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Abstract <p>In this study, a facile approach for fabrication of high-speed aircraft components has been developed from a silicon nitride-based ceramic composite material using hot casting followed by reaction sintering. Prototype air pressure/braking temperature probes were fabricated using this material. High-enthalpy flow tests were conducted on a firing rig with a supersonic nozzle, generating a supersonic, high-temperature flow and subjecting the samples to thermal shock with an incident flow temperature gradient of approximately 800&#xa0;degrees per second, significantly increasing the load on the samples. Prototype air pressure probes successfully passed high-enthalpy flow tests for a total duration of at least 900 seconds under conditions corresponding to atmospheric flight at an altitude of 9–11 km with a Mach number &gt;6. The positive results demonstrated the potential application of the developed composite for thermally loaded aircraft components.</p>

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Testing of Silicon Nitride-based Composite Ceramic Samples in a High-enthalpy Gas Flow

  • 期刊论文

  • 发表日期：

    2025年9月1日

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  • S. A. Sitnikov,
  • V. N. Avrashkov,
  • D. V. Mesheryakov,
  • O. A. Butusova,
  • V. V. Spiryagin,
  • S. A. Kolesnik

摘要

Abstract

In this study, a facile approach for fabrication of high-speed aircraft components has been developed from a silicon nitride-based ceramic composite material using hot casting followed by reaction sintering. Prototype air pressure/braking temperature probes were fabricated using this material. High-enthalpy flow tests were conducted on a firing rig with a supersonic nozzle, generating a supersonic, high-temperature flow and subjecting the samples to thermal shock with an incident flow temperature gradient of approximately 800 degrees per second, significantly increasing the load on the samples. Prototype air pressure probes successfully passed high-enthalpy flow tests for a total duration of at least 900 seconds under conditions corresponding to atmospheric flight at an altitude of 9–11 km with a Mach number >6. The positive results demonstrated the potential application of the developed composite for thermally loaded aircraft components.