固体火箭技术2026，Vol.49Issue(3)：468-476,9.DOI:10.7673/j.issn.1006-2793.2026.03.017
高黏度流体药浆离心混合过程温度仿真与实验
Temperature simulation and experiment of centrifugal mixing process for high viscosity fluid slurry
吴睿 1杜鑫立 1段军鸿 2高朦 3吴伟潇 3李锡文1
作者信息
- 1. 华中科技大学 机械科学与工程学院,武汉 430074
- 2. 华中科技大学 机械科学与工程学院,武汉 430074||湖北航天江河化工有限公司,宜昌 444200
- 3. 湖北航天江河化工有限公司,宜昌 444200
- 折叠
摘要
Abstract
In the mixing process of solid propellant preparation,centrifugal mixing equipment achieves efficient blending of components through a combined rotational motion of the container's self-rotation and orbital rotation,forming a high-viscosity fluid slurry.To reveal the temperature change patterns dominated by viscous dissipation during mixing,a finite element analysis model was established using ANSYS Fluent,taking tri-component esterified polypropylene glycol(HTPB)propellant as an example.Static temperature was used as the observation index to study the effects of orbital rotation speed N and the ratio i between self-rotation and orbital rotation speeds on propellant temperature.Results show that the temperature of HTPB propellant exhibits a strong linear correlation with mixing time(r2>0.98),which can be effectively characterized by the average temperature rise ΔT over 10 seconds during mixing.Increasing both orbital and self-rotation speeds leads to higher propellant temperatures,with orbital rotation speed having a more significant impact.When i=-1,increasing the orbital speed from 300 r/min to 600 r/min results in a ΔT of approximately 1.89℃,significantly higher than the 0.72℃increase caused by the same increment in self-rotation speed(at N=600 r/min).Propellant temperature is slightly higher under co-directional rotation compared to counter-directional rotation.The minimum simulated temperature rise ΔT occurs at i=-0.5,corresponding to the highest safety level during the mixing process.关键词
固体推进剂/高黏度流体/离心混合/温度场仿真Key words
solid propellant/high viscosity fluid/centrifugal mixing/temperature field simulation分类
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吴睿,杜鑫立,段军鸿,高朦,吴伟潇,李锡文..高黏度流体药浆离心混合过程温度仿真与实验[J].固体火箭技术,2026,49(3):468-476,9.
