Aircraft landing gear monitoring system and method

Abstract

The present disclosure relates to an aircraft landing gear monitoring system and method. A landing gear (106, 108, 108a, 108b, 108c) monitoring system and method for an aircraft (102) includes a landing gear timing analysis control unit (114) configured to analyze one or both of the landing gear motion of one or more landing gears (106, 108, 108a, 108b, 108c) of the aircraft (102) and the door motion of one or more doors (110, 110a) proximate to the landing gear (106, 108, 108a, 108b, 108c) to determine the operating status of one or both of the landing gear (106, 108, 108a, 108b, 108c) and the door (110, 110a).

Description

Technical Field

[0001] Embodiments of the present disclosure generally relate to aircraft landing gear monitoring systems and methods. Background Art

[0002] Various types of aircraft are used to transport passengers and cargo between various locations. Each aircraft usually flies between different locations according to a defined flight plan or path. For example, an aircraft departs from a departure location and flies to an arrival location.

[0003] A typical aircraft includes at least one landing gear configured to move between a deployed position (such as when the aircraft is on the ground, taking off, or about to land) and a retracted position (such as when the aircraft is in flight). For example, the aircraft includes three landing gears, namely a nose landing gear, a left main landing gear, and a right main landing gear.

[0004] Over time and repeated use, each landing gear may require attention from ground crew, such as for maintenance, service, or replacement. Normal wear and tear may require that certain portions of the landing gear be replaced, renewed, fixed, etc. Thus, ground crew typically inspect each landing gear on a regular basis, such as after each flight of the aircraft.

[0005] However, visual inspections of the landing gear may not always accurately assess whether the landing gear requires attention. Furthermore, performing maintenance on aircraft systems and subsystems after the landing gear is no longer effective interrupts aircraft operations, resulting in lost revenue and often requiring the rescheduling of one or more flights. Summary of the invention

[0006] There is a need for a system and method for monitoring the landing gear of an aircraft. In addition, there is a need for a system and method for accurately determining when the landing gear of an aircraft requires service and maintenance. In addition, there is a need for a system and method for evaluating the current and future effectiveness of the landing gear of an aircraft.

[0007] In view of those needs, certain embodiments of the present disclosure provide a landing gear monitoring system for an aircraft. The landing gear monitoring system includes a landing gear timing analysis control unit configured to analyze one or both of a landing gear motion of one or more landing gears of the aircraft and a door motion of one or more doors proximate to the one or more landing gears to determine an operational status of one or both of the landing gears and the doors.

[0008] In at least one embodiment, the door is configured to cover the landing gear when the landing gear is in the retracted position. The door is configured to open to allow the landing gear to move to the deployed position. The landing gear may include a front landing gear, a left main landing gear, and a right main landing gear.

[0009] In at least one embodiment, one or more sensors are in communication with the landing gear timing analysis control unit. The sensors are configured to detect one or both of landing gear movement and door movement.

[0010] In at least one embodiment, the timer is in communication with a landing gear timing analysis control unit. The landing gear timing analysis control unit is configured to detect, via the timer, one or both of a landing gear movement time of the landing gear movement between the retracted position and the deployed position and a door movement time of the door movement between the closed position and the open position.

[0011] In at least one embodiment, the landing gear timing analysis control unit is configured to analyze the landing gear movement between the retracted position and the deployed position relative to at least one normal landing gear operation time for the landing gear to determine the operating state of the landing gear. In at least one example, a timing database is in communication with the landing gear timing analysis control unit. The normal landing gear operation time can be stored in the timing database. As an example, the at least one normal landing gear operation time includes one or both of a normal landing gear deployed operation time and a normal landing gear retracted operation time.

[0012] In at least one embodiment, the landing gear timing analysis control unit is configured to analyze the door movement between the closed position and the open position relative to at least one normal door operation time for the door to determine the operating state of the door. In at least one embodiment, a timing database is in communication with the landing gear timing analysis control unit. The normal door operation time may be stored in the timing database. As an example, the at least one normal door operation time includes one or both of a normal door open operation time and a normal door closed operation time.

[0013] In at least one embodiment, the landing gear timing analysis control unit is configured to analyze one or both of the landing gear movement and the door movement and predict the effective time of one or both of the landing gear and the door.

[0014] Certain embodiments of the present disclosure provide a landing gear monitoring method for an aircraft. The landing gear monitoring method includes analyzing (by a landing gear timing analysis control unit) one or both of a landing gear movement of one or more landing gears of the aircraft and a door movement of one or more doors proximate to the landing gear, and determining the operating status of one or both of the landing gear and the door by analyzing (by the landing gear timing analysis control unit).

[0015] In at least one embodiment, the landing gear monitoring method further includes communicatively coupling one or more sensors to the landing gear timing analysis control unit, and detecting, by the sensors, one or both of the landing gear movement and the door movement.

[0016] In at least one embodiment, the landing gear monitoring method also includes communicatively coupling a timer to a landing gear timing analysis control unit, and detecting (by the landing gear timing analysis control unit via the timer) one or both of a landing gear movement time of the landing gear movement between the retracted position and the deployed position and a door movement time of the door movement between the closed position and the open position.

[0017] In at least one embodiment, the analyzing includes analyzing the landing gear movement between the retracted position and the deployed position relative to at least one normal landing gear operation time for one or more landing gears.

[0018] In at least one embodiment, the analyzing includes analyzing the door movement between the closed position and the open position relative to at least one normal door operation time for the door.

[0019] In at least one embodiment, a landing gear monitoring method includes predicting a valid time for one or both of the landing gear and the door. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] Figure 1 A schematic block diagram of a landing gear monitoring system for an aircraft according to an embodiment of the present disclosure is shown.

[0021] Figure 2 is a diagrammatic representation of a bottom perspective view of an aircraft according to an exemplary embodiment of the present disclosure.

[0022] Figure 3 A flow chart of a landing gear monitoring method for an aircraft according to an embodiment of the present disclosure is shown.

