In order to understand the ignition risk and fire hazard of LOX/kerosene leakage at space rocket launching sites, the experimental methods of kerosene ignition in oxygen-rich atmosphere will be established focusing on fire safety issues of kerosene. The mixture of oxygen and kerosene vapor was formed in a semi-closed experimental space by heating rocket kerosene, while the ignition test of rocket kerosene under different initial kerosene temperature and oxygen concentration were carried out by electric ignition. The results showed that the ignition risk of kerosene vapor increased with the increase of oxygen concentration, while the ignition energy required for kerosene ignition decreased with the increase of oxygen concentration. The ignition energy required for ignition of kerosene had a better linear relationship with the reciprocal of the kerosene initial kerosene temperature. Under the condition of same oxygen concentration, the higher initial kerosene temperature, the smaller the ignition energy required for ignition of kerosene. By theoretical analysis of the relationship between kerosene ignition energy(E) and ignition time(Ï„), oxygen concentration (x) and initial oil temperature(T), the ln(E/T2) and ln(t) can be correlated well with the form of (k/T+C(x)), where k is a constant and C(x) is also a constant related to the oxygen concentration. The research results can provide key scientific data and models for the fire risk assessment of LOX/kerosene leakage.
Keywords oxygen-rich atmosphere, rocket kerosene, initial kerosene temperature, ignition time, ignition energy