QJ 1188-1987 in English

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

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