[0023] Figure 4 A flow chart of a landing gear monitoring method for an aircraft according to an embodiment of the present disclosure is shown. DETAILED DESCRIPTION

[0024] When reading in conjunction with the accompanying drawings, the following detailed description of the foregoing overview and certain embodiments will be better understood. As used herein, an element or step described in the singular and preceded by the word "one" or "an" should be understood to not necessarily exclude the plural number of elements or steps. In addition, reference to "an embodiment" is not intended to be interpreted as excluding the existence of additional embodiments that also include the features. In addition, unless explicitly stated to the contrary, an embodiment that "includes" or "has" an element or multiple elements with a specific condition may include additional elements that do not have the condition.

[0025] Certain embodiments of the present disclosure provide a landing gear monitoring system and method configured to determine and predict when the landing gear is to be serviced and / or replaced. Embodiments of the present disclosure allow the landing gear to be serviced, replaced, etc. prior to a potential failure of the landing gear.

[0026] In at least one embodiment, a method for monitoring and analyzing landing gear performance to provide predictive maintenance includes receiving landing gear output data from sensors on and / or proximate to the landing gear; compiling a database of landing gear output data from multiple aircraft; applying statistical methods to determine acceptable times for operations (including landing gear door and mechanism operations); determining thresholds for normal landing gear operation; identifying operations outside of normal thresholds; and providing maintenance or repair recommendations in response to determining that the landing gear is operating outside of normal thresholds. Certain embodiments of the present disclosure combine aircraft landing gear life cycle history with predictive maintenance analysis to identify potential abnormal conditions and provide maintenance recommendations prior to potential failures.

[0027] Figure 1 A schematic block diagram of a landing gear monitoring system 100 for an aircraft 102 according to an embodiment of the present disclosure is shown. The aircraft 102 includes a fuselage 104 defining a landing gear well 106 (e.g., a landing gear storage bay), and a landing gear 108 is positioned in the landing gear well in a retracted position. In the retracted position, the landing gear 108 within the landing gear well 106 may be covered by one or more doors 110. When the aircraft 102 is in flight, such as during a cruise phase, the landing gear 108 is in the retracted position. For example, when the aircraft 102 transitions to a landing phase, the doors 110 open and the landing gear 108 moves to a deployed position so that the aircraft 102 can land. For example, when the aircraft 102 is on the ground, during a takeoff phase and during a landing phase, the landing gear 108 is in a deployed position. The landing gear 108 is configured to move between a retracted position and a deployed position within the landing gear well 106 when the door 110 is open and at least a portion of the landing gear 106 extends out of the landing gear well 106. The aircraft 102 may include a plurality of landing gears 108. For example, the aircraft 102 includes a nose landing gear, a left main landing gear, and a right main landing gear, each of which is configured to move into and out of its own landing gear well 106.

[0028] The landing gear monitoring system 100 includes one or more sensors 112 associated with the landing gear 108 and / or the door 110. For example, the one or more sensors 112 may be on or near the landing gear 108 and configured to detect when the landing gear 108 is in a retracted position and a deployed position. Additionally or optionally, the one or more sensors 112 may be on or near the door 110 and configured to detect when the door 110 is closed and opened. In at least one embodiment, the sensor 112 may be a position sensor such as an encoder, an infrared sensor, an ultrasonic sensor, a camera, etc.

[0029] The landing gear monitoring system 100 also includes a landing gear timing analysis control unit 114, which communicates with the sensor 112, the timer 116, and the timing database 118, such as through one or more wired or wireless connections. In at least one embodiment, the landing gear timing analysis control unit 114 can include the timer 116 and / or the timing database 118.

[0030] As shown, the landing gear monitoring system 100 may be on or within the aircraft 102. In at least one other embodiment, at least a portion of the landing gear monitoring system 100 may be remote from the aircraft 102, such as at a central monitoring station. For example, the sensor 112 may be on the aircraft 102, but the landing gear timing analysis control unit 114, the timer 116, and the timing database 118 may be at a central monitoring center, such as at an airport.

[0031] In operation, the sensor 112 detects when the landing gear 108 is in the retracted position and the deployed position. Additionally, in at least one embodiment, the sensor 112 detects when the door 110 is in the closed position and the open position. The landing gear timing analysis control unit 114 is configured to analyze the landing gear movement (from the retracted position to the deployed position, and vice versa) relative to normal operating times for the landing gear 108 (such as normal landing gear deployment operating times and normal landing gear retracting operating times) to determine whether the landing gear 108 is operating properly. In at least one embodiment, the landing gear timing analysis control unit 114 is also configured to analyze the door movement (from the closed position to the open position, or vice versa) relative to normal operating times for the door 110 (such as normal door opening operating times and normal door closing operating times) to determine whether the door 110 is operating properly.

[0032] When the landing gear 108 moves between the retracted position and the deployed position, the landing gear timing analysis control unit 114 receives a sensor signal from the sensor 112. The sensor signal includes a retracted position sensor signal and a deployed position sensor signal. The landing gear timing analysis control unit 114 determines that the landing gear 108 is in the retracted position when receiving the retracted position sensor signal. Similarly, the landing gear timing analysis control unit 114 determines that the landing gear 108 is in the deployed position when receiving the deployed position sensor signal.

[0033] The sensor signals also include a closed door sensor signal and an open door sensor signal. The landing gear timing analysis control unit 114 determines that the door 110 is closed when receiving the closed door signal. Similarly, the landing gear timing analysis control unit 114 determines that the door 110 is open when receiving the open door signal.

[0034] The timer 116 detects the movement time between the retracted position of the landing gear 108 and the deployed position of the landing gear 108 (or vice versa). The timer 116 may be, for example, a digital clock configured to detect such time and output a timing signal to the landing gear timing analysis control unit 114.

[0035] The landing gear timing analysis control unit 114 receives a sensor signal from the sensor 112 from the landing gear 108 indicating that the landing gear 108 is moving from the retracted position to the deployed position, or vice versa. At the same time, the landing gear timing analysis control unit 114 receives a timing signal from the timer 116 and is therefore able to determine the time when the landing gear 108 moves from the retracted position to the deployed position (or vice versa). In this way, the landing gear timing analysis control unit 114 determines the time when the landing gear 108 moves between the retracted position to the deployed position (whether from the retracted position to the deployed position or from the deployed position to the retracted position).

