Numerical Modeling of the Processes within the Combustion Chamber of a Solid Propellant Rocket Engine during the Stabilization of the Design Operation Mode

G. N. Amarantov; M. Yu. Egorov; S. M. Egorov; D. M. Egorov; V. I. Nekrasov

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Numerical Modeling of the Processes within the Combustion Chamber of a Solid Propellant Rocket Engine during the Stabilization of the Design Operation Mode

机译：设计运行模式稳定过程中固体推进剂火箭发动机燃烧室内过程的数值模拟

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Comprehensive numerical modeling of the processes occurring in the combustion chamber of a solid propellant rocket engine during the stabilization of the design operation mode is performed. The self-consistent problem considered includes nonstationary operation of an ignition device, warmup and ignition of a solid propellant charge followed by its nonstationary burning, nonstationary three-phase homogeneous-heterogeneous flow of the combustion products in the combustion chamber, in the nozzle, and behind the engine nozzle unit, engine depressurization, and nozzle unit plug blowing-out. The results of the calculations are presented.

机译：在设计操作模式稳定期间，对固体推进剂火箭发动机燃烧室中发生的过程进行了全面的数值建模。所考虑的自洽问题包括点火装置的非平稳运行，固体推进剂装料的预热和点火，然后是燃烧室，喷嘴中燃烧产物的非平稳燃烧，三相非均相非均匀流动。在发动机喷嘴单元后面，发动机降压和喷嘴单元塞子喷出。给出了计算结果。

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《Fluid Dynamics》 |2011年第3期|共12页
作者
G. N. Amarantov; M. Yu. Egorov; S. M. Egorov; D. M. Egorov; V. I. Nekrasov;
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正文语种 eng
中图分类流体力学;
关键词
Numerical modeling; Processes in combustion chambers; Solid propellant rocket engine;

机译：数值模拟;燃烧室中的过程;固体推进剂火箭发动机;

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1. Numerical Modeling of the Processes within the Combustion Chamber of a Solid Propellant Rocket Engine during the Stabilization of the Design Operation Mode [J] . G. N. Amarantov, M. Yu. Egorov, S. M. Egorov, Fluid Dynamics . 2011,第3期

机译：设计运行模式稳定过程中固体推进剂火箭发动机燃烧室内过程的数值模拟
2. Mathematical Modeling and Experimental Investigations of Oxygen-Methane Fuel Combustion at Coaxial-Jet Supply into the Combustion Chamber of Liquid-Propellant Rocket Engine [J] . V. R. Rubinskii, S. P. Khrisanfov, V. Yu. Klimov, Russian Aeronautics . 2010,第1期

机译：液体推进火箭发动机同轴射流供氧-甲烷燃料燃烧的数学模型与实验研究
3. Modeling and Simulation of Solid Propellant Particle Path in the Combustion Chamber of a Solid Rocket Motor [J] . R. S. AMANO, YUMIN XIAO Heat Transfer Research . 2008,第3期

机译：固体火箭发动机燃烧室内固体推进剂颗粒路径的建模与仿真
4. Vaporization-controlled simplified model for liquid propellant rocket engine combustion chamber design [C] . H Belal, Ah El-S Makled, M A Al-Sanabawy International Conference on Aerospace Sciences Aviation Technology . 2019

机译：液相推进剂火箭发动机燃烧室设计汽化控制的简化模型
5. Numerical modeling of boundary-layer cooling of rocket engine combustion chambers. [D] . Pitalo, Gerald Alexander. 2000

机译：火箭发动机燃烧室边界层冷却的数值模型。
6. Stability of combustion waves in a simplified gas–solid combustion model in porous media [O] . Fatih Ozbag, Stephen Schecter -1

机译：多孔介质中简化气固燃烧模型中燃烧波的稳定性
7. On the question of solid-propellant rocket engine design preventing unstable operation in the combustion chamber [O] . G. A. Glebov, S. A. Vysotskaya 2017

机译：关于固体推进剂火箭发动机设计的问题，防止燃烧室中不稳定运行

Numerical Modeling of the Processes within the Combustion Chamber of a Solid Propellant Rocket Engine during the Stabilization of the Design Operation Mode

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