The present application relates to the field of
rocket engine
nozzle testing, and particularly relates to a flexible
rocket engine
nozzle cold swing test
simulation test
system and a test method thereof, the
system comprising a
pressure vessel, a
servo mechanism, an
inclinometer, a
linear displacement sensor and a real-time simulator, the
pressure vessel provides a cold pressurized environment, the
servo mechanism drives the
nozzle to swing, the
inclinometer calibrates the swing angle, and the
linear displacement sensor detects the swing and outputs an
analog signal. During testing, the swing angle-
voltage relationship is calibrated through the
inclinometer and the
linear displacement sensor; then the real-time simulator sends a sine instruction to drive the nozzle to swing, and synchronously collects the displacement
signal, analyzes the dynamic characteristics of the
servo mechanism and the coordination with the nozzle. Through the swing angle-
voltage equation obtained by calibrating the swing, combined with continuous attitude
simulation controlled by the simulator, the nozzle swing angle data is calculated, and the dynamic response of the servo mechanism under the pressurized condition is evaluated, the present application can truly reflect the continuous swing working condition of the nozzle, and improve the reliability and authenticity of the
test data.