Detail of QJ 1188-1987

Introduction of QJ 1188-1987

QJ 1188-1987 Terminology for solid rocket motors Terminology for solid rocket motors This standard specifies the definitions, units and symbols of the main terms commonly used in scientific research, design, test and service of solid rocket motors in the Ministry of Aerospace Industry. 1 Motor classification 1.1 rocket motor jet motor that directly generates thrust by the reaction principle of force using the energy and working medium carried by the aircraft itself, which is independent of the ambient atmosphere 1.2 chemical rocket motor rocket motor using chemical propellant, which converts the chemical energy of chemical propellant into heat energy to form high-temperature gas, and then ejects it at high speed through nozzle to generate a reaction thrust 1.3 solid rocket motor, SRM chemical rocket motor using solid propellant 1.4 segmented solid rocket motor solid rocket motor with the combustion chamber case and the propellant loaded manufactured and assembled in segments 1.5 pulse solid rocket motor solid rocket motor with multiple ignition starts, multiple flameouts and available thrust-time curve of variable pulse waveform, which may be classified into single pulse, double pulse or multi-pulse solid rocket motor according to the number of starts 1.6 dual thrust solid rocket motor solid rocket motor capable of generating two thrust stages in one operation 1.7 standard testing motor solid rocket motor with the same specification, operating conditions and operating rules, which is used to identify the performance such as specific impulse and burning rate of solid propellant 2 Performance parameters 2.1 pressure-time curve, p-t curve indicating the variation of combustion chamber pressure with time during the working process of solid rocket motor 2.2 thrust-time curve, F-t curve indicating the variation of thrust with time during the working process of solid rocket motor 2.3 combustion chamber pressure, pc pressure of gas in combustion chamber, which shall be taken as the total instantaneous pressure of gas at the head of combustion chamber when used to calculate the performance of solid rocket motor Unit: Pascal; symbol: Pa 2.4 initial pressure, pi pressure when the combustion chamber pressure rises to 5% of the design average pressure during burning time after motor ignition Unit: Pascal; symbol: Pa 2.5 expected initial pressure, pie pressure when the combustion chamber pressure rises to a design expected pressure value after motor ignition Unit: Pascal; symbol: Pa 2.6 maximum pressure, pmax maximum pressure except the initial pressure peak on the pressure-time curve during the working process of solid rocket motor Unit: Pascal; symbol: Pa 2.7 cutoff instantaneous pressure, pcu instantaneous combustion chamber pressure at the cutoff of solid rocket motor Unit: Pascal; symbol: Pa 2.8 burn final pressure, pfb instantaneous pressure at the end of burning of grain along web thickness Unit: Pascal; symbol: Pa 2.9 effective action time final pressure, pfef design expected pressure at the end of motor action Unit: Pascal; symbol: Pa

Contents of QJ 1188-1987

1 Motor classification 2 Performance parameters 3 Construction 4 Test Additional explanation