Mars Exploration Rover transverse impulse rocket cover thermal protection system design verification

Arc jet test results are summarized of the Mars Exploration Rover silicone-impregnated reusable ceramic ablator (SIRCA) transverse impulse rocket system (TIRS) cover test series in the Panel Test facility at NASA Ames Research Center. The primary objective of this arc jet test series was to evaluate design details of the SIRCA TIRS cover interface to the aeroshell under simulated atmospheric entry heating conditions. Four test articles were tested in an arc jet environment with three different seal configurations. The test condition was designed to match the predicted peak flight heat load at the gap region between the SIRCA and the backshell and resulted in an overtest for the apex region of the SIRCA TIRS cover. Repeatable thermocouple data were obtained and compared with SIRCA thermal response analyses. The one-dimensional thermal response prediction compared well with the thermocouple data for the location at the backshell interface. For the apex region of the SIRCA TIRS cover, a one-dimensional thermal response analysis resulted in an overprediction because there were strong multidimensional conduction effects due to the TIRS cover geometry. In general, the test results provide strong experimental evidence that supports the adequacy of the baseline seal design.