The invention provides a non-load-sharing piezoelectric thrust test device, belongs to the technical field of sensors and measuring and control technology, and particularly relates to the test technology of the pulse thrust of
attitude control rocket engine. The test device comprises an outer shell, an inner shell, four
piezoelectric quartz sensors, four square press plates, four support rods, an engine installation
flange, pre-fastening bolts and connection bolts.
Piezoelectric quartz sensors made of four YO
cut type
quartz chip resemble
a diamond shape and are located between the inner shell and the outer shell. Four pre-fastening bolts and square press plates are used for pressing all the
piezoelectric quartz sensors tightly.
Rocket thrust force generated by fuel ejection is transmitted to the piezoelectric sensors through the installation
flange, the four support rods and the inner shell, thus eliminating the load division phenomenon in the traditional piezoelectric test
system caused by bolts connection or an elastic ring clamping which are adopted by the
piezoelectric quartz sensors for pre-fastening, and enhancing the sensitivity and the dynamic measurement accuracy of the test
system. The device has the advantages of having high sensitivity, good
frequency response performance, being high in dynamic measurement accuracy, therefore can be adopted for testing the pulse thrust of the
attitude control rocket engine.