[0036] The landing gear timing analysis control unit 114 then compares the movement time of the landing gear 108 to one or more normal landing gear operation times stored in the timing database 118. The normal landing gear operation time can be determined empirically by analyzing the landing gear movements for a large number of aircraft (e.g., hundreds or thousands) over a specific time period. Based on such analysis, a normal landing gear operation time (such as a threshold or range) is established. In at least one other embodiment, the normal landing gear operation time can be defined by the manufacturer.

[0037] In at least one embodiment, the landing gear timing analysis control unit 114 compares the deployment time of the movement of the landing gear 108 from the retracted position to the deployed position, and compares the deployment time of the movement to the normal landing gear deployment operation time stored in the timing database 118. If the deployment time of the movement is consistent with the normal landing gear deployment operation time (e.g., matches or is within an acceptable range), the landing gear timing analysis control unit 114 determines that the landing gear 108 is properly (i.e., normally) deployed. However, if the deployment time of the movement is inconsistent with the normal landing gear deployment operation time (e.g., too fast or too slow), the landing gear timing analysis control unit 114 determines that the landing gear 108 is inappropriately (i.e., abnormally) deployed. In this way, the landing gear timing analysis control unit 114 can output an alert that the landing gear 108 needs attention (e.g., maintenance, or replacement) to, for example, a flight computer of the aircraft 102, a monitoring center, etc.

[0038] In at least one embodiment, the landing gear timing analysis control unit 114 compares the retraction time of the movement of the landing gear 108 from the deployed position to the retracted position, and compares the retraction time of the movement with the normal landing gear retraction operation time stored in the timing database 118. If the retraction time of the movement is consistent with the normal landing gear retraction operation time (e.g., matches or is within an acceptable range), the landing gear timing analysis control unit 114 determines that the landing gear 108 is being properly (i.e., normally) retracted. However, if the retraction time of the movement is inconsistent with the normal landing gear retraction operation time (e.g., too fast or too slow), the landing gear timing analysis control unit 114 determines that the landing gear 108 is being inappropriately (i.e., abnormally) retracted. In this way, the landing gear timing analysis control unit 114 can output an alert that the landing gear 108 needs attention (e.g., maintenance, repair, or replacement) to, for example, a flight computer of the aircraft 102, a monitoring center, etc.

[0039] In at least one embodiment, the landing gear timing analysis control unit 114 stores movement times (e.g., deployment times of movements and retraction times of movements) over a specific time period, such as one or more months or years. The landing gear timing analysis control unit 114 analyzes timing trends over the time period. Based on the timing trends (such as increasing or decreasing times), the landing gear timing analysis control unit 114 predicts future movement times. For example, based on the decreasing or increasing slope of a specific timed movement (whether retracting or deploying), the landing gear timing analysis control unit 114 predicts movement times for one or more future flights. In this way, the landing gear timing analysis control unit 114 is able to accurately predict when the landing gear 108 may no longer be effective. Therefore, the landing gear timing analysis control unit 114 can output the predicted effective time to a pilot, maintenance personnel, etc., so that the landing gear 108 (or one or more portions thereof) can be replaced before the landing gear 108 becomes ineffective.

[0040] In at least one embodiment, the landing gear timing analysis control unit 114 also receives a sensor signal from the door 110 from the sensor 112, the sensor signal indicating that the door 110 is moving from the closed position to the open position, or vice versa. At the same time, the landing gear timing analysis control unit 114 receives a timing signal from the timer 116 and is therefore able to determine when the door 110 moves from the closed position to the open position, or vice versa. In this way, the landing gear timing analysis control unit 114 determines the time when the door 110 moves between the closed position to the open position (whether from the closed position to the open position or from the open position to the closed position).

[0041] The landing gear timing analysis control unit 114 then compares the movement time of the door 110 to one or more normal operation times stored in the timing database 118. The timing range can be empirically determined by analyzing the movement of doors of a large number of aircraft (e.g., hundreds or thousands) over a specific time period. Based on this analysis, a normal operation time (such as a threshold or range) is established. In at least one other embodiment, the normal operation time can be defined by the manufacturer.

[0042] In at least one embodiment, the landing gear timing analysis control unit 114 compares the opening time of the movement of the door 110 from the closed position to the open position, and compares the opening time of the movement with the normal door opening operation time stored in the timing database 118. If the opening time of the movement is consistent with the normal door opening operation time (e.g., matches or is within an acceptable range), the landing gear timing analysis control unit 114 determines that the door 110 is opening properly (i.e., normally). However, if the opening time of the movement is inconsistent with the normal door opening operation time (e.g., too fast or too slow), the landing gear timing analysis control unit 114 determines that the door 110 is opening improperly (i.e., abnormally). In this way, the landing gear timing analysis control unit 114 can output an alert that the door 110 needs attention (e.g., maintenance, repair, or replacement), such as to a flight computer, a monitoring center, etc. of the aircraft 102.

[0043] In at least one embodiment, the landing gear timing analysis control unit 114 compares the closing time of the movement of the door 110 from the open position to the closed position, and compares the closing time of the movement with the normal door closing operation time stored in the timing database 118. If the closing time of the movement is consistent with the normal door closing operation time (e.g., matches or is within an acceptable range), the landing gear timing analysis control unit 114 determines that the door 110 is closing properly (i.e., normally). However, if the closing time of the movement is inconsistent with the normal door closing operation time (e.g., too fast or too slow), the landing gear timing analysis control unit 114 determines that the door 110 is closing improperly (i.e., abnormally). In this way, the landing gear timing analysis control unit 114 can output an alert that the door 110 needs attention (e.g., maintenance, repair, or replacement) to, for example, a flight computer, a monitoring center, or the like of the aircraft 102.

