BR102017020399B1 - FLAP ASYMMETRY DETECTION SYSTEM AND METHOD - Google Patents

Abstract

AIRCRAFT WING FLAP ASYMMETRY DETECTION SYSTEMS AND METHODS. A flap asymmetry detection system (100) is configured to detect flap asymmetry of one or more flaps (102, 108) movably attached to one or more wings (104, 110) of an aircraft (106). The flap asymmetry detection system (100) includes a flap support assembly (112a, 112b, 112c, 112d) that couples a flap (102, 108) to a wing (104, 110). The flap support assembly (112a, 112b, 112c, 112d) includes a fixed portion (200) that is configured to attach to the wing (104, 110), a movable portion (222) that is movably coupled to the fixed portion (200) and configured to securely support the flap (102, 108), and a link (232) movably coupled to the fixed part (200) and the movable part (222). The link (232) includes a cylinder (304) defining an internal chamber (306) including a hydraulic fluid chamber (314), a piston (309) having a piston head (308) within the internal chamber (306), and hydraulic fluid (318) retained within the hydraulic fluid chamber (314). A pressure sensor (116) is fluid coupled to the hydraulic fluid chamber (314). The pressure detector (116) is configured to detect a fluid pressure of the hydraulic fluid (318) within the hydraulic fluid chamber (314). A (...).

Description

Field of Invention

[0001] Embodiments of the present description generally refer to systems and methods for detecting asymmetry of aircraft wing flaps.

Description Background

[0002] High lift systems are used on aircraft wings to increase lift and dredging during landings and takeoffs. One type of high-lift system includes flaps on the trailing edges of the wings. Flaps are movable control surfaces that can be extended during takeoffs and landings, and retracted at cruising speeds.

[0003] A variety of drive systems can be used to extend and retract the trailing edge flaps on a wing. One known type of drive system includes two drive stations, each with a drive station connected to the opposite side of the flap. In short, each flap is typically actuated by a mechanical system from two locations on the flap.

[0004] A flap support couples a flap to a fixed part of a wing. The flap support includes flap support ribs, a driver, a link, a drive arm, and a carrier fitting. The driver rotates the drive arm, which moves the link, which in turn pushes or pulls the carrier fitting. The carrier fitting rotates about a point with respect to the fixed flap support ribs.

[0005] If the flap disconnects from one of the flap supports (e.g., the link disconnects from the carrier fitting), the other flap support that remains attached to the other end of the flap and wing provides support for the entire flap plus the load donate. In this situation, the flap suffers from free rotation asymmetry. While the connected flap support can carry the resulting loads for a given number of flights, the singular flap support is unable to support the flap through an increased number of flights. That is, the single flap support is not designed to fully support the flap through numerous flights, as the single flap will wear at an increased rate and/or may be susceptible to failure due to fatigue.

[0006] Since the loss of both flap supports is potentially dangerous below a certain altitude, disconnected flap supports must be detected as promptly as possible; preferably within a single flight. In known aircraft, one or more position sensors are used to detect free rotation asymmetry. Position sensors are used to detect flap deformations in a specific flight configuration and compare them with the same deformation on the ground. If the difference between the two deformations exceeds a certain limit, an asymmetry alert is sent, and the aircraft is then inspected during a maintenance operation.

[0007] With ever-increasing performance demands, aircraft wings are becoming increasingly thinner and more rigid. Similarly, flaps are also becoming thinner and stiffer. For performance reasons, certain flaps may be so stiff that they do not deform sufficiently to be detected by a position-based sensor. As such, known asymmetry detection methods using position-based sensors may not be able to detect flap disconnections or free-rotation asymmetry.

[0008] Other known flap asymmetry detection methods directly measure the load on a drive mechanism, such as through load cell-based voltage calibration. However, a single calibration-based sensor is sensitive to unexpected and uncompensated loads, such as twist introduced into a connection due to friction. Additionally, strain gauges are very small and include very small connecting wires, thus making them relatively delicate when installed in a high-vibration environment, such as a flap support that is located directly behind the engine. an aircraft. Additionally, strain gauges are, by definition, fatigue machines. For example, copper alloy strain gauges may have a shorter fatigue life (in cycles) than various parts to which they are attached. As such sensors based on strain gauges can be too delicate and unreliable for use with wing flaps.

Description Summary

[0009] There is a need to create a system and method for efficient detection of aircraft wing flap asymmetry. There is a need to create a system and method for the rapid, accurate and reliable detection of flap asymmetry.

[00010] With these needs in mind, certain embodiments of the present disclosure provide a flap asymmetry detection system that is configured to detect flap asymmetry of one or more flaps movably attached to one or more wings of an aircraft. The flap asymmetry detection system includes a flap support assembly that couples a flap to a wing. The flap support assembly includes a fixed portion that is configured to securely attach to the wing, a movable portion that is movably coupled to the fixed portion and configured to securely support the flap, and a link movably coupled to the fixed portion. and the mobile part. The connection includes a cylinder defining an internal chamber including a hydraulic fluid chamber, a piston having a piston head within the internal chamber, and hydraulic fluid (such as an incompressible grease) retained within the hydraulic fluid chamber. A pressure sensor is fluid coupled to the hydraulic fluid chamber. The pressure detector is configured to detect a fluid pressure from the fluid pressure within the hydraulic fluid chamber. The fluid pressure detected by the pressure detector is used to determine the existence of flap asymmetry.

[00011] In at least one embodiment, the flap asymmetry detection system includes a flap asymmetry detection unit in communication with the pressure detector. The flap asymmetry detection unit receives a pressure signal indicative of fluid pressure from the pressure detector. The flap asymmetry detection unit determines the existence of flap asymmetry through an analysis of the pressure signal. For example, the flap asymmetry detection unit may compare the pressure signal with another pressure signal output from another pressure detector coupled to another flap support assembly that is coupled to the flap or another flap in order to determine the existence of flap asymmetry. The flap asymmetry detection unit sends a flap asymmetry warning signal upon determination that flap asymmetry exists.

