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Icing in helicopter intake systems poses significant risks to flight safety, and sand prevention devices can provide certain anti-icing effects. Combining the optimization research on sand prevention and bypass for a specific helicopter intake system, icing tests with bypass simulation were conducted on a helicopter sand prevention device prototype in the FL-61 icing wind tunnel. By designing and constructing the test system and performing icing tests, the ice shape characteristics of the prototype under given conditions were obtained. The influences of windward angle, temperature, wind speed, and water droplet diameter on the icing of the sand prevention device prototype were preliminarily determined. Additionally, pressure change data inside the device under different icing degrees were acquired to analyze the initial impact of icing on the intake performance of the prototype.

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Experimental Research on Icing Test of Sand Control Device Samples for the Helicopter

  • 会议论文

  • 发表日期：

    2026年

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  • Zhang Zhiqiang,
  • Gu Hongyu,
  • Zhang Yijun

摘要

Icing in helicopter intake systems poses significant risks to flight safety, and sand prevention devices can provide certain anti-icing effects. Combining the optimization research on sand prevention and bypass for a specific helicopter intake system, icing tests with bypass simulation were conducted on a helicopter sand prevention device prototype in the FL-61 icing wind tunnel. By designing and constructing the test system and performing icing tests, the ice shape characteristics of the prototype under given conditions were obtained. The influences of windward angle, temperature, wind speed, and water droplet diameter on the icing of the sand prevention device prototype were preliminarily determined. Additionally, pressure change data inside the device under different icing degrees were acquired to analyze the initial impact of icing on the intake performance of the prototype.