Abstract: A system for releasing a blowout panel and softcover release of an evacuation slide in an aircraft is provided. The system includes a first actuator, a second actuator; and a controller. The controller is configured to receive an indication that an evacuation event has begun; and, responsive to receiving the indication of the evacuation event beginning: send a first signal to the first actuator that magnetizes a first magnetostriction material within the first actuator, thereby releasing the blowout panel of a packboard compartment in which the evacuation slide is present; and send a second signal to the second actuator that magnetizes a second magnetostriction material within the second actuator, thereby releasing a key-loop of lacing associated with the softcover in which the evacuation slide is present in the packboard compartment.

Abstract: A system for controlling in-flight services using gestures is disclosed. The system comprises: a gesture detection device; an actuator; and a controller. The controller is configured to: receive a detected free space gesture from the gesture detection device; compare the detected free space gesture to a plurality of identified free space gestures; responsive to identifying a free space gesture from the plurality of identified free space gestures, identify an associated in-flight service based on the identified free space gesture; and responsive to identifying the associated in-flight service, send a first command to the actuator to perform the associated in-flight service.

Abstract: An electrothermal ice protection system (IPS) installed on an aircraft includes a sensor, a parting strip assembly, and a controller. The sensor monitors a direction of a local incident airflow that is imparted on the sensor. The parting strip assembly is coupled to the critical surface and includes a plurality of heating sections. The controller is in signal communication with the sensor and the parting strip assembly. The controller determines a direction of surface airflow incident on a critical surface of the aircraft based on the local incident airflow and selectively concentrates power to at least one targeted heating section among the plurality of heating sections with respect to non-targeted heating sections among the plurality of heating sections based on the direction of the surface airflow.

Abstract: An aircraft light includes a support board and a supporting profile. The support board supports at least one electric light source, in particular at least one LED. The support board has two lateral edges, which extend in a longitudinal direction of the support board and which are spaced apart from each other in a transverse direction (T) of the support board. The supporting profile comprises a receiving space for receiving and supporting the support board. The receiving space is defined by a base, extending in a longitudinal direction (L) of the supporting profile and in a transverse direction (T) of the supporting profile, and two opposing side walls protruding from the base. The supporting profile further comprises two undercut sections, forming opposing slots in the two opposing side walls that are dimensioned for accommodating a lateral edge of the support board, respectively.

Abstract: Automated control of one or more exterior aircraft lights is presented, for instance exterior aircraft lights that enhance visibility by a pilot and including landing lights, taxi lights, and runway turnoff lights. One aspect of this automated control is that one or more of such exterior aircraft lights may be automatically activated, for instance when the aircraft has at least initiated movement and has not yet reached a certain altitude (e.g., while the aircraft is taxiing on the ground and including during takeoff). Another aspect of this automated control is that a trained image classification model may determine a visibility classification for an image acquired by an exterior aircraft camera, and this visibility classification may be used to automatically control the operation of one of more of such exterior aircraft lights (e.g., an intensity of the light output from such an exterior aircraft light(s)).

Abstract: A method of making an adhesive for an ice protection assembly includes transferring Z-CNTs from a substrate carrier into the adhesive. De-bonding of the adhesive for ice protection assembly inspection or repair or repositioning at initial installation includes heating the Z-CNTs in the adhesive to soften the adhesive and allow for easy removal.

Abstract: A hydraulic fluid system is disclosed herein. The hydraulic fluid system includes a hydraulic motor including an output shaft, a reduction gear box having a first side and an opposing second side, the reduction gear box being coupled to the output shaft at the first side and coupled to a reduction shaft at the second side, and a magneto-rheological fluid brake (MRF) brake coupled to the reduction shaft.

Abstract: A brake system and method of braking for an aircraft are provided. The brake system includes a primary brake control unit and an alternate brake control unit. In response to the primary brake control unit being placed in an active mode, the primary brake control unit is configured to send data on a set of channels to control brake operation of at least one brake, while the alternate brake control unit is configured to monitor brake temperature on another, separate set of channels coupled to at least one brake temperature sensor associated with the at least one brake.

Abstract: A system for controlling tension on textile material used in forming a preform is disclosed herein. The system includes a sensor and a controller, where the controller is configured to: receive a signal, from the sensor, indicative of a compressive force applied by the textile material feeding into the system; determine whether the compressive force is within range of a setpoint of the tension for the textile material; and responsive to the compressive force being outside the range, send a command of at least one of an increase or a decrease of the tension on the textile material.

Abstract: A shaft assembly includes a composite tube and an impact shield. The composite tube has a longitudinal centerline axis and the impact shield may be disposed around the composite tube and may extend along a length of the composite tube. A gap may be defined between the composite tube and the impact shield. Generally, shaft assembly is configured to inhibit impact damage to the composite tube and/or facilitate visual detection of damage from impacts. The shaft assembly may further include a shock absorbing sleeve disposed in the gap between the composite tube and the impact shield.

