Aircraft landing gear monitoring and warning system and method

Abstract

To provide a system for monitoring and warning of an aircraft landing gear.SOLUTION: A system for monitoring and warning of a landing gear includes a locking pin, a magnetic sensor, and a communication module. An aperture is disposed in an extended aircraft landing gear assembly and the locking pin is inserted into the aperture to establish a locked state of the extended landing gear assembly and to inhibit movement of a linkage. The magnetic sensor is disposed proximate the aperture and is configured to sense magnetic response indicative of the locking pin being disposed within the aperture. The magnetic sensor is configured to generate sensor output indicative of the locking pin being disposed within the aperture. The communication module has a transmitter coupled to the magnetic sensor in order to receive the sensor output and is configured to responsively transmit a signal indicative of the locking pin being disposed within the aperture.SELECTED DRAWING: Figure 2

Description

[Technical field]

[0001] The present disclosure relates generally to aircraft, and more particularly to aircraft landing gear monitoring and warning systems and methods. [Background technology]

[0002] Some aircraft include landing gear. During landing, the landing gear of the aircraft contacts the surface of the airport runway to facilitate a smooth landing. Additionally, the landing gear is used during taxiing to facilitate the movement of the aircraft over the airport runway. Summary of the Invention

[0003] The present disclosure describes an aircraft landing gear monitoring and warning system and method. The landing gear monitoring and warning system alerts flight crew and ground crew when a locking pin is positioned within an aperture in the linkage of an extended landing gear assembly. The locking pin inhibits movement of the linkage, thereby preventing the landing gear assembly from moving from an extended position to a retracted position. It is desirable for the locking pin to be removed from the linkage aperture before the aircraft takes off to allow the landing gear assembly to retract. Failure to do so may increase drag on the aircraft, thereby increasing fuel consumed by the aircraft. Eventually, the aircraft will have to divert its flight plan to return to the airport to allow ground crew to remove the locking pin from the linkage aperture. This diversion may result in financial expenses to the airline in the form of, among other things, airport parking fees, additional fuel costs, and unexpected takeoff slot waiting times. It is therefore desirable to develop a system and method for alerting ground crew and aircraft flight crew when a locking pin is positioned inside an aperture in a landing gear assembly linkage.

[0004] The disclosed aircraft landing gear monitoring and warning system detects when a locking pin is located inside an aperture extending through a linkage of a landing gear assembly in an extended position. Upon detection of a locking pin inside the aperture, the disclosed aircraft landing gear monitoring and warning system alerts the flight crew and ground crew that a locking pin is located within the aperture extending through the linkage of the landing gear assembly and allows the ground crew to remove the locking pin from the aperture prior to takeoff of the aircraft.

[0005] In some embodiments of the present disclosure, the landing gear monitoring and warning system includes a locking pin configured to be inserted into an aperture extending through at least one linkage of an extended landing gear assembly. When inserted into the aperture, the locking pin inhibits movement of the linkage to establish a locked state of the extended landing gear assembly. The aircraft landing gear monitoring and warning system further includes a magnetic sensor disposed proximate the aperture and configured to detect a magnetic response indicative of the locking pin being disposed within the aperture to establish a locked state of the extended landing gear assembly. The magnetic sensor is configured to generate a sensor output indicative of the locking pin being disposed within the aperture. The aircraft landing gear monitoring and warning system further includes a communication module having a transmitter. The transmitter is coupled to the magnetic sensor to receive the sensor output indicative of the locking pin being disposed within the aperture of the linkage. The communication module is configured to responsively transmit a signal indicative of the locking pin being disposed within the aperture to establish a locked state of the extended landing gear assembly.

[0006] In some aspects of the disclosure, a landing gear monitoring and warning system may include a display device within a primary field of view in a cockpit of an aircraft, the display device configured to display information about a locking pin being positioned within an aperture to establish a locked condition of an extended landing gear assembly in response to a transmitted signal being received by the display device over a data network of the aircraft.

[0007] In aspects of the present disclosure, the magnetic sensor may include a magnetic sensor-activated switch configured to activate the magnetic sensor upon magnetically detecting that the locking pin is disposed within the aperture, the magnetic sensor-activated switch also providing a sensor output to the communications module.

[0008] In aspects of the disclosure, the linkage may include a pair of pivotally coupled linkage members, an aperture in the linkage extending through the pair of pivotally coupled linkage members, and a locking pin configured to be inserted into the aperture extending through the pair of pivotally coupled linkage members to restrain the pair of pivotally coupled linkage members from moving relative to one another such that the pair of pivotally coupled linkage members are held in a fixed relationship relative to one another.

[0009] In some aspects of the disclosure, a communications module may include a microcontroller configured to receive a sensor output from the magnetic sensor and may include an integrated wifi component configured to wirelessly transmit a signal indicating that the locking pin is positioned within the linkage aperture.

[0010] In aspects of the present disclosure, the microcontroller may be a universal host controller interface that transmits a signal via a universal asynchronous receiver-transmitter indicating that the locking pin is positioned within the aperture.

[0011] In some aspects of the disclosure, the communications module may be configured to transmit a signal to a ground crew handheld device indicating that the locking pin is located within the aperture in response to receiving a sensor output indicating that the locking pin is located within the aperture.

[0012] In some aspects of the disclosure, the communications module may be configured to transmit a signal indicating that the locking pin is located within the aperture in response to (a) receiving a sensor output indicating that the locking pin is located within the aperture, and (b) receiving flight phase information indicative of a taxiing movement by the aircraft.

[0013] In an aspect of the present disclosure, the landing gear monitoring and warning system may further include a display device within a primary field of view in the aircraft cockpit, configured to display information on a synoptic page regarding the locking pin being positioned within the linkage aperture to establish a locked condition of the extended landing gear assembly in response to the transmitted signal being received by the display device over the aircraft data network.

[0014] The present disclosure also describes a method of operating a landing gear monitoring and warning system. In some aspects of the present disclosure, the method includes monitoring a magnetic field in the vicinity of an aperture in a landing gear assembly. The landing gear assembly includes at least one linkage. The aperture extends through the linkage. The landing gear assembly includes a locking pin configured to be inserted into the aperture when the landing gear assembly is in the extended position to inhibit movement of the linkage and establish a locked state of the landing gear assembly in the extended position. The method further includes detecting a magnetic response indicative of the locking pin being disposed in the aperture to establish a locked state of the landing gear assembly in the extended position. The method further includes transmitting a signal indicative of the locking pin being inserted into the aperture and the locked state of the landing gear assembly being established in response to detecting a magnetic response indicative of the locking pin being disposed in the aperture to establish a locked state of the landing gear assembly in the extended position.

