C2.2 - Design and Selection Criteria of High Temperature Accelerometers for Aerospace Propulsion
- Event
- AMA Conferences 2015
2015-05-19 - 2015-05-21
Nürnberg, Germany - Band
- Proceedings SENSOR 2015
- Chapter
- C2 - Applications
- Author(s)
- B. Metz - PCB Piezotronics, Inc., Depew, NY (USA), P. Ensinger - Sensoren-Beratung Ensinger, Reilingen (Germany)
- Pages
- 367 - 376
- DOI
- 10.5162/sensor2015/C2.2
- ISBN
- 978-3-9813484-8-4
- Price
- free
Abstract
Accelerometers and pressure sensors for measurement in aerospace propulsion systems require special consideration during design and manufacturing processes. Specialized applications frequently require use of a single sensor model, which must be capable of operating over significantly wider temperature ranges, for example, -420 to +1300 °F (-251 to +705 °C), while providing high accuracy, stability and reliability. Typical applications for high temperature aerospace propulsion sensors include measurement on gas turbine engines both in-flight and in test cells, as well as rocket motors and thruster assemblies. The same sensor might be required to withstand radiation and be used in monitoring vibration inside a nuclear power plant or space vehicle, or the cryogenic conditions of liquid propellants. These environments present a multitude of measurement challenges.