feet. In other embodiments, the horizontal length of the wingtip 102 can be shorter or longer. In some implementations, the end of the wingtip 102 can include a winglet.

[0033] Sensor data associated with one or more components of the folding wingtip system is processed by the wingtip extension anomaly detector 110 to determine whether the folding wingtip system is operating properly to position the wingtip 102 in the proper position (e.g., folded position or flight position). Figure 1A and Figure 1B , the wingtip extension anomaly detector 110 is shown using dashed lines to indicate that it is generally not visible from the outside of the aircraft 100. Figures 2 to 7 An embodiment of the operation of the wingtip extension anomaly detector 110 is described.

[0034] Figure 2 A block diagram of an aircraft 100 is depicted. The aircraft 100 includes wings 104, a flight control computer 202; input devices 204 (e.g., bogies, sidesticks, control rods, buttons, dials, keyboards, touch screens, etc.) for receiving data, commands, and other information from crew members and external sources; output devices 206 (e.g., displays, instruments, speakers, headphones, haptic devices, etc.) for providing information about operating conditions associated with the aircraft 100 to the crew members and external sources; engines 208 that provide power to the aircraft 100; an operating system 210; a sensor system 212 that enables the flight control computer 202, the operating system 210, or both to determine operating conditions associated with the aircraft 100; and other components. Each wing 104 includes a main section 106 and a wingtip 102 that is configured to rotate relative to the main section 106 about a hinge axis 214.

[0035] The flight control computer 202 controls the operation of the aircraft 100 based on inputs received from the crew members and from external sources and based on the conditions of use. The flight control computer 202 includes one or more processors 216 and a memory 218. The memory 218 stores data 220 associated with the operation of the aircraft 100 and instructions 222 executable by the processor 216 to perform the operation. The instructions 222 may include flight instructions 224 for operating the aircraft 100, a warning system 226 for providing an indication when one or more abnormal conditions occur, a maintenance scheduler 228 for scheduling maintenance of the aircraft 100, the wingtip extension anomaly detector 110A, other applications, or a combination thereof. The maintenance scheduled by the maintenance scheduler 228 may include routine maintenance, specific maintenance for resolving a problem detected by the flight control computer 202, or a combination thereof.

[0036] The operating system 210 is configured to implement control commands sent by the flight control computer 202, provided by the crew member through the input device 204, or both. The operating system 210 includes folding wingtip systems 230, navigation systems, communication systems, and other systems utilized during use of the aircraft 100. Each folding wingtip system 230 is associated with a wing 104 and is configured to rotate a wingtip 102 of the wing 104 relative to the main portion 106 of the wing from a folded position to a flight position, and vice versa. Each folding wingtip system 230 is also configured to secure the wingtip 102 in the flight position and the folded position.

[0037] The use of the folding wingtip system 230 is controlled by the flight instructions 224. The flight instructions 224 include logic for determining when the folding wingtip system 230 is available. For example, when the aircraft 100 is in the takeoff phase or the flight phase, the flight instructions 224 prohibit the flight control computer 202 from sending a folding command to fold the wingtip 102 from the flight position to the folded position, and prohibit the flight control computer 202 from sending a folding command during the landing phase until the aircraft 100 is on the ground and traveling at a speed below a threshold speed. The threshold speed is below the speed required for the aircraft 100 to resume flight. In some implementations, the threshold speed is a taxiing speed. As another example, when the aircraft 100 is not in flight and is in the taxi-in phase, the taxi-out phase, or at a station (e.g., a parking stand), based on a comparison of the current position of the aircraft 100 with the wingspan limitation data of the airport where the aircraft 100 is located, the flight instructions 224 prohibit the flight control computer 202 from sending an extension command to extend the wingtip 102 from the folded position to the flight position.

[0038] The wingtip extension anomaly detector 110A may represent a portion of the wingtip extension anomaly detector 110 implemented at the flight control computer 202 and operating based on input from the sensor system 212, the folding wingtip system 230, or both. In response to a command sent from the flight control computer 202 to the folding wingtip system 230, the wingtip extension anomaly detector 110A receives a notification signal regarding the operation of the folding wingtip system 230. When the received notification signal includes one or more error codes, the wingtip extension anomaly detector 110A is configured to change a setting to instruct the aircraft 100 to be grounded, to provide information to the warning system 226 so that the crew is notified of one or more problems with the folding wingtip system 230 and that the aircraft is grounded, and to provide one or more error codes to the maintenance scheduler 228 so that specific maintenance for resolving the one or more problems can be performed.

[0039] The flight control computer 202 may determine that the last completed command of the folding wingtip system 230 was a fold command. This determination may be made when the aircraft 100 transitions from an idle or low power state to a powered state, periodically, when the flight control computer 202 determines to implement one or more extension commands to move the wingtip 102 from the folded position to the flight position, or a combination thereof. For example, before one or more extension commands are sent to the folding wingtip system 230, the wingtip extension anomaly detector 110A sends a request for the position of the wingtip 102 to the folding wingtip system 230 and determines the last implemented command of the folding wingtip system 230 based on the data 220. When the response to the wingtip position request indicates that the wingtip 102 is in the folded position and the last implemented command of the folding wingtip system 230 is a fold command, the wingtip extension anomaly detector 110A determines that there is no anomaly and sends one or more extension commands to the folding wingtip system 230.

[0040] When the wingtip extension anomaly detector 110A determines that one or both of the wingtips 102 are not in the folded position and the last command implemented by the folding wingtip system was a fold command, the wingtip extension anomaly detector 110A determines that an anomaly exists. The wingtip extension anomaly detector 110A sets a setting for grounding the aircraft 100 and sets an error code associated with the anomaly. The error code includes one or more codes used by the maintenance scheduler 228 to specify specific maintenance to be performed to return the aircraft 100 to service. The error code includes an indication that the brake system (e.g., Figure 3 a braking system 308 configured to maintain the wing tip 102 in the folded position and prevent accidental movement of the wing tip 102 from the folded position; and a wing tip actuation system of the folding wing tip system 230 (e.g., Figure 3and error codes associated with the position of wingtips 102 that are not in the folded position. For example, if one of wingtips 102 is at or near the flight position, the error code associated with the position of wingtip 102 enables maintenance scheduler 228 to specify a specific maintenance (e.g., wingtip to stop lowering maintenance) that addresses issues associated with lowering wingtip 102 from the folded position to the flight position.

[0041] Figure 3 is a block diagram of a folding wingtip system 230 for a wing 104 of an aircraft 100. The folding wingtip system 230 includes a control system 302, a wingtip actuation system 304 that rotates the wingtip 102 between a folded position and a flight position, a locking pin system 306 that locks the wingtip 102 in the flight position, a brake system 308 that locks the wingtip 102 in the folded position, a portion of the sensor system 212 (e.g., hinge sensors 310A, 310B, drive train actuator position sensors 312A, 312B, and drive train position sensors 314A, 314B), other components, or a combination thereof.

[0042] Control system 302 includes electronic controller 316A, hydraulic controller 318A coupled to electronic controller 316A, redundant electronic controller 316B, redundant hydraulic controller 318B coupled to electronic controller 310B, and isolation valve 320 communicatively coupled to electronic controllers 316A, 316B. Electronic controllers 316A, 316B are communicatively coupled to flight control computer 202.

[0043] In some embodiments, the electronic controllers 316A, 316B are shared by the folding wing tip system 230 of the other wing 104 of the aircraft 100 to enable simultaneous control of the two folding wing tip systems 230 via one of the electronic controllers 310A, 310B in response to commands received from the flight control computer 202. When each folding wing tip system 230 includes its own electronic controller 316A, 316B, sharing the electronic controllers 316A, 316B by the folding wing tip systems 230 enables the folding wing tip aircraft 100 to have two electronic controllers 316A, 316B instead of four electronic controllers 316A, 316B. Similarly, in some embodiments, the hydraulic controllers 318A, 318B are shared by the folding wing tip system 230 of the other wing 104 of the aircraft 100. Spacing and system weight considerations for components and connection systems (e.g., wiring for electronic controllers 316A, 316B and hydraulic lines for hydraulic controllers 318A, 318B) may be considerations during the design phase of aircraft 100 to determine whether to use two or four electronic controllers 316A, 316B and whether to use two or four hydraulic controllers 318A, 318B.

[0044] Each electronic controller 316A, 316B includes one or more processors 322 and a memory 324. The memory 324 is configured to store data and instructions. The instructions include an extension instruction 326, a folding instruction 328, and a wingtip extension anomaly detector 110B. When a particular electronic controller 316 receives an extension command from the flight control computer 202, the one or more processors 322 execute the extension instruction 326 to implement a process that causes the folding wingtip system 230 to rotate the wingtip 102 from the folded position to the flight position and fix the wingtip 102 in the flight position. When a particular electronic controller 316 receives a folding command from the flight control computer 202, the one or more processors 322 execute the folding instruction 328 to implement a process that causes the folding wingtip system 230 to rotate the wingtip 102 from the flight position to the folded position and fix the wingtip 102 in the folded position.

[0045] The wingtip extension anomaly detector 110B may represent a portion of the wingtip extension anomaly detector 110 implemented at the electronic controller 316 and monitoring the execution of a particular command received from the flight control computer 202 via the extend command 326 or the fold command 328. When the command is correctly implemented, the wingtip extension anomaly detector 110B provides a notification indicating the successful implementation of the received command to the wingtip extension anomaly detector 110A of the flight control computer 202. When the wingtip extension anomaly detector 110B detects based on the sensor data that the implementation of the received command is stopped before completion, the wingtip extension anomaly detector 110B stops further implementation of the command (e.g., the extend command 326 or the fold command 328), closes the isolation valve 320, sets one or more error codes associated with the folding wingtip system 230, sends a notification signal including the one or more error codes to the wingtip extension anomaly detector 110A, or a combination thereof.

[0046] Each electronic controller 316 is communicatively coupled to a corresponding hydraulic controller 318. Each hydraulic controller 318 is coupled to an isolation valve 320 via a hydraulic supply line to receive 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 wing tip system 230 of each wing 104 of the aircraft 100. Each hydraulic controller 318 is coupled to a return hydraulic line that directs return hydraulic fluid to the hydraulic fluid system 330. The hydraulic controller 318 includes a plurality of ports. The supply hydraulic lines and the return hydraulic lines are connected to ports of the folding wing tip system 230 and hydraulic units (e.g., a power drive unit 332, a locking pin actuator 334, a brake system 308, etc.). When the electronic controller 316 executes a first command (e.g., an extend command or a fold command), the electronic controller 316 sends an open signal to the isolation valve 320 and sends various signals to the corresponding hydraulic controller 318 during the execution of the first command to cause the hydraulic controller 318 to direct the pressurized hydraulic fluid to the appropriate hydraulic unit at the appropriate time and to stop supplying the hydraulic fluid to the specific unit at a specific time. During the implementation of the first command, the last or near last signal sent by the electronic controller 316 is a closing signal to close the isolation valve 320, which stops the operation of the folding wingtip system 230 until the electronic controller 316 receives a second command signal (e.g., a fold command or an extend command) from the flight control computer 202 to use the folding wingtip system 230 and the electronic controller 316 sends a signal to open the isolation valve 320 as part of the process of implementing the second command.

