| 摘要 |
FIELD: rocketry; methods of ignition of solid-propellant charge. ^ SUBSTANCE: proposed method comes to ignition of igniter, propagation of burning products to charge, heating of charge surface and subsequent ignition of charge. First combustion products from igniter placed in semiclosed space of engine combustion chamber are directed to front end face of charge. After ignition of part of charge surface, combustion products from igniter are delivered to rear end face of charge. After combustion of igniter combustion products of charge formed at front end face are passed through space into prenozzle space of engine. Method of ignition of charge is implemented in solid-propellant rocket engine containing combustion chamber with nozzle unit, igniter and multigrain charge with support grid. Tube is secured on support grid from side of nozzle unit coaxially to chamber. Tube is divided into two spaces by partition with through holes closed by diaphragm. Diaphragm is installed between end face of partition and end face of igniter arranged in space pointed to front end face of charge. Annular channel is formed between free end of tube and front bottom of combustion chamber. Area of said channel is chosen to provide the following condition: summary area of holes in partition should be smaller than area of channel which, in its turn, should be smaller than area of cross section of tube. ^ EFFECT: increased reliability of solid-propellant rocket engine with charge with large relative elongation in wide temperature range. ^ 3 cl, 1 dwg |
