Textron Aviation Inc.

An ice protection system, including a first multifunctional composite (MFC) battery cell disposed at an exterior surface of a vehicle, a second MFC battery cell disposed at the exterior surface, a switching system connected to the first MFC battery cell and the second MFC battery cell, and at least one controller, configured for performing first switching control by controlling the switching system to connect the first MFC battery cell to the second MFC battery cell in an arrangement causing the first MFC battery cell to discharge by charging the second MFC battery cell, where the first MFC battery cell discharging by charging the second MFC battery cell heats the exterior surface and at least one of melts an ice accretion on the exterior surface or prevents accretion of ice on the exterior surface.

A doorway side guide system includes a base mechanically coupled with a bottom portion of a doorway. A mounting member is rotatably coupled to the base via a hinge for rotating between a deployed position and a stowed position. A contact member is mechanically coupled with the mounting member via a pivot such that the contact member is configured to rotate about the pivot. The contact member extends outside of the doorway in the deployed position for guiding cargo through the doorway and for protecting a doorframe of the doorway.

An aircraft rudder control system having one or more rudder pedal adjustment systems, each including a rudder pedal actuatable to control movement of a rudder, and further including a support frame component, a rudder pedal arm, a pin, a pin receiving component, a first lever, a second lever, and/or a solenoid. The rudder pedal arm is rotatably attached to the support frame component and the rudder pedal is attached to the rudder arm. While the pin is received in the pin receiving component, the rudder pedal arm is prevented from rotating. When the pin is withdrawn from the pin receiving component, the rudder pedal arm is freed to be rotatably repositioned by user foot actuation. The first lever can manually actuate the pin into and out of the pin receiving component, and the second lever is operated by the solenoid, actuating the pin when the solenoid is activated and deactivated.

Modular electrical and/or data distribution rail systems include a rail assembly which defines a C-shaped channel track having an elongate front slot, and a plurality of electrical conductors carried by the elongate support structure. A modular connector pod assembly is provided with an H-shaped rear mounting member configured to be operatively connected to the rail assembly for sliding movements within the C-shaped channel track, and a front connector housing attached to the rear mounting member for housing at least one electrical and/or data port The rear mounting member includes an array of spring-biased pin connectors (e.g., so-called “pogo pins”) each establishing electrical contact with a respective one of the electrical conductors carried by the elongate support structure when the rear mounting member is operatively connected to the rail assembly. A temporary structural interface (TSI) module adapted to mount an accessory to the rail assembly may also be provided.

An aircraft monitoring system includes a data collection module configured to collect a video feed of an aircraft interior. The video feed is directed towards a target, and a recognition module is configured to receive the video feed from the data collection module. The recognition module is configured to recognize the target and an interaction directed towards the target by a user. A decision making component is configured to determine an adjustment to an aircraft component based on the recognized target and interaction thereof.

An integrated display device cabinet door includes a cabinet door for supporting a display device. The door includes a device frame which holds the display device in the door and fits between an outer shell and backing panel. A channel is formed into the door, which receives wiring from the display device and provides a path for the wiring to be carried away from the display device and out of the door. The door includes an opening, which exposes the screen of the display device on a façade of the cabinet door.

An aircraft skin alignment system includes at least one support structure to support one or more aircraft skins and one or more assembly tools; the one or more assembly tools having a holding mechanism to releasably engage with a first aircraft skin; a pulling mechanism to apply a pulling force to the first aircraft skin; and an edge locator; the pulling mechanism is to pull the first aircraft skin such that a first edge of the first aircraft skin abuts the edge locator, the edge locator preventing the first edge from being pulled past the edge locator; and one or more tool holes can be drilled into the first aircraft skin such that the one or more tool holes are aligned based on an edge index due to a position of the edge locator.

A control servo for an aircraft engine control system, the control servo broadly comprising a housing, a stepper motor, a drivetrain, an output shaft, and an output lever. The housing includes a drivetrain chamber, a drive opening, and an output opening. The stepper motor includes a drive shaft extending through the drive opening into the drivetrain chamber. The drivetrain is at least partially positioned in the drivetrain chamber. The output shaft extends through the output opening from the drivetrain chamber. The drivetrain drivably connects the drive shaft and output shaft. The output lever includes an output lever arm and a friction interface. The output lever arm has opposing proximal and distal ends and is connected to the output shaft near the proximal end. The friction interface is near the proximal end and configured to be adjusted to set a slip friction threshold between the output lever and the output shaft.

A pneumo-mechanical landing gear deployment system includes a dual-stage handle operatively connected to a pressurized tank, a nose landing gear pneumatically connected to the pressurized tank, and a main landing gear pneumatically connected to the pressurized tank. Actuation of the dual-stage handle to a first position opens the pressurized tank thereby deploying the nose landing gear. Actuation of the dual-stage handle to a second position causes further opening of the pressurized tank thereby deploying the main landing gear. The system may be employed as a backup landing gear deployment system in the case of a primary landing gear system failure.

A window roller shade and dimming pane assembly includes a rigid frame having a first side member on a first side and a second side member on a second side opposite the first side. An outer pane and an inner pane are disposed within the rigid frame with a gap between the outer pane and the inner pane. A roller shade includes a motor for rolling and unrolling the roller shade. A first constant force spring and a second constant force spring are each configured to pull the roller shade downwardly through the gap while the motor is unrolling the roller shade. A dimming film is disposed on the inner pane for dimming light through the inner pane. A window interface is operatively coupled to the inner pane for receiving touch input for controlling the dimming film and the roller shade.