Goodrich Corporation

Rosemount Aerospace Limited

B/e Aerospace, Inc.

Simmonds Precision Products, Inc.

Arinc, Inc.

Goodrich Aerospace Services Private Limited

Rameshkumar Balasubramanian

Venkatesan Muthulingam

Sudhendra Nayak

Cal Roeske

Pullaiah Dussa

Naveen Kumar Mallipattana Hiriyannaiah

Michael Anthony Lynch

Sujoy Khanra

Skanda Gopalakrishna

Aaron James Roberts

Joseph T Pesik

Brian Brent Naslund

Frank E Hashberger

Ashutosh Kumar Jha

William Kunik

Aravinda Mahabaleshwara

Rajesh Mohanam

Shad Kish

Sivakumar Dwaraganathan

Mahesh Ainapure

Ashwin Srinivasa

Steve T McQueen

Praveen Valiyaparambil

Michael A Lynch

Naveen Kumar Hiriyannaiah

A vision-based aircraft cabin light monitoring/control system is used to maintain the light intensity level within the aircraft cabin at a desired level. The system uses video cameras to continuously monitor the ambient light entering the passenger cabin windows, analyzes the video stream/feed to identify the light intensity level within the cabin, identifies the window whose state should be controlled, and generates commands to control the window through central cabin controllers. The system further compensates for light sources internal to the cabin and monitors the phase of flight to ensure compliance to specific light conditions within the aircraft cabin.

Vision based aircraft cabin ambient light control

A locking system for an overhead stowage bin may comprise a latch and an electromechanical actuator configured to actuate the latch. A bin controller may be electrically coupled to the electromechanical actuator. A passenger input and a master controller may be in operable communication with the bin controller.

Overhead stowage bin with electronic control system

A windscreen wiper system (WWS) architecture is provided. The WWS architecture includes a wiper assembly and an electronic control unit (ECU) configured to control operations of the wiper assembly. The ECU is configured to recognize that a command to engage a predefined wiper mode is received. The predefined wiper mode is characterized in that a windscreen is divided into sectors and the wiper assembly is controllably operated to sweep across one or more of the sectors in a predefined pattern with a predefined sweep speed. The ECU is further configured to control the wiper assembly to operate in the predefined wiper mode according to the command being received.

Programmable pattern-based sweep mechanism for aircraft windscreen wiper system

Provided are embodiments for a system having an avionics system that is configured to dynamically communicate one or more configurable parameters of a wiper and wash system based at least in part on a selected mode, and an avionics bus that is configured to communicate dynamic parameters from the avionics system. The system also includes a wash system having a fluid reservoir and fluid level sensor, and a wiper system including a control unit (ECU) that is configured to operate the system based at least in part on the one or more configurable parameters, wherein the wiper system is coupled to the wash system and supplies the wash fluid to the wiper system. Also provided are embodiments of a method for performing dynamic control of the aircraft windscreen wiper and wash system configuration parameters.

Dynamic control of aircraft windscreen wiper and wash system configuration parameters

A windshield wiper system (WWS) is provided. The WWS includes a brushless direct current (BLDC) motor, a wiper arm and blade, a gearbox/converter operably interposed between the BLDC motor and the wiper arm and blade and a smart motor drive configured to determine a WWS failure condition and to operate the BLDC motor according to the determination.

Fault diagnostics in aircraft windshield wiper systems

A method of inspecting an air data probe for damage or misalignment on a mounting surface includes retrieving reference data for the air data probe from a database, capturing images of the air data probe via a camera and generating dimensions from the captured images of the air data probe via a feature extractor. An alignment calculator analyzes the generated dimensions from the captured images of the air data probe and the reference data for the air data probe from the database to identify misalignment of the air data probe, and analyzes the generated dimensions from the captured images of the air data probe and the reference data for the air data probe from the database to identify damage of the air data probe. A maintenance recommendation for the air data probe is generated and outputted, based on the identified misalignment or damage of the air data probe.

