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Ultrasonic thermometric measurement system for solid rocket combustion chambers.

Yanlong Wei1, Haijian Liang2, Gao Wang3

  • 1Science and Technology on Sensor Test & Intelligent Information Processing Laboratory, Department of Computer Science, Taiyuan Normal University, Taiyuan 030619, China.

Ultrasonics
|February 6, 2021
PubMed
Summary
This summary is machine-generated.

A new ultrasonic thermometer using an iridium-rhodium-40% alloy waveguide accurately measures solid rocket motor (SRM) temperatures up to 1800 °C. This reliable in situ device achieved 97% repeatability and detected a peak SRM temperature of 1744 °C.

Keywords:
Iridium rhodium alloySolid Rocket Motor (SRM)TemperatureUltrasonic thermometryUltrasonic velocity

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Area of Science:

  • Materials Science
  • Aerospace Engineering
  • Sensor Technology

Background:

  • Accurate in situ temperature measurement in solid rocket motors (SRMs) is critical but challenging due to extreme conditions.
  • Existing methods like thermocouples have limitations in reliability and accuracy at high temperatures.
  • A need exists for advanced sensor technology capable of withstanding and measuring temperatures exceeding 1000 °C.

Purpose of the Study:

  • To design and validate an ultrasonic temperature measurement system for high-temperature environments.
  • To assess the performance of an iridium-rhodium-40% alloy waveguide for in situ temperature sensing.
  • To evaluate the system's applicability and accuracy within a solid rocket motor.

Main Methods:

  • Development of an ultrasonic thermometer utilizing an iridium-rhodium-40% alloy waveguide.
  • Laboratory calibration experiments conducted from room temperature up to 1800 °C.
  • Testing the sensor's stability, repeatability, and error margins under high-temperature conditions.
  • Integration of the sensor into an application structure for a solid rocket motor test.

Main Results:

  • The ultrasonic thermometer successfully obtained signals up to 1800 °C with high accuracy.
  • A repeatable calibration curve was achieved with 97% repeatability and a 95% confidence error band.
  • Sensor sensitivity increased with temperature, reaching a maximum of 0.0035 µs/°C above 1000 °C.
  • In a solid rocket motor test, the system recorded a peak temperature of 1744 °C.

Conclusions:

  • The developed ultrasonic thermometer is a reliable in situ device for measuring high temperatures in SRMs.
  • The iridium-rhodium-40% alloy waveguide demonstrates excellent performance and stability in extreme thermal environments.
  • This technology offers a significant advancement for monitoring critical parameters in rocket propulsion systems.