横向过载下气- 粒两相流对固体火箭发动机点火过程影响

Due to the acceleration environment induced by the high-speed spinning of the solid rocket, the coupling relationships of flow, heat transfer and combustion are obviously different from those in the conventional ignition process, posing a potential threat to ignition reliability and projectile safety. To investigate the ignition characteristics solid rocket motor under acceleration, a new comprehensive ignition model considering the inertial acceleration field effect of the fluid and particle, particle collision heat-transfer enhancement of propellant, acceleration-induced combustion and erosion is developed . The dynamic gas-particle distribution law is obtained during ignition under lateral acceleration of the different directions and particle sizes. The influence of particle size and acceleration on pressure peak p_max, ignition delay time ξ₁, flame propagation time ξ₂ and flame filling time ξ₃ in the ignition process is analyzed. The results show that the gas-particle distribution is effectively changed by the acceleration-loads direction, which affects the heat transfer of the propellant and the shortening of the internal ballistics in the time domain. Under the same acceleration-loads condition, the smaller particle size, the shorter the ignition delay time ξ₁ and the flame propagation time ξ₂, while the effect on the flame filling time ξ₃ can be basically ignored. At the same particle size condition, the ignition delay time ξ is reduced by the increased acceleration-loads for large aspect ratio solid rocket.