Patent Description:
A typical airplane includes wings having control surfaces, such as flaps. For example, a wing includes a flap that is moveably connected to a main body.

A flap is typically coupled to a plurality of supports, such as main supports and optionally a mid-idler support between two main supports. The main supports include actuators that are configured to drive motion of the flap between retracted and extended positions, while the mid-idler support typically does not include an actuator.

A jam at a main support normally causes skew in the flap during deployment, with one side of the flap further extended or retracted than the other. Certain known airplanes include skew detection systems, which detect the skew. As another example, an actuator torque limiter stops motion before skew is detected.

However, when an idler support between main supports jams, little to no skew occurs, and the existing skew detection system cannot detect the jam. Instead, such a jam at a mid-idler support can cause the flap to experience a high magnitude of load, nearly instantaneously, as both actuators on either side continue to push at maximum capacity, which can cause damage to structures, such as the supports and/or the flap.

As one possible solution, the flap and idler support can be sized, shaped, and configured to endure such extreme loads and trip a torque brake setting before potentially damaging primary structure. However, such a design likely results in a very large weight penalty.

Certain wings require a mid-idler support for low and high speed deflection control at the inboard flap due to the length and thin nature of the flap. Attempting to design such a wing without a mid-idler support may result in aerodynamic performance penalties due to greater deflections.

In short, certain wings can include supports less susceptible to jamming, but may be too large, bulky, heavy, and/or the like for certain types of aircraft.

<CIT>, in accordance with its abstract, states an accurate and compact flap skew detection system operates independent of the flap-drive system and comprises three major elements; a rotary position sensor located on fixed wing structure; a push-pull link and crank arm to convert translational flap motion into rotary sensed motion at the sensor; and a computer processing means to process the rotational sensed information and to compute a flap skew algorithm. Inter-flap and intra-flap translational motion is sensed and compared using a plurality of rotary sensors. Sensors falling outside of predetermined limits or violating control law rules indicate a non-synchronous or asymmetrical "skewed" condition.

<CIT>, in accordance with its abstract, relates to monitoring of the landing flaps on an airfoil for an aircraft, and to an aircraft having such an airfoil. The airfoil has a wingbox, a support which is mounted relative to the wingbox such that it can rotate with respect to a flap rotation axis, a flap which is attached to the support and rotates with respect to the flap rotation axis during rotation of the support relative to the wingbox, a movement mechanism which is coupled to the support in order to set an angle position of the flap with respect to the wingbox and a measurement apparatus for detection of the angle position of the flap. The measurement apparatus has a rotation sensor, which is arranged on the support, and a four-element coupling transmission which couples the rotation sensor to the movement mechanism.

<CIT>, in accordance with its abstract, states a method for detecting freewheeling skew failures in the wing flaps of an aircraft includes measuring the outputs of flap skew sensors when the aircraft is in flight (IF) and the flaps are extended to a selected position, and when the aircraft is next on the ground (OG) and the flaps are extended to the selected position. The respective differences between the IF and OG outputs of symmetrical pairs of the flap skew sensors are computed, and then the respective difference between the computed IF output difference and the computed OG output difference of each symmetrical pair of the sensors is computed. The computed IF and OG difference of each symmetrical pair of the sensors is then compared with each of predetermined maximum and minimum threshold value to determine whether a freewheeling skew failure exists in any of the flaps of the aircraft.

<CIT>, in accordance with its abstract, states a sensor assembly for detecting movement and a position of a wing flap includes a sensing device that generates a signal corresponding to a position of the flap. The sensor assembly includes a linkage that is attached to the movable flap for mechanically communicating movement of the flap to the sensing device. The linkage includes a first pivot shaft mounted to the flap that is disposed about a first axis and a second pivot shaft attached to the first pivot shaft for movement about a second axis transverse to the first axis.

<CIT>, in accordance with its abstract, states an adjustment system of an aeroplane, having: at least one adjustable flap on each of the wing of an aeroplane, adjustable with an adjustment device, a drive device for purposes of driving the adjustment devices, and a load sensor for purposes of recording the load occurring in the load path between the actuator and the adjustable flap of the respective adjustment device. The load sensor is embodied as a sensor for purposes of measuring the longitudinal force occurring in a drive rod along its longitudinal direction.

