Rapid calculation system for pulse residual impulses of liquid-propellant rocket engine

The invention provides a rapid calculation system for the pulse residual impulses of a liquid-propellant rocket engine. The rapid calculation system comprises a data collecting device, a power supply device, a combustion chamber pressure indicating switch, a valve current indicating switch, a pulse information device, a pulse number recorder, a pulse width recorder, an impulse register and a display interface. The data collecting device is used for collecting test parameters and synchronously shunting combustion chamber pressure information included in the test parameters and valve current pulse signals used for controlling a combustion chamber to be opened and closed. The combustion chamber pressure indicating switch is used for indicating the start time and the end time of the residual impulses. The valve current indicating switch is used for indicating the start time and the end time of valve current pulse signals. The pulse information device is used for updating the number of pulses stored in the pulse number recorder, and the pulse width recorder is used for analyzing the pulse widths. The impulse register is used for calculating the residual impulses. The display interface is used for displaying residual impulse integral results corresponding to all the pulses.