[0047] The isolation valve 320 is associated with a first valve coil controlled by a first electronic controller 316A to open and close the isolation valve 320, a second valve coil controlled by a second electronic controller 316B to open and close the isolation valve 320, and one or more valve sensors configured to monitor the operation of each valve sensor of the valve coil. The electronic controller 316 uses data from the valve sensor to determine whether to implement an open valve command or a close valve command. When a specific electronic controller 316 implements a specific command (i.e., a valve open command or a valve close command) and the valve sensor data indicates that the specific command is not completed, a first isolation valve error code associated with the specific controller is set, and the specific electronic controller 316 causes the specific command to be implemented by another electronic controller 316. When the valve sensor data indicates that the specific command is completed by another electronic controller 316, the notification signal sent to the flight control computer 202 includes the first isolation valve error code. The presence of a first isolation valve error code in the notification signal without a second isolation valve error code associated with the other electronic controller 316 allows the flight control computer 202 to keep the aircraft in service and schedule maintenance for the aircraft 100 to address issues with the particular electronic controller 316, the valve sensor associated with the particular electronic controller 316, or both.

[0048] When the valve sensor data indicates that the particular command has also not been completed by the other electronic controller 316, a second isolation valve error code associated with the other electronic controller is set, and a notification signal including the first isolation valve error code and the second isolation valve error code is sent to the flight control computer 202. The flight control computer 202, in response to the presence of the first isolation valve error code and the second isolation valve error code in the notification signal, causes a setting to be changed to instruct the aircraft 100 to be grounded, and causes maintenance to be scheduled to address one or more issues associated with the valve sensor, the isolation valve 320, or both.

[0049] The wing tip actuation system 304 includes a power drive unit 332 that rotates a first torque tube 336, an angular gear box 338 driven by the first torque tube 336, a second torque tube 340 driven by the angular gear box 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 is coupled to a wing tip structure 344. Rotation of the second torque tube 340 causes rotation of the rotary fold actuator 342 about the hinge axis 214, which causes rotation of the wing tip 102 about the hinge axis 214. The power drive unit 332 is coupled to a main portion structure 346 of the main portion 106 of the wing 104. The power drive unit 332 may be a hydraulic unit having a first unit configured to rotate the first torque tube 336 in a first direction, resulting in the wing tip 102 rotating about the hinge axis 214 toward the flight position by rotating the fold actuator 342, and a second unit configured to rotate the first torque tube 336 in a second direction, resulting in the wing tip 102 rotating about the hinge axis 214 toward the folded position by rotating the fold actuator 342. The first unit and the second unit of the power drive unit 332 are both connected to the hydraulic controller 318 via a supply hydraulic line and a return hydraulic line.

[0050] The locking pin system 306 includes a plurality of locking pin actuators 334, a drive train 348 coupled to a drive shaft of a locking system 350 of the locking pin actuators 334, a drive train actuator 352 configured to rotate the drive train 348, a plurality of wingtip lugs 354 structurally coupled to the wingtip structure 344 such that rotation of the rotary fold actuator 342 about the hinge axis 214 rotates the plurality of wingtip lugs 354, and a plurality of main portion lugs 356 that are part of the main portion structure 346. The lugs 354, 356 include a support structure having an opening sized to receive the locking pins 358 of the locking pin actuators 334 when the openings are aligned and the wingtip 102 is in the flight position.

[0051] The locking pin actuator 334 is coupled to the main portion structure 346 in working relationship with the opening in the main portion lug 356. The locking pin actuator may be or may be similar to the locking pin actuator shown and described in U.S. Patent No. 5,427,329. Figure 3Four locking pin actuators 334 are shown. In other embodiments, each folding wing tip system 230 may include a different number of locking pin actuators 334. Each locking pin actuator 334 may be a hydraulic unit configured to extend a locking pin 358 of the locking pin actuator 334 through an opening of a lug 354, 356 associated with the locking pin actuator 334 to secure the wing tip 102 in the flight position. Each locking pin actuator 334 is also configured to retract the locking pin 358 from the opening of the lug 354, 356 to allow the wing tip actuation system 304 to rotate the wing tip 102 to the folded position.

[0052] Each locking pin actuator 334 includes a first hydraulic fluid port, a second hydraulic fluid port, a locking pin 358, and a locking system 350. When hydraulic fluid is supplied to the first hydraulic fluid port of the locking pin actuator 334 through one of the hydraulic controllers 318 through the first hydraulic line, the hydraulic fluid fills and expands the first chamber of the locking pin actuator 334 to extend the locking pin 358 from the housing of the locking pin actuator 334. The expansion of the first chamber causes the second chamber of the locking pin actuator 334 to decrease. Hydraulic fluid from the second chamber flows to the hydraulic controller 318 through the second hydraulic port and the second hydraulic line. When hydraulic fluid is supplied to the second hydraulic fluid port through the second hydraulic line through one of the hydraulic controllers 318, the hydraulic fluid fills and expands the second chamber of the locking pin actuator 334 to retract the locking pin 358 into the housing. The expansion of the second chamber causes the decrease of the first chamber. Hydraulic fluid from the first chamber flows to the hydraulic controller 318 through the first hydraulic port and the first hydraulic line.

[0053] The drive train actuator 352 is configured to rotate the drive train 348 in a first direction to a locked position to cause the locking system 350 to place the lock members in a position that prohibits the retraction of the locking pin 358 of the locking pin actuator 334, and is configured to rotate the drive train 348 in a second direction to an unlocked position to cause the locking system 350 to move the lock members to a position that allows the locking pin 358 to retract into the housing of the locking pin actuator 334. The drive train actuator 352 can be a hydraulic unit or an electric drive unit.

[0054] During implementation of a command received by one of the electronic controllers 316 from the flight control computer 202 to use the folding wingtip system 230, the electronic controller 316 implements the extension instruction 326 or the folding instruction 328 according to the command. Implementation of the instruction 326 or the instruction 328 causes the electronic controller 316 to send signals to use the locking pin system 306. These signals include signals to the drive train actuator 352 to idle the drive train actuator 352, to rotate the drive train 348 to an unlocked position, or to rotate the drive train 348 to a locked position. The wingtip extension anomaly detector 110B receives sensor data from the corresponding drive train actuator position sensor 312 and the corresponding drive train position sensor 314. The wingtip extension anomaly detector 110B analyzes the sensor data, and if the analysis indicates that the locking pin system 306 is not operating correctly, the wingtip extension anomaly detector 110B stops the implementation of the process, sets one or more error codes, and sends a notification signal to the flight control computer 202 indicating that the command failed. The notification signal includes one or more error codes. In response to the notification signal, flight control computer 202 may change settings to instruct aircraft 100 to be grounded, and may schedule maintenance of aircraft 100 based on the one or more error codes.

[0055] For example, if the electronic controller 316A sends a signal to the power train actuator 352 to cause the power train actuator 352 to rotate the power train 348 to a locked position and data from the power train actuator position sensor 312A indicates that the power train 348 is idling and data from the power train position sensor 314A associated with the electronic controller 316A indicates that the power train 348 is not in the locked position, the notification signal sent to the flight control computer 202 via the wingtip extension anomaly detector 110B includes one or more first error codes (e.g., one or more numbers, one or more characters, or both), which causes maintenance scheduled for the aircraft 100 to include power train actuator maintenance. As another example, if the electronic controller 316A sends a signal to the transmission actuator 352 to cause the transmission actuator 352 to rotate the transmission 348 to an unlocked position and data from the transmission actuator position sensor 312A indicates that the transmission 348 is set to rotate the transmission 348 to an unlocked position, but data from the transmission position sensor 314A indicates that the transmission 348 is not in the unlocked position after a threshold time has elapsed, the notification signal includes one or more second error codes that cause maintenance scheduled for the aircraft 100 to include locking pin actuator maintenance to identify one or more locking pin actuators 334 that are not operating properly.

[0056] The brake system 308 secures the wing tip 102 in the folded position. In some embodiments, the brake system 308 is a hydraulic unit coupled to the output of the power drive unit 332. The brake system 308 includes a torque limiter and a clutch. When the brake system 308 is in a locked configuration, no hydraulic fluid is supplied to the brake system 308, and the torque limiter is biased against the output of the power drive unit 332 to secure the wing tip 102 in place and prevent movement of the wing tip 102. When hydraulic fluid is supplied to the brake system 308, the brake system 308 transitions to an unlocked configuration. The hydraulic fluid activates the clutch to disengage the torque limiter and allow the first torque tube 336 to rotate the wing tip 102 through rotation of the power drive unit 332.

[0057] During use of the aircraft 100, the flight control computer 202 is configured to send a fold command to the electronic controllers 316 associated with the folding wingtip system 230 to rotate the wingtip 102 of the aircraft 100 from the flight position to the folded position. The fold command may be automatically sent based on one or more conditions associated with the operation of the aircraft 100 (e.g., a taxiing flight phase after landing and a speed less than a threshold speed) or may be sent in response to a crew member input that does not violate one or more conditions associated with moving the wingtip 102 from the flight position to the folded position using the folding wingtip system 230. If the crew member input violates one or more conditions associated with use of the folding wingtip system 230, the warning system 226 provides an indication of any violation, and the flight control computer 202 does not send a fold command to one of the electronic controllers 316.

[0058] 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 isolation valve 320. The electronic controller 316 sends a plurality of signals to the drive train actuator 352 and to the hydraulic controller 318 associated with the electronic controller 316 to retract the locking pin 358 of the locking pin actuator 334 from the main portion lug 356 and the wing tip lug 354. When 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 locking pin 358 is retracted, the electronic controller 316 sends a signal to the brake system 308, which causes the brake system 308 to change from the locked configuration to the unlocked configuration, and sends a signal to the hydraulic controller 318, which causes the hydraulic controller 318 to activate 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 sensor 310 indicates that the wing tip 102 is in the folded position, the electronic controller 316 sends a signal to stop the operation of the drive train actuator 352 to rotate the drive train 348, and sends a plurality of signals to the hydraulic controller 318, which cause the brake system 308 to change from an unlocked configuration to a locked configuration to lock the wing tip 102 in the folded position, stop the operation of the power drive unit 332, and stop the supply of hydraulic fluid to the locking pin actuator 334 that holds the locking pin 358 in the retracted position. The wing tip extension anomaly detector 110B sends a notification signal to the flight control computer 202 indicating the completion of the fold command. A closing signal is sent to the isolation valve 320.