A need exists for an efficient and effective system and method for detecting a jam in relation to a support for a flap of a wing of an aircraft. Further, a need exists for a jam detection system for a mid-idler support of a flap of a wing of an aircraft.

There is described herein wing of an aircraft, the wing comprising a flap and a jam detection system. The jam detection system comprises a linkage coupled to the flap and a support of the wing, and a sensor configured to detect a position of at least a portion of the linkage. The sensor is further configured to compare the position of the at least a portion of the linkage to a jam threshold to determine if a jam condition exists. The linkage is further coupled to a carriage moveably coupled to the support. The carriage is coupled to the flap through a link that allows slight relative motion and the sensor is configured to detect the slight relative motion by detecting the position of the at least a portion of the linkage.

In at least one example, the sensor is further configured to output a jam signal in response to the position of the portion of the linkage meeting or exceeding the jam threshold. In response to receiving the jam signal, a control unit is configured to stop one or more actuators that are configured to move the flap between a retracted position and an extended position.

As an example, the support is a mid-idler support between a first main support and a second main support. As a further example, the support is devoid of an actuator.

In at least one example, the sensor is a rotary variable displacement transducer configured to detect an angular position of the at least a portion of the linkage. In at least one other example, the sensor is a linear variable displacement transducer configured to detect a linear position of the at least a portion of the linkage.

In a least one example, the linkage includes a first link arm pivotally coupled to a bracket of the support, a second link arm pivotally coupled to the first link arm, and a third link arm pivotally coupled to the second link arm and the flap. As a further example, the third link arm is coupled to a carriage that is moveably coupled to the support by a spherical bearing. In at least one example, the sensor is configured to detect an angular position of the first link arm.

Certain examples of the present disclosure provide a jam detection method for a flap of a wing of an aircraft. The jam detection method includes detecting, by a sensor configured to detect a position of at least a portion of a linkage coupled to the flap and a support of the wing; and comparing, by the sensor, the position of the least a portion of the linkage to a jam threshold to determine if a jam condition exists.

Certain examples of the present disclosure provide an aircraft including a wing having a flap and a support, and a jam detection system, as described herein.

Examples of the present disclosure provide a jam detection system for flap supports. In at least one example, the jam detection system is configured for a mid-idler support, and includes a sensor such as a rotary or linear variable displacement transducer coupled to a linkage, such as a kinematic four-bar linkage, which includes one or more bars. The system is configured to detect a jam at the support during flap actuation by being mounted to both the flap and a carriage, which are coupled together through a link to allow slight relative motion that can be detected by the sensor. Under normal operation, relative motion between the flap and carriage is minimal and does not trip a predetermined jam detection threshold.

Examples of the present disclosure are configured to detect and annunciate (for example, output a signal indicating) a jam at a support, such as at a flap mid-idler support. Examples of the present disclosure provide systems and methods for reducing induced loads in primary structure (for example, flaps and flap supports) while increasing sensitivity in relation to jam detection.

In at least one example, the sensor is a rotary variable displacement transducer mounted on a kinematic four-bar linkage. The linkage is attached to the carriage using a spherical bearing, and to the flap using a hinge. The carriage and flap are attached to each other with two links, allowing relative deflection which can be sensed by the sensor. The system accurately detects any off-nominal deflection caused by a jam and quickly shuts down the flap actuation prior to the flap and idler developing full combined torque brake load.

In at least one example, the sensor measures the angle of a first link arm. During normal operation, the first link arm moves in one rotational direction. However, when a jam is encountered, the first link arm both reverses the rotational direction and measures a different angle than expected. The sensor detects the rotational difference (such as via an angular difference), thereby detecting when a jam has occurred, and distinguishes a jam scenario from the slight nominal rocking that one or more links experience during normal operation (to avoid falsely tripping the sensor when there is no jam). For a jam during retraction or extension, at any point during the stroke, the first link arm clearly measures and senses the difference.

In some examples, the sensor can be programmed to recognize an expected nominal position based on flap positioning, or it can compare against a counterpart flap on an opposite side of the aircraft. If one track jams, the sensors on opposite sides of the aircraft result in different readings, which may signal that a jam exists.

Additionally, the systems and methods described herein are small and lightweight, with no, minimal, or reduced performance impacts to the aircraft, as compared to prior known solutions. The system can allow the use of a main-auxiliary-main configuration for long and thin flaps on small wing planforms with no, minimal, or reduced performance penalty, and can potentially allow an even longer flap. The system can also be used on a flap main support to quickly detect jams or pin failures on a normal flap carriage.