[00012] The fixed portion may include a bracket that is configured to attach to the wing. The movable part may include a carrier accessory that is movably coupled to the fixed support.

[00013] In at least one embodiment, the pressure detector includes a pressure switch. Optionally, the pressure detector includes a pressure sensor.

[00014] The flap asymmetry detection system may include a fluid accessory coupled to the cylinder. The fluid fitting is configured to allow fluid to enter the hydraulic fluid chamber. The fluid accessory is configured to allow pressure detector testing.

[00015] Certain embodiments of the present disclosure provide a flap asymmetry detection method that is configured to detect flap asymmetry of one or more flaps movably attached to one or more wings of an aircraft. The method of detecting flap asymmetry includes attaching a fixed portion of a flap support assembly to a wing, movably coupling a movable portion of the flap support assembly to the fixed portion, securely supporting the flap with the movable part, movably coupling a connection to the fixed part and movable part, positioning a piston head of a piston within an internal chamber of the connection, retaining hydraulic fluid within a hydraulic fluid chamber of the internal chamber, coupling by fluid pressure detector to the hydraulic fluid chamber, detecting a fluid pressure of the hydraulic fluid within the hydraulic fluid chamber with a pressure detector, and determining the existence of flap asymmetry through fluid pressure detection.

[00016] In at least one embodiment, the method includes communicatively coupling a flap asymmetry detection unit to the pressure detector, and receiving (by the flap asymmetry detection unit) a pressure signal indicative of the pressure of fluid from the pressure detector. The determination includes analysis (by the flap asymmetry detection unit) of the pressure signal to determine the existence of flap asymmetry. In at least one embodiment, the analysis includes comparing the pressure signal with another pressure signal sent from another pressure detector coupled to another flap support assembly that is coupled to the flap or another flap in order to determine the existence of flap asymmetry. The method may also include sending (by the flap asymmetry detection unit) a flap asymmetry warning signal after determining that flap asymmetry exists.

[00017] In at least one embodiment, the method includes entering fluid into the hydraulic fluid chamber fitting through a fluid fitting coupled to the cylinder, and testing the pressure detector based, at least in part, on the input.

[00018] Certain embodiments of the present disclosure provide an aircraft that includes a fuselage, a first wing extending outwardly from the fuselage, a first flap securely attached to the first wing, a second wing extending outwardly from the fuselage opposite the first wing, a second flap attached to the first wing, and a flap asymmetry detection system that is configured to detect flap asymmetry of the first and second flaps, the flap asymmetry detection system includes flap support assemblies flap that couple the first and second flaps.

Brief Description of the Drawings

[00019] Figure 1 is a schematic representation of a flap asymmetry detection system, according to an embodiment of the present description;

[00020] Figure 2 is a diagrammatic representation of a side perspective view of a flap support assembly, in accordance with an embodiment of the present description;

[00021] Figure 3 is a diagrammatic representation of a side cross-sectional view of a connection of a flap support assembly, in accordance with an embodiment of the present description;

[00022] Figure 4 is a diagrammatic representation of a top plan view of an aircraft, according to an embodiment of the present description;

[00023] Figure 5 illustrates a flowchart of a method for detecting flap asymmetry of one or more wings of an aircraft, according to an embodiment of the present description.

Detailed description of the Description

[00024] The above summary, in addition to the following detailed description of certain embodiments, will be better understood when read in conjunction with the attached drawings. As used herein, an element or step mentioned in the singular form and preceded by the word "a", "an" shall be considered as not necessarily excluding the plural form of the elements or steps. Additionally, references to "an embodiment" should not be construed as excluding the existence of additional embodiments that also incorporate the aforementioned features. Furthermore, unless explicitly mentioned otherwise, embodiments "comprising" or "having" an element or a plurality of elements having a particular condition may include additional elements that do not have that condition.

[00025] Embodiments of the present disclosure provide flap asymmetry detection systems and methods that monitor loads within a load path of a flap support assembly, rather than through incremental position changes. Embodiments of the present disclosure provide a flap asymmetry detection system and method that includes a piston/cylinder connection for the flaps, wherein the hydraulic pressure of a hydraulic fluid in the cylinder is used to measure free-rotating flap asymmetry, e.g. example.

[00026] Figure 1 is a schematic representation of a flap asymmetry detection system 100, according to an embodiment of the present description. The flap asymmetry detection system 100 may include a flap 102 on a wing 104 of an aircraft 106 and a flap 108 on an opposite wing 110 of the aircraft 106. The flaps 102 and 108 may be trailing edge flaps on the wings 104 and 110, respectively.

[00027] Flap 102 is coupled to two flap support assemblies 112a and 112b, while flap 108 is coupled to two flap support assemblies 112c and 112d. As illustrated, flap support assemblies 112a and 112b are proximate to respective opposite ends of flap 102, while flap support assemblies 112c and 112d are proximate to respective opposite ends of flap 108. Flap support assemblies 112b and 112d may be external, while flap support assemblies 112a and 112c may be internal.

[00028] Each of the flap support assemblies 112a, 112b, 112c and 112d includes an actuator 114 that is configured to move the respective flaps 102 and 108 between the retracted and extended positions. The actuators 114 may be electromechanical actuators that are configured to actuate the flaps 102 and 108 between the retracted and extended positions. In at least one embodiment, the actuators 114 are geared rotary actuators. Optionally, the actuators 114 may be various other types of devices that are used to move the flaps 102 and 108. For example, the actuators 114 may be or include energized articulated wiring, connections, and/or the like.

[00029] While the flap 102 is illustrated coupled to two flap support assemblies 112a and 112b, and the flap 108 is illustrated coupled to two flap support assemblies 112c and 112d, each of the flaps 102 and 108 may be coupled to the additional flap support assemblies. For example, each of flaps 102 and 108 may be coupled to three or more actuators.

