Self Diagnostic Accelerometer Ground Testing on a C-17 Aircraft Engine

• Published in: NASA Center for AeroSpace Information (CASI). Conference Proceedings
• Main Authors: Tokars, Roger P, Lekki, John D
• Format: Conference Proceeding
• Language: English
• Published: Hampton NASA/Langley Research Center 02.03.2013
• Subjects: Accelerometers; Aircraft accidents; Aircraft accidents & safety; Aircraft components; Aircraft engines; Airplane engines; Attachment; Change detection; Cross correlation; Diagnostic systems; Engine tests; Fault detection; Flight tests; Ground tests; Health; Idling; Maximum power; Military aircraft; Pattern recognition; R&D; Research & development; Robustness; Sensors; Shutdowns

The self diagnostic accelerometer (SDA) developed by the NASA Glenn Research Center was tested for the first time in an aircraft engine environment as part of the Vehicle Integrated Propulsion Research (VIPR) program. The VIPR program includes testing multiple critical flight sensor technologies. One such sensor, the accelerometer, measures vibrations to detect faults in the engine. In order to rely upon the accelerometer, the health of the accelerometer must be ensured. Sensor system malfunction is a significant contributor to propulsion in flight shutdowns (IFSD) which can lead to aircraft accidents when the issue is compounded with an inappropriate crew response. The development of the SDA is important for both reducing the IFSD rate, and hence reducing the rate at which this component failure type can put an aircraft in jeopardy, and also as a critical enabling technology for future automated malfunction diagnostic systems. The SDA is a sensor system designed to actively determine the accelerometer structural health and attachment condition, in addition to making vibration measurements. The SDA uses a signal conditioning unit that sends an electrical chirp to the accelerometer and recognizes changes in the response due to changes in the accelerometer health and attachment condition. In an effort toward demonstrating the SDAs flight worthiness and robustness, multiple SDAs were mounted and tested on a C-17 aircraft engine. The engine test conditions varied from engine off, to idle, to maximum power. The two SDA attachment conditions used were fully tight and loose. The newly developed SDA health algorithm described herein uses cross correlation pattern recognition to discriminate a healthy from a faulty SDA. The VIPR test results demonstrate for the first time the robustness of the SDA in an engine environment characterized by high vibration levels.