<FIG> illustrates a schematic block diagram of a jam detection system <NUM> for an aircraft <NUM>, according to an example of the present disclosure. The aircraft <NUM> includes wings, such as the wing <NUM>. The wing <NUM> includes a flap <NUM> and a support <NUM> coupled to the flap <NUM>. In at least one example, the support <NUM> is a mid-idler support. In other examples the support <NUM> is a main support.

The support <NUM> includes a bracket <NUM> having a track <NUM>. A carriage <NUM> having one or more rollers is moveable coupled to the track <NUM>. For example, the one or more rollers are moveably secured to and/or within the track <NUM>.

The jam detection system <NUM> includes a linkage <NUM> coupled to the flap <NUM> and the carriage <NUM> moveably coupled to the support <NUM>. The linkage <NUM> includes one or more bars, arms, rods, and/or the like. A sensor <NUM> is configured to detect a position of the linkage <NUM>, such as in relation to the support <NUM>. In at least one example, the sensor <NUM> is a rotary variable displacement transducer that is configured to detect an angular position of at least a portion of the linkage <NUM>. In other examples, the sensor <NUM> is a linear variable displacement transducer configured to detect a linear position of at least a portion of the linkage <NUM>. In other examples, the sensor <NUM> is an encoder that is configured to detect one or more of an angular position, a linear position, and/or the like of the linkage <NUM>.

The sensor <NUM> is communicatively coupled to a control unit <NUM>, such as through one or more wired or wireless connections. The control unit <NUM> is configured to control operation of the flap <NUM>, such as by controlling motion of the flap <NUM> between a retracted position and extended position. The control unit <NUM> is further in communication with one or more actuators coupled to the flap, such as through one or more wired or wireless connections. For example, the control unit <NUM> is in communication with actuators of main supports coupled to the flap <NUM>. The support <NUM> may or may not include an actuator. For example, the support <NUM> can be a mid-idler support that is devoid of an actuator. Optionally, the support <NUM> can be a main support that includes an actuator.

The control unit <NUM> can be located at various locations of the aircraft <NUM>. For example, the control unit <NUM> can be disposed within the wing <NUM>. In other examples, the control unit <NUM> can be disposed within an actuator coupled to the flap <NUM>. In other examples, the control unit <NUM> can be remote from the wing <NUM>, such as within a fuselage of the aircraft <NUM>.

In operation, the flap <NUM> is moved between a retracted position and an extended position, such as via one or more actuators coupled to the flap <NUM>. As the flap <NUM> moves, the linkage <NUM> moves in response thereto, as the linkage <NUM> is coupled to the support <NUM> and the flap <NUM>. The sensor <NUM> detects the motion of the linkage <NUM>. Data regarding normal motion (that is, expected motion in which there is no jam) of the flap <NUM> is stored in a memory, such a memory of, and/or in communication with, the control unit <NUM>. Normal motion of the flap <NUM> is calibrated with a known motion of the linkage <NUM>. When the sensor <NUM> detects such normal motion (such as less than a predetermined jam threshold, for example, within <NUM>% or less deviation from the predetermined normal motion), the sensor <NUM> refrains from outputting a jam signal to the control unit <NUM>. Also, a pilot may be notified that there has been an anomaly in the flap drive system so proper measures can be taken.

If, however, the sensor <NUM> detects motion of the linkage <NUM> that exceeds the predetermined jam threshold, such as an angular or linear motion of a portion of the linkage <NUM> that exceeds the predetermined jam threshold), the sensor <NUM> outputs a jam signal <NUM> to the control unit <NUM>. The control unit <NUM> receives the jam signal <NUM>. In response to receiving the jam signal <NUM>, the control unit <NUM> ceases motion of the flap <NUM>, such as by ceasing operation of the one or more actuators coupled to the flap <NUM>. In this manner, potential damage to the support <NUM>, the flap <NUM>, or other portions of the wing <NUM> is eliminated, minimized, or otherwise reduced.