[00030] The flap support assemblies 112a, 112b, 112c and 112d also include a pressure detector 116. The pressure detectors 116 are configured to detect hydraulic fluid pressure within portions of the flap support assemblies 112a, 112b , 112c and 112d. Pressure detectors 116 are configured to send pressure signals that indicate hydraulic fluid pressure with parts of flap support assemblies 112a, 112b, 112c and 112d. The pressure detectors 116 may be pressure switches, such as mechanical switches having one or more diaphragms, piezoelectric switches, or the like. In such an embodiment, a change in pressure changes a state of the pressure switch, and pressure signals are sent each time a state change occurs. In at least one other embodiment, the pressure detectors 116 may be pressure sensors, such as electronic pressure sensors, that continuously monitor a hydraulic pressure and send a pressure signal.

[00031] An asymmetry detection unit 118 is in communication with pressure detectors 116, such as through one or more wired or wireless connections. The asymmetry detection unit 118 may be located within an aircraft fuselage 106 (such as within an electronics bay, cockpit, and/or the like). In at least one other embodiment, the asymmetry detection unit 118 is housed within at least one of the flap support assemblies 112a, 112b, 112c, or 112d. In another embodiment, the asymmetry detection unit 118 is housed within a wing, fuselage, empennage, or the like of the aircraft 106. In at least one other embodiment, the asymmetry detection unit 118 may be located remotely with respect to the aircraft. 106, such as within a land-based monitoring station.

[00032] As illustrated, the asymmetry detection unit 118 is in communication with each of the pressure detectors 116. In at least one other embodiment, an asymmetry detection unit 118 may be in communication with the pressure detectors 116 of each flap 102 or 108. For example a first asymmetry detection unit 118 may be in communication with the pressure detectors 116 of the flap support assemblies 112a and 112b, while a second asymmetry detection unit 118 may be in communication with the pressure detectors 116 of the flap support assemblies 112c and 112d. In at least one other embodiment, a separate and distinct asymmetry detection unit 118 may be in communication with each of the pressure detectors 116. For example, four asymmetry detection units 118 may be in communication with a respective pressure detector. 116 of each flap support assembly 112a, 112b, 112c, and 112d.

[00033] In operation, pressure detectors 116 are configured to detect variations in hydraulic pressure of parts of flap support assemblies 112a, 112b, 112c and 112d. The asymmetry detection unit 118 may include or be coupled to a memory that stores a previously measured non-free rotation condition of the flaps 102 and 108, and/or a predetermined fluid pressure of the portions of the flap support assemblies that is correlated with a non-free rotation condition. The asymmetry detection unit 118 may also be used to detect an energized asymmetry, such as that may be caused by obstruction of one or more of the flap support assemblies 112a, 112b, 112c and/or 112d. For example, if a received pressure signal is relatively low compared to an expected value for a specific flight condition, the asymmetry detection unit 118 may determine that a disconnection in the load path exists. Similarly, if the pressure signal is greater than the expected value, the asymmetry detection unit 118 may determine that an opposing flap support is carrying little or no load, or that an energized asymmetry due to an obstruction is in progress.

[00034] As noted above, the pressure detectors 116 are in communication with the asymmetry detection unit 118. The pressure detectors 116 send pressure signals to the asymmetry detection unit 118, which analyzes the received pressure signals. For example, the asymmetry detection unit 118 can compare received pressure signals and determine whether there is a difference therebetween. A difference between the pressure signals can be interpreted by the asymmetry detection unit 118 as the existence of flap asymmetry. If the asymmetry detection unit 118 determines that the received pressure signals are within a predetermined acceptable range, the asymmetry detection unit 118 determines that the flap support assemblies 112a, 112b, 112c and 112d are securely coupled to the flaps 102 and 108 (that is, flaps 102 and 108 are not in a freely rotating asymmetry condition). If, however, the asymmetry detection unit 118 determines that one or more received pressure signals exceed a predetermined asymmetry threshold (e.g., a threshold difference between pressure signals), the asymmetry detection unit 118 determines that a condition of free rotation asymmetry exists, and sends an asymmetry warning signal to a pilot, for example.

[00035] As used herein, the term "control unit", "unit", "central processing unit", "CPU", "computer" or the like may include any microprocessor-based or processor-based system including using microcontrollers, reduced instruction set computers (RISC), application-specific integrated circuits (ASICs), logic circuits, and any other circuit or processor including hardware, software or a combination thereof capable of performing the functions described here. Such are illustrative only, and shall in no way limit the definition and/or meaning of such terms. For example, the asymmetry detection unit 118 may be or include one or more processors.

[00036] The asymmetry detection unit 118 is configured to execute a set of instructions that are stored in one or more storage elements (such as one or more memories) in order to process data. For example, the asymmetry detection unit 118 may include or be coupled to one or more memories. Storage elements can also store data or other information as desired or needed. Storage elements can be in the form of an information source or a physical memory element within a processing machine.

[00037] The instruction set may include various commands that instruct the asymmetry detection unit 118 as a processing machine to perform specific operations such as methods and processes of various embodiments of the subject matter described herein. The instruction set may be in the form of a software program. Software can be in various forms such as system software or application software. Additionally, the software may be in the form of a collection of separate programs, a subset of a program within a larger program, or a part of a program. Software may also include modular programming in the form of object-oriented programming. Processing of input data by the processing machine may occur in response to user commands, or in response to the results of previous processing, or in response to a request made by another processing machine.

[00038] The diagrams of embodiments herein may illustrate one or more control or processing units, such as the asymmetry detection unit 118. It should be understood that the processing or control units may represent circuits, sets of circuits, or parts thereof that may be implemented as hardware with associated instructions (e.g., software stored on a tangible, non-transitory, computer-readable storage medium such as a computer hard drive, ROM, RAM, or similar) that performs the described operations here. The hardware may include a set of hard-wired state machine circuits to perform the functions described herein. Optionally, the hardware may include electronic circuits that include and/or are connected to one or more logic-based devices, such as microprocessors, processors, controllers, or the like. Optionally, the asymmetry detection unit 118 may represent a set of processing circuits such as one or more of a field programmable gate assembly (FPGA), application specific integrated circuit (ASIC), microprocessors, and/or the like. Circuits in various embodiments may be configured to execute one or more algorithms to perform the functions described herein. One or more algorithms may include aspects of the embodiments described herein, whether or not expressly identified in a flow chart or method.