[0015] In some aspects of the disclosure, the method may further include displaying, in response to the transmitted signal being received by the display device over the aircraft data network, information about the locking pin being located in the aperture on a display device of the aircraft, the display device having a primary view of a cockpit of the aircraft.

[0016] In the disclosed method, sensing the magnetic response may include activating a magnetic sensor activated switch upon magnetically detecting that the locking pin is positioned within the aperture, and in response to activating the magnetic sensor activated switch, transmitting a sensor output from the magnetic sensor activated switch to a communications module of a landing gear monitoring and warning system.

[0017] In the methods of the present disclosure, transmitting a signal indicating that the locking pin is inserted into the aperture may include wirelessly transmitting a signal indicating that the locking pin is inserted into the aperture.

[0018] In the method of the present disclosure, transmitting a signal indicating that the locking pin is inserted into the aperture may include transmitting, using a universal asynchronous transceiver, a signal indicating that the locking pin is inserted into the aperture.

[0019] In the method of the present disclosure, transmitting a signal indicating that the locking pin is inserted within the aperture may include transmitting a signal to a ground crew gripping device indicating that the locking pin is positioned within the aperture in response to detecting a magnetic response indicating that the locking pin is positioned within the aperture to establish a locked state of the landing gear assembly in the extended position.

[0020] In the method of the present disclosure, transmitting a signal indicating that the locking pin is inserted within the aperture may include detecting a magnetic response indicating that the locking pin is positioned within the aperture to establish a locked state of the landing gear in an extended position, and transmitting a signal indicating that the locking pin is positioned within the aperture in response to receiving flight phase information indicating a taxiing movement by the aircraft.

[0021] The method of the present disclosure may further include displaying information on the overview page about the locking pin being positioned in the aperture in response to the transmitted signal being received by the display device via the aircraft data network.

[0022] The present disclosure also describes an aircraft including a fuselage and a landing gear assembly movable relative to the fuselage. The landing gear assembly has an extended position and includes at least one linkage and an aperture extending through the linkage. The landing gear assembly also includes a locking pin configured to be inserted into the aperture extending through the linkage. When inserted into the aperture, the locking pin inhibits movement of the linkage to establish a locked state of the landing gear assembly in the extended position. The aircraft further includes a landing gear monitoring and warning system coupled to the landing gear assembly. The landing gear monitoring and warning system includes a magnetic sensor disposed proximate the aperture and configured to detect a magnetic response indicative of the locking pin being disposed within the aperture to establish a locked state of the landing gear assembly in the extended position. The magnetic sensor is configured to generate a sensor output indicative of the locking pin being disposed within the aperture. The landing gear monitoring and warning system further includes a communication module having a transmitter. The transmitter is coupled to the magnetic sensor to receive a sensor output indicative of the locking pin being disposed within the aperture. The communications module is configured to responsively transmit a signal indicating that the locking pin is disposed within the aperture and a locked condition of the landing gear assembly in the extended position is established.

[0023] In some aspects of the disclosure, the aircraft may further include a cockpit and a display device disposed within the cockpit within a primary field of view of the cockpit and configured to display information about the locking pin being disposed within the aperture to establish a locked condition of the landing gear assembly in the extended position in response to the transmitted signal being received by the display device via the aircraft data network.

[0024] In some aspects of the disclosure, the aircraft magnetic sensor may include a magnetic sensor activated switch configured to activate the magnetic sensor activated switch upon magnetically detecting that the locking pin is disposed within the aperture, the magnetic sensor activated switch also configured to provide a sensor output to the communication module.

[0025] The above and other features and advantages of the present teachings will become readily apparent from the following detailed description of modes for carrying out the present teachings when taken in conjunction with the accompanying drawings.

[0026] The accompanying drawings, which are incorporated in and constitute a part of this specification, illustrate implementations of the disclosure and, together with the description, serve to explain the principles of the disclosure. [Brief description of the drawings]

[0027] [Figure 1] FIG. 1 is a schematic perspective view of an aircraft including a landing gear assembly and a landing gear monitoring and warning system. [Diagram 2] FIG. 2 is a schematic perspective view of a landing gear assembly of the aircraft shown in FIG. [Diagram 3] FIG. 3 is a schematic side view of a portion of the landing gear assembly shown in FIG. [Figure 4] FIG. 4 is a schematic exploded perspective view of the linkage of the landing gear assembly shown in FIG. 3, illustrating a locking pin spaced from an aperture extending through the linkage. [Diagram 5] FIG. 2 is a schematic perspective view of the cockpit of the aircraft shown in FIG. 1. [Figure 6] 2 is a schematic front view of a display device of the aircraft shown in FIG. 1 depicting an image 144 of an aircraft having a landing gear assembly. [Figure 7] FIG. 2 is a schematic front view of the instrument panel of the aircraft shown in FIG. 1, including landing gear lights. [Figure 8]FIG. 2 is a schematic front view of a display device of the aircraft shown in FIG. 1 including an Engine Instrument and Crew Alerting System (EICAS) page. [Figure 9] 2 is a schematic block diagram of the aircraft landing gear monitoring and warning system shown in Figure 1. [Figure 10] 10 is a flowchart of a method of operating the landing gear monitoring and warning system shown in FIG. DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS

[0028] The above summary, as well as the following detailed description of certain embodiments, will be better understood when read in conjunction with the accompanying drawings. As used herein, it is to be understood that the use of "a" or "an" in the singular form of an element or step does not necessarily exclude a plurality of such elements or steps. Moreover, references to "one embodiment" should not be interpreted as excluding the existence of additional embodiments that incorporate the features described herein. Additionally, unless expressly stated to the contrary, an embodiment "comprising," "including," or "having" one or more elements having a particular property may include additional elements that do not have that property.

