THRUST CONTROL DEVICE FOR THE PROPULSION SYSTEMS OF THE SOYUZ-2 AND ANGARA SPACE ROCKETS, BASED ON THE ASSESSMENT OF THE CURRENT VALUES OF THRUST DURING FLIGHT ACCORDING TO TELEMETRIC INFORMATION FOR FALLING SEPARABLE PARTS INTO A GIVEN AREA Russian patent published in 2023 - IPC B64G1/00 

FIELD: rocket engineering.

SUBSTANCE: devices for analyzing the flight performance of space rockets (SR) and controlling the power supply system for space rocket propulsion systems during flight. The thrust control device for the propulsion systems (PS) of the Soyuz-2 and Angara space rockets, based on the assessment of the current values of thrust during flight according to telemetric information (TMI) for falling separable parts (SP) into a given area, consists of a filtering unit and rejection of TMI and information storage unit, the outputs of which are connected to the input of an arithmetic logic unit (ALU), the output of which is connected to a converter into command signals, which directly transmits control signals to the executive bodies of the apparent speed control system in order to control the PS thrust. The ALU is configured to provide calculation of the values of changes in the propulsion characteristics of the PS and the thrust coefficient of the propulsion system based on the TMI parameters at the pace of flight and the data coming from the onboard computer (OBC) and the information storage unit.

EFFECT: increased accuracy of hitting SP in a given dispersion ellipse.

1 cl, 1 dwg