[0059] If the wingtip extension anomaly detector 110B determines that the fold command was not completed during the implementation of the fold instruction 328, the wingtip extension anomaly detector 110B stops further implementation of the fold instruction 328 and sends a notification signal indicating the failure of the fold command to the flight control computer 202. 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 failure of the folding wingtip system 230 and repair the folding wingtip system 230 so that the aircraft 100 is suitable for flight.

[0060] For example, if the wingtip extension anomaly detector 110B detects, based on data from the hinge sensor 310 associated with the electronic controller 116, that the wingtip 102 initially moves from the flight position toward the folded position and then moves back toward the flight position, the wingtip extension anomaly detector 110B stops further implementation of the folding instruction 328 and the notification signal sent to the flight control computer 202 includes an error code indicating that the wingtip 102 is down. The error code includes one or more first codes that cause the aircraft 100 to be scheduled for maintenance of the wingtip actuation system 304 to identify and repair one or more parts of the wingtip actuation system 304 that failed and caused the wingtip 102 to fall (e.g., the first torque tube 336, the second torque tube 340, etc.), and one or more second codes based on the position of the wingtip 102.

[0061] 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 a wing tip to stop descent maintenance of the aircraft. The wing tip to stop descent maintenance includes instructions to remove the wing tip lugs 354 and lug stops 360 of the main section 106, which limit the range of rotation of the wing tip 102, and replace the removed wing tip lugs 354 and lug stops 360. The first group of removed wing tip lugs 354 with visible damage (e.g., warping, cracks, etc.) are identified as scrap. The second group of removed wing tip lugs 354 without visible damage are subjected to inspection (e.g., x-ray imaging, sonic imaging, or other non-destructive inspection methods) to determine whether the wing tip lugs 354 are resistant to non-visible damage. Wing tip lugs 354 having non-visible damage are identified as scrap, and in some implementations, wing tip lugs 354 having no visible or non-visible damage may be reused.

[0062] If the position of the wing tip 102 is within the locking pin interference range, the one or more second codes include one or more codes instructing the flight control computer 202 to schedule a wing tip to locking pin descent maintenance of the aircraft 100. The locking 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 sensor 310, in which one or more wing tip lugs 354 may contact one or more locking pins 358 of the locking pin actuator 334. The locking pin interference range may be a narrow range (e.g., 14 to 15 degrees or some other range) for a locking pin system 306 in which the central axis of the locking pin 358 is aligned relative to the hinge axis 214, and may be a wide range (e.g., 10 to 20 degrees or some other range) for a locking pin system 306 in which the central axis of the one or more locking pins 358 is not aligned relative to the hinge axis 214. The central axis of one or more locking pins 358 may be misaligned relative to the hinge axis 214 due to spacing limitations in the wing 104, the ability to determine the specific one or more locking pins 358 contacted by one or more wingtip lugs 354 based on the angle of the wingtip 102, or both.

[0063] The wing tip to locking pin down position includes instructions for identifying one or more specific locking pins 358 contacted by one or more specific wing tip lugs 354 and replacing each of the one or more specific locking pins 358 with a replacement locking pin 358. Replacing the locking pin 358 may require removing the locking pin 358 from the locking pin actuator 334 and replacing the locking pin 358 with a replacement locking pin 358, or replacing the locking pin actuator 334 with another locking pin actuator 334. The first subset of contacted locking pins 358 with visible damage (e.g., dents or cracks) are identified as scrap. The second subset of contacted locking pins 358 that do not include visible damage are inspected to determine whether there is invisible damage. Based on the inspection, and in some implementations, the contacted locking pins 358 without visible damage and invisible damage can be reused, and the contacted locking pins 358 with visible damage or invisible damage are identified as scrap.

[0064] In addition, the wingtip to locking pin drop maintenance includes instructions for identifying one or more specific wingtip lugs 354 that contact the locking pin 358 and replacing each of the one or more specific wingtip lugs 354 with a replacement wingtip lug 354. A first subset of wingtip lugs 354 that contact the locking pin 358 and include visible damage are identified as scrap. A second subset of wingtip lugs 354 that contact the locking pin 358 but do not include visible damage are tested to determine if non-visible damage is present. Based on the testing, and in some implementations, wingtip lugs 354 without visible damage and non-visible damage may be reused, and wingtip lugs 354 with visible damage or non-visible damage are identified as scrap.

[0065] During use of the aircraft 100, the flight control computer 202 is configured to send an extension command to the electronic controller 316 associated with the folding wingtip system 230 to move the wingtip 102 of the aircraft 100 from the folded position to the flight position. The flight control computer 202 may automatically send the extension command based on the occurrence of one or more conditions (e.g., the position of the aircraft 100 is in a region that allows the wingtip 102 to be in the flight position and the flight phase of the aircraft 100 is taxi-out or taxi-in, etc.), or in response to crew member input that does not violate one or more conditions that prohibit the wingtip 102 from being in the flight position (if implemented).

[0066] Before sending the extension 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 the one or more electronic controllers 316 indicating the position of the wingtip 102. When the wingtip extension anomaly detector 110A determines that the folding wingtip system 230 is functional, the wingtip extension anomaly detector 110A sends the extension command to the one or more controllers 316.

[0067] In response to the extend command, the electronic controller 316 implements the extend command 326 and sends an open signal to the isolation valve 320. The electronic controller 316 sends a plurality of signals to the drive train actuator 352, to the hydraulic controller 318 associated with the electronic controller 316, and to the locking pin system 306 to retract the locking pins 358 of the locking pin actuator 334 so that the wing tip lugs 354 can rotate into position relative to the main portion lugs 356 without contacting any locking pins 358. When 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 locking pins 358 are retracted, the electronic controller 316 sends a signal to change the brake system 308 from the locked configuration to the unlocked configuration, and sends a signal to the hydraulic controller 318 to cause the hydraulic controller 318 to activate the wing tip actuation system 304 to rotate the wing tip 102 to the flight position. When the electronic controller 316 determines that the data from the hinge sensor 310 indicates that the wing tip 102 is in the flight position, the electronic controller 316 sends a signal to the drive train actuator 352 to cause the drive train actuator 352 to rotate the drive train 348 toward the locked position, and sends a plurality of signals to the hydraulic controller 318, which cause the locking pin actuator 334 to extend the locking pin 358 through the openings of the main part lug 356 and the wing tip lug 354, stop the operation of the power drive unit 332, and change the brake system 308 from the unlocked configuration to the locked configuration. When the data from the drive train position sensor 314 indicates that the locking system 350 is fully locked, the wing tip extension anomaly detector 110B 316 sends a notification signal to the flight control computer 202 indicating the completion of the extension command. A closing signal is sent to the isolation valve 320.

[0068] If wingtip extension anomaly detector 110B determines that the extension command stalled before completion, wingtip extension anomaly detector 110B halts further implementation of extension instruction 326 and sends a notification signal to flight control computer 202 to indicate the failure of the extension command. The notification signal includes one or more error codes that can be used by maintenance scheduler 228 to schedule specific maintenance to address the possible cause of the failure of the extension command and repair aircraft 100.

[0069] For example, if the wingtip extension anomaly detector 110B detects, based on data from the hinge sensor 310 associated with the electronic controller 116, that the wingtip 102 initially moves from the folded position toward the flight position and stops before reaching the flight position, the wingtip extension anomaly detector 110B stops further implementation of the folding instruction 328 and sends a notification signal with one or more specific error codes to the flight control computer 202. 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 locking 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 on the aircraft 100, which includes inspecting components of the wingtip actuation system 304 to determine why the movement of the wingtip 102 has stopped and repairing the wingtip actuation system 304. If the angle of the wing tip 102 is within the locking pin interference range, the one or more specific error codes include one or more second error codes that cause the flight control computer 202 to schedule maintenance on the aircraft 100, the maintenance including determining whether one or more wing tip lugs 354 contact the corresponding locking pins 358, and if there is contact, performing wing tip to locking pin down maintenance. The one or more second error codes also include one or more error codes that cause a determination of why the movement of the wing tip 102 ceased and repair of the wing tip actuation system 304 if the one or more wing tip lugs 354 are not in contact with the corresponding locking pins 358.

[0070] As another example, if the wingtip extension anomaly detector 110B determines that the wingtip 102 reaches the flight position or approaches the flight position at a time faster than the threshold time, the notification signal sent to the flight control computer 202 includes one or more third error codes indicating that there is a wingtip-to-stop descent. The flight control computer 202 changes specific settings to instruct the aircraft 100 to be grounded, and schedules maintenance of the aircraft 100 based on the one or more third error codes, including wingtip-to-stop descent and wingtip actuation system maintenance to repair the wingtip actuation system.

[0071] Figure 4A flow chart of an embodiment of a first method 400 for using the folding wingtip system 230 is shown. 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 completed command of the folding wingtip system 230 was a fold command. The determination may include checking that the last implemented command of the folding wingtip system 230 was a fold command based on the 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, and may be made periodically when the aircraft 100 is powered by the engines 208 of the aircraft 100 or powered by a connection to an external power source.

[0072] The above determination may also be made in response to a determination to send an extension command to move the wing tip 102 from the folded position to the flight position using the folding wing tip system 230. The determination to use the folding wing tip system 230 may be performed automatically based on a condition of use of the aircraft 100 determined by the flight control computer 202 based on sensor data from the sensor system 212 (e.g., the aircraft 100 is in a taxi-out phase and is not in a sector of an airport that prohibits the wing tip 102 from being in the flight position), based on input received from a crew member to implement an extension command that will not violate one or more conditions associated with the change to the flight position, or a combination thereof. If the input from the crew member would violate one or more conditions, the warning system 226 provides an output notifying the crew member of a problem associated with the extension command, and the flight control computer 202 does not cause implementation of the extension command.

[0073] The method 400 includes, at block 404, determining a wingtip position of the wingtip 102. Determining the wingtip position may include sending a wingtip position request to the folding wingtip system 230 and receiving position data from the hinge sensor 310. The position data corresponds to an angle of the wingtip 102 relative to the main portion 106 of the wing 104.

