Goodrich Corporation

Goodrich Lighting Systems Gmbh

Petchi Subramanian

Ashish Kumar Agarwal

Elangovan Palaniappan

Chana Kesava Reddy

Sreekanth Koti Ananda Rao

Poly Puthur John

Mohinder Saini

Bharath Marappan

Nikhil Anthony Saldanha

Scott A Luobikis

Tony Pope

Jayant V Deshpande

Guruprasad Srikanta Prasad

Jagadish Thammanna

Scott A Loubikis

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

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 releasable restraint may comprise a bracket and a puller removably coupled to the bracket. A first tube portion and a second tube portion may be rotatably coupled to the puller. A torsion spring may be configured to bias the first tube portion in a first circumferential direction and the second tube portion in a second, opposite circumferential direction.

Reusable releasable restraint for evacuation assemblies

An evacuation system health monitoring system for use on an aircraft is disclosed herein. The system comprises a digital pressure sensor, an evacuation system readiness device, and a memory. The digital pressure sensor is in electronic communication with a controller. The system may further comprise a customer system in communication with the controller. The customer system may communicate a pressure data from the digital pressure sensor to a customer device in real-time during an aircraft flight. The evacuation system readiness device may be in electronic communication with the controller. The evacuation system readiness device may be configured to display a visual indication of system readiness based on operations of the controller.

Health monitoring system of an aircraft evacuation system

A self-powered, wireless lighting system for an aircraft evacuation system. The lighting system includes a piezoelectric sensor configured to generate electrical energy under an aircraft evacuation event when the aircraft evacuation system is deployed, and a first light source disposed on the aircraft evacuation system, the first light source configured to provide illumination to the aircraft evacuation system. The piezoelectric sensor is operably connected to the first light source and configured to supply electrical energy to the light source based on vibrations in the evacuation system during deployment of the evacuation system and during use of the evacuation system as passengers evacuate the aircraft.

Energy autonomous aircraft evacuation slide systems and methods

A wireless lighting system for an aircraft evacuation system. The wireless lighting system includes a wireless controller disposed in the aircraft having at least a transmitter configured to communicate an activation under an aircraft evacuation event when the aircraft evacuation system is deployed, and a first light source disposed on the aircraft evacuation system, the first light source configured to provide illumination to the aircraft evacuation system. The wireless lighting system also includes a first energy storage device disposed on the aircraft evacuation system and a first wireless receiver disposed on the aircraft evacuation system and configured to receive the activation signal from the wireless controller. The first wireless receiver is operably connected to the first energy storage device and the first light source and configured to activate the first light source based on the activation signal.

Wireless lighting system for aircraft evacuation systems

A heated inflation system for an inflatable device on an aircraft is provided. The heated inflation system includes an inflation cylinder configured to hold a gas mixture under pressure, a heating element configured to selectively heat the gas mixture, and a temperature sensor configured to sense a temperature of the gas mixture. The heated inflation system also includes a control module coupled to the heating element and the temperature sensor. The control module is configured to regulate heat applied by the heating element to the gas mixture based on a sensed temperature from the temperature sensor.

Growing community of inventors

Bengaluru, India

Petchi Subramanian