FIELD: space engineering; terminal control of cryogenic stages with non-adjustable cruise engines. SUBSTANCE: proposed system includes phantom acceleration meter, reciprocal magnitude finder and first integrator connected in succession. First integrator is connected to first input of arbitrary time computer. Provision is also made for time counter whose output is connected to second input of said computer through time adder and clock period counter whose output is connected to third input of computer. System is additionally provided with measured interval meter, multiplier, second integrator and divider. Output of said clock period counter is connected to first input of divider through measured interval meter, multiplier and second integrator which are connected in series. Second output of measured interval meter is connected with second input of divider. Output of arbitrary time computer is connected with second input of multiplier. Proposed system reduces effect of spread of rocket engine characteristics on process of control. EFFECT: enhanced accuracy of determination of engine cut-off time. 5 dwg