[0074] The method 400 determines whether the wing tip position is in the folded position at decision block 406. When it is determined at decision block 406 that the wing tip 102 is in the folded position and the method 400 is implemented based on a determination to send an extend command to the folding wing tip system 230, the method 400 includes the electronic controller 316 sending an extend command to the folding wing tip system 230 associated with the wing tip 102 at optional block 408, and the method 400 ends at block 410. When it is determined at decision block 406 that the wing tip 102 is in the folded position and the method is not implemented based on a determination to send an extend command to the folding wing tip system 230, the method 400 ends at block 410.

[0075] When it is determined at decision block 406 that the wing tip 102 is not in the folded position, the method 400 includes setting an error code for the folding wing tip system 230 at block 412. The error code includes 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. The error code associated with the failure of the braking system 308 causes the maintenance scheduler 228 of the flight control computer 202 to schedule braking system maintenance to determine why the braking system 308 failed and to repair the braking system 308. The error code associated with the failure of the wing tip actuation system 304 causes the maintenance scheduler 228 to schedule wing tip actuation system maintenance to determine which component(s) of the wing tip actuation system 304 failed to enable the wing tip 102 to be lowered and to repair the wing tip actuation system 304.

[0076] The error code also includes one or more additional error codes depending on the angle of the wingtip 102 determined based on the position data. For example, if the angle of the wingtip 102 is within the locking pin interference range, the error code includes one or more additional error codes indicating that the wingtip 102 is down and may have contacted the locking pin 358, and maintenance will include wingtip to locking pin down maintenance; and if the wingtip is in the flight position, or substantially in the flight position (e.g., within 1 degree, 2 degrees, or some other small number of degrees of the flight position), the error code includes one or more additional error codes indicating that the wingtip 102 is down and maintenance will include wingtip to stop down maintenance.

[0077] The method 400 includes changing a setting at block 414 to instruct the aircraft 100 to be grounded. The setting prevents the flight control computer 202 from allowing the aircraft 100 to fly. The method 400 also includes scheduling maintenance for the aircraft 100 at block 416. The type of maintenance scheduled for the aircraft is based on the error code. The method 400 then ends at block 410.

[0078] Figure 5 A flow chart of an embodiment of a second method 500 for using the folding wingtip system 230 is shown. The method 500 may be performed by the flight control computer 202. The method 500 includes sending a command to the first electronic controller 316A of the folding wingtip system 230 to move the wingtip 102 from the first position to the second position at block 502. The command may be a fold command to move the wingtip 102 from the flight position to the folded position, or the command may be an extend command to move the wingtip 102 from the folded position to the flight position.

[0079] The method 500 includes receiving a first notification signal from the first electronic controller 316A regarding the implementation of the command at block 504. The method 500 includes determining, at a decision block 506, whether the command was successfully completed based on the content of the notification. When the determination at the decision block 506 is that the command was successfully completed, the method 500 ends at block 508. When the determination at the decision block 506 is that the command was not successfully completed, the method 500 includes changing a setting to instruct the aircraft 100 to be grounded at block 510. The method 500 includes scheduling maintenance of the aircraft 100 at block 512, wherein the type of maintenance is based on one or more error codes included in the first notification signal.

[0080] When the determination at decision block 506 indicates that the command was not successfully completed, there is a possibility that the problem with the folding wingtip system 230 is a problem with one or more sensors associated with the first electronic controller 316A rather than a problem with the mechanical structure of the folding wingtip system 230. The redundant control system 316B of the folding wingtip system 230 can be used to determine whether the problem with the folding wingtip system 230 is a problem with one or more 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 be grounded for maintenance, but maintenance can be scheduled for the sensors associated with the electronic controller 316A at a convenient time, and the aircraft 100 can be used for one or more additional flights.

[0081] In conjunction with determining whether the command was not successfully completed 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 the implementation of the command at block 516.

[0082] The method 500 includes, at decision block 518, determining whether the command was successfully completed based on the content of the second notification. When it is determined at decision block 518 that the command was successfully completed, the method 500 includes, at block 520, changing the setting to instruct the aircraft 100 not to stop flying. The method 500 includes, at block 522, changing the scheduled maintenance to include maintenance of the sensor system associated with the first electronic controller 316A. The method 500 then ends at block 508.

[0083] When it is determined at decision block 518 that the command was not successfully completed, the method 500 includes determining whether the error codes of the notification signal are the same at decision block 524. When it is determined at decision block 518 that the notification signal includes the same error code, the method 500 ends at block 508. When it is determined at decision block 524 that the notification signal includes different error codes, the method 500 includes modifying the scheduled maintenance for the aircraft to include maintenance based on all error codes in the notification signal at block 526. The method 500 then ends at block 508.

[0084] Figure 6 A flow chart of an embodiment of a third method 600 for implementing an extension command using the folding wing tip system 230 is shown. The method 600 may be used to change the position of the wing tip 102 from the folded position to the flight position. The method 600 may be performed by one of the electronic controllers 316 in response to receiving an extension command from the flight control computer 202, and the method 600 includes using the extension instruction 326 and the wing tip extension anomaly detector 110B. The method 600 includes sending an opening signal to the isolation valve 320 at box 602. Opening the isolation valve enables the hydraulically powered components of the folding wing tip system 230 to operate when supplied with hydraulic fluid by the hydraulic controller 318 associated with the electronic controller 316.

[0085] The method 600 determines at decision block 604 whether the isolation valve 320 is open. The determination is based on data from the valve sensor. When the determination at decision block 604 is that the isolation valve is not open, the method 600 includes setting an isolation valve error code at block 606. The method 600 includes sending a notification signal to the flight control computer 202 at block 608. The notification signal includes the isolation valve error code, which prompts the aircraft 100 to be grounded and prompts maintenance to be scheduled for the aircraft 100 to address one or more issues associated with the isolation valve, the valve sensor, or both. The method 600 ends at block 610.

[0086] When the determination at decision block 604 is that the isolation valve 320 is open, the method 600 includes sending a first series of signals that cause the locking pin 358 of the locking pin actuator 334 to fully retract at block 612. These first signals may include signals to the hydraulic controller 318 that cause hydraulic fluid to be supplied to the locking pin system 306 and signals to the driveline actuator 352 that cause the driveline 348 to rotate.

[0087] The method 600 determines whether the locking system 350 of the locking pin actuator 334 is operating properly at decision block 614. This determination may be based on sensor data from the powertrain actuator position sensor 312 and the powertrain position sensor 314. When the determination at decision block 614 is that the locking system 350 is not operating properly, the method 600 includes closing the isolation valve 320 by sending a closing signal to the isolation valve 320 at block 616.

[0088] The method 600 determines at decision block 618 whether the isolation valve 320 is operating correctly to close the isolation valve 320. When the determination at decision block 618 is that the isolation valve 320 is not operating correctly, the method includes setting one or more isolation valve error codes at block 620. The method 600 includes setting one or more error codes at block 622. Also, when the determination at decision block 618 is that the isolation valve is operating correctly to close the isolation valve 320, the method 600 moves to block 622 and sets one or more error codes. The error code may indicate that one or more of the locking systems 350 are not operating correctly. The method 600 proceeds to block 608 to send a notification signal to the flight control computer 202. The notification signal includes the error code, any isolation valve error code, and indicates that the extension command failed. The method 600 then ends at block 610.

[0089] When the determination at decision block 614 is that the locking system 350 is operating properly, the method 600 includes sending a second series of signals at block 624 to cause the braking system 308 to change from the locked configuration to the unlocked configuration and cause activation of the wingtip actuation system 304 to move the wingtip 102 from the folded position to the flight position.

[0090] The method 600 determines whether the wingtip 102 has achieved the flight position at decision block 626 . This determination may be based on hinge sensor data from the hinge sensor 310 indicating the angle of the wingtip 102 relative to the main portion 106 of the wing 104 .

[0091] When the determination at decision block 626 is that the wing tip 102 has not achieved the flight position, the method 600 proceeds to block 616 and then to decision block 618. The method 600 returns to block 622 to set one or more error codes after implementing decision block 618 or decision block 618 and block 620. The one or more error codes may include a specific error code based on an analysis of the hinge sensor data, the clock data, or both. If the hinge sensor data indicates that the wing tip 102 has not moved from the folded position, a specific error code is set indicating a problem with the brake system 308 and the wing tip actuation system 304.

[0092] If the hinge sensor data indicates that the wingtip 102 has stopped in a position outside of the locking pin interference range, a specific error code is set indicating a problem associated with the wingtip actuation system 304. If the hinge sensor data indicates that the wingtip 102 has stopped in the locking pin interference range, a specific error code is set indicating that a wingtip to locking pin drop has occurred. The specific error code prompts scheduling maintenance to determine and resolve a problem that may have occurred if the wingtip 102 has stopped in the locking pin interference range but has not contacted one or more locking pins 358 due to a malfunction of the wingtip actuation system 304, if the wingtip actuation system 304 has failed and the wingtip lugs 354 have dropped and contacted one or more locking pins 358, or if the wingtip actuation system 304 has not failed but one or more of the wingtip lugs 354 have been driven against one or more locking pins 358 by the wingtip actuation system 304.

[0093] If the clock data indicates that the wingtip acquires position too quickly (e.g., faster than a threshold time) at or near the flight position, a specific error code indicates that a wingtip-to-stop drop has occurred. The error code prompts maintenance to be scheduled to address the problem with the wingtip actuation system 304 allowing the wingtip 102 to drop, and to address damage that may have occurred as a result of the wingtip 102 dropping.

[0094] When the determination at decision block 626 is that the wingtip 102 has indeed achieved the flight position, the method 600 includes sending a third series of signals to stop operation of the wingtip actuation system 304, supplying hydraulic fluid to the locking pin actuator 334 to extend the locking pin 358 through the wingtip lug 354 and the main section lug, and changing the brake system 308 to a locked configuration at block 628. When the locking pin 358 extends through the wingtip lug and the main section lug, the wingtip is secured to the main section 106, and the aircraft 100 is configured for flight.

[0095] The method 600 includes determining at decision block 630 whether the action based on the third series of signals was successfully completed. When it is determined at block 630 that the action based on the third series of signals was not successfully completed, the method 600 proceeds to block 616 and then to decision block 6618. 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 the data from the transmission position sensor 314 indicates that the transmission 348 has not achieved a fully locked position, the one or more error signals include a specific error code to indicate a fault in the locking system 150, the transmission 348, or both.

