| Kinetic Simulation of Nozzle Flow in a Micronewton-Class Cold Gas Thruster | |
Sun WJ(孙文进)1,3 ; Liu, Xuhui2; Long, Jun2; Wang, Xudong2; Sun QH(孙泉华)1,3; Huang HJ(黄河激)1,3; Li, Yong2; Hu Y(胡远)1
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| Corresponding Author | Li, Yong([email protected]) ; Hu, Yuan([email protected]) |
| Source Publication | AIAA JOURNAL
 |
| 2024-08-27 | |
| Pages | 10 |
| ISSN | 0001-1452 |
| Abstract | Many scientific space missions need highly precise attitude and orbit control or ultrafine drag compensation, which relies on the variable-thrust propulsion technology operating at the micronewton level. Cold gas thruster (CGT) is a very promising solution, mainly because of its high reliability. One of the keys to the success of micronewton variable-thrust CGT is to understand the flow in its nozzle, whose configuration is much more complex than traditional CGT nozzles. This paper applies kinetic-based multiscale models to investigate the gas flow in the complex nozzle of a micronewton variable-thrust CGT. The simulations reveal that the flow simultaneously experiences all kinds of regimes from continuum to free molecular. The continuum breakdown is likely to occur near the throat region due to large gradients of flow variables and in the expander due to low gas density. Frictional choking is observed, and the nozzle length can be optimized to improve the thruster performance. Nozzle performance measures such as thrust, discharge coefficient, and thrust efficiency are found to change only with the throat Knudsen number Knt. The performance curves can be divided into two sections at Knt similar or equal to 0.1, and thereby an empirical piecewise formula for thrust prediction is proposed. |
| Keyword | Direct Simulation Monte Carlo Micro Thruster Variable Thrust Multiscale Flow Continuum Breakdown |
| DOI | 10.2514/1.J064335 |
| Indexed By | SCI ; EI |
| Language | 英语 |
| WOS ID | WOS:001302135900001 |
| WOS Keyword | PLANCK-DSMC ALGORITHM ; LOW-DENSITY NOZZLE ; MONTE-CARLO ; NUMERICAL SIMULATIONS ; PERFORMANCE ; EQUATIONS ; BOLTZMANN |
| WOS Research Area | Engineering |
| WOS Subject | Engineering, Aerospace |
| Funding Project | National Key Research and Development Program of China[U21B2074] ; National Natural Science Foundation of China[2020YFC2201100] |
| Funding Organization | National Key Research and Development Program of China ; National Natural Science Foundation of China |
| Classification | 一类/力学重要期刊 |
| Ranking | 1 |
| Contributor | Li, Yong ; Hu, Yuan |
| Citation statistics | |
| Document Type | 期刊论文 |
| Identifier | http://dspace.imech.ac.cn/handle/311007/96473 |
| Collection | 高温气体动力学国家重点实验室 |
| Affiliation | 1.Chinese Acad Sci, Inst Mech, State Key Lab High Temp Gas Dynam, Beijing 100190, Peoples R China; 2.Beijing Inst Control Engn, Beijing 100190, Peoples R China; 3.Univ Chinese Acad Sci, Sch Engn Sci, Beijing 100094, Peoples R China |
| Recommended Citation GB/T 7714 | Sun WJ,Liu, Xuhui,Long, Jun,et al. Kinetic Simulation of Nozzle Flow in a Micronewton-Class Cold Gas Thruster[J]. AIAA JOURNAL,2024:10.Rp_Au:Li, Yong, Hu, Yuan |
| APA | 孙文进.,Liu, Xuhui.,Long, Jun.,Wang, Xudong.,孙泉华.,...&胡远.(2024).Kinetic Simulation of Nozzle Flow in a Micronewton-Class Cold Gas Thruster.AIAA JOURNAL,10. |
| MLA | 孙文进,et al."Kinetic Simulation of Nozzle Flow in a Micronewton-Class Cold Gas Thruster".AIAA JOURNAL (2024):10. |
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