Honeywell International Inc.

Honeywell G.m.b.h.

Kyusung Kim

Raj Mohan Bharadwaj

Onder Uluyol

Bin Dong

Qingqiu Ginger Shao

Chris Hickenbottom

David Daniel Lilly

Paul Frederick Dietrich

Charles M Ball

Kwong Wing Au

Emmanuel Obiesie Nwadiogbu

Robert C McCroskey

Andrew Peter Vechart

Gary Kumagai

Megan L Hawley

Piyush Ranade

Roy Araki

Wenyan Guo

Abraham Reddy

Eric Shi

Dinkar A Mylaraswamy

Vibhor L Bageshwar

Eric Blumer

Sunil K Menon

Mike S Koerner

Tomas Rudolecky

Mohit Singhai

Craig L Schimmel

Andrew Earl

Qi Li

Craig Schimmel

Zdenek Hrncir

John Linert

Doug Sturm

Jinkun Liu

Robert C Mccroskey

A method in an aircraft of using prognostic indicators for aircraft maintenance includes retrieving aircraft health data for a plurality of aircraft components wherein the aircraft health data includes at least one of mechanical systems condition indicator (CI) data, vibration spectrum data, resampled time-domain (RTD) data, and RTD spectrum data. The method includes estimating component health status information for the plurality of aircraft components using a plurality of prognostic modules wherein each prognostic module is configured to generate health status information for at least one of the aircraft components, the health status information includes at least one of a current health indicator and a prognostic indicator. The method also includes storing the component health status information for the aircraft components in a database onboard the aircraft, and causing the display of the health status information for the specific component on an aircraft display.

System and method of using mechanical systems prognostic indicators for aircraft maintenance

An example system for determining a performance status of an environmental control system (ECS) in a vehicle includes memory and processing circuitry. The processing circuitry is configured to determine, based on one or more of the aircraft data, the weather data, or the trending data, an estimated compressor exit temperature. The processing circuitry is configured to determine a current residual compressor exit temperature based on the estimated compressor exit temperature and a current compressor exit temperature. The processing circuitry is configured to determine whether a residual condition is met based at least in part on the residual compressor exit temperature and whether a pack condition is met based at least in part on a pack temperature. The processing circuitry is configured to provide an indication of the performance status of the ECS based on at least one of the residual condition or the pack condition being met.

Environmental control system performance monitoring

According to certain aspects of the disclosure, a computer-implemented method may be used for detecting health status of an environmental control system. The method may include receiving aircraft data of an aircraft and receiving flight data of an aircraft. Calculating a predicted performance of the aircraft based on the received aircraft data and the received flight data and generating at least one model scalar or residual, wherein the at least one model scalar or residual is generated based on the aircraft data of the aircraft. Identifying at least one pattern from the at least one model scalar or residual and classifying the at least one pattern into at least one of a plurality of classifications. Identifying a failure of modes or components from the classifications and transmitting a maintenance report once the failure of modes or components is identified.

Pattern classification system with smart data collection for environmental control system fault isolation

A vehicle management system includes an onboard vehicle system and a ground system. The onboard vehicle system includes a compressor exit temperature sensor configured to determine an ECS compressor exit temperature; a data acquisition unit coupled to receive the compressor exit temperature, an altitude of the first vehicle, and an ambient temperature and configured to generate a data report; and a communications system coupled to receive and transmit the data report. The ground system includes a ground data server coupled to receive the data report and determine a fouling condition of an environmental conditioning element of the ECS based on at least the compressor exit temperature, the altitude, and the ambient temperature; and a mobile application module coupled to receive the fouling condition from the ground data server and configured to provide an interface for displaying the fouling condition to a user on a mobile device.

Aircraft management systems and methods for ECS predictive maintenance

A maintenance system is provided for an environmental conditioning element of an environmental control system of a vehicle. The maintenance system includes a data acquisition module configured to determine an ambient temperature, an altitude of the vehicle, and a measured ECS compressor temperature; a fouling module coupled to receive the ambient temperature, the altitude, and the measured ECS compressor temperature from the data acquisition module and configured to generate a fouling condition of the environmental conditioning element based on at least the ambient temperature, the altitude, and the measured ECS compressor temperature; and a reporting module coupled to receive the fouling condition from the fouling module and configured to generate a report for a user that includes the fouling condition.