Abstract: A system is provided for measuring a thickness of a preform material. The system includes a material detection device and a controller, wherein the controller is configured to: receive, from the material detection device, a signal indicating a presence of the preform material; responsive to receiving the signal, receive a first set of measurements along at least a portion of a length of the preform material; convert the first set of measurements into a second set of measurements; and record the second set of measurements.

Abstract: An aircraft actuation system is disclosed that includes a pair of cylinders, a piston movably disposed in each cylinder, and a roller train that extends between the pistons in the two cylinders. A portion of the roller train is disposed beyond the cylinders to engage a pinion. Movement of the pistons in the two cylinders in opposite directions produces a corresponding movement of the roller train to in turn rotate the pinion. The roller train may be maintained in compression between its two ends by fluid pressure exerted on a common face of each of the pistons in the two cylinders. The cylinders may be disposed in non-colinear relation, including in parallel relation to one another. A guide may be used to maintain rollers of the roller train in a proper orientation for entry into a space between an outer race and the pinion.

Abstract: Aircraft headlight includes at least one light source; and a light transmissive cover, at least partially covering the at least one light source. The light transmissive cover includes a first layer made of a first material; a second layer made of a second material, which differs from the first material; and at least one electric heating wire for heating the light transmissive cover by passing an electric current through the electric heating wire. The at least one electric heating wire is embedded into the first layer.

Abstract: A half cap wear clip may comprise: a wear face configured to interface with a torque bar; a first flange disposed on a first side of the wear face and a second flange disposed on a second side of the wear face, the second side opposite the first side; and a deformable feature disposed on a first end of the first flange and the second flange and the wear face, the deformable feature configured to permanently deform a first distance in response to a load on the wear face exceeding a load threshold.

Abstract: An electromechanical actuator includes: an actuator rod housed in an actuator housing; a linear variable differential transformer “LVDT” fixed to the actuator housing; and an anti-rotation component configured to contact the outer surface of said LVDT. The outer surface of the linear variable differential transformer comprises a first anti-rotation surface feature and the anti-rotation component comprises a second anti-rotation surface feature. The first and second anti-rotation features are sized and shaped relative to each other such that, when in contact with each other, they are configured to prevent rotation of the actuator rod in use.

Abstract: A braking system includes a brake stack; a first brake cavity operably coupled to the brake stack, the first brake cavity including a first plurality of brake actuators; a second brake cavity operably coupled to the brake stack, the second brake cavity including a second plurality of brake actuators; and a brake control module, the brake control module being configured to activate either the first plurality of brake actuators or both the first plurality of brake actuators and the second plurality of brake actuators in response to an input brake load.

Abstract: A method of forming a composite component is provided. The method includes locating a fibrous preform, providing a slurry, mixing the slurry with sacrificial fibers, injecting the slurry into the fibrous preform, heating the fibrous preform, forming channels in the fibrous preform, and densifying the fibrous preform. The sacrificial fibers are suspended in the fibrous preform along an injection pathway such that heating the sacrificial fibers forms the channels along the injection pathway as the sacrificial fibers are burned away.

Abstract: A method of forming a dielectric barrier and torque transfer member between a drive shaft and a driven shaft of a torque transfer assembly. The method includes assembling the drive shaft and the driven shaft in axially adjacent relationship to one another, the drive shaft and the driven shaft each having a recess formed therein such that when the shafts are assembled, the recesses cooperate to define a chamber extending across the interface between the drive and driven shaft and into the interior of both the drive and the driven shaft. The method further includes injecting a dielectric adhesive or resin material into the chamber to fill the chamber and to extend across the interface between the drive and the driven shaft, and curing the dielectric material to form a dielectric barrier between and to provide torque transfer between the drive and the driven shaft.

Abstract: An aircraft light comprises a support board; a light source, arranged on the support board; a first optical element, which is at least partially light transmissive, which is arranged over the light source, and which is fixed to the support board; and a second optical element, which is at least partially light transmissive, wherein the first optical element is interposed between the light source and the second optical element. The first optical element has a first engagement portion and the second optical element has a second engagement portion. The first engagement portion and the second engagement portion establish a positive fit between the first optical element and the second optical element. At least a portion of light, which is emitted by the light source in operation, passes through the first optical element and through the second optical element.

Abstract: A double eccentric bushing arrangement comprises a first eccentric bushing comprising a first eccentric aperture, a second eccentric bushing comprising a second eccentric aperture, a fastener, a washer configured to be received around a portion of the second eccentric bushing, and a snap ring configured to be received around a portion of the second eccentric bushing to secure the washer in an installed position. The first eccentric bushing is configured to receive the second eccentric bushing in the first eccentric aperture. The second eccentric bushing is configured to receive the fastener in the second eccentric aperture. The first eccentric bushing is rotatable with respect to the second eccentric bushing to adjust a position of the fastener with respect to an adjacent component to which the fastener is being attached.