[00039] As used herein, the terms "software" and "firmware" are interchangeable, and include any computer program stored in memory for execution by a computer, including RAM memory, ROM memory, EPROM memory, EEPROM memory, and RAM memory non-volatile (NVRAM). The above memory types are illustrative only, and therefore not limiting as to the type of memory usable for storing a computer program.

[00040] Figure 2 is a diagrammatic representation of a side perspective view of a flap support assembly 112, in accordance with an embodiment of the present description. For clarity, most of the flap 102 is not illustrated in Figure 2. The flap support assembly 112 is an example of any of the flap support assemblies 112a, 112b, 112c and 112d illustrated in Figure 1. While the flap support assembly 112 is illustrated coupled to the wing 104 and the flap 102, it should be understood that the flap support assembly 112 may be coupled to the wing 110 and the flap 108.

[00041] The flap support assembly 112 includes a support 200 that is attached to the wing 104. The support 200 is an example of a fixed portion that attaches to the wing 104. Optionally, the fixed part may be or include one or more supports , walls, beams, stringers and/or similar materials of different shapes and sizes than those illustrated. A proximal end 202 of the strut 200 is attached to a spar 204 of the wing 104, while an outer cover liner 206 is secured over at least a portion of a top 208 of the strut 200, and a lower cover liner 210 is secured over the at least one part of a bottom 212 of the support 200. For clarity, only a part of the wing 104 is illustrated. For example, in order to illustrate support 200, portions of cover shells 206 and 210 are not illustrated.

[00042] A distal end 214 of bracket 200 includes one or more brackets 216 that rotatably retain alternating hinged elements 218 (such as brackets, rods, cylinders, shafts and/or the like) extending outwardly from a proximal end lower surface 220 of a carrier accessory 222. The flap 102 is secured over an upper surface 224 of the carrying accessory 222. The carrying accessory 222 is an example of a movable part that is movably coupled to the fixed part, such as the support 200. Optionally, the movable part may be or include one or more supports, walls, beams, stringers and/or the like of different shapes and sizes in addition to those illustrated. For clarity, only a portion of the flap 102 is illustrated. In particular, only one front nose 103 of flap 102 is illustrated in Figure 2.

[00043] Opposing projections 226 extend upwardly from an upper proximal end 228 of the carrier accessory 222. Opposing projections 226 securely retain a bracket 230 that rotatably couples to a distal end 231 of a connection 232. An opposing end 233 of link 232 is coupled to a drive arm 234 that is movably attached to bracket 200. Drive 114, such as a geared rotary drive, is operatively coupled to drive arm 234.

[00044] Pressure detector 116 is attached to port 232. Pressure detector 116 is configured to detect hydraulic fluid pressure within port 232.

[00045] The drive arm 234, the link 232, and the hinged elements 218 retained within the supports 216 cooperate to provide a four-bus connection. The geometric axis of rotation of the drive arm 234 represents point A, the geometric axis of rotation of the articulated elements 218 within the supports 216 represents point B, the connection of the end 231 of the connection 232 with the supports 230 represents point C, while the connection of end 233 of link 232 with drive arm 234 represents point D.

[00046] In operation, the driver 114 rotates the drive arm 234. The rotation of the drive arm 234 pushes or pulls the link 232. The movement (e.g., pushing or retracting) pushes or pulls the transport accessory 222. The transport accessory 222 rotates about point B with respect to the support 200. In this way, the flap 102 can be actuated between the extended and retracted positions.

[00047] Figure 3 is a diagrammatic representation of a side cross-sectional view of the connection 232 of the flap support assembly 112, in accordance with an embodiment of the present description. The connection 232 includes a main body 300 that includes a coupling 302 that rotatably couples the projections 226 (illustrated in Figure 2) of the transport accessory 222 (illustrated in Figure 2), such as through a spherical support 230. The shaft geometric rotation 303 of support 230 represents point C, as described above. Optionally, the coupling 302 can be rotatably coupled to the drive arm 234 (illustrated in figure 2), in which case the support 230 would represent point D.

[00048] The main body 300 also includes a cylinder 304 that extends distally away from the coupling 302. The cylinder 304 defines an internal chamber 306 within which a piston head 308 of a piston 309 is positioned. The piston head 308 includes one or more sealing elements 310 (such as O-rings, gaskets, or the like) that sealably engage an internal surface 313 of the cylinder 304 that defines the internal chamber 306.

[00049] A hydraulic fluid chamber 314 is positioned between the piston head 308 and an end wall 316 of the cylinder 304 that is proximate to the coupling 302. The hydraulic fluid chamber 314 holds a hydraulic fluid 318, such as grease, oil incompressible, or similar. In at least one embodiment, hydraulic fluid 318 is an incompressible soap-based lithium grease.

[00050] A piston rod 320 of the piston 309 extends linearly away from the piston head 308 from a surface 322 that is opposite the hydraulic fluid chamber 314. An opposite end (not shown) of the piston rod 320 couples to the drive arm 234 (illustrated in figure 2). A circumferential gland 324 extends around an outer circumferential portion of the piston rod 320. The gland 324 is held in place by a shear wire 326 and a key nut 328, thereby preventing the piston from 309 further moves in the direction of arrow 330 when the surface 322 of the piston head 308 abuts a proximal surface 332 of the gland 324. Alternatively, the gland 324 may be secured to the cylinder 304 through various other interfaces, such as threaded interfaces, fasteners and/or similar. As noted above, a compressive force in the direction of arrow 330 exerted by a flap forces the piston head 308 against the proximal surface 332 of the gland 324.

[00051] A fluid channel 334 is formed through a portion of the cylinder 304 and fluid couples to the hydraulic fluid chamber 314. The fluid channel 334 also fluid couples an internal cavity 336 of the pressure detector 116. In this way, the fluid channel 334 fluidly connects the hydraulic fluid chamber 314 to the internal cavity 336 of the pressure detector 116.