As described herein the jam detection system <NUM> for the flap <NUM> of the wing <NUM> of the aircraft <NUM> includes the linkage <NUM> coupled to the flap <NUM> and the carriage <NUM> moveably coupled to the support <NUM> of the wing <NUM>. The sensor <NUM> is configured to detect a position of at least a portion of the linkage <NUM>. The sensor <NUM> is further configured to compare the position of the least a portion of the linkage <NUM> to a jam threshold to determine if a jam condition exists. If the position of the portion of the linkage meets or exceeds the jam threshold, the sensor <NUM> outputs the jam signal to the control unit <NUM>, which stops one or more actuators that are configured to move the flap between a retracted position and an extended position.

As used herein, the term "control unit," "central processing unit," "CPU," "computer," or 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 circuit or processor including hardware, software, or a combination thereof capable of executing the functions described herein. Such are exemplary only, and are thus not intended to limit in any way the definition and/or meaning of such terms. For example, the control unit <NUM> may be or include one or more processors that are configured to control operation, as described herein.

The control unit <NUM> is configured to execute a set of instructions that are stored in one or more data storage units or elements (such as one or more memories), in order to process data. For example, the control unit <NUM> may include or be coupled to one or more memories. The data storage units may also store data or other information as desired or needed. The data storage units may be in the form of an information source or a physical memory element within a processing machine.

The set of instructions may include various commands that instruct the control unit <NUM> as a processing machine to perform specific operations such as the methods and processes of the various examples 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. Further, the software may be in the form of a collection of separate programs, a program subset 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 processing machine may be in response to user commands, or in response to results of previous processing, or in response to a request made by another processing machine.

The diagrams of examples herein may illustrate one or more control or processing units, such as the control unit <NUM>. It is to be understood that the processing or control units may represent circuits, circuitry, or portions thereof that 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, or the like) that perform the operations described herein. The hardware may include state machine circuitry hardwired 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 control unit <NUM> may represent processing circuitry such as one or more of a field programmable gate array (FPGA), application specific integrated circuit (ASIC), microprocessor(s), and/or the like. The circuits in various examples may be configured to execute one or more algorithms to perform functions described herein. The one or more algorithms may include features of examples disclosed herein, whether or not expressly identified in a flowchart or a method.

<FIG> illustrates a front perspective view of an aircraft <NUM>, according to an example of the present disclosure. The aircraft <NUM> includes a propulsion system <NUM> that can include two turbofan engines <NUM>, for example. Optionally, the propulsion system <NUM> may include more engines <NUM> than shown. The engines <NUM> may be carried by wings <NUM> of the aircraft <NUM>. In other examples, the engines <NUM> may be carried by a fuselage <NUM> and/or an empennage <NUM>. The empennage <NUM> may also support horizontal stabilizers <NUM> and a vertical stabilizer <NUM>. The fuselage <NUM> of the aircraft <NUM> defines an internal cabin, which may include a cockpit <NUM>, one or more work sections (for example, galleys, personnel carry-on baggage areas, and the like), one or more passenger sections (for example, first class, business class, and coach sections), and/or the like.

The aircraft <NUM> as shown in <FIG> is merely exemplary. The aircraft <NUM> can be sized, shaped, and configured differently than shown.

<FIG> illustrates a top plan view of a portion of a wing <NUM>, according to an example of the present disclosure. The wing <NUM> includes a main body <NUM>, and the flap <NUM> moveably coupled to the main body <NUM>. In at least one example, the flap <NUM> is an inboard flap. Optionally, the flap <NUM> can be an outboard flap.

The flap <NUM> is coupled to the main body <NUM> through a plurality of supports 108a, 108b, and 108c. In some examples, the support 108a is a first (for example, an outboard) main support, the support 108b is a mid-idler support, and the support 108c is a second (for example, an inboard) main support. Long, thin flaps (inboard, mid, or outboard) often include a mid-idler support in order to provide full stroke deflection control. In at least one example, each of the supports 108a and 108c includes an actuator, and the support 108b is devoid of an actuator. Alternatively, the support 108b can include an actuator. Referring to <FIG>, the jam detection system <NUM> is coupled to one of the supports 108a, 108b, or 108c. For example, the jam detection system <NUM> is coupled to the support 108b. In at least one other example, a jam detection system <NUM> can be coupled to each of two or more of the supports 108a, 108b, and 108c. For example, a jam detection system <NUM> can be coupled to each of the supports 108a, 108b, and 108c.

