ROCKET CONTROL SYSTEM WITH MULTISTAGE SOLID FUEL ENGINE Russian patent published in 2023 - IPC F02K9/08 

FIELD: propulsion systems.

SUBSTANCE: invention relates to propulsion systems for launch vehicles (in particular, small ones) and interceptor missiles for extra-atmospheric and fast-flying targets. The proposed rocket contains a control system (CS) and a multi-stage solid propellant engine, consisting of a plurality of combustion chambers (CC) (1) connected to each other in a longitudinal pattern and equipped with a mechanism (4) for automatic combustion transfer between them. The combustors are separated one by one as the fuel in them burns out. In this case, the control system has servos in the head stage, the action of which is transmitted (by rods 11) to all underlying stages, without creating interruptions in control. The executive bodies of the control system are made in the form of hinged (in areas I) steering dampers, combined with cutouts in the supercritical part of the CC nozzles. These dampers have mechanical connections between themselves that do not interfere with the separation of stages.

EFFECT: ensuring effective manoeuvring of the rocket during flight both in the atmosphere and outside it, as well as in the possibility of quickly configuring stages for a specific flight mission.

4 cl, 6 dwg