[0029] With reference to FIG. 1 , the aircraft 100 includes a fuselage 102 and two or more wings 104 coupled to the fuselage 102. In addition to the wings 104, the aircraft 100 includes one or more landing gear assemblies 106 coupled indirectly or directly to the fuselage 102. As one non-limiting example, the aircraft 100 may include two landing gear assemblies 106, each coupled to a respective wing 104, and one landing gear assembly 106 coupled to a nose 108 of the fuselage 102. Regardless of the quantity, each landing gear assembly 106 is movable relative to the fuselage 102 between a retracted position and an extended position (as shown in FIG. 1 ). During landing and takeoff, each landing gear assembly 106 is in an extended position to facilitate movement of the aircraft 100 on the ground. When the aircraft 100 is airborne, the landing gear assembly 106 is in a retracted position to minimize drag.

[0030] 2-4, each of the landing gear assemblies 106 includes a shock strut 110, one or more tires 112, and a shock absorber 113 coupled between the shock strut 110 and the tire 112. The shock absorber 113 is movable relative to the shock strut 110 to dampen movement on the landing gear assembly 106. In addition to the shock absorber 113, the landing gear assembly 106 may include one or more trunnions 114 coupled to the shock strut 110 that allow the landing gear assembly 106 to rotate relative to the fuselage 102 (FIG. 1). The landing gear assembly 106 further includes a torque link 116 pivotally coupled to each other. The torque link 116 is coupled to the shock strut 110 and the shock absorber 113 to allow linear movement of the shock absorber 113 relative to the shock strut 110 while preventing relative rotation between the shock absorber 113 and the shock strut 110.

[0031] The landing gear assembly 106 further includes at least one linkage 118 pivotally coupled to the shock strut 110. The linkage 118 facilitates movement of the landing gear assembly 106 relative to the fuselage 102 between a retracted position and an extended position. To move the linkage 118, the landing gear assembly 106 includes an actuator 120. In the depicted embodiment, the actuator 120 is a hydraulic actuator. However, the actuator 120 may be an alternative type of actuation system capable of moving the linkage 118. The actuator 120 may include an actuation cylinder 122 and hydraulic tubing 125 in fluid communication with the actuation cylinder 122. The actuation cylinder 122 is coupled to the linkage 118. Upon actuation, the actuator 120 moves the linkage 118 to move the landing gear assembly 106 between the retracted position and the extended position.

[0032] The linkage 118 includes a pair of pivotally coupled linkage members 124. In the depicted embodiment, the linkage 118 includes a first linkage member 124a and a second linkage member 124b that are pivotally coupled to one another. The first linkage member 124a may be referred to as a lower drag brace, and the second linkage member 124b may be referred to as an upper drag brace. The landing gear assembly 106 has an aperture 126 that extends through at least one linkage 118 when the landing gear assembly 106 is in the extended position. In particular, the aperture 126 extends through the pair of pivotally coupled linkage members 124. In the depicted embodiment, the aperture 126 extends through the first linkage member 124a and the second linkage member 124b. The landing gear assembly 106 includes a locking pin 128 configured, sized and shaped to be inserted into an aperture 126 extending through the linkage 118. When inserted into the aperture 126, the locking pin 128 inhibits movement of the pair of pivotally coupled linkage members 124 to establish a locked state of the landing gear assembly 106 in the extended position. Specifically, when the locking pin 128 is inserted into the aperture 126, the pair of pivotally coupled linkage members 124 are held in a fixed relationship relative to one another, thereby establishing a locked state of the landing gear assembly 106 in the extended position. In other words, when the locking pin 128 is inserted into the aperture 126, the first linkage member 124a and the second linkage member 124b are locked relative to one another, preventing the landing gear assembly 106 from moving from the extended position to the retracted position. As a result, the landing gear assembly 106 is locked in the extended position. The landing gear assembly 106 may further include a flag 130 attached to the locking pin 128 to alert ground crew that the locking pin 128 should be removed from the aperture 126 before the aircraft 100 begins taxiing.

[0033] The landing gear assembly 106 may further include a locking hook 132 and a locking actuation rod 134 coupled to the locking hook 132 to lock the locking pin 128 within the aperture 126. When actuated by the actuator 120, for example, the locking actuation rod 134 drives the locking hook 132 toward the locking pin 128 to lock the locking pin 128 within the aperture 126.

[0034] 5, the aircraft 100 further includes a cockpit 136 inside the nose 108 of the fuselage 102. The cockpit 136 includes one or more display devices 138 to visually provide information to the flight crew of the aircraft 100. The display devices 138 may be part of an instrument panel 140 of the aircraft 100, which may include analog gauges. As one non-limiting example, the display devices 138 may be liquid crystal display (LCD) screens. Regardless of the type of display device 138 employed, each of the display devices 138 is within a primary field of view of the cockpit 136 of the aircraft 100, thereby enabling the flight crew to view information output by the display devices 138. At least one of the display devices 138 is configured to display information about whether the locking pin 128 is positioned within the aperture 126 to establish a locked state of the extended landing gear assembly 106 in response to receiving a signal transmitted by the landing gear monitoring and warning system 300 ( FIG. 9 ), as described in more detail below. The information about whether the locking pin 128 is positioned within the aperture 126 may be output on a summary page 142 of one of the display devices 138 upon receiving a signal transmitted by the landing gear monitoring and warning system 300. As non-limiting examples, the display device 138 may be configured as a multifunction display (MFD), an electronic flight bag (EFB), or an illuminated symbol or word on the instrument panel 140.

[0035] With reference to FIG. 6 , a display device 138, such as an MFD or EFB, may display an image 144 of an aircraft 100 having landing gear assemblies 106. In response to receiving a signal from the landing gear monitoring and warning system 300, the display device 138 may, for example, change a color (e.g., from black to red) of the image 144 of the landing gear assembly 106 having a locking pin 128 disposed within an aperture 126 of the linkage 118. Additionally, the display device 138 may display a message 146 indicating that the locking pin 128 is disposed within an aperture 126 in one or more of the landing gear assemblies 106. For example, in one depicted embodiment, the message 146 shown in the display device 138 states “Nose wheel pin engaged” to indicate that the locking pin 128 of the landing gear assembly 106 positioned in the nose 108 is disposed within the aperture 126 of the landing gear assembly 106.