System for the inspection of air data probes

Disclosed is a method of operating a Portable Cargo Panel (PCP) for an aircraft, including: detecting a gesture on a display of the PCP; determining that the gesture is a command to view on the display a first cargo compartment; securing a wireless connection with the first control panel therein; receiving, from the first control panel, a health state of each of a plurality of Cargo Handling Units (CHUs) therein; displaying, on the display, the first cargo compartment with the plurality of CHUs and the operational state of the plurality of CHUs; controlling one or more of the CHUs in the first cargo compartment by transmitting, to the first control panel, a command to: run a diagnostic test against the one or more of the plurality of CHUs; or control the plurality of CHUs to move a Unit Load Device (ULD) into, within or out of the first cargo compartment.

Method of handling aircraft cargo from a portable panel

A sensor assembly for monitoring a heater system for an aircraft probe sensor includes a current sensor module with a current sensor core and a high electromagnetically permeable enclosure around the current sensor core. An input wire pathway extends through the current sensor core and is configured to receive a heater input wire. A return wire pathway extends through the current sensor core and is configured to receive a heater return wire. A high electromagnetically permeable tube extends through the current sensor core and is configured to extend around one of the input wire and the heater return wire.

Inline sensor assembly to monitor air data probe heater

Provided are embodiments for a method for monitoring a wiper system, the method includes reading a radio frequency identification (RFID) tag embedded in a wiper blade using a reader, comparing the read RFID tag to stored wiper blade information, determining a blade usage ratio for the wiper blade based on determining whether the wiper blade has been replaced, and providing an indication of a status of the wiper blade based at least in part on the blade usage ratio. Also provided are embodiments for a system for monitoring the health of the wiper system.

Monitoring aircraft windscreen blade usage and health

Provided are embodiments that include techniques for a wireless portable cargo control panel with physical controls. The techniques include a portable electronic device (PED) including a display, the PED configured to communicate with a master control panel (MCP) that controls a cargo handling system and a portable control panel (PCP). The PCP includes an interface configured to couple the PED, one or more dedicated physical input selection devices, a directional controller, and one or more orientation indicator displays, wherein each of the one or more orientation indicator displays are configured to be updated based at least in part on orientation information associated with the cargo handling system, PCP, and PED.

Wireless portable aircraft cargo control panel with physical controls

A portable wireless communications adapter includes a wireless receiver, a wireless transmitter, an electronic interface connector, and a location sensing module. The wireless receiver is configured to receive wireless data over a Wireless Avionics Intra-Communication (WAIC) frequency range between 4.2 gigahertz (GHz) and 4.4 GHz. The wireless transmitter is configured to send wireless data over the WAIC frequency range between 4.2 GHz and 4.4 GHz. The electronic interface connector is configured to mate with a portable electronic device for communication of the wireless data with the portable electronic device. The location sensing module is configured to determine a location of the portable wireless communications adapter relative to an interior of an aircraft based on WAIC communications received at the wireless receiver and selectively enable and disable the wireless transmitter based on the determined location.

Portable wireless communication adapter for avionics frequencies selectively enabled based on location within aircraft

A Wireless Avionics Intra-Communication (WAIC) system includes a communication network and a WAIC adapter location system. The communication network is configured to exchange data with a portable wireless device via WAIC adapter. The WAIC adapter location system is configured to determine a location of the WAIC adapter, which selectively connects and disconnects the portable device from the communication network based on the location.

Portable wireless avionics intra-communication adapter location system

Embodiments include techniques for managing multiple portable control panels in aircraft cargo handling system are provided. The embodiments include a master control panel (MCP), and a plurality of wireless coordinators in communication with the MCP. The embodiments also include a plurality of zones of a cargo storage area, wherein each zone of the plurality of zones is defined by a portion of the cargo storage area that is controlled by a wireless coordinator of the plurality of wireless coordinators and includes at least one of power drive units (PDU) and turntables, and a plurality of portable control panels (PCP) in communication with the wireless coordinators, the PCP configured to operate and monitor states of the PDU and turntables.

Growing community of inventors

Karnataka, India

Rameshkumar Balasubramanian