[0044] In at least one embodiment, the landing gear timing analysis control unit 114 stores movement times (e.g., opening times of movements and closing times of movements) over a specific time period, such as one or more months or years. The landing gear timing analysis control unit 114 analyzes timing trends over the time period. Based on the timing trends (such as increasing or decreasing times), the landing gear timing analysis control unit 114 predicts future movement times. For example, based on the decreasing or increasing slope of a specific timed movement (whether opening or closing), the landing gear timing analysis control unit 114 predicts movement times for one or more future flights. In this way, the landing gear timing analysis control unit 114 is able to accurately predict when the door 110 may no longer be effective. Therefore, the landing gear timing analysis control unit 114 can output the predicted effective time to the pilot, maintenance personnel, etc., so that the door 110 (or one or more portions thereof) can be replaced before the door 110 becomes ineffective.

[0045] As described herein, certain embodiments of the present disclosure provide a landing gear monitoring system 100 for an aircraft 102. The landing gear monitoring system 100 includes a landing gear timing analysis control unit 114 configured to analyze one or both of a landing gear motion of one or more landing gears 108 of the aircraft 102 and a door motion of one or more doors 110 proximate to the landing gear 108 to determine an operational status of the landing gear 108 and / or the door 110. The operational status of the landing gear 108 and / or the door 110 includes whether one or both of the landing gear 108 or the door 110 are operating properly (or improperly).

[0046] As used herein, the terms "control unit," "central processing unit," "unit," "CPU," "computer," and the like may include any processor-based or microprocessor-based system, including systems using microcontrollers, reduced instruction set computers (RISC), application specific integrated circuits (ASICs), logic circuits, and any other circuits or processors including hardware, software, or a combination thereof capable of performing the functions described herein. This is exemplary only, and thus is not intended to limit the definition and / or meaning of these terms in any way. For example, as described herein, the landing gear timing analysis control unit 114 may be or include one or more processors configured to control the operation of the landing gear timing analysis control unit 114.

[0047] The landing gear timing analysis control unit 114 is configured to execute a set of instructions stored in one or more data storage units or elements (such as one or more memories) in order to process data. For example, the landing gear timing analysis control unit 114 may include or be coupled to one or more memories. The data storage unit may also store data or other information as desired or required. The data storage unit may be in the form of an information source or physical memory element within a processor.

[0048] The set of instructions may include various commands instructing the landing gear timing analysis control unit 114 as a processor to perform specific operations such as the methods and processes of various embodiments of the subject matter described herein. The set of instructions may be in the form of a software program. The software may be in various forms such as system software or application software. In addition, the software may be in the form of a collection of separate programs, a subset of programs within a larger program, or a portion of a program. The software may also include modular programming in the form of object-oriented programming. The processing of input data by the processor may be in response to user commands, or in response to the results of previous processing, or in response to a request made by another processor.

[0049] The diagrams of the embodiments herein may illustrate one or more control or processing units such as the landing gear timing analysis control unit 114. It should be understood that the processing or control unit may represent a circuit, circuit diagram, or portion thereof, which may be implemented as hardware with associated instructions (e.g., software stored on a tangible and non-transitory computer-readable storage medium such as a computer hard drive, ROM, RAM, etc.) to perform the operations described herein. The hardware may include a state machine circuit that is hardwired to perform the functions described herein. Alternatively, the hardware may include an electronic circuit that includes and / or is connected to one or more logic-based devices such as a microprocessor, a processor, a controller, etc. Alternatively, the landing gear timing analysis control unit 114 may represent a processing circuit such as one or more of a field programmable gate array (FPGA), an application specific integrated circuit (ASIC), a microprocessor, etc. The circuits in various embodiments may be configured to execute one or more algorithms to perform the functions described herein. Whether or not explicitly identified in a flowchart or method, the one or more algorithms may include aspects of the embodiments disclosed herein.

[0050] As used herein, the terms "software" and "firmware" are interchangeable and include any computer program stored in a data storage unit (e.g., one or more memories) for execution by a computer, including RAM memory, ROM memory, EPROM memory, EEPROM memory, and non-volatile RAM (NVRAM) memory. The above data storage unit types are exemplary only, and are therefore not limited to the types of memories that can be used to store computer programs.

[0051] Figure 21 is a diagrammatic representation of a bottom perspective view of an aircraft 102 according to an exemplary embodiment of the present disclosure. The aircraft 102 includes a propulsion system 212, which may include, for example, two turbofan engines 214. Optionally, the propulsion system 212 may include more engines 214 than shown. The engines 214 are carried by wings 216 of the aircraft 102. In other embodiments, the engines 214 may be carried by the fuselage 104 and / or the tail 220. The tail 220 may also support a horizontal stabilizer 222 and a vertical stabilizer 224. The fuselage 104 of the aircraft 102 defines an interior cabin, which may include a cockpit 230.

[0052] The size, shape, and configuration of aircraft 102 may vary. Figure 2 As shown. For example, aircraft 102 may be a non-fixed wing aircraft such as a helicopter. As another example, aircraft 102 may be an unmanned aerial vehicle (UAV).

[0053] As shown, the aircraft 102 includes three landing gears 108, namely a front landing gear 108a, a left main landing gear 108b, and a right main landing gear 108c. Optionally, the aircraft 102 may include more or less than three landing gears 108. Each landing gear 108a, 108b, and 108c includes a corresponding wheel assembly 230a, 230b, and 230c, and the wheel assembly 230a, 230b, and 230c is operably coupled to a corresponding lever assembly 232a, 232b, and 232c, respectively.

[0054] The landing gear 108a, 108b and 108c are Figure 2 106a. To move the nose landing gear 108a to the deployed position, the front door 110a is opened. The left main landing gear 108b is configured to move into and out of the left landing gear well 106b. To move the left main landing gear 108b to the deployed position, the left door 110b is opened. The right main landing gear 108c is configured to move into and out of the right landing gear well 106c. To move the right main landing gear 108c to the deployed position, the right door 110c is opened.

[0055] Sensors 112a, 112b, 112c are positioned on and / or near the nose landing gear 106a, door 110a, left main landing gear 108b, door 110b, right main landing gear 108c, and door 110c to detect their positions. More or fewer sensors may be used. In addition, sensors 112a, 112b, and 112c may be located at locations other than those shown.

