Disclosed herein is an apparatus for determining a position of a first part relative to a second part. The first part is movable relative to the second part. The apparatus comprises a magnetic position indicator and a magnetic field sensor. The magnetic position indicator is non-movably fixed to the first part and comprises a plurality of magnetic field sources positioned along a length of the magnetic position indicator. Each magnetic field source of the plurality of magnetic field sources generates a magnetic field having a unique magnetic signature. The magnetic field sensor is non-movably fixed to the second part and configured to detect the unique magnetic signatures of the magnetic fields generated by the plurality of magnetic field sources of the magnetic position indicator.

Disclosed herein is an apparatus for determining a position of a first part relative to a second part. The first part is movable relative to the second part. The apparatus comprises a magnetic position indicator and a magnetic field sensor. The magnetic position indicator is non-movably fixed to the first part and comprises a plurality of magnetic field sources positioned along a length of the magnetic position indicator. Each magnetic field source of the plurality of magnetic field sources generates a magnetic field having a unique magnetic signature. The magnetic field sensor is non-movably fixed to the second part and configured to detect the unique magnetic signatures of the magnetic fields generated by the plurality of magnetic field sources of the magnetic position indicator.

An aircraft assembly may have a drag-inducing discontinuity 112. A seal assembly 101 includes a seal body 110 arranged to fair and/or seal the discontinuity 112; and a sealed chamber 114, wherein the sealed chamber 114 being pressurised such that in response to changes in the ambient pressure relative to the internal pressure of the chamber 114 the sealed chamber 114 alters the behaviour of the seal body 110.

A blade seal for covering an interface between first and second components of an aircraft includes a mounting portion extending in a longitudinal first direction for connection to the first component. A contact portion maintains contact with the second component. A plurality of pockets positioned along the first direction are separated by projections extending in a second direction perpendicular to the length. Each pocket has a variable depth and facing the second component.

A blade seal for covering an interface between first and second components of an aircraft includes a mounting portion extending in a longitudinal first direction for connection to the first component. A contact portion maintains contact with the second component. A plurality of pockets positioned along the first direction are separated by projections extending in a second direction perpendicular to the length. Each pocket has a variable depth and facing the second component.

An aircraft wing system and method comprising: an aircraft wing; an edge device coupled to a leading edge or trailing edge of the aircraft wing; a drive shaft rotatable about its axis; a crank arm, a first end of the crank arm being coupled to the drive shaft, and a second end of the crank arm opposite to the first end being coupled to the edge device; and a gear system (e.g. a strain wave gear system) coupled between the drive shaft and the first end of the crank arm.

An aircraft wing system and method comprising: an aircraft wing; an edge device coupled to a leading edge or trailing edge of the aircraft wing; a drive shaft rotatable about its axis; a crank arm, a first end of the crank arm being coupled to the drive shaft, and a second end of the crank arm opposite to the first end being coupled to the edge device; and a gear system (e.g. a strain wave gear system) coupled between the drive shaft and the first end of the crank arm.

A wing for an aircraft includes a wing structure attachable to a body of an aircraft, at least one high lift body movably supported at the wing structure, a drive unit coupled with the wing structure and the high lift body and adapted to move the high lift body relative to the wing structure in a chordwise direction between a retracted position and an extended position, and a sealing device coupled with the high lift body and the wing structure. The high lift body comprises at least one outer edge facing to the wing structure, which at least one outer edge creates a gap to the wing structure at least in an extended position. The sealing device includes a flexible sealing body, which seals the intermediate space between the high lift body and the wing structure in extended positions of the high lift body.

A wing for an aircraft includes a wing structure attachable to a body of an aircraft, at least one high lift body movably supported at the wing structure, a drive unit coupled with the wing structure and the high lift body and adapted to move the high lift body relative to the wing structure in a chordwise direction between a retracted position and an extended position, and a sealing device coupled with the high lift body and the wing structure. The high lift body comprises at least one outer edge facing to the wing structure, which at least one outer edge creates a gap to the wing structure at least in an extended position. The sealing device includes a flexible sealing body, which seals the intermediate space between the high lift body and the wing structure in extended positions of the high lift body.

An aircraft wing incorporating an active flow control (AFC) device The AFC device comprises a fluid chamber housed in the wing providing a conduit for receiving fluid and accommodating the fluid at elevated pressure. Forward and rearward fluid channels having respective inlets and outlets are also provided, wherein the inlets are in fluid communication with the fluid chamber and the outlets emerge on the upper surface of the wing at or adjacent the leading edge. A valve assembly allows the channels to be opened and closed as desired. During flight, fluid at elevated pressure can be supplied to the fluid chamber and released through either the forward or the rearward fluid channel or both, so as to influence the air flow, e.g., to reduce or increase lift, or to equalize pressure in the air stream direction.