<FIG> illustrates a lateral view of the support 108a coupled to the flap <NUM>, according to an example of the present disclosure. The support 108c can be coupled to the flap <NUM> similar as shown in <FIG>.

The support 108c includes a bracket <NUM> that is secured (for example, fixed in relation to) the main body <NUM> (shown in <FIG>). The bracket <NUM> includes a track <NUM>. A carriage <NUM> includes one or more rollers <NUM> moveably secured within the track <NUM>. The carriage <NUM> also includes a pivot member <NUM> (such as an axle, roller, and/or the like) that is moveably coupled to an actuator <NUM>. The carriage <NUM> is further pivotally coupled to an underside <NUM> of the flap <NUM>, such as through one or more pivot members, hinges, and/or the like.

Referring to <FIG>, the actuator <NUM> of the support 108a (and optionally, the support 108c) drives motion of the flap <NUM> between a retracted position and an extended position. The control unit <NUM> controls operation of the actuator <NUM> to drive motion of the flap <NUM>.

<FIG> illustrates a lateral view of the jam detection system <NUM> coupled to a support <NUM> and a flap <NUM> in a retracted position, according to an example of the present disclosure. The support <NUM> can be one of the supports 108a, 108b, and 108c, shown in <FIG>. For example, the support <NUM> is the support 108b, which is a mid-idler support that is devoid of an actuator.

The carriage <NUM> includes a housing <NUM> including rollers <NUM> moveably secured within the track <NUM>, which includes a defined range between a fore stop <NUM> and an aft end <NUM>. Pivot hinges <NUM> extend upwardly from the housing <NUM> and pivotally couple to reciprocal pivot hinges <NUM> of the flap <NUM> through pivot arms <NUM>. The carriage <NUM> can pivotally couple to the flap <NUM> through one or more pivot hinges <NUM> and pivot arms <NUM> than shown.

As noted, the jam detection system <NUM> includes the linkage <NUM>. In at least one example, the linkage <NUM> includes a first link arm <NUM> having a first end <NUM> and a second end <NUM>. The first link arm <NUM> can be a linear rod, beam, column, or the like. The first end <NUM> is pivotally coupled to a fixed portion of the bracket <NUM>, such as a securing member <NUM> (for example, a fin, bracket, prong, body portion, or the like of the bracket <NUM>). The first end <NUM> is pivotally coupled to the bracket <NUM>, such as through a pivot axle, pin, or the like.

The second end <NUM> of the first link arm <NUM> is pivotally coupled to a first end <NUM> of second link arm <NUM>. The second link arm <NUM> can be a linear rod, beam, column, or the like. The second link arm <NUM> includes a second end <NUM> that is pivotally coupled to a first end <NUM> of a third link arm <NUM>, which can also be a linear rod, beam, column, or the like. The third link arm <NUM> includes an intermediate body <NUM> between the first end <NUM> and a second end <NUM>. The intermediate body <NUM> passes through a spherical bearing <NUM> rotatably retained within a ring coupling <NUM> extending outwardly from the housing <NUM> of the carriage <NUM>. The second end <NUM> of the third link arm <NUM> is pivotally coupled to a portion of the flap <NUM>, such as via a fin, bracket, prong, body portion, or the like.

In at least one example, the sensor <NUM> is coupled to the first link arm <NUM>. For example, the sensor <NUM> is coupled between the first end <NUM> of the first link arm <NUM> and the securing member <NUM>. The sensor <NUM> can be secured to the first end <NUM>. Optionally, the sensor <NUM> can be secured to the securing member <NUM>. In at least one other example, the sensor <NUM> can be secured between the first end <NUM> and the second end <NUM> of the first link arm <NUM>.

In at least one example, the sensor <NUM> is a rotary variable displacement transducer that is configured to detect an angular position of the first link arm <NUM> at all points within the range between the retracted position of the flap <NUM>, as shown in <FIG>, and a fully extended position. As such, the sensor <NUM> is configured to detect a position of at least a portion of the linkage <NUM>, and therefore the relative positions of the flap <NUM> and the support <NUM>, throughout a range of motion of the flap <NUM> between the retracted position and the fully extended position.

