| 摘要 |
FIELD: rocketry; self-propelled missiles; volley fire systems. ^ SUBSTANCE: proposed solid-propellant rocket engine has housing, nozzle unit, igniter and electric igniter. Igniter and electric igniter are arranged in axial tube in supersonic part of nozzle unit. Plate and bushing connected with nozzle unit are secured on ends of axial tube. Bushing is connected with nozzle unit by stop with fixed shear force made in form of ring joint. Ring with axial hole is installed coaxially with axial tube in supersonic part of nozzle unit by means of easily detachable glue joint. Diameter of axial hole of ring is 1.1-1.2 of outer diameter of axial tube. ^ EFFECT: reduced spread of characteristics of solid-propellant rocket engine during ignition period. ^ 1 dwg |
