United Technologies Corporation

Carrier Corporation

Raytheon Technologies Corporation

Sikorsky Aircraft Corporation

Cagatay Tokgoz

Sameh Dardona

Joseph Zacchio

Nicholas Charles Soldner

Joseph V Mantese

Alan Matthew Finn

Ziyou Xiong

Wayde R Schmidt

Paul Sheedy

Marcin Piech

Sanjay Bajekal

Xin Wu

Lesia V Protsailo

Thomas D Kasprow

Mathias Pantus

Daniel Anthony Grande

Brian Dean Bouquillon

Jeroen Te Paske

Pascal Van De Mortel

A radar presence detection system is configured to detect oscillations within a building. The radar presence detection system includes an accelerometer, a radar, and a processing unit. The accelerometer is attached to the building and configured to detect structural vibration waves. The radar is configured to transmit a monitoring wave and receive a reflected wave. The processing unit includes a filter, an adaptive filter, and a detector. The filter is configured to receive a first signal indicative of the reflected wave and output a filtered reflected wave signal spanning a frequency range indicative of an oscillation within the building. The adaptive filter is configured to receive a second signal indicative of the structural vibration wave signal and output a focused vibration signal spanning a frequency range for the cancellation of vibration noise.

Radar detection system

A presence detection system includes an infrared detector and a radar detector. A computer processor of the system is configured to receive respective signals from the infrared and radar detectors and process the signals via execution of an algorithm.

Presence detection system

A fault detection assembly for an aircraft system according to an example of the present disclosure includes, among other things, a transmitter that communicates an electrical input signal to a first portion of an electrical connector, the first portion moveable between a fully seated position and a fully unseated position relative to a second portion of the electrical connector to define a range of insertion depths, a receiver that senses an electrical output signal relating to the electrical input signal, and a comparison module that determines an insertion depth in the range of insertion depths based on a change in a resonant frequency of the electrical output signal with respect to the electrical input signal.

Fault detection assembly

A method of data collection from a rotor system of an aircraft includes positioning a plurality of sensors at a plurality of locations of a rotating portion of the rotor system. One or more antennae are located at one or more rotationally fixed locations of the aircraft. Rotor system data is collected via the sensors and is wirelessly transmitted from the sensors to the antennae and is transferred from the antennae to a gateway where it is normalized and synchronized. In another embodiment, a data collection system for a rotor includes a plurality of sensors located at rotating locations of the rotor, the sensors configured to collect and wirelessly transmit rotor data. Antennae are located at a fixed location of the aircraft. The antennae are configured to send and receive data from the sensors. A gateway is connected to the antennae to normalize and synchronize the rotor data.

Rotor wireless load and motion monitoring sensor network

An apparatus and method for detecting a short in a blade of a gas turbine engine, the apparatus including: a first plate configured to form a first capacitor with the protective sheath when the apparatus is located proximate to the blade; a second plate configured to form another capacitor with a portion of the airfoil when the apparatus is located proximate to the blade; and a voltage source electrically connected to the first plate and the second plate.

Apparatus and method for non-destructive detection of fan blade electrical isolation

A magnetic communication system for a gas turbine engine may include a sensor coupled to a microcontroller. A low frequency radio-frequency identification integrated chip may be coupled to the microcontroller. A first coupling circuit may be coupled to the low frequency radio-frequency identification integrated chip and may include a first coil winding wound within a first core. The first coil winding operatively associated with a low frequency magnetic flux.

Embedded sensor system

A wear monitoring system for measuring incursion depth into an abradable coating includes a layer of abradable coating including a depth. At least one measurement circuit includes a plurality of conductive leads disposed within the abradable coating. The conductive leads are spaced radially apart within a common radial plane corresponding to the depth of the abradable coating. A plurality of resistor elements corresponds with the plurality of conductive leads. Each of the plurality of resistor elements are in electrical communication with one of the plurality of conductive leads disposed within the common radial plane of the corresponding one of the plurality of conductive leads. An electrical characteristic of the circuit varies responsive to cutting of one or more of the plurality of conductive leads by a passing airfoil. A gas turbine engine and method are also disclosed.

Embedded sensor for in-situ monitoring of blade tip incursion

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Beaumont, TX, United States of America

Cagatay Tokgoz