Development of temperature-sensitive paint with high performance and responsivity for aerodynamic heating measurement

Takehito Horagiri, Hiroki Nagai

研究成果: Conference contribution

2 被引用数 (Scopus)

抄録

Heat flux measurement data are indispensable in the design of a heat protection system for the atmospheric re-entry of a spacecraft. One of the instrumentation techniques used to obtain heat flux data is Temperature-Sensitive Paint (TSP). Shock tubes and shock tunnel are used to simulate re-entry, but the duration of a shock tunnel test is extremely short. In order to apply TSP to high speed phenomena, a new TSP with a large luminescence and high responsivity was developed. In a luminescence test, the luminescent intensity peaked when the mixing ratio was set at 50%, and the intensity was about twice the original one. In a response time evaluation test, the response time was improved by increasing the mixing ratio. When the calcium silicate mixing ratio was set at 50%, the improved TSP achieved a response with a time constant of 0.205ms. We applied this TSP to a high-enthalpy wind tunnel and could obtain the heat flux data.

本文言語English
ホスト出版物のタイトル52nd Aerospace Sciences Meeting
出版社American Institute of Aeronautics and Astronautics Inc.
ISBN(印刷版)9781624102561
出版ステータスPublished - 2014
イベント52nd Aerospace Sciences Meeting 2014 - National Harbor, United States
継続期間: 2014 1 132014 1 17

Other

Other52nd Aerospace Sciences Meeting 2014
国/地域United States
CityNational Harbor
Period14/1/1314/1/17

ASJC Scopus subject areas

  • 航空宇宙工学

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