[0036] 7, the display devices 138 of the instrument panel 140 are configured as illuminated words. Each display panel 138 may correspond to one of the landing gear assemblies 106. For example, in one embodiment depicted, three display devices 138 include respective messages, i.e., "nose gear," "left gear," and "right gear," to indicate which of the landing gear assemblies 106 have the locking pin 128 inserted in the aperture 126. In this embodiment, the display devices 138 may be configured as associated landing gear lights 141 and positioned above the landing gear down-lock light 143. The display devices 138 may light up one or more messages corresponding to the landing gear assemblies 106 that have the locking pin 128 still inserted in the aperture 126 in response to receiving a signal from the landing gear monitoring and warning system 300 (FIG. 9), as described in more detail below.

[0037] 8 , the display device 138 may include an Engine Instrument and Crew Alerting System (EICAS) page 148. Upon receiving a signal from the landing gear monitoring and alerting system 300, the display device 138 may display information on the EICAS page 148 indicating that the locking pins 128 of one or more landing gear assemblies 106 are within the apertures 126 of the linkages 118. For example, the display device 138 may display information in the form of indicia 150, such as “pin in nose,” to indicate that the locking pins 128 in one of the landing gear assemblies 106 are still within the apertures 126. By displaying the “pin in nose” indicia 150, the display device 138 indicates that the locking pins 128 of the landing gear assembly 106 positioned in the nose 108 are inserted within the apertures 126 of the linkages 118.

[0038] 9, the landing gear monitoring and warning system 300 monitors whether the locking pin 128 is disposed within the aperture 126 of at least one linkage 118. As described above, the locking pin 128 may extend through the linkage 118 (e.g., the first linkage member 124a and the second linkage member 124b) via the aperture 126 to establish a locked state of the extended landing gear assembly 106. The locking pin 128, which may be considered to be part of the landing gear monitoring and warning system 300, inhibits movement of the linkage 118 when inserted into the aperture 126 to lock the landing gear assembly 106 in the extended position. Before the aircraft 100 takes off, the locking pin 128 should be removed to allow the landing gear assembly 106 to move from the extended position to the retracted position. If the locking pin 128 is not removed, the landing gear monitoring and warning system 300 alerts the aircraft operator (e.g., flight crew or ground crew) that the locking pin 128 is positioned inside the aperture 126 in the linkage 118.

[0039] The landing gear monitoring and warning system 300 includes a magnetic sensor 302 disposed near the aperture 126. The magnetic sensor 302 is thus configured to detect a magnetic response indicative of the locking pin 128 being disposed within the aperture 126 of the linkage 118 to establish a locked state of the extended landing gear assembly 106. In other words, the magnetic sensor 302 detects disturbances and changes, such as strength, direction, and flux, of the magnetic field near the aperture 126 of the linkage 118 to determine whether the locking pin 128 is inside the aperture 126 of the linkage 118. As a non-limiting example, the magnetic sensor 302 may be a Hall-effect magnetic sensor. To calibrate the magnetic sensor 302, tests may be performed to detect the strength, direction, or flux of the magnetic field near the aperture 126 when the locking pin 128 is inserted within the aperture 126 and when the locking pin 128 is not within the aperture 126. Based on this test, the magnetic sensor 302 determines whether the locking pin 128 is disposed within the aperture 126 of the linkage 118 in response to detecting a strength, direction, or flux of a magnetic field identified during the test when the locking pin 128 is disposed within the aperture 126. In certain embodiments, the magnetic sensor 302 includes a magnetic sensor activation switch 304. The magnetic sensor 302 is configured to activate the magnetic sensor activation switch 304 when the magnetic sensor 302 magnetically detects that the locking pin 128 is disposed within the aperture 126 of the linkage 118. In response to activation of the magnetic sensor activation switch 304, the magnetic sensor 302 generates and provides a sensor output. The sensor output is indicative of the locking pin 128 being disposed within the aperture 126 of the linkage 118. The magnetic sensor 302 may further include a sensor communication module 306 configured to transmit the sensor output. The sensor communication module 306 of the magnetic sensor 302 may transmit the sensor output via wire or wirelessly. In some embodiments, the sensor communications module 306 includes a transmitter configured to transmit a wireless signal (eg, a wireless sensor output).As one non-limiting example, the sensor communication module 306 may be configured as a system on a chip microcontroller that includes a built-in antenna capable of transmitting wireless signals, such as WI-FI® or BLUETOOTH® signals, to minimize the size and cost of the landing gear monitoring and warning system 300.

[0040] The landing gear monitoring and warning system 300 further includes a communication module 308 in wired or wireless communication with the magnetic sensor 302. The communication module 308 includes a transmitter 310 coupled to the magnetic sensor 302. In effect, the communication module 308 is configured to receive a sensor output generated from the magnetic sensor 302. As described above, the sensor output indicates that the locking pin 128 is disposed within the aperture 126 of the linkage 118. The communication module 308 is configured to transmit a signal accordingly, indicating that the locking pin 128 is disposed within the aperture 126 of the linkage 118, thereby establishing a locked state of the extended landing gear assembly 106. In other words, by the transmitter 310, the communication module 308 is configured to transmit a signal, in response to receiving the sensor output from the magnetic sensor 302, indicating that the locking pin 128 is disposed within the aperture 126 of the linkage 118. In that case, the sensor output indicates that the locking pin 128 is located within the aperture 126 of the linkage 118. As one non-limiting example, the communication module 308 includes a microcontroller 312 configured to receive the sensor output from the magnetic sensor 302. The communication module 308 may include an integrated wifi component 314 configured to wirelessly transmit a signal indicating that the locking pin 128 is located within the aperture 126 of the linkage 118 to minimize the size of the communication module 308. For example, the integrated wifi component 314 may include a built-in antenna integrated on the microcontroller 312, which may be an integrated chip. The microcontroller 312 may be a universal host controller interface that transmits a signal indicating that the locking pin 128 is located within the aperture 126 of the linkage 118 via a universal asynchronous transmitter / receiver. The microcontroller 312 may be a universal host controller interface to minimize the power required to operate the microcontroller 312.Additionally, the transmitter 310 may be a universal asynchronous transceiver to allow the magnetic sensor 302 and the communication module 308 to exchange data at their own pace.

