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Acta Armamentarii ›› 2022, Vol. 43 ›› Issue (8): 1792-1807.doi: 10.12382/bgxb.2021.0321

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Influence of Gas-particle Two-phase Flow on Ignition of the Solid Rocket Motor under Lateral Acceleration

GUAN Dian1, GUO Yawen2, LI Shipeng2, TANG Jianing3, WANG Ningfei2   

  1. (1.Beijing System Design Institute of Electro-mechanic Engineering, Beijing 100854 China; 2.School of Aerospace Engineering,Beijing Institute of Technology, Beijing 100081, China; 3.School of Electrical and Information Technology, Yunnan Minzu University, Kunming 650500, Yunan, China)
  • Online:2022-08-12

Abstract: 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 pmax, 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.

Key words: solidpropellantrocket, lateralacceleration, particlecollisionheattransfers, numericalsimulation, ignitioninterval

CLC Number: