MOCKUP ENGINE FOR DETERMINING BURNING RATE OF ROCKET SOLID PROPELLANT

摘要

FIELD: rocketry; testing facilities. SUBSTANCE: proposed engine for determining rate of burning of rocket solid propellants serves for finding power law dependence of burning rate in form of u = u₁•P^ν, where u is burning rate, u₁ is coefficient, P is pressure and ν is power index. Engine has cylindrical housing, glued-in channel accompanying charge, end face covers, pressure transmitter, nozzle and igniter. Accompanying charge is made of rocket solid propellant with power index ν not exceeding 0.3 in power law dependence of burning rate from pressure. Housing is butt-joined with additional housing and charge of the same dimensions. Middle cylindrical part of additional charge consists of several channel disk charges of rocket solid propellants to be tested having power index ν in power law dependence of burning rate from pressure not less than 0.9. Disk charges are glued to each other by epoxy compound. Burning rate of accompanying charge is greater than burning rates of channel disk charges. EFFECT: possibility of determining burning rate of rocket solid propellant on several samples under conditions close to their burning in full-scale solid propellant rocket engine. 3 dwg