[0041] Communications module 308 communicates with a flight management system (FMS) 316 of aircraft 100. As a result, communications module 308 is configured to receive information from FMS 316 about the flight phase of aircraft 100. For example, FMS 316 may transmit flight phase information to communications module 308 that is indicative of a taxiing movement of aircraft 100. In some embodiments, communications module 308 is configured to transmit a signal indicating locking pin 128 is disposed within aperture 126 of linkage 118 in response to: (a) receiving a sensor output that is indicative of locking pin 128 being disposed within aperture 126; and (b) receiving (from FMS 316) flight phase information that is indicative of a taxiing movement by aircraft 100.

[0042] The communication module 308 communicates with at least one display device 138 via a data network 318. The data network 318 may be a wired or wireless data network. As described above, the display device 138 may be within a primary field of view within the cockpit 136 of the aircraft 100 and is configured to receive a signal from the communication module 308 indicating that the locking pin 128 is positioned within the aperture 126 of the linkage 118 to establish a locked state of the extended landing gear assembly 106. In response to receiving the signal from the communication module 308, the display device 138 is configured to display information about the locking pin 128 being positioned within the aperture 126 to establish a locked state of the extended landing gear assembly 106. Information about whether the locking pin 128 is positioned within the aperture 126 may be output on an overview page 142 of one of the display devices 138. Alternatively, display device 138 may display information on EICAS page 148 indicating that one or more locking pins 128 of landing gear assemblies 106 are positioned within apertures 126 of linkage 118. Regardless of the configuration of display device 138, display device 138 may be considered to be part of landing gear monitoring and warning system 300.

[0043] Upon receiving a sensor output from the magnetic sensor 302 indicating that the locking pin 128 is within the aperture 126, the communications module 308 is configured to transmit a signal to the ground crew gripping device 320 indicating that the locking pin 128 is disposed within the aperture 126 of the linkage 118. For example, the ground crew gripping device 320 may be a cell phone or any other suitable device capable of displaying information to the ground crew that the locking pin 128 is disposed within the aperture 126 of the linkage 118. Upon receiving this information at the ground crew gripping device 320, the ground crew may remove the locking pin 128 from the aperture 126 of the linkage 118. The communications module 308 may transmit a signal via an on-board networking system (ONS) 322 of the aircraft 100 indicating that the locking pin 128 is disposed within the aperture 126 of the linkage 118. The ONS 322 then transmits the signal to an Airline Operations Control (AOC) server 324 via the airport's wireless data network (e.g., the airport's WI-FI network) or the Aircraft Communications Addressing and Reporting System (ACARS) 326. The AOC server 324 then transmits the signal to the ground crew's handheld device 320.

[0044] 10 is a flow chart of a method 400 of operating the landing gear monitoring and warning system 300. The method 400 begins at block 402 (i.e., a start block). The method 400 then proceeds to block 404. In block 404, the landing gear monitoring and warning system 300 monitors a magnetic field proximate the apertures 126 of one or more landing gear assemblies 106. To do so, the microcontroller 312 reads a sensor output from the magnetic sensor 302. The method 400 then proceeds to block 406.

[0045] In block 406, the microcontroller 312 uses the sensor output of the magnetic sensor 302 to determine whether the locking pin 128 is inserted within the aperture 126 of the linkage 118 by detecting a magnetic response indicating that the locking pin 128 is disposed within the aperture 126 of the linkage 118 to establish a locked state of the landing gear assembly 106 in the extended position. Detecting the magnetic response may entail activating the magnetic sensor activation switch 304 upon magnetically detecting that the locking pin 128 is disposed within the aperture 126. Further, detecting the magnetic response may entail transmitting a sensor output from the magnetic sensor activation switch 304 to the communication module 308 of the landing gear monitoring and warning system 300 in response to activating the magnetic sensor activation switch 304. In response to receiving a sensor output indicating that the locking pin 128 is disposed within the aperture 126 of the linkage 118, the microcontroller 312 determines that the locking pin 128 is disposed inside the aperture 126 of the linkage 118. If the locking pin 128 is not inserted within the aperture 126, the method 400 proceeds to block 412 where the communications module 308 transmits a signal regarding the status of the locking pin 128. In this case, the signal indicates that the locking pin 128 is not disposed within the aperture of the linkage 118, and thus no alarm is activated. On the other hand, if the locking pin 128 is inserted within the aperture 126, as determined in block 406, the method 400 continues to block 408.

[0046] In block 408, the communications module 308 receives a signal from the FMS 316 indicative of the flight phase of the aircraft 100. After block 408, the method 400 proceeds to block 410.

[0047] At block 410, microcontroller 312 determines whether the flight phase has transitioned to taxiing based on a signal received from FMS 316. If the flight phase of aircraft 100 has not transitioned to taxiing, method 400 proceeds to block 412. As described above, at block 412, microcontroller 312 transmits a signal indicating (for example) that locking pin 128 is not positioned within aperture 126 of linkage 118. After block 412, method 400 continues to block 416. At block 416, a signal is transmitted to ONS 322 indicating (for example) that locking pin 128 is not positioned within aperture 126 of linkage 118. If the flight phase has transitioned to taxiing, as determined at block 410, method 400 proceeds to block 414.

[0048] At block 414, the communications module 308 transmits a signal indicating that the locking pin 128 is inserted into the aperture 126 of the linkage 118 (i.e., an alert signal) in response to: (a) detecting a magnetic response indicating that the locking pin 128 is positioned within the aperture 126 of the linkage 118 to establish a locked condition of the landing gear assembly in the extended position; and (b) receiving flight phase information indicative of a taxiing movement by the aircraft 100. After block 414, the method 400 continues to block 416.

[0049] At block 416, the communications module 308 transmits a signal to the ONS 322 of the aircraft 100 indicating that the locking pin 128 is inserted within the aperture 126. Alternatively, at block 416, a signal is transmitted to the ONS 322 indicating that the locking pin 128 is not inserted within the aperture 126. When the locking pin 128 is removed from the aperture 126, a signal is transmitted to the ONS 322 indicating that the locking pin 128 is not inserted within the aperture 126 and the locking pin 128 is securely stored within the safety locking pin case. These signals may be transmitted wirelessly. After block 416, the method 400 proceeds to block 418.