[00052] A fluid fitting 340 may extend through a portion of the cylinder 304. The fluid fitting 340 may be a valve that couples fluid to the hydraulic fluid chamber 314. In at least one other embodiment, the fluid fitting 340 may be a cap, plug, or the like that secures within an alternating channel formed through cylinder 304. Fluid fitting 340 allows fluid to enter hydraulic fluid chamber 314.

[00053] With reference to figures 1 to 3, during flight, a load on connection 232 is in compression. That is, the air load exerted within the flap 102 tends to retract the flap 102, thereby exerting a compressive force in the direction of arrow 330 away from the coupling 302 and into the connection 232. The compressive force exerted on the direction of arrow 338 in the direction of coupling 302 forces the piston head 308 away from the surface 332 of the gland 324. The compression force is correlated with a fluid pressure of the hydraulic fluid 318 within the hydraulic fluid chamber 314. When the assembly of flap support 112 is securely coupled to wing 104 and flap 102, a known fluid pressure of hydraulic fluid 318 is detected by pressure detector 116. For example, when piston head 308 is forced away from the surface 332 of the gland 324, a fluid pressure that correlates with a secure connection of the flap 102 to the wing 104 through the flap support assembly 112 exists. Notably, the air charge in the flap support assembly 112 is carried, in compression, from the distal end (not shown) of the piston rod 320 through the hydraulic fluid 318 and into the cylinder 304. The hydraulic fluid 318 provides a portion of the charging path. The asymmetry detection unit 118 receives the pressure signal from the pressure detector 116 and determines that the flap 102 is securely and operably connected to the wing 104 via the flap support assembly 112. In at least one embodiment, when the asymmetry detection unit 118 does not receive any pressure signal from the pressure detector 116 (such as when the pressure detector 116 is a switch, and a signal is received only after a change of state of the switch), the detection unit 118 asymmetry sensor 118 determines that the flap 102 is safely and operably connected to the wings 104 via the flap support assembly 112. In at least one embodiment, the asymmetry detection unit 118 may compare the pressure signal received by the detector pressure 116 with a predefined acceptable range. If the pressure signal is within the acceptable range, then the asymmetry detection unit 118 determines that the flap 102 is securely and operably connected to the wing 104.

[00054] If, however, the flap 102 disconnects from a secure and operational connection with the wing 104, such as if the connection 232 disconnects from the transport accessory 222 and/or support 200, the compression force in the direction of the arrow 338 is reduced, and the piston 309 slides in a direction opposite to that denoted by arrow 330. As the piston 309 moves back linearly within the cylinder 304 in the direction of arrow 330, the piston head 308 slides in the direction of the proximal surface 332 of gland 324, reducing the force on the incompressible hydraulic fluid 318, which then passes into fluid channel 334 and cavity 336, thereby changing the volume of hydraulic fluid 318 within cavity 336. fluid pressure change through the hydraulic fluid 318 entering the cavity 336, and sends the change in pressure as a pressure signal, which is received by the asymmetry detection unit 118. If the pressure change exceeds a predetermined limit (such as an asymmetry threshold representing a particular difference between the pressure signals of two different connections 232 coupled to a different flap or flaps), the asymmetry detection unit 118 determines that flap asymmetry is present. At this point, the asymmetry detection unit 118 sends an asymmetry alert to a computer, workstation, portable device, or the like on board the aircraft 106 to alert flight personnel to the asymmetry condition.

[00055] While connection 232 is illustrated as having a single hydraulic fluid chamber 314, an additional hydraulic fluid chamber may be positioned on an opposite side of the piston head 308, which allows determination of stress loads on connection 232. In this connection In one embodiment, the pressure detector 116 or another pressure detector may be in fluid communication with the additional hydraulic fluid chamber. The asymmetry detection unit 118 can determine the asymmetry conditions based on pressure signals based on the hydraulic fluid pressure within each of the hydraulic fluid chambers.

[00056] As described above, embodiments of the present description provide a system and method for detecting flap asymmetry of an aircraft wing. In at least one embodiment, the method includes configuring the connection 232 to include the cylinder 304 and the piston head 308. The hydraulic fluid chamber 314 is filled with hydraulic fluid 318. The piston 309 is coupled to the transport accessory 222 and to the support 200. As such, the load on the flap 102 is directly transmitted to the piston 309. The pressure detector 116 detects a pressure of hydraulic fluid 318 within the hydraulic fluid chamber 314. The asymmetry detection unit 118 compares the pressure detection of hydraulic fluid 318 within the hydraulic fluid chamber 314 with a previously measured non-free rotation condition of the flap 102, or with the hydraulic fluid fluid pressure of a different connection 232 coupled to the same flap 102 or another flap 108 of the aircraft 106. When the asymmetry detection unit 118 detects a variation in fluid pressure that exceeds a predefined threshold, the asymmetry detection unit 118 determines that an asymmetry condition is present and sends an alert signal to personnel on board the aircraft.

[00057] When the link 232 decouples from the transport accessory 222 or the support 200, the normal compression force of the flap 102 is no longer translated from the flap 102 into the link 232. Therefore, the piston head 308 moves back into the cylinder 304 in the direction of arrow 330, which does not additionally force hydraulic fluid 318 into the pressure detector 116, thereby reducing the fluid pressure. The change in fluid pressure is sent as a pressure signal to the asymmetry detection unit 118, which indirectly determines the actual load on the flap support 102 by analyzing the fluid pressure signal which is indicative of the fluid pressure of the flap. hydraulic fluid 318 within the hydraulic fluid chamber 314. When the fluid pressure within the hydraulic chamber 312 is compared with the other strut on the same flap, or a mirror-image strut on the other wing, unexpected excursions in the load (high, low or none) can be interpreted as an asymmetry event.

[00058] In at least one embodiment, the available time of the cylinder 304 is limited so that in the event of fluid loss, the piston head 308 bottoms out on the end wall 316 and provides a suitable load path.

[00059] The pressure detector 116 can be checked on the ground during maintenance by pressurizing the pressure detector 116 through the fluid accessory 340, for example. For example, fluid may enter the hydraulic fluid chamber 314 through the fluid fitting 340 and pressure signals sent by the pressure detector 116 may be monitored to ensure that the pressure signals are commensurate with the additional fluid pressure caused by the volume of increasing fluid. After the test, the internal pressure can be relieved. As such, the fluid accessory 340 allows the pressure detector 116 to be tested to ensure proper operation.

