Sikorsky Aircraft Corporation

Michael G Mastrianni

John H Judge

Mark W Davis

Payman Sadegh

James N Rozak

Michael C Kingsley

Howard A Winston

Daniel Alfred Ciaburri

Brian Drost

Anthony Santo Maniaci

Andrew Palladino

A system for weight measurement for an aircraft having a weight on wheels threshold between a flight mode and a ground mode includes a weight on wheels sensor arrangeable on a landing gear assembly of the aircraft, and a computing device receiving first detected data from the sensor related to strain on the landing gear assembly. The computing device calculates a rate of change of the strain over time to determine when the landing gear assembly reaches the weight on wheels threshold. The system also measures aircraft gross weight in a static condition.

Measurement system for aircraft, aircraft having the same, and method of measuring weight for aircraft

A system for acceptance testing includes a data acquisition system operable to receive a plurality of sensor inputs from a component under test. The system also includes a health and usage monitoring system (HUMS) interface operable to receive data from a HUMS coupled to the sensor inputs. The system further includes a data processing system operable to determine a plurality of condition indicators based on the sensor inputs acquired by the data acquisition system, receive a plurality of HUMS data from the HUMS interface based on the sensor inputs, compare the condition indicators to the HUMS data, and output a test result based on results of the comparison.

Acceptance testing system

A measuring system and method that computes and analyzes sensor data fused with multiple mechanical and thermally induced strain measurements is provided. Further, the measuring system and method realizes physics-based relations between sensor readings due to mechanical and thermal sources by optimally de-coupling a total strain into its mechanical and thermal components. The measuring system and method also auto-tunes coefficients involved in the optimal de-coupling equations using sensor specification data and previous system test results for initialization.

Fiber optic weight sensor optimization for landing gear

A method of electrical system fault detection and location determination includes measuring a baseline time domain reflectometry (TDR) waveform along a wire path of the electrical system and obtaining an operating TDR waveform along the wire path. The operating TDR waveform is compared to the baseline TDR waveform to derive a difference TDR waveform, and a difference energy is calculated utilizing the difference TDR waveform. The difference energy is monitored over time for peaks in the difference energy and potential electrical system faults are identified via the peaks in the difference energy.

System and method for health monitoring of electrical systems

Growing community of inventors

Orange, CT, United States of America

Michael G Mastrianni