[0050] At block 418, a signal indicating that the locking pin 128 is inserted in the aperture 126 (i.e., a warning signal) or a signal indicating that the locking pin 128 is not inserted in the aperture 126 is transmitted via the AOS server 324 to the display device 138 and the ground crew gripping device 320. The signal indicating that the locking pin 128 is inserted in the aperture 126 (i.e., a warning signal) is transmitted in response to detecting a magnetic response indicating that the locking pin 128 is positioned in the aperture 126 to establish a locked state of the landing gear assembly 106 in the extended position. The method 400 then proceeds to blocks 420, 422, and 424.

[0051] At blocks 420, 422, and 424, respectively, the method 400 entails displaying information about the locking pin 128 being positioned within the aperture 126 on the display device 138 of the aircraft 100 in response to the transmitted signal being received by the display device via the data network 318 of the aircraft 100. As discussed above, the display device 138 has a primary view within the cockpit 136 of the aircraft 100. In some aircraft 100, displaying information about the locking pin 128 being positioned within the aperture 126 at block 420 entails illuminating associated landing gear lights 141, as shown in FIG. 7. These lights may be positioned above the landing gear down-locked light 143. In aircraft 100 with an EFB, a flash warning may be displayed on the display device 138 at block 422. For example, as shown in FIGURE 6, the image 144 of the associated landing gear assembly 106 may change color (e.g., from black to red) to indicate which of the landing gear assemblies 106 have the locking pin 128 disposed in the aperture 126. Additionally, as also shown in FIGURE 6, the display device 138 may display a message 146 indicating that the locking pin 128 is disposed in the aperture 126 in one or more of the landing gear assemblies 106. In an aircraft 100 having an EICAS and MFD page, at block 424, a flash warning may be displayed on the overview page 142 or other suitable page on the display device 138 to indicate which of the landing gear assemblies 106 are in a locked state. For example, as shown in FIGURE 8, the EICAS page 148 of the display device 138 displays a red message in the form of indicia 150. Indicia 150 indicates which of the landing gear assemblies 106 is in a locked state (because locking pin 128 is disposed within aperture 126 of linkage 118).

