The paper presents a description and the technical characteristics of newly created and upgraded systemsof automated thermovacuum fire stand for testing and research of the workflow of liquid rocket thrusters (smallthrust jet engines) working on hypergolic propellant components. The stand allows to determine the energy anddynamic characteristics of small thrust jet engine with thrust from 0.1 to 100 N in the continuous and pulsed operatingmodes; to explore the intrachamber workflows; to study kinetic properties of gasified liquid intermediatesof liquid-phase interaction of hypergolic propellants; to explore the thermal state of the engine under highaltitude conditions; to provide research of the power, heat and polluting impacts of small thrust jet engine jet onelements of structure surface of the spacecraft; to explore of diagnostic methods of the small thrust jet enginefunctioning and others. Automated measuring and information system of the stand provides small thrust jet enginemanagement on a given cyclogram; carrying out the calibration of channels for measurement of parametersof small thrust jet engine: thrust, flow rate of components, pressure, temperature, etc.; collecting informationfrom the measuring channels of the stand during tests and information storage on the hard disk; processing ofmeasurement results on the computer during the test and their representation in the required form (protocols,characteristics, charts and tables); formation of database of engines studied. For measuring the temperature of theouter surface of the chamber of small thrust jet engine is used contactless method using an infrared thermal imagingsystem. Complex work for improvement of element base and systems of automated thermovacuum firestand for testing and research of workflow of small thrust jet engine working on hypergolic fuel components wasexpanded the opportunities of stand in the field of new tasks statement for workflow working off and increasethe accuracy of the main parameters measurement for the engines.