Aircraft maintenance systems and methods for ECS fouling predictions

A system and method for identifying engine wear based on engine oil debris is provided. The provided system and method utilize metallic debris data provided in summary reports. For each object of metallic debris, a zap count, an initial (pre-zap) impedance and an impedance change (post zap) are processed with configurable reference variables. Alerts (suggesting potential engine wear) are generated responsive to the impedance values of the objects of metallic debris and the reference variables.

System and method for evaluating chip zap data

An environmental control system (ECS) includes a controller; and a mode selector in communication with the controller and configured to select at least one of a plurality of modes. The mode is based on one of: number of occupants in an environment; activity of the occupants in the environment; destination of the environment; and performance of an engine that moves the environment. The controller is configured to change an ECS load on the system based upon the selected mode.

ECO mode ECS logic

An inertial navigation system (INS) includes a primary inertial navigation system (INS) unit configured to receive accelerometer measurements from an accelerometer and angular velocity measurements from a gyroscope. The primary INS unit is further configured to receive global navigation satellite system (GNSS) signals from a GNSS sensor and to determine a first set of kinematic state vectors based on the accelerometer measurements, the angular velocity measurements, and the GNSS signals. The INS further includes a secondary INS unit configured to receive the accelerometer measurements and the angular velocity measurements and to determine a second set of kinematic state vectors of the vehicle based on the accelerometer measurements and the angular velocity measurements. A health management system is configured to compare the first set of kinematic state vectors and the second set of kinematic state vectors to determine faults associated with the accelerometer or the gyroscope based on the comparison.

Systems and methods for determining inertial navigation system faults

A system and method are provided for monitoring vibration data. A vehicle, for example, may include at least one engine component, a sensor coupled to the at least one engine component and configured to monitor a vibration of the at least one engine component, and a processor communicatively coupled to the sensor, the processor configured to determine a plurality of envelope spectrums based upon vibration data from the sensor, determine fault frequencies for each of the at least one engine component based upon a rotating speed of each of the at least one components, and monitor each envelope spectrum for changes at the determined fault frequencies.

System and method for monitoring vibration data

Methods and systems for estimating wear damage of a rolling-element bearing system including at least one rolling-element bearing are provided. A first number of first condition indicators representative of the wear damage of the at least one rolling-element bearing are generated. A second number of second condition indicators are generated based on the first plurality of first condition indicators. The second number is less than the first number an indication of the wear damage of the at least one rolling-element bearing is generated based on the second number of second condition indicators.

Method and system for detecting incipient bearing failures

Systems and methods for isolating a performance anomaly within one or more line replaceable units (LRUs) on a gas turbine engine by monitoring the start up transient are presented. The system comprises a set of sensors, an anomaly detector and a fault isolation reasoner. Each sensor of the set monitors at least one operating parameter of at least one engine component. The anomaly detector is configured to detect an anomaly in a component by comparing a particular value of an operating parameter to a base line value of that parameter. The specific cause of the startup anomaly is isolated utilizing a set of component reasoners that is based on the nature of the detected anomaly. The key events during the engine startup are identified by the combination of monitoring physically relevant phases of a startup and monitoring the engine control schedule. The values at these key events are used for comparing at the anomaly detector.

Methods and systems for turbine line replaceable unit fault detection and isolation during engine startup

A computer implemented method and system includes using information provided from sensors to monitor a wind turbine generator and provide signals representative of operation of the wind turbine generator, extracting signal level features from the signals, extracting model based features from the signals, calculating signal based conclusions, model based conclusions and spectral feature reinforcement based conclusions, and fusing the conclusions to provide a fault detection indication.

Wind turbine generator fault diagnostic and prognostic device and method

Methods and systems are provided for detecting temporal relationships that are uniquely associated with a selected root cause. The method comprises identifying error codes associated with a root cause, wherein each error code comprises a plurality of event indicators and temporal data describing when the event indicator was generated, analyzing each of the error codes to detect a combination of event indicators that is associated with error codes corresponding to the selected root cause and to a non-selected root cause, and detecting a temporal relationship involving the combination of event indicators, wherein the temporal relationship is uniquely associated with error codes corresponding to the selected root cause.

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Plymouth, MN, United States of America

Kyusung Kim