[0052] Furthermore, the present disclosure includes embodiments according to the following clauses: Article 1. a locking pin (128) configured to be inserted into an aperture (126) extending through at least one linkage (118) of an extended landing gear assembly (106), the locking pin (128) when inserted inhibiting movement of the at least one linkage (118) to establish a locked state of the extended landing gear assembly (106); a magnetic sensor (302) disposed proximate the aperture (126) and configured to detect a magnetic response indicative of the locking pin (128) being disposed within the aperture (126) to establish the locked state of the extended landing gear assembly (106), the magnetic sensor (302) configured to generate a sensor output indicative of the locking pin (128) being disposed within the aperture (126); a communications module (308) having a transmitter (310) coupled to the magnetic sensor (302) to receive the sensor output indicating that the locking pin (128) is disposed within the aperture (126), the communications module (308) configured to responsively transmit a signal indicating that the locking pin (128) is disposed within the aperture (126) and that the locked state of the extended landing gear assembly (106) has been established. Article 2. The landing gear monitoring and warning system (300) described in clause 1, further comprising a display device (138) within a primary field of view within a cockpit (136) of the aircraft (100), configured to display information about the locking pin (128) being positioned within the aperture (126) to establish the locked state of the extended landing gear assembly (106) in response to the transmitted signal being received by the display device (138) via a data network (318) of the aircraft (100). Article 3. The landing gear monitoring and warning system (300) described in clause 1, wherein the magnetic sensor (302) is provided with a magnetic sensor activation switch (304), and the magnetic sensor (302) is configured to activate the magnetic sensor activation switch (304) and provide the sensor output to the communication module (308) when it magnetically detects that the locking pin (128) is positioned within the aperture (126). Article 4. The landing gear monitoring and warning system (300) described in clause 1, wherein the at least one linkage (118) includes a pair of pivotally coupled linkage members (124), the aperture (126) extending through the pair of pivotally coupled linkage members (124), and the locking pin (128) is configured to be inserted into the aperture (126) extending through the pair of pivotally coupled linkage members (124) to inhibit movement of the pair of pivotally coupled linkage members (124) relative to one another such that the pair of pivotally coupled linkage members (124) are held in a fixed relationship relative to one another. Article 5. The landing gear monitoring and warning system (300) described in clause 1, wherein the communications module (308) comprises a microcontroller (312) configured to receive the sensor output from the magnetic sensor (302), and the communications module (308) includes an integrated WiFi component (314) configured to wirelessly transmit the signal indicating that the locking pin (128) is positioned within the aperture (126). Article 6. The landing gear monitoring and warning system (300) described in clause 5, wherein the microcontroller (312) is a universal host controller interface that transmits the signal indicating that the locking pin (128) is positioned within the aperture (126) via a universal asynchronous transmitter / receiver. Article 7. The landing gear monitoring and warning system (300) described in clause 1, wherein the communications module (308) is configured to transmit the signal indicating that the locking pin (128) is positioned within the aperture (126) to a ground crew gripping device (320) in response to receiving the sensor output indicating that the locking pin (128) is positioned within the aperture (126). Article 8. The landing gear monitoring and warning system (300) described in clause 1, wherein the communications module (308) is configured to receive the sensor output indicating that the locking pin (128) is positioned within the aperture (126) and to transmit the signal indicating that the locking pin (128) is positioned within the aperture (126) in response to receiving flight phase information indicating a taxiing movement by the aircraft (100). Article 9. The landing gear monitoring and warning system (300) described in clause 1, further comprising a display device (138) within a primary field of view within a cockpit (136) of the aircraft (100), configured to display on an overview page (142) information that the locking pin (128) is positioned within the aperture (126) to establish the locked state of the extended landing gear assembly (106) in response to the transmitted signal being received by the display device (138) via a data network (318) of the aircraft (100). Article 10. A method (400) of operating a landing gear monitoring and warning system (300), comprising: monitoring a magnetic field proximate an aperture (126) of a landing gear assembly (106), the landing gear assembly (106) including at least one linkage (118), the aperture (126) extending through the at least one linkage (118), the landing gear assembly (106) including a locking pin (128) configured to be inserted into the aperture (126) when the landing gear assembly (106) is in an extended position to inhibit movement of the at least one linkage (118) and establish a locked state of the landing gear assembly (106) in the extended position; sensing a magnetic response indicative of the locking pin (128) being disposed within the aperture (126) to establish the locked condition of the landing gear assembly (106) in the extended position; and in response to detecting the magnetic response indicating that the locking pin is positioned within the aperture to establish the locked state of the landing gear assembly in the extended position, transmitting a signal indicating that the locking pin has been inserted into the aperture and the locked state of the landing gear assembly has been established. Article 11. The method (400) of clause 10, further comprising, in response to the transmitted signal being received by a display device (138) of the aircraft (100) via a data network (318) of the aircraft (100), the display device (138) having a primary field of view within a cockpit (136) of the aircraft (100), displaying information about the locking pin (128) being positioned within the aperture (126) on the display device (138). Article 12. The method (400) according to clause 10, wherein detecting the magnetic response includes activating a magnetic sensor activation switch (304) when the locking pin (128) is magnetically detected to be positioned within the aperture (126), and in response to activating the magnetic sensor activation switch (304), transmitting a sensor output from the magnetic sensor activation switch (304) to a communication module (308) of the landing gear monitoring and warning system (300). Article 13. 11. The method (400) of claim 10, wherein transmitting the signal indicating that the locking pin (128) is inserted into the aperture (126) includes wirelessly transmitting the signal indicating that the locking pin (128) is inserted into the aperture (126). Article 14. 11. The method (400) of clause 10, wherein transmitting the signal indicating that the locking pin (128) is inserted into the aperture (126) includes transmitting the signal indicating that the locking pin (128) is inserted into the aperture (126) using a universal asynchronous transmitter / receiver. Article 15. 11. The method (400) of clause 10, wherein transmitting the signal indicating that the locking pin (128) is inserted into the aperture (126) comprises transmitting the signal indicating that the locking pin (128) is positioned within the aperture (126) to a ground crew gripping device (320) in response to detecting the magnetic response indicating that the locking pin (128) is positioned within the aperture (126) to establish the locked state of the landing gear assembly (106) in the extended position. Article 16. 11. The method (400) of claim 10, wherein transmitting the signal indicating that the locking pin (128) is inserted into the aperture (126) includes detecting the magnetic response indicating that the locking pin (128) is positioned within the aperture (126) to establish the locked state of the landing gear assembly (106) in the extended position, and transmitting the signal indicating that the locking pin (128) is positioned within the aperture (126) in response to receiving flight phase information indicative of a taxiing movement by the aircraft (100). Article 17. The method (400) of clause 10, further comprising, in response to the transmitted signal being received by a display device (138) via a data network (318) of the aircraft (100), displaying information about the locking pin (128) being positioned within the aperture (126) on an overview page (142) displayed by the display device (138). Article 18. A body (102); a landing gear assembly (106) movable relative to the fuselage (102), the landing gear assembly (106) having an extended position, the landing gear assembly (106) including at least one linkage (118) and an aperture (126) extending through the at least one linkage (118), the landing gear assembly (106) including a locking pin (128) configured to be inserted into the aperture (126) extending through the at least one linkage (118), the locking pin (128) when inserted inhibiting movement of the at least one linkage (118) to establish a locked state of the landing gear assembly (106) in the extended position; a landing gear monitoring and warning system (300) coupled to the landing gear assembly (106), the landing gear monitoring and warning system (300) comprising: a magnetic sensor (302) disposed adjacent the aperture (126) and configured to detect a magnetic response indicative of the locking pin (128) being disposed within the aperture (126) to establish the locked state of the landing gear assembly (106) in the extended position, the magnetic sensor (302) configured to generate a sensor output indicative of the locking pin (128) being disposed within the aperture (126); 1. The aircraft (100) comprising: a communications module (308) having a transmitter (310) coupled to the magnetic sensor (302) to receive the sensor output indicating that the locking pin (128) is disposed within the aperture (126), the communications module (308) configured to responsively transmit a signal indicating that the locking pin (128) is disposed within the aperture (126) and that the locked condition of the landing gear assembly (106) in the extended position has been established. Article 19. The aircraft (100) described in clause 18, further comprising a cockpit (136) and a display device (138) disposed within the cockpit (136), the display device (138) being within a primary field of view within the cockpit (136), and the display device (138) being configured to display information about the locking pin (128) being disposed within the aperture (126) to establish the locked state of the landing gear assembly (106) in the extended position in response to the transmitted signal being received by the display device (138) via a data network (318) of the aircraft (100). Article 20. The aircraft (100) described in clause 18, wherein the magnetic sensor (302) includes a magnetic sensor activation switch (304), and the magnetic sensor (302) is configured to activate the magnetic sensor activation switch (304) and provide the sensor output to the communication module (308) when the magnetic sensor (302) magnetically detects that the locking pin (128) is positioned within the aperture (126).

[0053] As used herein, a system, device, structure, article, element, component, or hardware that is "configured to" perform a particular function is not in fact capable of performing that particular function without any modification, but rather may perform that particular function after further modification. In other words, a system, device, structure, article, element, component, or hardware that is "configured to" perform a particular function is specifically selected, created, implemented, utilized, programmed, and / or designed for the purpose of performing that particular function. As used herein, the term "configured to" refers to the existing characteristics of a system, device, structure, article, element, component, or hardware that enable the system, device, structure, article, element, component, or hardware to perform a particular function without further modification. For purposes of this disclosure, a system, device, structure, article, element, component, or hardware described as being "configured" to perform a particular function may additionally or alternatively be described as being "adapted to" and / or "operative to" perform that function.

[0054] The illustrations of the embodiments described herein are intended to provide a general understanding of the structure of the various embodiments. These illustrations are not intended to serve as an exhaustive description of all of the elements and features of apparatus and systems utilizing the structures or methods described herein. Many other embodiments may become apparent to those skilled in the art upon review of this disclosure. Other embodiments may be utilized and derived from this disclosure, such that structural and logical substitutions and changes may be made without departing from the scope of the disclosure. For example, the operations recited within the method 400 of FIG. 10 may be performed in an order different from that shown, two or more of the operations may be performed simultaneously (or in combination), or one or more of the operations may be omitted. For illustrative purposes, the electric field strength data may be generated before the electric arc is generated, such as simultaneously with applying a voltage to a corona generator. Thus, the present disclosure and the figures should be considered illustrative rather than limiting.