[0096] When the determination at decision block 630 is that the action based on the third series of signals was successfully completed, the method 600 includes closing the isolation valve 320 at block 632. The method 600 determines at decision block 634 whether the isolation valve is closed. When the determination at decision block 634 is that the isolation valve 320 is not closed, the method 600 includes setting an isolation valve error code at block 636. The method proceeds to block 608 to send a notification signal to the flight control computer 202, and the method 600 ends at block 610. The notification signal indicates that the extension command failed and includes an isolation valve error code. In response to the notification signal, the flight control computer 202 grounds the aircraft 100 and schedules appropriate maintenance to address the problem with the isolation valve 320.

[0097] When the determination at decision block 634 is that the isolation valve 320 is indeed closed, the method 600 includes sending a notification signal to the flight control computer 202 at block 638 to indicate completion of the extend command. The method then ends at block 610. If the open signal sent to the isolation valve 320 at block 602, the close signal sent to the isolation valve at block 632, or both, is not implemented by the electronic controller 316 executing the extend command 326 but is implemented by the redundant electronic controller 316, then the notification signal sent to the flight control computer 202 at block 638 may include one or more isolation valve error codes, the one or more isolation valve error codes indicating a problem with one or more valve sensors. In response to the presence of at least one isolation valve error code in the notification signal indicating completion of the extend command, the flight control computer 202 schedules maintenance to resolve the problem with the valve sensor.

[0098] Figure 7 A flow chart depicting an implementation of a fourth method 700 for implementing a fold command using the folding wing tip system 230. The method 700 may be used to change the position of the wing tip 102 from a flight position to a folded position. The method 700 may be performed by one of the electronic controllers 316 in response to receiving a fold command from the flight control computer 202, and the method 700 includes using the fold instruction 328 and the wing tip extension anomaly detector 110B. The method 700 includes sending an open signal to the isolation valve 320 at block 702.

[0099] The method 700 determines at decision block 704 whether the isolation valve 320 is open. The determination is based on data from the valve sensor. When the determination at decision block 704 is that the isolation valve is not open, the method 700 includes setting an isolation valve error code at block 706. The method 700 includes sending a notification signal to the flight control computer 202 at block 708. The notification signal includes the isolation valve error code, which causes the aircraft 100 to be grounded and causes maintenance to be scheduled for the aircraft 100 to address one or more issues associated with the isolation valve, the valve sensor, or both. The method 700 ends at block 710.

[0100] When the determination at decision block 704 is that the isolation valve is open, the method 700 includes sending a first series of signals at block 712 to place the brake system 308 in an unlocked configuration and cause the locking pin system 306 to retract the locking pin 358 from the openings in the wingtip lugs 354 and the openings in the main portion lugs 356. These signals may include signals from the electronic controller 316 to the corresponding hydraulic controller 318 and to the driveline actuator 352 to rotate the driveline 348.

[0101] The method 700 determines whether the locking system 350 of the locking pin actuator 334 is operating properly at decision block 714. This determination may be based on sensor data from the powertrain actuator position sensor 312 and the powertrain position sensor 314. When the determination at decision block 714 is that the locking system 350 is not operating properly, the method 700 includes closing the isolation valve 320 at block 716.

[0102] The method 700 determines at decision block 718 whether the isolation valve 320 is operating correctly to close the isolation valve 320. When the determination at decision block 718 is that the isolation valve 320 is not operating correctly, the method includes setting one or more isolation valve error codes at block 720. The method 700 includes setting one or more error codes at block 722. Also, when the determination at decision block 718 is that the isolation valve is operating correctly to close the isolation valve 320, the method 700 moves to block 722 and sets one or more error codes. The error code may indicate that one or more of the locking systems 350 are not operating correctly. The method 700 proceeds to block 708 to send a notification signal to the flight control computer 202. The notification signal includes the error code, any isolation valve error code, and indicates that the fold command failed. The error code notifies the flight control computer 202 to ground the aircraft 100 and enables the flight control computer 202 to schedule appropriate maintenance of the aircraft 100 to allow the aircraft 100 to be returned to service. The method 700 ends at block 710.

[0103] When the determination at decision block 714 is that the locking system 350 is operating properly, the method 700 includes sending a second series of signals to the wingtip actuation system 304 to move the wingtip 102 to the folded position at block 724. The method 700 determines whether the wingtip 102 has achieved the folded position at decision block 726. This determination may be based on hinge sensor data from the hinge sensor 310 indicating the angle of the wingtip 102 relative to the main portion 106 of the wing 104.

[0104] When the determination at decision box 726 is that the wing tip 102 has not achieved the folded position, the method 700 proceeds to box 716 and then to decision box 718. The method 700 proceeds from decision box 718 or from box 718 and box 720 to box 722 to set one or more error codes. For example, one or more specific error codes may be based on an analysis of the hinge sensor data. If the hinge sensor data indicates that the wing tip 102 is not raised, the specific error code may include one or more error codes indicating a problem with one or more torque tubes 336, 340 of the wing tip actuation system 304. If the hinge sensor data indicates that the wing tip 102 initially rises and stops at a specific angle, the specific error code may be one or more error codes indicating a problem with the power drive unit 332, the angle gear box 338, the rotary fold actuator 342, or a combination thereof. If the wing tip 102 is initially raised and then lowered back to or near the flight position, the specific error code may be an error code indicating a problem with one or more torque tubes 336, 340 of the wing tip actuation system 304 and an error code indicating that a wing tip to stop descent of the wing tip 102 occurred. If the wing tip 102 is initially raised and then lowered and stops within the locking pin interference range, the specific error code 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 that a wing tip to stop descent occurred. Additional error codes may be set based on hinge sensor data or other sensor data.

[0105] When the determination at decision block 726 indicates that the wing tip 102 has achieved the folded position, the method 700 includes sending a third series of signals to stop the supply of hydraulic fluid to retract the locking pin 358, stop operation of the wing tip actuation system 304, and set the brake system 308 to the locked configuration at block 728. The method 700 proceeds to decision block 730 to determine whether the actions implemented by the third set of signals were successfully completed.

[0106] When the determination at decision block 730 is that the action implemented by the third set of instructions was not successfully completed, the method 700 proceeds to block 716, and then to decision block 718. The method 700 proceeds to block 722 from decision block 618 or from decision block and block 720 to set one or more error codes after decision block 718. For example, if data from a brake system sensor indicates that the brake system 308 has not changed to a locked configuration, a specific error code is set to indicate a problem with the brake system 308 or a brake system sensor.

[0107] When the determination at decision block 730 is that the action based on the third series of signals was successfully completed, the method 700 includes closing the isolation valve 320 at block 732. The method 700 determines at decision block 734 whether the isolation valve 320 is closed. When the determination at decision block 734 is that the isolation valve 320 is not closed, the method 700 includes setting an isolation valve error code at block 736. The method proceeds to block 708 to send a notification signal to the flight control computer 202, and the method 700 ends at block 710. The notification signal indicates that the extension command failed and includes an isolation valve error code. In response to the notification signal, the flight control computer 202 causes the aircraft 100 to be grounded and schedules appropriate maintenance to address the problem with the isolation valve 320.

[0108] When the determination at decision block 734 is that the isolation valve 320 is indeed closed, the method 700 includes sending a notification signal to the flight control computer 202 at block 738 to indicate completion of the fold command. The method then ends at block 710. If the open signal sent to the isolation valve 320 at block 702, the close signal sent to the isolation valve at block 732, or both, is not implemented by the electronic controller 316 executing the fold instruction 328 but by the redundant electronic controller 316, the notification signal sent to the flight control computer 202 at block 738 may include one or more isolation valve error codes, the isolation valve error code indicating a problem with one or more valve sensors. In response to the presence of at least one isolation valve error code in the notification signal indicating completion of the fold command, the flight control computer 202 schedules maintenance to resolve the problem with the valve sensor.

[0109] Figure 8 is a flow chart showing a method 800 for representing a life cycle of an aircraft, the aircraft including Figure 2 The exemplary method 800 includes, at block 802, an aircraft (such as a reference aircraft) that is configured to include a wingtip extension anomaly detector 110A and a flight control computer 202 of a folding wingtip system 230. The folding wingtip system 230 includes (or is otherwise coupled to) the wingtip extension anomaly detector 110B. Figures 1A to 3 During the specification and design of the aircraft, the method 800 may include the specification and design of the flight control computer 202 and the folding wing tip system 230. The method 800 includes material procurement at block 804, which may include obtaining components of the flight control computer 202 and the folding wing tip system 230.

[0110] During production, the method 800 includes component and subassembly manufacturing at block 806, and system integration of the aircraft at block 808. For example, the method 800 may include component and subassembly manufacturing of the flight control computer 202 and the folding wingtip system 230. The method 800 includes certification and delivery of the aircraft at block 810, and placing the aircraft into service at block 812. The certification and delivery may include certification of the flight control computer 202 and the folding wingtip system 230 to place the flight control computer 202 and the folding wingtip system 230 into service. When in service by a customer, the aircraft may be scheduled for routine maintenance and service (which may also include modification, reconfiguration, refurbishment, etc.). The method 800 includes performing maintenance and service on the aircraft at block 814, which may include performing maintenance and service on the flight control computer 202 and the folding wingtip system 230.

[0111] Each process of method 800 may be performed or executed by a system integrator, a third party, and / or an operator (e.g., a customer). For the purposes of this specification, a system integrator may include, but is not limited to, any number of aircraft manufacturers and main system subcontractors; 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.

[0112] Aspects of the disclosure may be described in the context of embodiments of an aircraft. Figure 1A - Figure 3 A specific embodiment of the aircraft 100 is Fig. 9 Shown in.

[0113] exist Fig. 9 In the embodiment of the invention, aircraft 100 includes fuselage 902 having plurality of systems 904 and interior 906. Embodiments of plurality of systems 904 include one or more of propulsion system 908, electrical system 910, environmental system 912, and hydraulic system 914. Any number of other systems may be included. Fig. 9 In the illustrated embodiment, Figure 2 Some components of folding wingtip system 230 are included in electrical system 910 , and other components of folding wingtip system 230 are included in hydraulic system 914 . Figure 2 The flight control computer 202 is included in the electrical system 910 .

[0114] Fig.10 is an illustration of a block diagram of a computing environment 1000 including a computing device 1002 configured to support implementation of computer-implemented methods and computer-executable program instructions (or code) according to the present disclosure. For example, the computing device 1002 or a portion thereof may execute instructions to perform or cause the device to perform reference Figure 2-Figure 9In one embodiment, the computing device 1002 is Figure 1A-Figure 3 The aircraft 100, the flight control computer 202, the folding wingtip system 230 and the electronic controller 316 are or are parts thereof.

