Goodrich Corporation

Goodrich Lighting Systems Gmbh

Ami Industries, Inc.

Winslow Marine Products Corporation

Ashish Kumar Agarwal

Poly Puthur John

Chana Kesava Reddy

Christopher L Chapman

Satya Swaroop Panda

Petchi Subramanian

Sreekanth Koti Ananda Rao

Srijith Purushothaman

Vasantha Kumara Jnanegowda

Jeevanandham Masilamani

Harish Venkateshaiah

Aashik Udupi

Poly Purthur John

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.

Stretch sensor assembly and method of assembling stretch sensor assemblies for evacuation system inflatables

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.

Smart landing light deicing using advanced transparent metal mesh conductor

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.

Solenoid operated pressure cartridge for inflation system

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.

De-icing light systems, assemblies, and methods for aircrafts

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.

Smart pressure regulator for emergency evacuation inflation system

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.

Exterior lighting water removal valve

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.

Compressed gas cylinder actuation device

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.

Solenoid valve for inflation system

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.

Pneumatic inflation system

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.

Fire retardant aviation laminate

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.

Fire-resistant aviation laminate

An incombustible, non-telegraphing substrate for facing with a decorative aviation veneer is provided. The incombustible, non-telegraphing substrate comprises a backing layer comprising a polymer resin-impregnated paper and a fire-retardant chemical included in the backing layer and rendering the backing layer incombustible. An aviation panel and a method for installing the incombustible, non-telegraphing substrate in the aviation panel assembly are also provided.

Incombustible, non-telegraphing substrates for aviation panel assemblies and methods for installing the incombustible, non-telegraphing substrate into an aviation panel assembly

A flexible lumbar support for an aircraft seat includes a frame and flexible seat pad connected thereto for supporting a seat user. At least first and second rods are spaced from each other and the frame, extend across and are secured to the seat pad, and define respectively at least first and second control lines about which the seat pad is rotatable. A third rod is spaced from the seat pad, extends across and is secured to the frame, and defines a third control line. At least a first actuator extends between and is attached to the first and third rods. A second actuator extends between and is attached to the second and third rods. The actuators are movable along the frame and pivotable about the third control line for allowing a change of respective positions of the control lines to generate multiple profiles of the flexible lumbar support.

Flexible lumbar support of aircraft seat

A life raft is provided having a base having a top side and a bottom side, one or more buoyancy elements attached to the top side of the base, and a righting-device attached to the bottom side of the base, the righting-device is configured to shift a center of gravity of the life raft. When the life raft is subject to an instability event, the righting-device is configured to provide a shifted center of gravity such that a righting moment is generated to automatically return the life raft to an upright position.

Growing community of inventors

Karnataka, India

Ashish Kumar Agarwal