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EP-4434895-B1 - MONITORING ADAPTABLE SEGMENTS OF AN AIRFOIL

EP4434895B1EP 4434895 B1EP4434895 B1EP 4434895B1EP-4434895-B1

Inventors

  • Lynn, Janning
  • DEHNBOSTEL, Sarah
  • Wyrembek, Jörg
  • Naue, Christoph

Dates

Publication Date
20260506
Application Date
20230323

Claims (14)

  1. A monitoring arrangement (10) for a plurality of adaptable segments of an airfoil, the arrangement comprising: - a plurality of sensor cable segments (12); - a plurality of cable connections (14); and - a signal data processing unit (16); wherein the sensor cable segments are each configured: to be attached between adjacent adaptable segments of the plurality of the adaptable segments; and to detect a spatial relative movement of the adjacent adaptable segments and to generate a signal representing the relative movement; wherein the cable connections are configured to supply the signals of the sensor cable segments to the data processing unit; wherein the data processing unit is configured to determine relative changes in a spatial arrangement of the plurality of adaptable segments based on the supplied signals; and wherein at least a part of the cable connections is provided as interconnecting cable segments (14'), which are configured to be arranged between two sensor cable segments in order to connect successive sensor cable segments for the connection to the data processing unit.
  2. Monitoring arrangement according to claim 1, wherein the plurality of the cable connections is used for connecting the sensor cable segments to the data processing unit; and wherein the cable connections connect the sensor cable segments to a common data bus connection to the data processing unit.
  3. Monitoring arrangement according to claim 1 or 2, wherein the sensor cable segments each comprise a plurality of consecutive sensor units that detect relative movements of determined consecutive points along a longitudinal extension of the sensor cable segments; and wherein the sensor units are configured to detect a relative motion of the two ends of a sensor cable segment.
  4. Monitoring arrangement according to one of the preceding claims, wherein each of the sensor cable segments comprises a first and a second sensor segment arranged in a common cable shielding.
  5. Monitoring arrangement according to one of the preceding claims, wherein the sensor cable segments, and the cable connections provide a linear arrangement configured to be arranged along an adaptable edge of an airfoil.
  6. Monitoring arrangement according to one of the preceding claims, wherein at least a part of the cable connections is provided as a second plurality of second sensor cable segments; and wherein the second sensor cable segments are each configured to be attached to one of the adaptable segments and to detect a spatial deforming of the respective adaptable segment and to generate a second signal representing the spatial deforming of the respective adaptable segment.
  7. An adaptable surface configuration (50) for an airfoil, the configuration comprising: - a plurality of adaptable segments (52) mountable to a support structure of an airfoil; - a mechanism (54) for changing locations or shapes of the adaptable segments in relation to the support structure; and - a monitoring arrangement (10) according to one of the claims 1-6; wherein the sensor cable segments of the monitoring arrangement detect relative movement between adjacent segments of the plurality of the adaptable segments.
  8. An airfoil (100), comprising: - a support structure (102); - an adaptable surface configuration (50) for an airfoil according to claim 7 with a monitoring arrangement (10) according to one of the claims 1-6; wherein the plurality of adaptable segments is mounted to the support structure; and wherein at least a part of the airfoil is adjustable in its aerodynamically effective geometry based on the changes of the sensor cable segments.
  9. Airfoil according to claim 8, wherein a cable connection is provided along each of the adaptable segments.
  10. Airfoil according to claim 8 or 9, wherein the sensor cable segments are attached to adjacent adaptable segments to span a distance between the adjacent adaptable segments of the plurality of the adaptable segments; wherein the sensor cable segments are each configured to detect a spatial relative movement of the adjacent adaptable segments and to generate a signal representing the relative movement; wherein the cable connections each supply the signals of the sensor cable segments to the data processing unit; and wherein the data processing unit determines a deviation of a spatial arrangement of the plurality of adaptable segments based on the supplied signals.
  11. Airfoil according to claim 8, 9 or 10, wherein the adaptable segments are slats (56) arranged along at least a part of a leading edge of the airfoil; wherein the moving mechanism comprises a plurality of actuators for moving the slats between a retracted position and a deployed position; and wherein the monitoring arrangement is a slat skew monitoring system.
  12. Airfoil according to one of the claims 8 to 11, wherein the adaptable segments are flaps (58) arranged in rows or row segments along a trailing edge of the airfoil; wherein the moving mechanism comprises a plurality of actuators for moving the flaps between a retracted position and a deployed position; and wherein the monitoring arrangement is a flap monitoring system.
  13. An aircraft (200), comprising: - a fuselage (202); and - at least one airfoil (100) according to one of the claims 8 to 12 with an adaptable surface configuration (50) for an airfoil according to claim 7 that comprises a monitoring arrangement (10) according to one of the claims 1-6; wherein the at least one airfoil is mounted to the fuselage.
  14. A method (300) for monitoring a plurality of adaptable segments of an airfoil by using the arrangement of one of the claims 1-13, the method comprising the following steps: - detecting (302) spatial relative movements of adjacent adaptable segments of the plurality of adaptable segments with sensor cable segments of a plurality of sensor cable segments that are attached between the adjacent adaptable segments of the plurality of the adaptable segments; - generating (304) signals representing the relative movements; - supplying (306) the signals of the sensor cable segments to the data processing unit with a plurality of cable connections; and - determining (308), based on the supplied signals, relative changes in a spatial arrangement of the plurality of adaptable segments with a signal data processing unit.

