FIELD: rocket and space engineering.
SUBSTANCE: invention relates to aerospace engineering and can be used in development of both disposable and reusable stages of carrier rocket. Propulsion system containing independent two-chamber engines with crosswise installed relative to each other chambers, wherein each engine is designed according to the scheme with a gas generator with or without generator gas afterburning and comprises gas generator, power supply, automation and control units. To ensure restart, at least one of the engines can be equipped with a multiple ignition system, which can be chemical, laser or electric – electroplasma or electric spark.
EFFECT: invention differs from known designs in that one of said engines features higher thrust while its chambers are fixed while every engine chamber with smaller thrust is equipped with drives and can be deflected within circular cone.
13 cl, 4 dwg