[0056] refer to Figure 1 and Figure 2 As described above, the landing gear timing analysis control unit 114 compares the movement times for the landing gears 108a, 108b, 108c and the doors 110a, 110b, and 110c with the normal operation times stored in the timing database 118. In at least one embodiment, the normal landing gear deployment time includes the normal front landing gear deployment operation time, the normal left main landing gear deployment operation time, and the normal right main landing gear deployment operation time. In at least one embodiment, the normal landing gear retraction operation time includes the normal front landing gear retraction operation time, the normal left main landing gear retraction operation time, and the normal right main landing gear retraction operation time. In at least one embodiment, the normal door opening operation time includes the normal front door opening operation time, the normal left door opening operation time, and the normal right door opening operation time. In at least one embodiment, the normal door closing operation time includes the normal front door closing operation time, the normal left door closing operation time, and the normal right door closing operation time.

[0057] The following table lists examples of time ranges used for various normal operating hours:

[0058]

[0059]

[0060] Each of the normal operating times shown above may be determined empirically or otherwise defined as a range and may be stored in Figure 1 The normal operating time may be a specific time threshold rather than a range. It should be understood that the normal operating time shown above is exemplary only and may be different for different aircraft and / or different types of aircraft. In addition, different normal operating times may be used for different parts of the landing gear and / or doors. For example, the movement of certain parts of a control rod, gear, piston, etc. may be analyzed and compared to corresponding normal operating times, rather than instead of (or in addition to) those times shown above.

[0061] Figure 3A flow chart of a landing gear monitoring method for an aircraft according to an embodiment of the present disclosure is shown. Figure 1 and Figure 3 At 300, the landing gear timing analysis control unit 114 detects the movement of the landing gear from the retracted position to the deployed position, or vice versa, such as via the sensor 112. At 302, the landing gear timing analysis control unit 114 detects the time of the landing gear movement (i.e., the landing gear movement time), such as via the timer 116.

[0062] At 304 , the landing gear timing analysis control unit 114 compares the landing gear movement time with the normal landing gear operation time for the associated landing gear movement. The normal landing gear operation time is stored in the timing database 118 .

[0063] At 306, the landing gear timing analysis control unit 114 determines whether the landing gear movement time is consistent with the normal landing gear operation time. If consistent, the method proceeds from 306 to 308, at 308, the landing gear timing analysis control unit 114 determines that the landing gear 108 is operating properly, and then the method returns to 300.

[0064] However, if there is no agreement at 306, the method proceeds from 306 to 310, where the landing gear timing analysis control unit 114 determines that the landing gear 108 is not operating properly. The method then proceeds to 312, where the landing gear timing analysis control unit 114 outputs an alarm regarding the landing gear 108.

[0065] Figure 4 A flow chart of a landing gear monitoring method for an aircraft according to an embodiment of the present disclosure is shown. Figure 1 and Figure 4 At 400, the landing gear timing analysis control unit 114 detects the door movement from the closed position to the open position, or vice versa, such as via the sensor 112. At 402, the landing gear timing analysis control unit 114 detects the time of the door movement (i.e., the door movement time), such as via the timer 116.

[0066] At 404 , the landing gear timing analysis control unit 114 compares the door movement time to the normal door operation time for the associated door movement. The normal door operation time is stored in the timing database 118 .

[0067] At 406, the landing gear timing analysis control unit 114 determines whether the door movement time is consistent with the normal door operation time. If consistent, the method proceeds from 406 to 408, at 408, the landing gear timing analysis control unit 114 determines that the door 110 is operating properly, and then the method returns to 400.

[0068] However, if there is no agreement at 406, the method proceeds from 406 to 410, where the landing gear timing analysis control unit 114 determines that the door 110 is not operating properly. The method then proceeds to 412, where the landing gear timing analysis control unit 114 outputs an alarm regarding the door 110.

[0069] refer to Figure 1 , Figure 3 as well as Figure 4 In at least one embodiment, the landing gear timing analysis control unit 114 operates to simultaneously determine the operating status of the landing gear 108 and the door 110. That is, in at least one embodiment, the landing gear timing analysis control unit 114 determines the operating status of the landing gear 108 and the door 110 according to Figure 3 and Figure 4 In at least one other embodiment, the landing gear timing analysis control unit 114 can be based on Figure 3 and Figure 4 Operate in one of the ways shown.

[0070] Additionally, in at least one embodiment, the landing gear timing analysis control unit 114 can store the landing gear movement times and / or the door movement times over time in the timing database 118. The landing gear timing analysis control unit 114 can analyze the landing gear movement time trends and / or the door movement time trends over time to predict when the landing gear 108 and / or the door 110 should be serviced or otherwise replaced to ensure proper effectiveness.

[0071] As described herein, embodiments of the present disclosure provide systems and methods for monitoring the landing gear of an aircraft. In addition, embodiments of the present disclosure provide systems and methods for accurately determining when the landing gear of an aircraft requires attention, such as for service, maintenance, or replacement. In addition, embodiments of the present disclosure provide systems and methods for assessing the current and future effectiveness of the landing gear of an aircraft.

[0072] Although various spatial and directional terms such as on top, on bottom, below, between, lateral, horizontal, vertical, in front, etc. may be used to describe embodiments of the present disclosure, it should be understood that these terms are used only with respect to the orientation shown in the drawings. The orientation may be inverted, rotated, or otherwise changed so that up is down and vice versa, horizontal becomes vertical, etc.

[0073] As used herein, a structure, limitation, or element that is "configured to" perform a task or operation is specifically structurally formed, constructed, or adapted in a manner corresponding to the task or operation. For purposes of clarity and avoidance of doubt, an object that is merely capable of being modified to perform a task or operation is not "configured to" perform a task or operation as used herein.