[0115] 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 non-transitory computer-readable media, including 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 starting the computing device 1002 and a complete operating system that enables the computing device 1002 to interact with users, other programs, and other devices. The system memory 1006 includes one or more applications 1016 (e.g., instructions) that can be executed by the processor 1004. For example, when computing device 1002 is flight control computer 202, one or more applications 1016 include flight instructions 224, warning system 226, maintenance scheduler 228, and wingtip extension anomaly detector 110A; and when computing device 1002 is electronic controller 316, one or more applications 1016 include extend instructions 326, fold instructions 328, and wingtip extension anomaly detector 110B.

[0116] In some configurations, the processor 1004 communicates with one or more storage devices 1008. For example, the storage device 1008 includes a non-transitory computer-readable medium, which may include a non-volatile storage device, such as a magnetic disk, an optical disk, or a flash memory device. The storage device 1008 may include removable and non-removable storage devices. The storage device 1008 may be configured to store an operating system, an image of the operating system, applications, and program data. In a specific implementation, the system memory 1006, the storage device 1008, or both include tangible computer-readable media that is incorporated in hardware and is not a signal.

[0117] 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 user interaction. The input / output interface 1010 may include a serial interface (e.g., a universal serial bus (USB) interface or an Institute of Electrical and Electronics Engineers (IEEE) interface), a parallel interface, a display adapter, an audio adapter, and other interfaces ("IEEE" is a registered trademark of the Institute of Electrical and Electronics Engineers of Piscataway, New Jersey). The input / output device 1018 may include a keyboard, a pointing device, a display (e.g., one or more monitors, one or more meters, etc.), a speaker, a microphone, a touch screen, a rotatable selector, a joystick, a knob, a slider, a switch, and other devices. The processor 1004 detects an interaction event based on user input received via the input / output interface 1010. In addition, the processor 1004 sends a display to a display device via the input / output interface 1010.

[0118] In some configurations, the processor 1004 can 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 Figure 3 When the electronic controller 316 is connected to the computer device 1002 via the interface 1012 Figure 2 The one or more communication interfaces 1012 may include a wired Ethernet interface, an IEEE 802 wireless interface, other wireless communication interfaces, one or more converters that convert analog signals to digital signals, one or more converters that convert electrical signals to optical signals, one or more converters that convert received optical signals to electrical signals, or other network interfaces.

[0119] In some embodiments, 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 executed to implement Figure 1A-Figure 10 In some embodiments, the same may be implemented 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, by dedicated hardware circuits, or any combination thereof. Figure 1A-Figure 10 Part or all of one or more associated operations or methods.

[0120] Certain aspects of the present disclosure are described in the following set of related embodiments:

[0121] Group A:

[0122] According to embodiment 1, an aircraft includes: a wing, wherein the wing includes a main section and a wingtip; and a folding wingtip system, wherein the folding wingtip system is configured to rotate the wingtip relative to the main section, wherein the folding wingtip system includes an electronic controller, wherein the electronic controller is configured to: implement an extension command received from a flight control computer to rotate the wingtip from a folded position to a flight position; and in response to determining that the rotation of the wingtip stops before the flight position during the implementation of the extension command, send a first signal to the flight computer to ground the folding wingtip aircraft and schedule maintenance of the folding wingtip aircraft, wherein in response to the control unit determining that a first specific angle of the wingtip relative to the main section is within a locking pin interference range, the first signal indicates that the maintenance includes wingtip to locking pin lowering maintenance.

[0123] Embodiment 2 includes an aircraft according to embodiment 1, wherein wingtip to locking pin descent maintenance includes instructions for: identifying one or more specific locking pins that contact one or more specific lugs of the wingtip; replacing the one or more specific locking pins; identifying a first subset of the one or more specific locking pins having visible damage as scrap; and testing a second subset of the one or more specific locking pins without visible damage for non-visible damage.

[0124] Embodiment 3 includes an aircraft according to embodiment 2, wherein the wingtip to locking pin descent maintenance further includes instructions for: replacing one or more wingtip lugs; identifying a first subset of wingtip lugs having visible damage as scrap; and causing a second subset of wingtip lugs without visible damage to be tested for non-visible damage.

[0125] Embodiment 4 includes an aircraft according to any of embodiments 1 to 3, wherein the first signal further causes the flight control computer to schedule wingtip actuation system maintenance for the aircraft.

[0126] Embodiment 5 includes an aircraft according to any one of embodiments 1 to 4, wherein when the determination by the electronic controller indicates that the first specific angle is not within the locking pin interference range, the first signal indicates that maintenance includes wingtip actuator maintenance.

[0127] Embodiment 6 includes an aircraft according to any one of embodiments 1 to 5, wherein the electronic controller is further configured to: receive a request for position data associated with the angle of the wing tip relative to the main part from a flight control computer; and send the position data to the flight control computer based on data received from the hinge sensor, wherein when the position of the wing tip indicated by the position data is not in the folded position, the flight control computer grounds the aircraft and schedules maintenance of the aircraft.

[0128] Embodiment 7 includes an aircraft according to embodiment 6, wherein the maintenance includes brake system maintenance of a brake system configured to hold the wing tip in a folded position.

[0129] Embodiment 8 includes an aircraft according to embodiment 6 or embodiment 7, wherein the maintenance includes a wingtip to locking pin lower maintenance when the angle of the wingtip relative to the main portion is within the locking pin interference range.

[0130] Embodiment 9 includes an aircraft according to embodiment 6 or embodiment 7, wherein maintenance when the wing tip is in or near the flight position includes wing tip to stop lower maintenance.

[0131] Embodiment 10 includes an aircraft according to embodiment 9, wherein the wingtip to stop descent maintenance includes: replacing the wingtip lugs; replacing the lug stops of the main part; identifying a first subset of wingtip lugs with visible damage as scrap; and causing a second subset of lugs without visible damage to be tested for non-visible damage.

[0132] According to embodiment 11, a method includes: implementing, via an electronic controller of a folding wingtip system of an aircraft, an extension command received by the electronic controller from a flight control computer to rotate the wingtip of a wing from a folded position to a flight position; and in response to a first determination made at the electronic controller that rotation of the wingtip stops before the flight position during implementation of the extension 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, wherein the first notification signal includes one or more first error codes, and wherein, in response to the electronic controller determining that a first specific angle indicating the wingtip relative to a main portion of the wing is within a locking pin interference range, the first notification signal causes the maintenance to include wingtip to locking pin lower maintenance.

[0133] Embodiment 12 includes a method according to embodiment 11, wherein, in response to a second determination that an implementation time of the extension command from the start of implementation of the extension command to the completion of implementation of the extension command indicated when the rotation of the wingtip relative to the main part stops in the flight position is shorter than a threshold implementation time, one or more first error codes indicate a wingtip-to-stop descent, and wherein the one or more first error codes are configured to cause maintenance of the aircraft to include wingtip-to-stop descent maintenance.

[0134] Embodiment 13 includes a method according to embodiment 11 or embodiment 12, further comprising: detecting at a control unit a transition of the aircraft from a power-off state to a power-on state; determining at the control unit a specific angle of the wing tip relative to the main part; determining at the control unit a last implemented command for a folding wing tip system to position the wing tip in a folded position; and when the specific angle is different from a first angle associated with the folded position, sending a signal to a flight computer to ground the aircraft and schedule maintenance of the aircraft.

[0135] Embodiment 14 includes the method of embodiment 13, wherein the maintenance includes wingtip to locking pin lower maintenance when the wingtip position data indicates that the wingtip is at a specific angle within the locking pin interference range.

[0136] Embodiment 15 includes the method according to embodiment 13, wherein when the wingtip position data indicates that the wingtip is at or substantially at the flight position, the maintenance includes wingtip-to-stop descent maintenance.

[0137] Embodiment 16 includes a method according to any one of Embodiments 11 to 15, further comprising: receiving a second command from a flight control computer at a control unit to transition the wingtip from a first position to a second position; sending a control signal to a powertrain actuator, a hydraulic control module, or both to implement the second command; and in response to the control unit determining that a locking system of a locking pin actuator is not functioning properly based on powertrain actuator data from a powertrain actuator sensor and powertrain position data from a powertrain position sensor, sending a specific notification signal to the flight control computer, wherein the specific notification signal includes one or more specific error codes associated with a locking system failure, wherein the specific notification signal grounds the aircraft and schedules specific maintenance of the aircraft, and wherein the specific maintenance includes locking pin system maintenance.

[0138] According to Embodiment 17, a device includes: a memory configured to store instructions; and a processor configured to execute the instructions to perform the method of any one of Embodiments 11 to 16.

[0139] According to embodiment 18, a non-transitory computer-readable medium stores instructions, which, when executed by a processor, cause the processor to perform the method of any one of embodiments 11 to 16.

[0140] According to embodiment 19, a device includes means for performing the method according to any one of embodiments 11 to 16.

[0141] According to embodiment 20, a non-transitory computer readable medium comprising instructions executable by one or more processors of an electronic controller of an aircraft to: implement an extension command received from a flight control computer to rotate a wingtip of a wing about a hinge axis from a folded position to a flight position; and in response to a first determination made during implementation of the extension command that rotation of the wingtip stops prior to the flight position, send a first signal to the flight control computer to ground the aircraft and schedule maintenance of the folding wingtip aircraft, wherein, in response to a second determination indicating that a first specific angle of the wingtip relative to a main portion of the wing is within a locking pin interference range, the first signal causes the maintenance to include wingtip to locking pin lowering maintenance.

[0142] Embodiment 21 includes a non-transitory computer-readable medium according to embodiment 20, wherein the instructions are further executable by one or more processors to: implement a fold command to transition the wing tip from a flight position to a folded position; determine that the position of the wing tip relative to the main portion is not in the folded position at the end of implementing the fold command; and send a second notification signal to the flight control computer, wherein the second notification signal includes one or more second error codes associated with the position, and wherein the second notification signal grounds the aircraft and causes specific maintenance of the aircraft to be scheduled based on the one or more second error codes.

[0143] Embodiment 22 includes a non-transitory computer readable medium according to embodiment 21, wherein when the position is within the locking pin interference range, the specific maintenance includes a wingtip to locking pin drop maintenance.

[0144] Embodiment 23 includes a non-transitory computer readable medium according to embodiment 21, wherein when the position is at or near the flight position, the maintenance includes wingtip-to-stop descent maintenance.

