Abstract: A de-icing light assembly may comprise: a housing; a plurality of lights coupled to the housing; a lens assembly coupled to the housing, the lens assembly comprising: a lens material; an indium tin oxide (ITO) film disposed on the lens material; and a silicon oxide coating disposed on the ITO film.

Abstract: A valve arrangement for a pressurized fluid source includes a regulating valve poppet configured to translate along a longitudinal axis of a valve housing, and a linear stepper motor configured to control a position of the regulating valve poppet. The linear stepper motor is controlled by a closed loop control system based upon temperature and pressure feedback signals to actively control the position and stroke rate of the regulating valve poppet.

Abstract: A pressure regulator system is disclosed. The system includes: a valve module; a controller; and a plurality of sensors. The controller is operably coupled to the valve module to adjust outflow of gas from an outlet of the valve module to a plurality of masks in an interior of an aircraft. The plurality of sensors comprises at least one of a pressure sensor and a temperature sensor and the controller is configured to receive feedback of sensed data at the outlet of the valve module about at least outlet pressure and ambient temperature from at least the pressure sensor and the temperature sensor and adjust the outflow of gas from the outlet of the valve module by determining an open-valve time based on the feedback of sensed data received from each sensor.

Abstract: A fluid removal assembly for an aircraft light is provided. The fluid removal assembly includes a condensate removal valve including a housing; a set of helical compression springs; and a stem disposed within the housing. The stem is configured to translate in a first direction responsive to the aircraft being pressurized and a first force, from the pressurization, forcing the stem to translate in the first direction; and translate in a second direction opposite the first direction responsive to the aircraft being depressurized and a second force from the set of helical compression springs forcing the stem to translate in the second direction. The condensate removal valve is configured to: responsive to an aircraft being depressurized, drain a fluid from one or more components of the aircraft light, the aircraft light being installed in the aircraft; and responsive to the aircraft being pressurized, maintain a pressure within the aircraft.

Abstract: An actuator for opening a hermetically sealed cylinder is disclosed herein. The actuator includes an actuation chamber configured to receive pressurized gas, the actuation chamber at least partially defined by a top wall and a bottom wall, a cutter body disposed within the actuation chamber between the top wall and the bottom wall, the cutter body including a top portion and a bottom portion, a cutting edge extending from the bottom portion of the cutter body, and a spring disposed between the top portion of the cutter body and the bottom wall of the actuation chamber.

Abstract: An actuator for opening a hermetically sealed cylinder is disclosed herein. The actuator includes an actuation chamber configured to receive pressurized gas, the actuation chamber at least partially defined by a top wall and a bottom wall, a cutter body disposed within the actuation chamber between the top wall and the bottom wall, the cutter body including a top portion and a bottom portion, a cutting edge extending from the bottom portion of the cutter body, and a spring disposed between the top portion of the cutter body and the bottom wall of the actuation chamber.

Abstract: An inflation valve arrangement includes an actuation cavity housing connected to a pneumatic valve, the actuation cavity housing comprising an actuation cavity and a piston rod extending from the actuation cavity at least partially into a main fluid channel of the pneumatic valve in an initially extended position for securing the pneumatic valve in a closed position. The arrangement further comprises a solenoid actuated pressure cartridge connected to the actuation cavity housing. The solenoid actuated pressure cartridge comprises a self-contained source of actuation gas. In response to the solenoid actuated pressure cartridge being energized, the solenoid operated pressure cartridge is configured to release the actuation gas from the pressure cavity into the actuation cavity, thereby retracting the piston rod into the actuation cavity, and opening the pneumatic valve body to release a source of inflation gas to an inflation device.

Abstract: A stretch senor assembly may comprise a stretch sensor, a first housing and a second housing. The stretch sensor may include a first mounting end, a second mounting end, and a sensing region extending between the first mounting end and the second mounting end. The first housing may define a connector opening and the first mounting end may be located in the first housing. The second housing may be located around the second mounting end.

Abstract: A de-icing light assembly may comprise: a housing; a plurality of lights coupled to the housing; a lens assembly coupled to the housing, the lens assembly comprising: a lens material; an indium tin oxide (ITO) film disposed on the lens material; and a silicon oxide coating disposed on the ITO film.

