Abstract
Radome is a thermo-structural member used in tactical missiles and houses the avionic systems like seeker. It is subjected to severe thermal as well as structural loads during the flight. The material of the radome is chosen such that it is transparent electromagnetic radiation. The ceramic radome is attached to the metallic bulkhead with high temperature glue. In the present manuscript, the experimental evaluation methodology implemented for evaluation of the structural integrity of the ceramic radome under combined thermal and structural loads is presented. Initially axial load, to simulate the resultant drag force and a distributed lateral load, to simulate the bending moment, are applied via a pre-casted contoured Teflon mock sections, up to proof load and then time varying temperature is applied. The time-varying temperature profile is applied via a closed loop control based on PID and the heating environment is created using short wave infra-red radiation. Exhaustive instrumentation is used in the experiments. Detailed results are also presented in the manuscript up to the structural failure.
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