| 摘要 |
FIELD: rocket engines. ^ SUBSTANCE: proposed method of monitoring and control of thermal conditions of outflow of combustion products in combustion products localization and cooling chamber includes localization and cooling of combustion products of solid propellant rocket engine by water At outflow of combustion products, temperature in each section of combustion products localization and cooling chamber is measured and additional amount of water and neutralizing solution is delivered in case of temperature rise over upper strength limit of section material. At destruction of charge, minimum pressure in gas holder (receiver) of 0.8 MPa is maintained and pressure of 0.6 MPa before shutters of water supply line, 0.4 MPa in independent water ducts before each shutoff and starting device of section and not less than 0.2 MPa before atomizing nozzles, are provided and volumetric water flow rate in each section is set to 0.5 - 1 cu.m/s. Combustion products localization and cooling chamber for implementing the method contains intake chamber consisting of separate sections including intake section, transient section and mixing and neutralizing chamber. Said sections are provided with independent water ducts, 1 - 4 pieces, and atomizing nozzles, 16 to 1000 pieces. Length of intake section is 1:1 of length of solid-propellant rocket engine, and length of mixing and neutralizing chamber is 4:1 of length of solid-propellant rocket engine. ^ EFFECT: reduced velocity of combustion products and their temperature to temperatures for effective neutralization of harmful matter, prevention of burning-through of housing of localization and cooling chamber sections. ^ 7 cl, 13 dwg |