[00060] Figure 4 is a diagrammatic representation of a top plan view of aircraft 106, according to an embodiment of the present description. The aircraft 106 includes a fuselage 107 and wings 104 and 110 extending from the respective right and left sides of the fuselage 107. The wings 104 and 110 include extendable flaps 102 and 108 that are configured to increase dredging or lift when extended to from a trailing edge of wings 104 and 110. Flaps 102 and 108 are part of a high-lift system implemented on aircraft 106. Although one flap is illustrated on each wing 104 and 110, it should be understood that multiple flaps can be installed on each of the wings 104 and 110.

[00061] Figure 5 illustrates a flowchart of a method for detecting flap asymmetry of one or more wings 104 or 110 of an aircraft 106, according to an embodiment of the present description. Referring to Figures 1 to 5, the method begins at 400, where the asymmetry detection unit 118 monitors pressure signals received from a plurality of pressure detectors 116 coupled to the flap support assemblies 112 of the aircraft 106. In 402, the asymmetry detection unit 118 receives a first pressure signal (indicative of hydraulic fluid pressure) from a first pressure detector 116 coupled to a first connection 232 of a first flap support assembly 112 coupled to a first flap 102. At 404, the asymmetry detection unit 118 receives a second pressure signal from a second pressure detector 116 coupled to a second link 232 of a second flap support assembly 112 coupled to the first flap 102 or a second flap 108. Steps 402 and 404 may occur simultaneously, or in a skewed manner. In at least one embodiment, step 402 may occur before or after step 404.

[00062] At 406, the asymmetry detection unit 118 compares the first and second received pressure signals. At 408, the asymmetry detection unit 118 determines whether there is a difference between the first and second pressure signals. If not, the method proceeds to 410, where the asymmetry detection unit 118 determines that the flaps 102 and 108 are securely coupled to the wings 104 and 110 via the flap support assemblies 112. The method then returns to 400.

[00063] If, however, there is a difference between the first and second pressure signals, the method proceeds from 408 to 412, where the asymmetry detection unit 118 determines whether the difference exceeds a predefined asymmetry threshold. If the difference does not exceed the asymmetry threshold, the method proceeds to 410 and then back to 400.

[00064] If, however, the difference does not exceed the asymmetry threshold at 412, the method proceeds to 414, where the asymmetry detection unit 118 determines that a flap asymmetry condition exists in at least one of the flaps 102 or 108 is present. Then, at 416, the asymmetry detection unit 118 sends a flap asymmetry alert 416 to the aircraft and/or maintenance personnel to check the flaps 102 and 108.

[00065] As another example, if a received pressure signal is relatively low compared to an expected value for a specific flight condition, the asymmetry detection unit 118 may determine that a disconnection in the load path exists. Similarly, if the pressure signal is greater than the expected value, the asymmetry detection unit 118 may determine that an opposing flap support is carrying little or no load, or that an energized asymmetry due to an obstruction is in effect. progress. In short, pressure signal values allow for sophisticated monitoring of the health of flap support load paths.

[00066] As described above, embodiments of the present description provide systems and methods for efficient and effective detection of aircraft wing flap asymmetry. Embodiments of the present disclosure provide systems and methods for quickly, accurately and reliably detecting aircraft wing flap asymmetry.

[00067] As used herein, a structure, limitation or element that is "configured to" perform a task or operation is particularly formed, constructed or structurally adapted in a manner corresponding to the task or operation. For the sake of clarity and to avoid doubt, an object that is merely capable of being modified to perform the task or operation is not "configured to" perform the task or operation as used herein.

[00068] It should be understood that the above description should be illustrative, and not restrictive. For example, the embodiments described above (and/or aspects thereof) may be used in combination with one another. Additionally, many modifications can be made to adapt a particular situation or material to the teachings of the various embodiments of the description without departing from their scope. While the dimensions and types of materials described herein shall define the parameters of various embodiments of the description, the embodiments are in no way limiting and are illustrative embodiments. Many other embodiments will be apparent to those skilled in the art upon review of the above description. The scope of the various embodiments of the description must therefore be determined with reference to the appended claims, together with the full scope of equivalences to which such claims are entitled. In the appended claims, the terms "including" and "wherein" are used as plain English equivalents of the respective terms "comprising" and "wherein". Furthermore, the terms "first", "second" and "third", etc. they are used merely as labels, and should not impose numerical requirements on their objects. Additionally, the following claim limitations are not written in a means-plus-function format and should not be construed in reliance on 35 U.S.C. §112(f), unless and until such claim limitations expressly utilize the phrase "means for" followed by a statement of lack of function of the additional structure.

[00069] Additionally, the description comprises modalities according to the following clauses:

[00070] Clause 1. A flap asymmetry detection system that is configured to detect flap asymmetry of one or more flaps movably attached to one or more wings of an aircraft, the flap asymmetry detection system comprising:

[00071] a flap support assembly that couples a flap to a wing, the flap support assembly including:

[00072] a fixed part that is configured to attach to the wing;

[00073] a movable part that is movably coupled to the fixed part, where the movable part is configured to securely support the flap;

[00074] a connection movably coupled to the fixed part and the movable part, wherein the connection includes: (a) a cylinder defining an internal chamber including a hydraulic fluid chamber; (b) a piston having a piston head within the inner chamber; and (c) hydraulic fluid retained within the hydraulic fluid chamber; It is

[00075] a pressure detector fluid-coupled to the hydraulic fluid chamber, wherein the pressure detector is configured to detect a fluid pressure of the hydraulic fluid pressure within the hydraulic fluid chamber, where the fluid pressure detected by the pressure detector pressure is used to determine the existence of flap asymmetry.

[00076] Clause 2. The flap asymmetry detection system according to Clause 1, further comprising a flap asymmetry detection unit in communication with the pressure detector, wherein the flap asymmetry detection unit receives a pressure signal indicative of fluid pressure from the pressure detector, and wherein the flap asymmetry detection unit determines the existence of flap asymmetry through an analysis of the pressure signal.