[0074] It should be understood that the above description is intended to be illustrative, not restrictive. For example, the above embodiments (and / or aspects thereof) can be used in combination with each other. In addition, many modifications can be made to adapt specific situations or materials to the teachings of various embodiments of the present disclosure without departing from the scope of the present disclosure. Although the size and type of materials described herein are intended to limit the parameters of various embodiments of the present disclosure, the embodiment is by no means restrictive, but an exemplary embodiment. Upon reviewing the above description, many other embodiments will be apparent to those skilled in the art. Therefore, the scope of various embodiments of the present disclosure should be determined with reference to the appended claims and the full range of equivalents to which these claims are entitled. In the appended claims, the terms "including" and "in which" are used as the equivalents of the plain-English equivalents of the corresponding terms "comprising" and "wherein". In addition, the terms "first", "second", and "third", etc. are used only as labels and are not intended to impose numerical requirements on their objects. In addition, the limitations of the following claims are not written in a device + function format unless and until such claim limitations explicitly use the phrase "device for...", followed by a functional statement without further structure.

[0075] Furthermore, the present disclosure includes embodiments according to the following items:

[0076] Item 1: A landing gear (106, 108, 108a, 108b, 108c) monitoring system for an aircraft (102), the landing gear (106, 108, 108a, 108b, 108c) monitoring system comprising:

[0077] A landing gear (106, 108, 108a, 108b, 108c) timing analysis control unit configured to analyze the landing gear (106, 108, 108a, 108b, 108c) of one or more landing gears (106, 108, 108a, 108b, 108c) of an aircraft (102) One or both of movement of one or more doors (110, 110a) of and movement of one or more doors (110, 110c) of one or more landing gears (106, 108, 108a, 108b, 108c) to determine an operational status of one or both of the one or more landing gears (106, 108, 108a, 108b, 108c) and the one or more doors (110, 110a).

[0078] Item 2: A landing gear (106, 108, 108a, 108b, 108c) monitoring system according to Item 1, wherein one or more doors (110, 110a) are configured to cover one or more landing gears (106, 108, 108a, 108b, 108c) when the one or more landing gears (106, 108, 108a, 108b, 108c) are in a retracted position, and wherein one or more doors (110, 110a) are configured to open to allow one or more landing gears (106, 108, 108a, 108b, 108c) to move to a deployed position.

[0079] Item 3: A landing gear (106, 108, 108a, 108b, 108c) monitoring system according to item 1 or 2, wherein one or more landing gears (106, 108, 108a, 108b, 108c) include a front landing gear (106a, 106, 108, 108a, 108b, 108c), a left main landing gear (108b) (106, 108, 108a, 108b, 108c) and a right main landing gear (106, 108, 108a, 108b, 108c).

[0080] Item 4: A landing gear (106, 108, 108a, 108b, 108c) monitoring system according to any one of items 1 to 3, further comprising one or more sensors (112, 112a, 112b, 112c) communicating with a landing gear (106, 108, 108a, 108b, 108c) timing analysis control unit, wherein the one or more sensors (112, 112a, 112b, 112c) are configured to detect one or both of the movement of the landing gear (106, 108, 108a, 108b, 108c) and the movement of the door (110, 110b, 110c).

[0081] Item 5: A landing gear (106, 108, 108a, 108b, 108c) monitoring system according to any one of items 1 to 4, further comprising a timer (116) communicating with a landing gear (106, 108, 108a, 108b, 108c) timing analysis control unit, wherein the landing gear (106, 108, 108a, 108b, 108c) timing analysis control unit is configured to detect via the timer (116) one or both of a movement time of the landing gear (106, 108, 108a, 108b, 108c) between a retracted position and a deployed position and a movement time of a door (110, 110b, 110c) between a closed position and an open position.

[0082] Item 6: A landing gear (106, 108, 108a, 108b, 108c) monitoring system according to any one of items 1 to 5, wherein a landing gear (106, 108, 108a, 108b, 108c) timing analysis control unit is configured to analyze the movement of the landing gear (106, 108, 108a, 108b, 108c) between a retracted position and a deployed position relative to at least one normal landing gear (106, 108, 108a, 108b, 108c) operation time for one or more landing gears (106, 108, 108a, 108b, 108c) to determine the operating status of one or more landing gears (106, 108, 108a, 108b, 108c).

[0083] Item 7: The landing gear (106, 108, 108a, 108b, 108c) monitoring system according to any one of items 1 to 6 also includes a timing database (118) that communicates with the landing gear (106, 108, 108a, 108b, 108c) timing analysis control unit, wherein at least one normal landing gear (106, 108, 108a, 108b, 108c) operation time is stored in the timing database (118).

[0084] Item 8: A landing gear (106, 108, 108a, 108b, 108c) monitoring system according to any one of items 1 to 7, wherein at least one normal landing gear (106, 108, 108a, 108b, 108c) operation time includes one or both of a normal landing gear (106, 108, 108a, 108b, 108c) deployment operation time and a normal landing gear (106, 108, 108a, 108b, 108c) retraction operation time.

[0085] Item 9: A landing gear (106, 108, 108a, 108b, 108c) monitoring system according to any one of items 1 to 8, wherein a landing gear (106, 108, 108a, 108b, 108c) timing analysis control unit is configured to analyze the movement of the door (110, 110b, 110c) between a closed position and an open position relative to at least one normal door (110, 110b, 110c) operation time for one or more doors (110, 110a) to determine the operating status of one or more doors (110, 110a).

[0086] Item 10: A landing gear (106, 108, 108a, 108b, 108c) monitoring system according to any one of items 1 to 9, further comprising a timing database (118) communicating with a landing gear (106, 108, 108a, 108b, 108c) timing analysis control unit, wherein at least one normal door (110, 110b, 110c) operation time is stored in the timing database (118).

[0087] Item 11: A landing gear (106, 108, 108a, 108b, 108c) monitoring system according to any one of items 1 to 9, wherein at least one normal door (110, 110b, 110c) operation time includes one or both of a normal door (110, 110b, 110c) open operation time and a normal door (110, 110b, 110c) closed operation time.

