| 摘要 |
FIELD: rocketry. ^ SUBSTANCE: invention relates to solid-propellant rocket engines and it can be used in volley fire systems and anti-aircraft rocket complexes, controlled tank-killer rockets, both under development and modernization. Proposed method of manufacture of solid-propellant rocket engine includes placing of engine embedded parts onto end faces of mandrel installed on shaft, laying of heat protection coating, winding of power envelope of housing and heat treatment. Used as mandrel is powder charge of solid-propellant with gas outlet channel equidistant to shaft of mandrel. Sealing layer is placed between embedded parts of engine and heat protection coating. Heat treatment of wound housing of rocket engine is provided by cold curing method. ^ EFFECT: provision of solid-propellant propellant rocket engine with high coefficient of filling of combustion chamber. ^ 3 cl, 2 dwg |
