Development of high-speed aerodynamic simulator of aerobraking spacecraft

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The massively parallel computing system for simulating the aerodynamic characteristics of the aerobraking spacecraft was investigated. The simulation scheme is the direct simulation Monte Carlo method, which is widely used for the rarefied gas flow. the conceptural design for the unit of the massively parallel computing system was carried out. It is found that the unit of the massively parallel computing system is realized by the pipeline method, and is composed not of the central procession unit but of the distributed processing units. The trail manufacturing of the unit was successfully conducted and demonstrated the computation performance as was expected. The computation preformance of the unit is proportional to the system clock sped and reached about 0.3 GFLOOPS for the 20 MHz system clock. The more computational performance can be attained by a proper manufacturing of the system. Furthermore the computational performance will be significantly enhanced by realizing the unit as an integrated circuit. The bottle neck of the present computational performance is the communication speed between the host computer, which can be improved by means of more high-speed communication bas system like PCI.It is also found the idea for the present computing system is applicable to various simulation schemes for the fluid motion. Especially the LB (Lattice Boltzmann) method is suitable to such an application. The conceptual disign for the computing system for the fluid simulation based on LB method was carried out.