[0145] According to embodiment 24, an aircraft includes: a wing, wherein the wing includes a main portion and a wingtip; a folding wingtip system, configured to rotate the wingtip relative to the main portion; and a flight control computer, wherein the flight control computer is configured to: set a first error code for the folding wingtip system in response to a first determination that the wingtip position of the wingtip is not in a folded position when a second determination indicates that the last completed command of the folding wingtip system is a folding command; and change a setting based on the first error code to instruct the aircraft to ground.

[0146] Embodiment 25 includes the aircraft of Embodiment 24, wherein the flight control computer is further configured to schedule maintenance of the aircraft based on the first error code.

[0147] Embodiment 26 includes an aircraft according to embodiment 25, wherein the maintenance includes maintenance of a brake system configured to hold the wing tip in a folded position.

[0148] Embodiment 27 includes an aircraft according to Embodiment 25 or Embodiment 26, wherein the maintenance includes maintenance of a wingtip actuation system.

[0149] Embodiment 28 includes the aircraft of any of Embodiments 25 to 27, wherein the maintenance includes wingtip to locking pin lower maintenance performed in response to a third determination that the wingtip position is within the locking pin interference range.

[0150] Embodiment 29 includes an aircraft according to embodiment 28, wherein wingtip to locking pin descent maintenance includes instructions for: identifying one or more specific locking pins that contact one or more specific lugs of the wingtip; replacing the one or more specific locking pins; identifying a first subset of the one or more specific locking pins having visible damage as scrap; and causing a second subset of the one or more specific locking pins without visible damage to be tested for non-visible damage.

[0151] Embodiment 30 includes an aircraft according to embodiment 29, wherein the wingtip to locking pin drop maintenance also includes instructions to: replace one or more wingtip lugs; identify a first subset of the one or more wingtip lugs having visible damage as scrap; and cause a second subset of the one or more wingtip lugs not having visible damage to be tested for non-visible damage.

[0152] Embodiment 31 includes the aircraft of any of Embodiments 25 to 27, wherein in response to a third determination that the wingtip position is at or near the flight position, the maintenance includes a wingtip-to-stop descent maintenance.

[0153] Embodiment 32 includes an aircraft according to embodiment 31, wherein wingtip to stop descent maintenance includes instructions to: replace a wingtip lug of a wingtip; replace a lug stop of a main portion; identify a first subset of wingtip lugs having visible damage as scrap; and cause a second subset of wingtip lugs without visible damage to be tested for non-visible damage.

[0154] Embodiment 33 includes an aircraft according to any one of Embodiments 24 to 32, wherein the flight control computer is further configured to send an extension command to an electronic controller of the folding wingtip system in response to the wingtip position indicating that the wingtip is in the folded position and determining to send an extension command to move the wingtip from the folded position to the flight position.

[0155] Embodiment 34 includes an aircraft according to any one of Embodiments 24 to 33, wherein the flight control computer is further configured to: send a first extension command to a 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 a failure of the first extension command; change a setting based on the first notification signal to indicate that the aircraft is grounded; and schedule maintenance of the aircraft based on one or more second error codes included in the first notification signal.

[0156] Embodiment 35 includes an aircraft according to embodiment 34, wherein the flight control computer is further configured to: send a second extension command to a 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 extension command; change a setting based on the second notification signal to indicate that the aircraft does not stop; and change the type of maintenance scheduled for the aircraft based on the second notification signal.

[0157] Embodiment 36 includes an aircraft according to embodiment 34, wherein the flight control computer is further configured to: send a second extension command to a second electronic controller in response to the first notification signal; receive a second notification signal from the second electronic controller indicating that the second extension command failed; and modify the maintenance scheduled for the aircraft in response to the second notification signal to include additional maintenance, the second notification signal including one or more additional error codes not included in the first notification signal.

[0158] According to embodiment 37, a method includes: in response to a determination that the last command completed by a folding wingtip system was a folding command, determining a wingtip position of a wingtip at a flight control computer of an aircraft; and in response to the wingtip position indicating that the wingtip is not in a folded position: setting a first error code for the folding wingtip system via the flight control computer; changing the setting via the flight control computer to instruct the aircraft to be grounded; and scheduling maintenance of the aircraft based on the first error code.

[0159] Embodiment 38 includes the method of embodiment 37, wherein determining the wingtip position of the wingtip is made in response to a transition of the aircraft from an idle or low power state to a power state.

[0160] Embodiment 39 includes the method of embodiment 37, wherein an implementation determination of a wingtip position of the wingtip is made in response to a specific determination being made to send an extend command to the folding wingtip system.

[0161] According to embodiment 40, a device includes: a memory configured to store instructions; and a processor configured to execute the instructions to perform the method of any one of embodiments 37 to 39.

[0162] According to embodiment 41, a non-transitory computer-readable medium stores instructions, which, when executed by a processor, cause the processor to perform the method of any one of embodiments 37 to 39.

[0163] According to embodiment 42, a device includes means for performing the method of any one of embodiments 37 to 39.

[0164] According to embodiment 43, a non-transitory computer-readable medium includes instructions that can be executed by one or more processors to: in response to a determination that the last completed command of a folding wingtip system was a folding command, determine a wingtip position of a wingtip of an aircraft; and in response to the wingtip position indicating that the wingtip is not in a folded position, set a first error code for the folding wingtip system; change a setting to indicate that the aircraft is grounded; and schedule maintenance of the aircraft based on the first error code.

[0165] Embodiment 44 includes a non-transitory computer-readable medium according to embodiment 42, wherein the instructions are capable of being further executed by one or more processors to: send a first fold command to a first electronic controller to change the wingtip position from a flight position to a folded position; receive a first notification signal from the first electronic controller indicating that the first fold command failed; change a setting based on the first notification signal to indicate that the aircraft is grounded; and schedule maintenance of the aircraft based on one or more second error codes in the first notification signal.

[0166] Embodiment 45 includes a non-transitory computer-readable medium according to embodiment 44, wherein the instructions are also executable by one or more processors to: send a second folding command to a 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 folding command; change a setting based on the second notification signal to indicate that the aircraft does not stop; and change the type of maintenance scheduled for the aircraft based on the second notification signal.

[0167] Embodiment 46 includes a non-transitory computer-readable medium according to embodiment 44, wherein the instructions are also executable by one or more processors to: send a second folding command to a second electronic controller in response to the first notification signal; receive a second notification signal from the second electronic controller indicating that the second folding command failed; and in response to the second notification signal including one or more additional error codes not included in the first notification signal, modify the maintenance scheduled for the aircraft to include additional maintenance.

[0168] Group B:

[0169] Embodiment 1. An aircraft, comprising:

[0170] A wing, wherein the wing comprises a main portion and a wing tip;

[0171] a folding wingtip system configured to rotate the wingtip relative to the main portion; and

[0172] A flight control computer, wherein the flight control computer is configured to:

[0173] setting a first error code for the folding wingtip system in response to a first determination that the wingtip position of the wingtip is not in a folded position when a second determination indicates that the last completed command for the folding wingtip system was a fold command; and

[0174] A setting is changed based on the first error code to instruct the aircraft to be grounded.

[0175] Embodiment 2. The aircraft of Embodiment 1, wherein the flight control computer is further configured to schedule maintenance of the aircraft based on the first error code.

[0176] Embodiment 3. The aircraft of Embodiment 2, wherein the maintenance comprises maintenance of a brake system configured to hold the wing tip in the folded position.

[0177] Embodiment 4. The aircraft of embodiment 2, wherein the maintenance comprises maintenance of a wingtip actuation system.

[0178] Embodiment 5. The aircraft of Embodiment 2, wherein in response to a third determination that the wingtip position is within a locking pin interference range, the maintenance comprises a wingtip to locking pin lower maintenance.

[0179] Embodiment 6. The aircraft of embodiment 5, wherein the wingtip to locking pin descent maintenance comprises instructions to:

[0180] identifying one or more locking pins contacting one or more wingtip lugs of the wingtip;

[0181] replacing the one or more latch pins;

[0182] identifying a first subset of one or more specific locking pins having visible damage as scrap; and

[0183] A second subset of one or more specific latch pins without visible damage is prompted to be tested for non-visible damage.

[0184] Embodiment 7. The aircraft of embodiment 6, wherein the wingtip to locking pin descent maintenance further comprises instructions to:

[0185] replacing the one or more wingtip lugs;

[0186] identifying a first subset of one or more wingtip lugs having visible damage as scrap; and

[0187] Causing a second subset of one or more wingtip lugs without visible damage to be tested for non-visible damage.

[0188] Embodiment 8 The aircraft of Embodiment 2, wherein in response to a third determination that the wingtip position is at or near a flight position, the maintenance comprises a wingtip-to-stop descent maintenance.

[0189] Embodiment 9. The aircraft of embodiment 8, wherein the wingtip to stop descent maintenance comprises instructions to:

[0190] replacing a wingtip lug of the wingtip;

[0191] replacing the lug stop of said main portion;

[0192] identifying a first subset of the wingtip lugs having visible damage as scrap; and

[0193] A non-visible damage test is performed on a second subset of said wingtip lugs having no visible damage.

[0194] Embodiment 10. An aircraft according to embodiment 1, wherein the flight control computer is further configured to send an extension command to an electronic controller of the folding wingtip system in response to the wingtip position indicating that the wingtip is in the folded position and determining to send an extension command to move the wingtip from the folded position to the flight position.

[0195] Embodiment 11. The aircraft according to embodiment 1, wherein the flight control computer is further configured to:

[0196] sending a first extension command to the first electronic controller to change the wing tip position from the folded position to the flight position;

[0197] receiving a first notification signal from the first electronic controller indicating a failure of the first extend command;

[0198] changing the setting to instruct the aircraft to be grounded based on the first notification signal; and

[0199] Maintenance of the aircraft is scheduled based on one or more second error codes included in the first notification signal.

[0200] Embodiment 12. The aircraft according to embodiment 11, wherein the flight control computer is further configured to:

[0201] sending a second extension command to a second electronic controller in response to the first notification signal;

[0202] receiving a second notification signal from the second electronic controller indicating successful completion of the second extend command;

[0203] changing the setting to indicate that the aircraft will not stop flying based on the second notification signal; and

[0204] A type of maintenance scheduled for the aircraft is changed based on the second notification signal.

[0205] Embodiment 13. The aircraft according to embodiment 11, wherein the flight control computer is further configured to:

[0206] sending a second extension command to a second electronic controller in response to the first notification signal;

[0207] receiving a second notification signal from the second electronic controller indicating that the second extend command failed; and

[0208] In response to the second notification signal including one or more additional error codes not included in the first notification signal, maintenance scheduled for the aircraft is modified to include additional maintenance.

