CYCLIC FATIGUE ANALYSIS OF ROCKET THRUST CHAMBERS: VOLUMEⅡ- ATTITUDE CONTROL THRUSTER HIGH CYCLE FATIGUE

摘要

A finite element stress analysis was performed for the film cooled throat section of an attitude control thruster. The analysis employed the RETSCP finite element computer program (NASA CR-134640). The analysis included thermal and pressure loads, and the effects of temperature dependent material properties, to determine the strain range corresponding to the thruster operating cycle. The configuration and operating conditions considered, correspond to a flightweight integrated thruster assembly which was thrust pulse tested at the NASA Lewis Research Center. The computed strain range was used in conjunction with Haynes 188 Universal Slopes minimum life data to predict throat section fatigue life. The computed number of cycles to failure was greater than the number of pulses to which the thruster was experimentally subjected without failure.