Description

FIELD OF THE INVENTION The present invention relates to adaptable segments of an aircraft, like slats or flaps, and relates in particular to a monitoring arrangement for a plurality of adaptable segments of an airfoil, to an adaptable surface configuration for an airfoil, to an airfoil, to an aircraft and to a method for monitoring a plurality of adaptable segments of an airfoil. BACKGROUND OF THE INVENTION For changing flight behavior of an aircraft, e.g. in order to optimize the characteristics for certain flight stages, adaptable segments of an airfoil may be provided on airfoils and other aerodynamic effective surfaces. For example, for operation during a landing phase, slats are provided along leading edges, which slats can be deployed to allow lower speeds for a landing phase. However, monitoring of the proper functioning is required, which may mean extra components leading to higher costs and increase in weight. US 5628477 A, according to its abstract, relates to detecting and signaling a skewing or misalignment of adjacent aircraft leading edge slats is disclosed. A cable is attached to an actuator having a compression spring system and located in an outboard slat. The cable passes through cable guides in several adjacent slats before being attached to an inboard slat. The compression spring system utilizes a dual concentric pair of compression springs for maintaining a tight cable. When a misaligned condition is detected by a proximity switch, the increased cable load will cause the actuator to lock itself in a position out of the range of the proximity sensor. US 5680124 A, according to its abstract, relates to determining whether or not auxiliary airfoils on an aircraft wing are skewed or lost. It employs either of two types of systems and their associated computer monitor and control requirements. One system utilizes a cable and a spring-loaded mechanism with a cable displacement position sensor. The second system utilizes a drive system position sensor, proximity sensors and segmented proximity targets. These two systems are capable of skew and loss detection for adjacent or individual auxiliary airfoil arrangements. A computer electronic unit is used to perform logic functions to verify the authenticity of sensor signals, and, if appropriate, to shut down the drive system and to compute new flight control parameters including those relating to stall speed and the stick shaker, while alerting the flight crew. US 2008 0265090 A1, according to its abstract, relates to monitoring the synchronism of one or more flaps of aircraft wings, wherein the device includes a control cable which is connected with the flaps such that the control cable follows the flap movement. In accordance with the invention, the path of installation of the control cable extends from a first point to a second point, one or both of which are arranged on non-movable structural components of the aircraft wing. US 6382566 B1, according to its abstract, relates to detection of skewing of high lift devices. The invention provides a system to sense the position of the inboard and outboard ends of each flap. This system preferably detects development of a skewed condition and shuts down the flap drive system before unacceptable aerodynamic or structural conditions occur. In one embodiment, a commercial aircraft has two trailing edge flaps on each wing. Each of the four flaps on the airplane is driven by two ballscrews, one near the outboard end and one near the inboard end of each flap. All ballscrews on all flaps are driven synchronously by a mechanical drive system. By comparing the revolutions of the ballscrews, the differential ballscrew travel can be determined. This differential is a direct measure of flap skew. US 2005/0151027 A1, according to its abstract, relates to a drive station that includes two drives connected via drive transmissions to one or more flaps or slats of a flap/slat group. The drives may be mechanically coupled to a rotational shaft, with a shaft brake arranged thereon. Guide transmissions are connected to the shaft and to respective flaps or slats of the flap/slat group. Alternatively, the two drives are not mechanically coupled, but are merely electrically or electronically synchronized. Each flap/slat group can be actuated individually and independently of the other groups by actuation commands provided by a central control unit connected to the drives and to a flight controller. Position sensors provide actual position feedback. Each flap/slat is driven by two transmissions, namely two drive transmissions, or two guide transmissions, or one drive transmission and one guide transmission. A redundant drive path is ensured if a component fails. SUMMARY OF THE INVENTION There may thus be a need for improved monitoring of adaptable segments of an airfoil. The object of the present invention is solved by the subject-matter of the independent claims; further embodiments are incorporated in the dependent claim