[0209] Example 14. A method comprising:

[0210] determining, at a flight control computer of the aircraft, a wingtip position of the wingtip in response to a determination that the last command completed by the fold wingtip system was a fold command; and

[0211] In response to the wingtip position indicating that the wingtip is not in the folded position:

[0212] setting, by the flight control computer, a first error code for the folding wingtip system;

[0213] changing a setting by the flight control computer to instruct the aircraft to ground; and

[0214] Maintenance of the aircraft is scheduled via the flight control computer based on the first error code.

[0215] Embodiment 15. The method of Embodiment 14, wherein the determining of the wingtip position of the wingtip is performed in response to a transition of the aircraft from an idle or low power state to a power state.

[0216] Embodiment 16. The method of Embodiment 14, wherein the determination of the wingtip position of the wingtip is made in response to a specific determination being made to send an extend command to the folding wingtip system.

[0217] Embodiment 17. A non-transitory computer-readable medium comprising instructions executable by one or more processors to:

[0218] In response to a determination that the last command completed by the fold wingtip system was a fold command, determining a wingtip position of a wingtip of the aircraft; and

[0219] In response to the wingtip position indicating that the wingtip is not in the folded position:

[0220] setting a first error code for the folding wingtip system;

[0221] changing a setting to instruct the aircraft to be grounded based on the first error code; and

[0222] Maintenance of the aircraft is scheduled based on the first error code.

[0223] Embodiment 18. The non-transitory computer readable medium of embodiment 17, wherein the instructions are further executable by the one or more processors to:

[0224] sending a first fold command to the first electronic controller to change the wing tip position from the flight position to the folded position;

[0225] receiving a first notification signal from the first electronic controller indicating that the first fold command failed;

[0226] changing the setting to instruct the aircraft to be grounded based on the first notification signal; and

[0227] Maintenance of the aircraft is scheduled based on the one or more second error codes in the first notification signal.

[0228] Embodiment 19. The non-transitory computer readable medium of embodiment 18, wherein the instructions are further executable by the one or more processors to:

[0229] sending a second folding command to a second electronic controller in response to the first notification signal;

[0230] receiving a second notification signal from the second electronic controller indicating successful completion of the second fold command;

[0231] changing the setting to indicate that the aircraft will not stop flying based on the second notification signal; and

[0232] A type of maintenance scheduled for the aircraft is changed based on the second notification signal.

[0233] Embodiment 20. The non-transitory computer readable medium of embodiment 18, wherein the instructions are further executable by the one or more processors to:

[0234] sending a second folding command to a second electronic controller in response to the first notification signal;

[0235] receiving a second notification signal from the second electronic controller indicating that the second fold command failed; and

[0236] In response to the second notification signal including one or more additional error codes not included in the first notification signal, maintenance scheduled for the aircraft is modified to include additional maintenance.

[0237] The illustrations of the embodiments described herein are intended to provide a general understanding of the structures of different implementations. These illustrations are not intended to serve as a complete description of all elements and features of the devices and systems utilizing the structures or methods described herein. After reviewing the present invention, many other embodiments may be apparent to those skilled in the art. Other implementations may be utilized and derived from the present disclosure, so that structural and logical replacements and changes may be made without departing from the scope of the present disclosure. For example, method operations may be performed in an order different from the order shown in the figure or one or more method operations may be omitted. Therefore, the present disclosure and the accompanying drawings are considered to be illustrative and not restrictive.

[0238] In addition, although specific embodiments have been shown and described herein, it should be understood that any subsequent arrangement designed to achieve the same or similar results may replace the specific implementation shown. This disclosure is intended to cover any and all subsequent adaptations or variations of different implementations. Combinations of the above implementations and other implementations not specifically described herein will be apparent to those skilled in the art upon reviewing this description.

[0239] Submit the abstract of the present disclosure, it should be understood that it is not used to explain or limit the scope or meaning of the embodiment. In addition, in the aforementioned specific implementation, for the purpose of streamlining the present disclosure, different features can be combined together or described in a single implementation. The above-mentioned embodiments illustrate but do not limit the present disclosure. It should also be understood that according to the principles of the present disclosure, many modifications and variations are possible. As reflected in the following embodiments, the subject matter claimed for protection may relate to features less than all features of any disclosed embodiment. Therefore, the scope of the present disclosure is limited by the attached embodiments and their equivalents.

Claims

1. An aircraft, comprising: A wing, wherein the wing comprises a main portion and a wing tip; and A folding wingtip system configured to rotate the wingtip relative to the main portion, wherein the folding wingtip system includes an electronic controller configured to: implementing an extension command received from a flight control computer to rotate the wingtips from a folded position to a flight position; and In response to a determination that rotation of the wingtip ceased prior to the flight position during implementation of the extend command, sending a first notification signal to the flight control computer to ground the aircraft and schedule maintenance of the aircraft, wherein the first notification signal includes one or more first error codes, and wherein, in response to a determination by the electronic controller indicating that a first particular angle of the wingtip relative to the main portion of the wing is within a locking pin interference range, the first notification signal causes the maintenance to include wingtip to locking pin lower maintenance.

2. The aircraft according to claim 1, wherein: The wingtip to locking pin descent maintenance includes instructions to: identifying one or more specific locking pins contacted by one or more specific lugs of the wing tip; replacing the one or more specific locking pins; identifying a first subset of the one or more specific locking pins having visible damage as scrap; and A second subset of the one or more specific locking pins without visible damage is caused to be tested for non-visible damage.

3. The aircraft according to claim 2, wherein: The wingtip to locking pin descent maintenance also includes instructions to: replacing one or more specific lugs of said wing tip; identifying a first subset of the one or more particular lugs having visible damage as scrap; and A second subset of the one or more specific lugs without visible damage is caused to be tested for non-visible damage.

4. The aircraft according to claim 1, wherein: The first notification signal also causes the flight control computer to schedule the aircraft for wingtip actuation system maintenance.

5. The aircraft according to claim 1, wherein: When the electronic controller's determination indicates that the first specific angle is not within the locking pin interference range, the first notification signal indicates that the maintenance includes wingtip actuator maintenance.

6. The aircraft according to claim 1, wherein: The electronic controller is further configured to: receiving a request from the flight control computer for position data associated with the angle of the wingtip relative to the main portion; and The position data is sent to the flight control computer based on data received from the hinge sensor, wherein the flight control computer grounds the aircraft and schedules maintenance of the aircraft when the position of the wing tip indicated by the position data is not in the folded position.

7. The aircraft according to claim 6, wherein: The maintenance includes brake system maintenance of a brake system configured to maintain the wing tip in the folded position.

8. The aircraft according to claim 6, wherein: When the wing tip is in the flight position or close to the flight position, the maintenance includes wing tip to stop position lowering maintenance.

9. The aircraft according to claim 8, wherein: The wingtip-to-stop descent maintenance includes instructions to: replacing a wingtip lug of the wingtip; replacing the lug stop of said main portion; identifying a first subset of the wingtip lugs having visible damage as scrap; and A second subset of said wingtip lugs having no visible damage is caused to be tested for non-visible damage.

10. A method for detecting abnormal wingtip extension, comprising: implementing, via an electronic controller of a folding wingtip system of the aircraft, an extension command to rotate the wingtip of the wing from a folded position to a flight position, the extension command being received by the electronic controller from a flight control computer; as well as In response to a first determination made at the electronic controller during implementation of the extend command that rotation of the wingtip ceased prior to the flight position, sending a first notification signal from the electronic controller to the flight control computer to ground the aircraft and schedule maintenance of the aircraft, wherein the first notification signal includes one or more first error codes, and wherein, in response to a determination made by the electronic controller indicating that a first particular angle of the wingtip relative to a main portion of the wing is within a locking pin interference range, the first notification signal causes the maintenance to include wingtip to locking pin lower maintenance.

11. The method according to claim 10, wherein: In response to a second determination that an implementation time of the extend command from initiation of implementation of the extend command to completion of implementation of the extend command indicated when rotation of the wingtip relative to the main portion stops in the flight position is shorter than a threshold implementation time, the one or more first error codes indicate a wingtip-to-stop descent, and wherein the one or more first error codes are configured to cause maintenance of the aircraft to include wingtip-to-stop descent maintenance.

12. The method according to claim 10, further comprising: providing wingtip position data to the flight control computer in response to a wingtip position request, wherein the flight control computer is configured to change a setting to instruct the aircraft to be grounded and to schedule specific maintenance for the aircraft based on a first determination that the wingtip is not in the folded position and based on a second determination that the last implemented command of the folding wingtip system was a fold command.

13. The method according to claim 12, wherein: When the wingtip position data indicates that the wingtip is at the flight position, the specific maintenance includes a wingtip-to-stop descent maintenance.

14. The method according to claim 10, further comprising: receiving at the electronic controller a second command from the flight control computer to transition the wing tip from the first position to a second position; sending a control signal to a powertrain actuator, a hydraulic control module, or both to implement the second command; as well as In response to the electronic controller determining that a locking system of the locking pin actuator is not operating properly based on the powertrain actuator data from the powertrain actuator sensor and the powertrain position data from the powertrain position sensor, a specific notification signal is sent to the flight control computer, wherein the specific notification signal includes one or more specific error codes associated with a locking system failure, wherein the specific notification signal grounds the aircraft and prompts scheduling of specific maintenance for the aircraft, and wherein the specific maintenance includes locking pin system maintenance.

15. A non-transitory computer readable medium comprising instructions executable by one or more processors of an electronic controller of an aircraft to: implementing an extension command received from a flight control computer to rotate the wingtips of the wings about the hinge axis from a folded position to a flight position; and sending a first notification signal to the flight control computer to ground the aircraft and schedule maintenance of the aircraft in response to a first determination that rotation of the wing tip ceased prior to the flight position during implementation of the extend command, wherein the first notification signal includes one or more first error codes, and wherein In response to a determination by the electronic controller indicating that a first specific angle of the wingtip relative to a main portion of the wing is within a locking pin interference range, the notification signal causes the maintenance to include a wingtip to locking pin lower maintenance.

16. The non-transitory computer readable medium of claim 15, wherein: The instructions are further executable by the one or more processors to: implementing a fold command to transition the wingtip from the flight position to the folded position; determining that the position of the wing tip relative to the main portion is not in the folded position at the end of the implementation of the fold command; as well as and sending a second notification signal to the flight control computer, wherein the second notification signal includes one or more second error codes associated with the location, and wherein the second notification signal causes the aircraft to be grounded and causes specific maintenance to be scheduled for the aircraft based on the one or more second error codes.

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