FIELD: astronautics.
SUBSTANCE: invention relates to a general field of aeronautics, in particular, it relates to control over the rocket engine. Method comprises: a stage (E10) of obtaining of a controlled parameter measurement, measured by a sensor and a corresponding to the engine operating point, wherein this operating point is determined by at least one parameter of engine regulation; a stage (E20) of the monitored parameter value estimating for this operating point based on a controlled value or a filtered set value of said at least one engine regulation parameter defining the operating point; error comparing stage (E40) between the monitored parameter measuring and its evaluation with respect to at least one threshold determined based on an error on said fault, estimated for the operating point; and a notification transmission stage (E60) in the event of a transition of said at least one threshold. Also provided are computer-readable storage medium on which a computer program is recorded containing instructions for performing of the control method stages, a rocket engine parameter monitoring device, and a rocket engine containing such device.
EFFECT: invention enables control over the rocket engine, which allows to detect affecting the rocket engine anomalies, both in real time and in delayed time.
12 cl, 7 dwg