[00077] Clause 3. The flap asymmetry detection system according to Clause 2, in which the flap asymmetry detection unit is configured to compare the pressure signal with another pressure signal sent from another detector pressure gauge coupled to another flap support assembly that is coupled to the flap or another flap in order to determine the existence of flap asymmetry.

[00078] Clause 4. The flap asymmetry detection system according to any of Clauses 2 and 3, in which the flap asymmetry detection unit sends a flap asymmetry warning signal after determining that flap asymmetry exists.

[00079] Clause 5. The flap asymmetry detection system according to any one of Clauses 1 to 4, in which the fixed part comprises a bracket that is configured to attach to the wing.

[00080] Clause 6. The flap asymmetry detection system according to any one of Clauses 1 to 5, in which the movable part comprises a transport accessory that is movably coupled to the fixed part.

[00081] Clause 7. The flap asymmetry detection system according to any one of Clauses 1 to 6, in which the pressure detector comprises a pressure switch.

[00082] Clause 8. The flap asymmetry detection system according to any one of Clauses 1 to 7, in which the pressure detector comprises a pressure sensor.

[00083] Clause 9. The flap asymmetry detection system according to any one of Clauses 1 to 8, further comprising a fluid accessory coupled to the cylinder, wherein the fluid accessory is configured to allow fluid to enter in the hydraulic fluid chamber, and where the fluid accessory is configured to permit testing of the pressure detector.

[00084] Clause 10. The flap asymmetry detection system according to any one of Clauses 1 to 9, in which the hydraulic fluid is incompressible grease.

[00085] Clause 11. A flap asymmetry detection method that is configured to detect flap asymmetry of one or more flaps movably attached to one or more wings of an aircraft, the flap asymmetry detection method comprising :

[00086] attaching a fixed portion of a flap support assembly to a wing;

[00087] movable coupling of a movable part of the flap support assembly to the fixed part;

[00088] the secure support of the flap with the movable part;

[00089] the movable coupling of a connection to the fixed part and the movable part;

[00090] positioning a piston head of a piston within an internal chamber of the connection;

[00091] retaining hydraulic fluid within a hydraulic fluid chamber of the inner chamber;

[00092] fluid coupling of a pressure detector to the hydraulic fluid chamber;

[00093] detecting a fluid pressure of the hydraulic fluid within the hydraulic fluid chamber with the pressure detector; It is

[00094] determining the existence of flap asymmetry by detecting fluid pressure.

[00095] Clause 12. The method of detecting flap asymmetry according to Clause 11, further comprising:

[00096] the communicative coupling of a flap asymmetry detection unit with the pressure detector;

[00097] receiving, by the flap asymmetry detection unit, a pressure signal indicative of fluid pressure from the pressure detector; It is

[00098] where the determination comprises the analysis, by the flap asymmetry detection unit, of the pressure signal to determine the existence of the flap asymmetry.

[00099] Clause 13. The method of detecting flap asymmetry according to Clause 12, wherein the analysis comprises comparing the pressure signal with another pressure signal sent from another pressure detector coupled to another flap support assembly. flap that is coupled to the flap or another flap in order to determine the existence of flap asymmetry.

[000100] Clause 14. The method of detecting flap asymmetry, according to any one of clauses 12 to 13, further comprising sending, by the flap asymmetry detection unit, a flap asymmetry warning signal by determining that flap asymmetry exists.

[000101] Clause 15. The method of detecting flap asymmetry, according to any one of Clauses 11 to 14, in which the fixed part comprises a bracket that is configured to attach to the wing.

[000102] Clause 16. The method of detecting flap asymmetry, according to any one of Clauses 11 to 15, in which the movable part comprises a transport accessory that is movably coupled to the fixed part.

[000103] Clause 17. The method of detecting flap asymmetry, according to any one of Clauses 11 to 16, in which the pressure detector comprises a pressure switch, or a pressure sensor.

[000104] Clause 18. The method of detecting flap asymmetry, in accordance with any of Clauses 11 to 17, further comprising:

[000105] fluid entering the hydraulic fluid chamber accessory through a fluid accessory coupled to a cylinder defining an internal chamber including the hydraulic fluid chamber; It is

[000106] testing the pressure detector based, at least in part, on the input.

[000107] Clause 19. An aircraft, comprising:

[000108] a fuselage;

[000109] a first wing extending outward from the fuselage;

[000110] a first flap movably attached to the first wing;

[000111] a second wing extending outwardly from the fuselage opposite the first wing;

[000112] a second flap movably attached to the first wing; It is

[000113] a flap asymmetry detection system that is configured to detect flap asymmetry of the first and second flaps, the flap asymmetry detection system comprising flap support assemblies that couple to the first and second flaps, where each One of the flap support sets includes:

[000114] a fixed support that is attached to one of the first or second wings;

[000115] a movable transport accessory that is movably coupled to the fixed support, wherein the transport accessory securely supports one of the first or second flap;

[000116] a connection movably coupled to the support and carrying accessory, wherein the connection includes: (a) a cylinder defining an internal chamber including a hydraulic fluid chamber, (b) a piston having a piston head within the internal chamber, and (c) an incompressible hydraulic fluid retained within the hydraulic fluid chamber;

[000117] a pressure detector fluid coupled to the hydraulic fluid chamber, wherein the pressure detector is configured to detect a fluid pressure of hydraulic fluid pressure within the hydraulic fluid chamber where the fluid pressure detected by the pressure detector is used to determine the existence of flap asymmetry of one or both of the first and second flaps; It is

[000118] a fluid fitting coupled to the cylinder, wherein the fluid fitting is configured to allow fluid to enter the hydraulic fluid chamber, and wherein the fluid fitting is configured to allow testing of the pressure detector.

