Abstract
Aiming at the ignition process of micro solid rocket motor in space, the effects of different structure on the ignition gas filling process were investigated by means of experiment and numerical simulation. By establishing numerical simulation model and the mass flow rate model of ignition chamber for black powder, pressure establishment process was researched under different parameters (the igniter quantity is 0.2g and 0.5g, outlet size of ignition chamber is Φ4mm and Φ7mm respectively). Meanwhile, the ignition experiment was conducted in vacuum (the ambient pressure is 16Pa) that pressure curve and vacuum plume phenomenon were obtained. The results indicate that simulation value of pressure establishing process relatively consistent with experimental one, so the mass flow rate model of ignition chamber for the black powder is evidently efficient. Therefore, the numerical method proposed in this paper can provide a theoretical basis for further research on the ignition process of micro solid rocket motor.
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