The sensor <NUM> is configured to distinguish between normal motion of the linkage <NUM> during motion of the flap, and motion that deviates from the normal motion. For example, the sensor <NUM> can be programmed to recognize the normal motion between the retracted position (as shown in <FIG>) and the fully extended position of the flap <NUM>, and deviated motion therefrom, which indicates a jam condition. The sensor <NUM> is calibrated to recognize the normal motion, and identify a deviation from the normal motion. For example, if the angular position of the first link arm <NUM> deviates from a predetermined jam threshold of +/- <NUM> degrees from the calibrated normal motion, the sensor <NUM> outputs the jam signal <NUM> to the control unit <NUM> (shown in <FIG>), which then ceases operation of the one or more actuators that drive motion of the flap <NUM>. Optionally, the predetermined jam threshold can be greater or less than +/- <NUM> degrees. For example, the predetermined jam threshold can be +/- <NUM> degree. In other examples, the predetermined jam threshold can be +/- <NUM> degrees or +/- <NUM> degrees.

As shown and described with respect to <FIG>, the sensor <NUM>, such as rotary variable displacement transducer, is configured to detect an angular position of a portion of the linkage <NUM>, such as an angular position of the first link arm <NUM>, to determine whether or not a jam condition exists. If the angular position of the portion of the linkage <NUM> is less than the predetermined jam threshold, then the sensor <NUM> does not output the jam signal <NUM>. If, however, the angular position of the portion of the linkage <NUM> meets or exceeds the predetermined jam threshold, the sensor <NUM> outputs the jam signal <NUM> to the control unit <NUM>, which stops the actuator(s) <NUM> (shown in <FIG>), thereby preventing or otherwise reducing a potential of damage to the flap <NUM>, the support <NUM>, and/or other portions of the wing <NUM>.

As shown, the sensor <NUM> is configured to detect angular motion of the first link arm <NUM>. Optionally, the sensor <NUM> can be disposed at various other portions of the support <NUM> and/or linkage <NUM>. As another option, the sensor <NUM> can be disposed to detect angular positions of other portions of the linkage <NUM>, such as the second link arm <NUM> or the third link arm <NUM>. In other examples, the sensor <NUM> can be a linear variable displacement transducer configured to detect a linear position of a portion of the linkage <NUM>, such as may be or include a telescoping link arm.

<FIG> illustrates a perspective lateral view of the intermediate body <NUM> of the third link arm <NUM> passing through the spherical bearing <NUM> rotatably retained within a ring coupling <NUM> extending outwardly from the housing <NUM> of the carriage <NUM>. The spherical bearing <NUM> rotatably secures to the ring coupling <NUM>, thereby moveably coupling the third link arm <NUM> to the carriage <NUM>, and allows the third link arm <NUM> to rotate through various degrees of freedom in relation to the carriage <NUM>. Referring to <FIG> and <FIG>, the linkage <NUM> directly couples to the carriage <NUM> through the spherical bearing <NUM>, and indirectly couples to the carriage <NUM> through the second end <NUM> of the third link arm <NUM> pivotally coupling to the flap <NUM>. Alternatively, the third link arm <NUM> may not couple to the carriage <NUM> via the spherical bearing <NUM>.

<FIG> illustrates a lateral view of the jam detection system <NUM> coupled to the support <NUM> and the flap <NUM> in a fully extended position, according to an example of the present disclosure. Referring to <FIG>, <FIG>, and <FIG>, the sensor <NUM> is configured to detect the position (for example, angular position) of at least a portion of the linkage <NUM> through a full range of motion of the flap <NUM> (such as between the retracted position shown in <FIG> and the fully extended position shown in <FIG>) in order to determine the presence of a jam of the flap <NUM>. As described, the sensor <NUM> compares the position of at least a portion of the linkage <NUM> in relation to a jam threshold. If the position of the portion of the linkage <NUM> meets or exceeds the jam threshold, the sensor <NUM> outputs the jam signal <NUM> to the control unit <NUM>, which, in response, stops the actuator(s) <NUM> (shown in <FIG>).

<FIG> show flap motion in nominal conditions. That is, <FIG> show flap motion free of any jams.

<FIG> illustrates a lateral view of the jam detection system <NUM> coupled to the support <NUM> and the flap <NUM> in a first jam condition, according to an example of the present disclosure. <FIG> illustrates a lateral view of the jam detection system <NUM> coupled to the support <NUM> and the flap <NUM> in a first jam condition, according to an example of the present disclosure. The jam condition shown in <FIG> occurs at <NUM>% stroke while the flap is extending. The jam condition shown in <FIG> occurs at <NUM>% stroke while the flap is retracting. <FIG> and <FIG> show examples of jam conditions. It is to be understood that various other jam conditions can exist between the retracted position and the fully extended position. The dashed lines <NUM>' represent the expected position of the linkage <NUM> (as recognized by the sensor <NUM>) during the motion of the flap <NUM>.