Abstract: Systems and methods for deicing an aircraft landing light may include a metal mesh conductor coupled to a lens of a landing light. The systems and methods may include a power supply, a temperature sensor, a deicing control unit, an aircraft light having a lens, and a mesh coupled to the lens. The temperature sensor may be a microwave resonator sensor configured to sense the temperature of the landing light and send signals to the deicing control unit. The signals may be configured to instruct the deicing control unit to either apply an electric current to the mesh, or cease applying an electric current to the mesh, depending on the landing light temperatures. The deicing control unit may receive landing pulses from a flight control system. The pulses may indicate that the aircraft is landing or has landed.

Abstract: A valve arrangement for a pressurized fluid source includes a regulating valve poppet configured to translate along a longitudinal axis of a valve housing, and a linear stepper motor configured to control a position of the regulating valve poppet. The linear stepper motor is controlled by a closed loop control system based upon temperature and pressure feedback signals to actively control the position and stroke rate of the regulating valve poppet.

Abstract: A passenger service unit for use in an aircraft cabin includes an output device configured to output information in the aircraft cabin. The passenger service unit further includes a touchless sensor configured to detect a presence of an object in a vicinity of the touchless sensor, and to output a signal for controlling the output device in response to detecting the presence of the object.

Abstract: A gauge device is provided and includes an analog display to signify a measured valued, a motor and worm gear arrangement which is configured to retain a current state of the analog display when de-energized or to change the analog display when energized and a control system. The control system is configured to normally de-energize the motor and worm gear arrangement and to energize the motor and worm gear arrangement only in accordance with a calculated state of the analog display differing from the current state by at least a threshold level.

Abstract: A method of operating an inflation system is provided. The method includes recognizing that the inflation system is activated or actuated by a user, supplying current to an electromagnet of a solenoid valve of the inflation system such that an armature-valve element of the solenoid valve is moved to an open position, wherein movement of the armature valve element to the open position actuates an actuator housing that in turn causes a normally-closed valve element of a valve housing of the inflation system to open, and ceasing current supply to the electromagnet once the actuator housing is actuated.

Abstract: A valve includes a valve body, an inlet in the valve body in fluid communication with the gas and an outlet in the valve body, and a rupture disc in fluid communication with and between the inlet and the outlet that prevents fluid communication between the inlet and the outlet. The valve also includes a piston that is urged by a gas from the gas source to rupture the rupture disc to allow fluid communication between the gas source and the outlet.

Abstract: An aviation laminate includes a plurality of wooden elements, and an adhesive disposed between the plurality of wooden elements, wherein the adhesive includes a thermal filler, wherein the thermal filler is at least one of graphene, hexagonal boron nitride and intumescent powder.

Abstract: An aviation laminate includes an intumescent backer sheet covered by a decorative sheet. The aviation laminate is generally fire-resistant, may be structural, and may be used to construct various components within an aircraft cabin that may be held to government/regulatory fire mitigation requirements.

Abstract: A valve includes a valve body, an inlet in the valve body in fluid communication with the gas and an outlet in the valve body, and a rupture disc in fluid communication with and between the inlet and the outlet that prevents fluid communication between the inlet and the outlet. The valve also includes a piston that is urged by a gas from the gas source to rupture the rupture disc to allow fluid communication between the gas source and the outlet.

Abstract: A method of operating an inflation system is provided. The method includes recognizing that the inflation system is activated or actuated by a user, supplying current to an electromagnet of a solenoid valve of the inflation system such that an armature-valve element of the solenoid valve is moved to an open position, wherein movement of the armature valve element to the open position actuates an actuator housing that in turn causes a normally-closed valve element of a valve housing of the inflation system to open, and ceasing current supply to the electromagnet once the actuator housing is actuated.

Abstract: An aviation laminate includes a plurality of wooden elements, and an adhesive disposed between the plurality of wooden elements, wherein the adhesive includes a thermal filler, wherein the thermal filler is at least one of graphene, hexagonal boron nitride and intumescent powder.