Bifunctional thrust-vector control system of launch vehicle space stage engine
Journal Title: Технічна механіка, Техническая механика, Technical Mechanics - Year 2015, Vol 1, Issue 1
Abstract
The results of the development and research of a bifunctional thrust-vector control system of the liquid rocket cruise engine for advanced upper stages of the Cyclon-4M type launch vehicle are reported to extend the capabilities of thrust-vector control in several times and functional system capabilities in retaining high static, dynamic and overall-mass characteristics of actuator devices for the flight control system of a flight vehicle, to improve the stability of conditions of the flight stabilization and an operational reliability and to decrease power consumption for the flight vehicle trajectory control. The system is based on a simultaneous use of mechanic (gimbal engine swinging) and gas dynamic (a solid plug-type spoiler in supersonic flow for propellant injection) systems. Dynamic qualities and the flight control of the launch vehicle stage are compared under autonomous conditions and in combination with the above-mentioned mechanical and gas dynamical systems of the thrust-vector control. Rational operational conditions for every type of the thrust-vector control system are determined in their simultaneous operation. Physical bases for creating controlled forces and the results of calculations of static and dynamic (controlled) characteristics of every system are presented. The emphasis is on the development of a new gas dynamic system that operates under relay conditions at the flight stabilization and under analogue conditions in control of the stage flight trajectory. Some new solutions for the system of nozzle liquid injection are given
Authors and Affiliations
T. Kovalenko, N. Sirotkina
Keywords
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