[0088] Item 12: A landing gear (106, 108, 108a, 108b, 108c) monitoring system according to any one of items 1 to 11, wherein a landing gear (106, 108, 108a, 108b, 108c) timing analysis control unit is configured to analyze one or both of the movement of the landing gear (106, 108, 108a, 108b, 108c) and the movement of the door (110, 110b, 110c), and predict the effective time of one or both of one or more landing gears (106, 108, 108a, 108b, 108c) and one or more doors (110, 110a).

[0089] Item 13: A method for monitoring a landing gear (106, 108, 108a, 108b, 108c) of an aircraft (102), the method comprising:

[0090] analyzing, by a landing gear (106, 108, 108a, 108b, 108c) timing analysis control unit, one or both of the movement of landing gear (106, 108, 108a, 108b, 108c) of one or more landing gears (106, 108, 108a, 108b, 108c) of the aircraft (102) and the movement of one or more doors (110, 110a) proximate to the one or more landing gears (106, 108, 108a, 108b, 108c); and

[0091] Through this analysis, the operating status of one or both of one or more landing gears (106, 108, 108a, 108b, 108c) and one or more doors (110, 110a) is determined by the landing gear (106, 108, 108a, 108b, 108c) timing analysis control unit.

[0092] Item 14: The landing gear (106, 108, 108a, 108b, 108c) monitoring method according to Item 13, further comprising:

[0093] communicatively coupling one or more sensors (112, 112a, 112b, 112c) to a landing gear (106, 108, 108a, 108b, 108c) timing analysis control unit; and

[0094] One or both of the movement of the landing gear (106, 108, 108a, 108b, 108c) and the movement of the door (110, 110b, 110c) are detected by one or more sensors (112, 112a, 112b, 112c).

[0095] Item 15: The landing gear (106, 108, 108a, 108b, 108c) monitoring method according to Item 13 or 14, further comprising:

[0096] communicatively coupling a timer (116) to a landing gear (106, 108, 108a, 108b, 108c) timing analysis control unit; and

[0097] A landing gear (106, 108, 108a, 108b, 108c) timing analysis control unit detects, via a timer (116), one or both of the movement time of the landing gear (106, 108, 108a, 108b, 108c) between a retracted position and an extended position and the movement time of the door (110, 110b, 110c) between a closed position and an open position.

[0098] Item 16: A landing gear (106, 108, 108a, 108b, 108c) monitoring method according to any one of items 13 to 15, wherein the analysis includes analyzing the movement of the landing gear (106, 108, 108a, 108b, 108c) between a retracted position and a deployed position relative to at least one normal landing gear (106, 108, 108a, 108b, 108c) operation time for one or more landing gears (106, 108, 108a, 108b, 108c).

[0099] Item 17: A method for monitoring a landing gear (106, 108, 108a, 108b, 108c) according to any one of items 1 to 16, wherein the analysis includes analyzing the movement of a door (110, 110b, 110c) between a closed position and an open position relative to the operation time of at least one normal door (110, 110b, 110c) for one or more doors (110, 110a).

[0100] Item 18: The landing gear (106, 108, 108a, 108b, 108c) monitoring method according to any one of items 1 to 17 also includes predicting the effective time of one or both of one or more landing gears (106, 108, 108a, 108b, 108c) and one or more doors (110, 110a).

[0101] Item 19: A landing gear (106, 108, 108a, 108b, 108c) monitoring system for an aircraft (102), the landing gear (106, 108, 108a, 108b, 108c) monitoring system comprising:

[0102] A landing gear (106, 108, 108a, 108b, 108c) timing analysis control unit configured to analyze the movement of a landing gear (106, 108, 108a, 108b, 108c) of a landing gear (106, 108, 108a, 108b, 108c) of an aircraft (102) and the movement of a door (110, 110a) approaching a door (110, 110b, 110c) of the landing gear (106, 108, 108a, 108b, 108c). 10c) movement to determine the operating state of the landing gear (106, 108, 108a, 108b, 108c) and the door (110, 110a), wherein the door (110, 110a) is configured to cover the landing gear (106, 108, 108a, 108b, 108c) when the landing gear (106, 108, 108a, 108b, 108c) is in a retracted position, and wherein the door (110, 110a) is configured to open to allow the landing gear (106, 108, 108a, 108b, 108c) to move to a deployed position;

[0103] a sensor (112, 112a, 112b, 112c) in communication with a landing gear (106, 108, 108a, 108b, 108c) timing analysis control unit, wherein each of the sensors (112, 112a, 112b, 112c) is configured to detect one or both of a landing gear (106, 108, 108a, 108b, 108c) movement and a door (110, 110b, 110c) movement;

[0104] A timer (116) in communication with a landing gear (106, 108, 108a, 108b, 108c) timing analysis control unit, wherein the landing gear (106, 108, 108a, 108b, 108c) timing analysis control unit is configured to detect, via the timer (116), a landing gear (106, 108, 108a, 108b, 108c) movement time of a landing gear (106, 108, 108a, 108b, 108c) movement between a retracted position and a deployed position and a door (110, 110b, 110c) movement time of a door (110, 110b, 110c) movement between a closed position and an open position, wherein the landing gear (106, 108, 108a, 108b, 108c) timing analysis control unit is configured to detect, relative to the landing gear (106, 108, 108a, 108b, 108c) movement time of a landing gear (106, 108, 108a, 108b, 108c) movement between a closed position and an open position. 106, 108, 108a, 108b, 108c) timing analysis control unit is configured to analyze the movement of the door (110, 110b, 110c) between the closed position and the open position relative to the normal door (110, 110a) operation time for the door (110, 110a) to determine the operating state of the door (110, 110a); and

[0105] A timing database (118) in communication with a landing gear (106, 108, 108a, 108b, 108c) timing analysis control unit, wherein normal landing gear (106, 108, 108a, 108b, 108c) operation time and normal door (110, 110b, 110c) operation time are stored in the timing database (118).