Claims

1. a locking pin (128) configured to be inserted into an aperture (126) extending through at least one linkage (118) of the extended landing gear assembly (106), the locking pin (128) inhibiting movement of the at least one linkage (118) when inserted to establish a locked state of the extended landing gear assembly (106); a magnetic sensor (302) disposed proximate the aperture (126) and configured to detect a magnetic response indicative of the locking pin (128) being disposed within the aperture (126) to establish the locked state of the extended landing gear assembly (106), the magnetic sensor (302) configured to generate a sensor output indicative of the locking pin (128) being disposed within the aperture (126); a communications module having a transmitter coupled to the magnetic sensor for receiving the sensor output indicating that the locking pin is disposed within the aperture, the communications module configured to responsively transmit a signal indicating that the locking pin is disposed within the aperture and that the locked state of the extended landing gear assembly has been established; 1. A landing gear monitoring and warning system comprising: a display device (138) within a primary field of view within a cockpit (136) of the aircraft (100), the display device (138) configured to display information about the locking pin (128) being positioned within the aperture (126) to establish the locked state of the extended landing gear assembly (106) in response to the transmitted signal being received by the display device (138) via a data network (318) of the aircraft (100).

2. 2. The landing gear monitoring and warning system of claim 1, wherein the magnetic sensor comprises a magnetic sensor activation switch configured to activate the magnetic sensor activation switch and provide the sensor output to the communication module when the magnetic sensor magnetically detects that the locking pin is disposed within the aperture.

3. 3. The landing gear monitoring and warning system of claim 1, wherein the at least one linkage includes a pair of pivotally coupled linkage members, the aperture extending through the pair of pivotally coupled linkage members, and the locking pin configured to be inserted into the aperture extending through the pair of pivotally coupled linkage members to inhibit movement of the pair of pivotally coupled linkage members relative to one another such that the pair of pivotally coupled linkage members are held in a fixed relationship relative to one another.

4. 4. The landing gear monitoring and warning system of claim 1, wherein the communication module (308) comprises a microcontroller (312) configured to receive the sensor output from the magnetic sensor (302), and the communication module (308) includes an integrated WiFi component (314) configured to wirelessly transmit the signal indicating that the locking pin (128) is positioned within the aperture (126).

5. 5. The landing gear monitoring and warning system of claim 4, wherein the microcontroller is a universal host controller interface that transmits the signal indicating that the locking pin is located within the aperture via a universal asynchronous transmitter / receiver.

6. 5. The landing gear monitoring and warning system of claim 4, wherein the communications module is configured to transmit the signal indicating that the locking pin is located within the aperture to a ground crew grasped device in response to receiving the sensor output indicating that the locking pin is located within the aperture.

7. 7. The landing gear monitoring and warning system of claim 1, wherein the communications module is configured to receive the sensor output indicating that the locking pin is located within the aperture and to transmit the signal indicating that the locking pin is located within the aperture in response to receiving flight phase information indicative of a taxiing movement by the aircraft.

8. A body (102), a landing gear assembly (106) movable relative to the fuselage (102), the landing gear assembly (106) having an extended position and including at least one linkage (118) and an aperture (126) extending through the at least one linkage (118), the locking pin (128) configured to be inserted into the aperture (126) extending through the at least one linkage (118), the locking pin (128) when inserted inhibiting movement of the at least one linkage (118) to establish a locked state of the landing gear assembly (106) in the extended position; 2. The landing gear monitoring and warning system of claim 1 included within an aircraft comprising a cockpit and a display device disposed within the cockpit, the display device being within a primary field of view within the cockpit, the display device being configured to display information about the locking pin being disposed within the aperture to establish the locked condition of the landing gear assembly in the extended position in response to the transmitted signal being received by the display device via a data network of the aircraft.

9. A method (400) of operating a landing gear monitoring and warning system (300), comprising: monitoring a magnetic field proximate an aperture (126) of a landing gear assembly (106), the landing gear assembly (106) including at least one linkage (118), the aperture (126) extending through the at least one linkage (118), the landing gear assembly (106) including a locking pin (128) configured to be inserted into the aperture (126) when the landing gear assembly (106) is in an extended position to inhibit movement of the at least one linkage (118) and establish a locked state of the landing gear assembly (106) in the extended position; sensing a magnetic response indicative of the locking pin (128) being disposed within the aperture (126) to establish the locked condition of the landing gear assembly (106) in the extended position; and in response to detecting the magnetic response indicating that the locking pin (128) is positioned within the aperture (126) to establish the locked state of the landing gear assembly (106) in the extended position, transmitting a signal indicating that the locking pin (128) has been inserted into the aperture (126) and the locked state of the landing gear assembly (106) has been established; the method (400) further comprising, in response to the transmitted signal being received by a display device (138) of the aircraft (100) via a data network (318) of the aircraft (100), the display device (138) having a primary field of view within a cockpit (136) of the aircraft (100), displaying information about the locking pin (128) being positioned within the aperture (126) on the display device (138).

10. 10. The method (400) of claim 9, wherein detecting the magnetic response includes activating a magnetic sensor activated switch (304) upon magnetically detecting that the locking pin (128) is positioned within the aperture (126), and in response to activating the magnetic sensor activated switch (304), transmitting a sensor output from the magnetic sensor activated switch (304) to a communications module (308) of the landing gear monitoring and warning system (300).

11. 11. The method (400) of claim 9 or 10, wherein transmitting the signal indicating that the locking pin (128) is inserted into the aperture (126) comprises transmitting the signal indicating that the locking pin (128) is inserted into the aperture (126) wirelessly or using a universal asynchronous transceiver to transmit the signal indicating that the locking pin (128) is inserted into the aperture (126).

12. 12. The method (400) of any one of claims 9 to 11, wherein transmitting the signal indicating that the locking pin (128) is inserted into the aperture (126) comprises transmitting the signal indicating that the locking pin (128) is positioned within the aperture (126) in response to detecting the magnetic response indicating that the locking pin (128) is positioned within the aperture (126) to establish the locked state of the landing gear assembly (106) in the extended position and receiving flight phase information indicative of a taxiing movement by the aircraft (100).

13. 13. The method (400) of any one of claims 9 to 12, further comprising, in response to the transmitted signal being received by a display device (138) via a data network (318) of the aircraft (100), displaying information about the locking pin (128) being positioned in the aperture (126) on an overview page (142) displayed by the display device (138).

Images