Application of Single Ignition Test to the Igniter Design of Small Solid Rocket Motor
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Abstract:
The roles and aims of the single ignition test of the igniters, which used in small solid rocket motor, were introduced in this paper. Based on a lot of single ignition tests, the influence of mass of ignition powder, initial ignition volume, the design status of the nozzle closure and environmental conditions on the ignition characteristic of igniters were also analyzed. According to the single ignition tests results, some measures, such as changing the ignition manners, adjusting the ignition charge etc, had been adopted in the redesign of the igniter. The research indicated that the design modification had been utilized to solve the ignition delay, the ignition failure under low temperature etc ever occurred in the initial design completely.Keywords:
Solid-fuel rocket
Rocket (weapon)
Ignition timing
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To realize reliably ignition for a small-scale solid rocket motor(SRM),a aft-ignition manner and a fore-ignition manner were designed and worked in SRM ground tests respectively,and the effect of installation position on ignition performance of ignition device was analyzed.The test result indicated that the aft-ignition manner in which the ignition device was mounted on nozzle closure,was not in favour of igniting for the motor.Compared with the aft-ignition manner,ignition charge mass needed in the fore-ignition manner,in which the ignition device was mounted on forward dome of SRM,was reduced 50%.The ignition performance of fore-ignition manner was increased efficiently and every performance can meet the requirements of the SRM ignition.
Solid-fuel rocket
Ignition timing
Rocket (weapon)
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According to the igniter design of similar solid rocket motors,celluloid was adopted as the igniter case and black powder as the amorce.Ignition pressure was chosen as a criterion of igniting the propellant.Based on the experimental formula of fore-ignition design,the initial amorce mass of a small solid rocket motor with end-and-lateral burning grain and aft-ignition manner was estimated firstly.A simulation combustion container was made to obtain the ignition characteristics of the igniter,such as the ignition peak,the delay time,and the opening manner of the nozzle closure.The ignition tests of the primers ignition manner and electric-squib ignition manner at different conditions were studied respectively.The results indicated that,though the amorce mass was the same,the ignition pressure,the ignition delay and opened manner of the nozzle closure were different.Finally,the electric-squib ignition manner was regarded as the suitable choice due to the thought of reliability and maintainability for the solid rocket motor and checked in a lot of motor ignition successfully.
Solid-fuel rocket
Closure (psychology)
Deflagration
Rocket (weapon)
Internal ballistics
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A kind of igniter has been designed for minute solid rocket motor. Many tests have been done to determine the ignition characteristics of minute solid rocket motor. A concept of initial ignition pressure has been introduced the principal principle which effected ignition delay time scatter has been found and determined the ignition scheme satisfying the demand for ignition performance of minute solid rocket motor determined.
Solid-fuel rocket
Rocket (weapon)
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Based on the improvement of heat transfer efficiency between the firing unit and igniter, the low temperature ignition failure occurred in the development of a small solid rocket motor was solved by means of changing the installation manner from free to adhesion; Through moving the ignition powder towards to the center of the igniter case and enhancing the ignition ability of the firing unit, an ignition failure occurred in a similar motor at low temperature would be also solved established on the successful simulation ignition test.
Flammable liquid
Solid-fuel rocket
Rocket (weapon)
Autoignition temperature
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