[0106] Item 20: A landing gear (106, 108, 108a, 108b, 108c) monitoring system according to Item 19, wherein the landing gear (106, 108, 108a, 108b, 108c) timing analysis control unit is also configured to analyze the movement of the landing gear (106, 108, 108a, 108b, 108c) and the movement of the door (110, 110b, 110c), and predict the effective time of the landing gear (106, 108, 108a, 108b, 108c) and the door (110, 110a).

[0107] This written description uses examples to disclose various embodiments of the present disclosure, including the best mode, and also enables any person skilled in the art to practice the various embodiments of the present disclosure, including making and using any device or system and performing any combined method. The patentable scope of the various embodiments of the present disclosure is defined by the claims, and may include other examples that occur to one skilled in the art. If the examples have structural elements that do not differ from the literal language of the claims, or if the examples include equivalent structural elements that do not differ substantially from the literal language of the claims, these other examples are intended to be within the scope of the claims.

Claims

1. A landing gear monitoring system (100) for an aircraft (102), the landing gear monitoring system (100) comprising: One or more sensors configured to detect door movement of one or more doors (110, 110a) proximate one or more landing gear (106, 108, 108a, 108b, 108c) of the aircraft; a landing gear timing analysis control unit (114) in communication with the one or more sensors, the landing gear timing analysis control unit (114) being configured to analyze the door movement to determine an operational status of the one or more doors (110, 110a); as well as A timer (116) in communication with the landing gear timing analysis control unit (114), wherein the landing gear timing analysis control unit (114) is configured to detect a door movement time of the door movement between a closed position and an open position via the timer (116).

2. The landing gear monitoring system (100) according to claim 1, wherein: The one or more sensors are further configured to detect landing gear movement of one or more landing gear of the aircraft; The landing gear timing analysis control unit (114) is further configured to analyze the landing gear movement of the one or more landing gears of the aircraft to determine the operating status of the one or more landing gears; The landing gear timing analysis control unit (114) is configured to detect a landing gear (106, 108, 108a, 108b, 108c) movement time of the landing gear movement between a retracted position and a deployed position via the timer, wherein the one or more doors (110, 110a) are configured to cover the one or more landing gears (106, 108, 108a, 108b, 108c) when the one or more landing gears (106, 108, 108a, 108b, 108c) are in a retracted position, and wherein the one or more doors (110, 110a) are configured to open to allow the one or more landing gears (106, 108, 108a, 108b, 108c) to move to a deployed position.

3. The landing gear monitoring system (100) according to claim 1 or 2, wherein: The one or more landing gears (106, 108, 108a, 108b, 108c) include a front landing gear (106a, 106, 108, 108a, 108b, 108c), a left main landing gear (108b) (106, 108, 108a, 108b, 108c) and a right main landing gear (106, 108, 108a, 108b, 108c).

4. The landing gear monitoring system (100) according to claim 1 or 2, wherein: The landing gear timing analysis control unit (114) is configured to analyze the landing gear movement between the retracted position and the deployed position relative to at least one normal landing gear operation time for the one or more landing gears (106, 108, 108a, 108b, 108c) to determine the operating state of the one or more landing gears (106, 108, 108a, 108b, 108c).

5. The landing gear monitoring system (100) of claim 4, further comprising a timing database (118) in communication with the landing gear timing analysis control unit (114), wherein: The at least one normal landing gear operation time is stored in the timing database (118).

6. The landing gear monitoring system (100) according to claim 5, wherein: The at least one normal landing gear operation time includes one or both of a normal landing gear extension operation time and a normal landing gear retraction operation time.

7. The landing gear monitoring system (100) according to claim 1 or 2, wherein: The landing gear timing analysis control unit (114) is configured to analyze the door movement between the closed position and the open position relative to at least one normal door operation time for the one or more doors (110, 110a) to determine the operating state of the one or more doors (110, 110a).

8. The landing gear monitoring system (100) of claim 7, further comprising a timing database (118) in communication with the landing gear timing analysis control unit (114), wherein: The at least one normal door operation time is stored in the timing database (118).

9. The landing gear monitoring system (100) according to claim 7, wherein: The at least one normal door operation time includes one or both of a normal door opening operation time and a normal door closing operation time.

10. The landing gear monitoring system (100) according to claim 1 or 2, wherein: The landing gear timing analysis control unit (114) is configured to analyze one or both of the landing gear movement and the door movement and predict the effective time of one or both of the one or more landing gears (106, 108, 108a, 108b, 108c) and the one or more doors (110, 110a).

11. A method for monitoring a landing gear (106, 108, 108a, 108b, 108c) of an aircraft (102), the method comprising: detecting door movement of one or more doors (110, 110a) proximate one or more landing gear (106, 108, 108a, 108b, 108c) of the aircraft by one or more sensors; Analyzing the door movement by a landing gear timing analysis control unit (114); as well as Through the analysis, the landing gear timing analysis control unit (114) determines the operating state of the one or more doors (110, 110a), The landing gear timing analysis control unit (114) detects the door movement time of the door movement between the closed position and the open position via a timer (116).

12. The landing gear (106, 108, 108a, 108b, 108c) monitoring method according to claim 11, wherein: The method further comprises: detecting, by the one or more sensors, landing gear movement of one or more landing gears of the aircraft; analyzing the landing gear movement by a landing gear timing analysis control unit (114) to determine an operating state of the one or more landing gears; The landing gear timing analysis control unit (114) detects the movement time of the landing gear (106, 108, 108a, 108b, 108c) of the landing gear movement between the retracted position and the deployed position via the timer, wherein the landing gear movement between the retracted position and the deployed position is analyzed by the landing gear timing analysis control unit relative to at least one normal landing gear operation time for the one or more landing gears (106, 108, 108a, 108b, 108c).

13. The landing gear (106, 108, 108a, 108b, 108c) monitoring method according to claim 11, wherein: The analyzing includes analyzing the door movement between the closed position and the open position relative to at least one normal door operation time for the one or more doors (110, 110a).

14. The landing gear (106, 108, 108a, 108b, 108c) monitoring method according to claim 11, further comprising predicting the effective time of one or both of the one or more landing gears (106, 108, 108a, 108b, 108c) and the one or more doors (110, 110a).

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