Abstract
The influence caused by the temperature to the pulsed thrust test stand (PTTS) for the attitude control rocket engine is analyzed. It's evident that the primary cause of the temperature influence to PTTS leaded by the rocket engine is the thermal deformation located in the mechanical joint elements as well as the thermal stress generated from the deformation. And a series tests have been conducted to validate the accuracy of the theoretical analysis. A test bolt gluing a strain-gauge is developed to measure the thermal stress generated between the flange and the upper cover of the thrust dynamometer and compensate PTTS voltages shift in the temperature varying conditions. Tests results demonstrate that it is possible to implement temperature compensation to PTTS by the test bolts.
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