Abstract For satellite design engineers, an exhaust plume from a liquid rocket engine has been classified as a potential source of local heat load and surface contamination on payload sensors or equipment because several kinds of chemical species at relatively high temperatures can severely impact on the performance of optically-sensitive components. Hence, an accurate prediction of plume influence on a given satellite configuration is an essential task for the satellite development process. In this sense, the objective of the present study was to focus on a numerical investigation of the detailed plume behavior of a liquid apogee engine (LAE) and its influence on a geostationary orbit (GEO) satellite. To deal with different continuum and rarefied flow regimes for the inside and outside of an engine nozzle during LAE operation, a combined approach of computational fluid dynamics (CFD) and parallelized Direct Simulation Monte Carlo (DSMC) was used to simulate the plume flow efficiently. Using the simulation results of the present study, the detailed plume behavior of the LAE and its influence were evaluated and analyzed on a three-dimensional satellite configuration during the early orbit raising phase condition.

中文翻译：

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使用并行 DSMC 方法对 GEO 卫星液体远地点引擎的羽流模拟

摘要 对于卫星设计工程师而言，液体火箭发动机的排气羽流已被归类为有效载荷传感器或设备局部热负荷和表面污染的潜在来源，因为在相对较高的温度下，几种化学物质会严重影响火箭发动机的性能。光敏元件。因此，准确预测羽流对给定卫星配置的影响是卫星开发过程中的一项基本任务。从这个意义上说，本研究的目标是对液体远地点发动机 (LAE) 的详细羽流行为及其对地球静止轨道 (GEO) 卫星的影响进行数值研究。为了在 LAE 操作期间处理发动机喷嘴内部和外部的不同连续介质和稀薄流态，计算流体动力学 (CFD) 和并行直接模拟蒙特卡罗 (DSMC) 的组合方法用于有效模拟羽流。使用本研究的模拟结果，在早期升轨阶段条件下，在三维卫星配置上评估和分析了 LAE 的详细羽流行为及其影响。