The invention discloses a whole-flight liquid-
oxygen input flow simulating test device for a
rocket engine. The device includes a simulating tank, a conveying
pipe, a flow meter, a low-temperature pneumatic
ball valve, low-temperature manually-operated ball valves, a pore plate and a
discharge pipe and is used for realizing whole-flight liquid-
oxygen input flow
simulation of the
rocket engine. The simulating device uses the pressure of the simulating tank as a power and adopts the bore plate and the low-temperature manually-operated ball valves, which are connected in parallel, as flow control and adjustment elements so that demands that under different flight conditions of a pressurization
system, a liquid-
oxygen input flow is within a range of XX.X+-1L / s are met. In the whole-flight liquid-oxygen input flow simulating test device for the
rocket engine, the liquid-oxygen
discharge pipe adopts an aluminum pipe which is 200mm in drift
diameter and 30m in length. During installation, an entrance of the
discharge pipe is higher than an exit and the axis of the discharge pipe forms an angle of 7 degrees with the plane. The outside of the pipe is thermally insulated through
polyurethane foaming so that
liquid oxygen safe
processing is realized and at the same time, effects of the backpressure of oxygen steam in the pipe on the input flow are reduced. The
system is simple, convenient to operate, high in adjustability and low in test cost.