| Many researches on propulsion technology are being conducted presently. Micro-propulsion system, based on a thermal propulsion principle, is also widely concerned because of its extensive applications. The performance of a propulsion system largely depends on the rationality of the chambers design. This paper aims to study a solar thermal micro-propulsion system, which is designed by a research team of our college. The research mainly focused on the flow and the heat transfer characteristics of the platelet heat exchanger core which is important for the chamber of a micro-propulsion system.Firstly, the finite volume method was introduced to solve the N-S equation and 2D/3D models were developed. The effect of the channel size was studied by program. The 2D and 3D results were compared with each other.The result shows that the increase of channel’s section enlarges the pressure but reduces the Mach number.The temperature and the dencity are merely influenced. These data can be used to design the chamber.Secondly, a parallel method was adapted to improve the calculation efficiency. The codes were modified for execute parallel computation. After a brief depiction of the parallel method, some simple cases were employed to testify the validity of the parallel method. Compared with results of single computational algorithm, we came to the conclusion that the parallel computational algorithm is valid.At last, the micro-channel flow was simulated using the DSMC method. The DSMC method used in solving rarefied gas dynamics was introduced including the application of the parallel method in the DSMC. After verifying the paralleled DSMC method, it was used to solve the problems of this thesis for rarefied gas flow. The results showed that the flow field of rarefied gas was quite different from the one of continuous gas. The distribution of the parameters such as temperature and the Mach number etc shows rarefied gas dynamic properties. |
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