Referring to <FIG>, <FIG>, and <FIG>, the sensor <NUM> detects the position of the first link arm <NUM> and compares the position against the expected position <NUM>'. An angular deviation Θ between the first link arm <NUM> at its actual position and the expected position <NUM>' is present. If the angular deviation Θ meets or exceeds the jam threshold, such as shown in <FIG>, the sensor <NUM> outputs the jam signal <NUM>, as described herein.

<FIG> illustrates a lateral view of the jam detection system <NUM> coupled to a support <NUM> and a flap <NUM>, according to an example of the present disclosure. In this and other examples, the sensor <NUM> is a linear variable displacement transducer configured to detect a linear position of a portion of the linkage <NUM>, such as the link arm <NUM>, which is coupled to the support <NUM>. The link arm <NUM> can be a telescoping arm that is configured to retract and extend, thereby changing lengths. The sensor <NUM> detects the changing length of the link arm <NUM> through a range of motion of the flap <NUM> and compares the length to a jam threshold to determine the existence of a jam.

<FIG> illustrates a flow chart of a jam detection method, according to an example of the present disclosure. Referring to <FIG>, at <NUM>, the flap <NUM> is moved, such as by one or more actuators <NUM>, between a retracted position and a fully extended position (for example, from the retracted position to the fully extended position, from the fully extended position to the retracted position, and all points in-between). At <NUM>, the sensor <NUM> detects a position of at least a portion of the linkage <NUM> coupled to the flap <NUM> and the support <NUM>. At <NUM>, the sensor <NUM> determines if the position of the portion of the linkage <NUM> equals or exceeds the predetermined jam threshold (such as by comparing the position to the predetermined jam threshold). If not, the method proceeds to <NUM>, at which the sensor <NUM> refrains from outputting the jam signal <NUM>.

If, however, the position of the portion of the linkage <NUM> equals or exceeds the predetermined jam threshold, the method proceeds from <NUM> to <NUM>, at which the sensor <NUM> outputs the jam signal <NUM> to the control unit <NUM>. In response to receiving the jam signal <NUM>, the control unit <NUM> stops the one or more actuators <NUM>.

As described herein, examples of the present disclosure provide an efficient and effective system and method for detecting a jam in relation to a support for a flap of a wing of an aircraft. Further, examples of the present disclosure provide jam detection systems and methods well-suited for a mid-idler support of a flap of a wing of an aircraft.

It is to be understood that the above description is intended to be illustrative, and not restrictive. For example, the above-described examples (and/or features thereof) can be used in combination with each other. In addition, many modifications can be made to adapt a particular situation or material to the teachings of the various examples of the disclosure without departing from the scope of the claims. While the dimensions and types of materials described herein are intended to define the parameters of the various examples of the disclosure, the examples are by no means limiting and are exemplary. Many other examples will be apparent to those of skill in the art upon reviewing the above description. In the appended claims and the detailed description herein, the terms "including" and "in which" are used as the plain-English equivalents of the respective terms "comprising" and "wherein. " Moreover, the terms "first," "second," and "third," etc. are used merely as labels, and are not intended to impose numerical requirements on their objects.

Claim 1:
A wing (<NUM>) of an aircraft (<NUM>), the wing (<NUM>) comprising:
a flap (<NUM>); and
a jam detection system (<NUM>) comprising:
a linkage (<NUM>) coupled to the flap (<NUM>) and a support (<NUM>) of the wing (<NUM>); and
a sensor (<NUM>) configured to detect a position of at least a portion of the linkage (<NUM>);
wherein:
the sensor (<NUM>) is further configured to compare the position of the at least a portion of the linkage (<NUM>) to a jam threshold to determine if a jam condition exists;
the linkage (<NUM>) is further coupled to a carriage (<NUM>) moveably coupled to the support (<NUM>);
the carriage is coupled to the flap through a link that allows slight relative motion and the sensor is configured to detect the slight relative motion by detecting the position of the at least a portion of the linkage.