METHOD FOR SEPARATION OF ACCELERATING ENGINE OF CONED-BORE ROCKET AND ROCKET FOR ITS REALISATION Russian patent published in 2010 - IPC F42B15/00 

FIELD: defense technology.

SUBSTANCE: accelerating engine is separated, including damping of disturbance moment acting at sustainer by means of transition fairing installed on after-part of sustainer and joined to front part of accelerating engine. At the moment sustainer separates from accelerating engine, fairing is disconnected from accelerating engine and is moved along after-part of sustainer through longitudinal force pulse in direction of flight. Then force of approaching air flow is used to move fairing towards back end of sustainer and discharged. In case attack angles of sustainer are available, force of fairing friction against after-part of sustainer is increased. Rocket comprises accelerating engine telescopically installed on after-part of sustainer, piston with powder charge and skirt that covers back end of sustainer, stop in front part of accelerating engine and transition fairing, which is installed on after-part of sustainer to create circular gap. Its back end is pressed to stop by means of threaded joint, and on inner surface of fairing there are circular bores arranged, where elastic deformable elements of friction material are installed.

EFFECT: improved reliability of rocket sustainer disturbances damping in process of separation.

2 cl, 2 dwg