Honeywell International Inc.

Air China Limited

Qixiang Li

Dinkar A Mylaraswamy

Dechao Zhong

Wenjing Bi

Timothy Griffith

Tang Li

Yuanbin Li

Weixi Chai

Xueliang Wu

Chengli Ouyang

Sapan Nitin Shah

Eric Blumer

Matthew Arend

Henry M Claeys

Ramon Blanco Encinas

Braxton Felts

C Arthur Dins

Hua Huang

Dennis Norman Oswell Dalton

Fong Wee

Joshua Allen Moore

Garry H Lee

Michael Easley

Disclosed are systems, methods, and non-transitory computer-readable medium for generating maintenance recommendation for an auxiliary power unit (APU). One system may include collecting APU data, applying an algorithm that may analyze the APU data using one or more tuning parameters to capture elements of the APU data that indicate an APU health concern, and transmitting the captured elements indicating the APU health concern to a cloud-based health monitoring system.

Internet connected auxiliary power unit airline maintenance system

In some examples, a device can be used for measuring a length of a wear indicator on a brake assembly. The device includes a moveable component configured to move based on contact with the wear indicator. The device also includes a sensor configured to detect a displacement of the moveable component. The device further includes processing circuitry configured to determine the length of the wear indicator based on the displacement of the moveable component detected by the sensor.

Measuring the length of a wear indicator

A processor implemented method in an aircraft-mounted edge computing device configured for real-time monitoring and analysis of APU health information onboard an aircraft is provided. The method comprises: receiving raw APU data from an electronic control unit associated with an APU; downloading one or more tuning parameters from a cloud-based health monitoring system, wherein the one or more tuning parameters includes a threshold level that is adjustable by the cloud-based health monitoring system based on analyzed APU health information; analyzing the raw APU data using the one or more tuning parameters to capture elements of the raw APU data that indicate an APU health concern; reducing the amount of raw APU data in the captured elements by removing raw APU data indicating intermittent or false-positive APU health concerns; and transmitting the captured elements indicating an APU heath concern using an Internet of things protocol to the cloud-based health monitoring system.

Edge computing based airplane auxiliary power unit health monitoring system

Systems and methods for measuring the wear of carbon brakes of an aircraft are disclosed herein. The systems and methods include a 3-axis acceleration sensor module mounted on a brake assembly, the 3-axis acceleration sensor module configured to detect acceleration events of the brake assembly in three different component directions. The systems and methods further include a memory module operably connected to the 3-axis acceleration sensor module, the memory module configured to store acceleration events detected by the 3-axis acceleration sensor module and to store a pre-determined threshold for determining carbon brake wear based upon a number of acceleration events detected in a single component direction of the three different component directions. The systems and methods also include a processor module operably connected the processor module configured to compare the stored acceleration events detected in a single direction of the three different directions to the stored pre-determined threshold.

Carbon brake wear status monitoring system

In one embodiment, a method is provided. The method comprises: receiving, in a vehicle, at least one pollution parameter; and adjusting at least one fluid flow regulating mechanism position, to regulate an intake of pollutants into an environmental control system of the vehicle, based upon the at least one pollution parameter.

Systems and methods for reducing environmental control system maintenance

A testing equipment of an airplane air conditioning system is disclosed. The test equipment includes a sound receiver and a sound processor. The sound processor processes running noise of airplane air conditioning system sampled by the sound receiver to assess the operative condition of the system. The sound receiver samples environmental noise when the airplane air conditioning system is not running, and the sound processor de-noises the running noise by using the environmental noise.

Testing equipment of onboard air conditioning system and a method of testing the same

A synchronized, aircraft light system includes a first light emitting diode (LED) light source disposed on the aircraft and a second LED light source disposed on the aircraft. The first LED light source and the second LED light source are operatively coupled to a direct current (DC) power source by a DC power bus. A power line communication (PLC) modem is operatively coupled to the DC power bus. The PLC modem is operable to impart a synchronization signal on the DC power bus, such that the first LED light source and the second LED light source are caused to illuminate via power supplied from the DC power source via the DC power bus, in a predetermined, synchronous manner with respect to each other.

Aircraft beacon light synchronization

A power line communication based monitoring system includes an alternating current (AC) power distribution bus, a data source (such as a sensor circuit), a system modulator/demodulator (modem), and a data converter. The sensor circuit is configured to sense a mechanical state of a component and to supply a modulated sensor signal representative of the mechanical state to the AC power distribution bus. The system modem is in operable communication with the AC power distribution bus and is coupled to receive the modulated sensor signal therefrom. The system modem is configured, upon receipt of the modulated sensor signal, to demodulate the modulated sensor signal and supply a demodulated sensor signal. The data converter is coupled to receive the demodulated sensor signal from the system modem and is configured to convert the demodulated sensor signal to digital data in a standard digital data communications protocol.

Power line communication based monitoring system

According to various embodiments, the present invention relates to a platform and method for testing aircraft message trigger logics are disclosed. Apparatus for testing message trigger logics of aircraft comprises: DFDAU (a Digital Flight Data Acquisition Unit), which is adapted to receive message trigger logics to be tested; an input interface, which is adapted to receive data of aircraft condition; and a simulation signal generator, which is adapted to generate simulation signals according to the data of aircraft condition; wherein, the DFDAU is adapted to receive the simulation signals, and generate messages according to the message trigger logics to be tested.

Apparatus and method for testing aircraft message trigger logics

The present invention relates to a test apparatus that includes a simulation signal generation portion and a test portion. Embodiments of the simulation signal generation portion include an input interface, a simulation signal generation module, and an output interface. Embodiments of the test portion include wiring extension apparatus, a Digital Flight Data Acquisition Unit and a comparison module.

Growing community of inventors

Beijing, China

Qixiang Li