[000119] Clause 20. The aircraft, in accordance with Clause 19, in which the flap asymmetry detection system further comprises a flap asymmetry detection unit in communication with the pressure detector, wherein the flap asymmetry detection unit flap asymmetry receives a pressure signal indicative of fluid pressure from the pressure detector, where the flap asymmetry detection unit determines the existence of the flap asymmetry through an analysis of the pressure signal, where the flap asymmetry detection unit flap asymmetry is configured to compare the pressure signal to another pressure signal sent from another detector coupled to another flap support assembly that is coupled to the flap or another flap in order to determine the existence of flap asymmetry, wherein the flap asymmetry detection unit sends a flap asymmetry warning signal upon determination that flap asymmetry exists.

[000120] This written description uses examples to describe the various embodiments of the description, including the best mode, and also to allow those skilled in the art to practice the various embodiments of the description, including creating and making use of any devices or systems or performing any built-in methods. The patentable scope of the various embodiments of the description is defined by the claims, and may include other examples that occur to those skilled in the art. Such other examples shall be within the scope of the claims 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 with insubstantial differences from the literal language of the claims.

Claims (9)

1. Flap asymmetry detection system (100) that is configured to detect flap asymmetry of one or more flaps (102, 108) movably attached to one or more wings (104, 110) of an aircraft (106) , the flap asymmetry detection system (100) comprising: a flap support assembly (112a, 112b, 112c, 112d) that couples a flap (102, 108) to a wing (104, 110), the flap support assembly flap (112a, 112b, 112c, 112d) including: a fixed part (200) that is configured to attach to the wing (104, 110); a movable part (222) that is movably coupled to the fixed part (200), wherein the movable part (222) is configured to securely support the flap (102, 108); a connection (232) movably coupled to the fixed part (200) and the movable part (222), wherein the connection (232) includes: (a) a cylinder (304) defining an internal chamber (306) including a chamber of hydraulic fluid (314); (b) a piston (309) having a piston head (308) within the internal chamber (306); and (c) hydraulic fluid (318) retained within the hydraulic fluid chamber (314); a pressure detector (116) fluid coupled to the hydraulic fluid chamber (314), wherein the pressure detector (116) is configured to detect a fluid pressure of the hydraulic fluid (318) within the hydraulic fluid chamber (314 ), and the flap asymmetry detection system (100) characterized by the fact that it further comprises: a flap asymmetry detection unit (118) in communication with the pressure detector (116), wherein the detection unit flap asymmetry (118) is configured to receive a pressure signal indicative of fluid pressure from the pressure detector (116), and is configured to determine the existence of flap asymmetry through an analysis of the pressure signal; wherein the asymmetry detection unit (118) is configured to compare the pressure signal to another pressure signal sent by another pressure detector (116) coupled to another flap support assembly (112a, 112b, 112c, 112d) which is coupled to the flap (102, 108) or another flap (102, 108) in order to determine the existence of flap asymmetry; and wherein the asymmetry detection unit (118) is configured to send a flap asymmetry warning signal upon determining that flap asymmetry exists. 2. Flap asymmetry detection system (100), according to claim 1, characterized in that the fixed part (200) comprises a support (200) that is configured to attach to the wing (104, 110). 3. Flap asymmetry detection system (100), according to claim 1 or 2, characterized in that the movable part (222) comprises a transport accessory (222) that is movably coupled to the fixed part ( 200). 4. Flap asymmetry detection system (100), according to any one of claims 1 to 3, characterized in that the pressure detector (116) comprises a pressure switch. 5. Flap asymmetry detection system (100), according to any one of claims 1 to 4, characterized in that the pressure detector (116) comprises a pressure sensor. 6. Flap asymmetry detection system (100), according to any one of claims 1 to 5, characterized in that it further comprises a fluid accessory (340) coupled to the cylinder (304), wherein the fluid fitting (340) is configured to allow fluid to enter the hydraulic fluid chamber (314), and wherein the fluid fitting (340) is configured to allow testing of the pressure detector (116). 7. Flap asymmetry detection system (100), according to any one of claims 1 to 6, characterized by the fact that the hydraulic fluid (318) is incompressible grease. 8. Flap asymmetry detection method (400) which is configured to detect flap asymmetry, using the flap asymmetry detection system (100) as defined in any one of claims 1 to 7, of one or more flaps (102, 108) movably attached to one or more wings (104, 110) of an aircraft (106), the method of detecting flap asymmetry characterized by the fact that it comprises: fixing a fixed part (200) of a flap support assembly (112a, 112b, 112c, 112d) to a wing (104, 110); movably coupling a movable part (222) of the flap support assembly (112a, 112b, 112c, 112d) to the fixed part (200); securely support the flap (102, 108) with the movable part (222); movably coupling a connection (222) to the fixed part (200) and the movable part (222); positioning a piston head (308) of a piston (309) within an internal chamber (306) of the connection (232); retaining hydraulic fluid (318) within a hydraulic fluid chamber (314) of the inner chamber (306); fluidly coupling a pressure detector (116) to the hydraulic fluid chamber (314); detecting a fluid pressure of the hydraulic fluid (318) within the hydraulic fluid chamber (314) with the pressure detector (116); determining the existence of flap asymmetry by detecting fluid pressure, the flap asymmetry detection method (400) characterized by the fact that it further comprises: communicatively coupling an asymmetry detection unit (118) to the flap detector pressure (116); receiving, by the asymmetry detection unit (118), a pressure signal indicative of fluid pressure from the pressure detector (116); analyzing, by the asymmetry detection unit (118), the pressure signal to determine the existence of flap asymmetry, wherein analyzing comprises comparing the pressure signal to another pressure signal sent from another pressure detector (116) coupled to another flap support assembly (112a, 112b, 112c, 112d) that is coupled to the flap (102, 108) or another flap (102, 108) so as to determine the existence of flap asymmetry; and sending, by the asymmetry detection unit (118), a flap asymmetry alert upon determining that flap asymmetry exists. 9. Method of detecting flap asymmetry, according to claim 8, characterized by the fact that it further comprises: introducing fluid into the hydraulic fluid chamber (314) through a fluid accessory (340) coupled to a cylinder ( 304) defining an internal chamber (306) including the hydraulic fluid chamber (314); and testing the pressure detector (116) based, at least in part, on the input.