Download e-book for iPad: Advances in Computation and Intelligence: Second by Zhuo Kang, Lishan Kang, Xiufen Zou, Minzhong Liu, Changhe

By Zhuo Kang, Lishan Kang, Xiufen Zou, Minzhong Liu, Changhe Li, Ming Yang, Yan Li (auth.), Lishan Kang, Yong Liu, Sanyou Zeng (eds.)

This e-book constitutes the refereed court cases of the second one foreign Symposium on Intelligence Computation and functions, ISICA 2007, held in Wuhan, China, in September 2007. The seventy one revised complete papers have been conscientiously reviewed and chosen from approximately 1000 submissions. the themes contain evolutionary computation, evolutionary studying, neural networks, swarms, trend acceptance, facts mining and others.

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Additional info for Advances in Computation and Intelligence: Second International Symposium, ISICA 2007 Wuhan, China, September 21-23, 2007 Proceedings

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Although the complete range of solutions from constrained to unconstrained minima is Pareto-optimal for minimizing f (x) and CV, in order to find the constrained minimum of f (x), we should concentrate the search effort in a region closer to the constrained minimum. The guided domination based method [1] or other preferred EMO methodologies can be used for this purpose. Here, we suggest and use a reference point based methodology. 38 K. Deb, S. Lele, and R. Datta f Feasible Search space Constrained optimum Pareto−optimal front Region of interest Unconstrained optimum 0 CV Fig.

The mission type Launch Vel. 46 is set to be a flyby type at the destination planet. Thus, the complete mission for the case is departure from Earth, swing-by from Venus, another swing-by from Venus, third swing-by from Earth and the final arrival to Jupiter. A typical trajectory (taken from [1]), GOSpel and SC solutions are compared in Table 4. From the table, it can be observed that solution found by GOSpel and SC are non-dominated GOSpel solution but time taken are more close to actual mission dates.

1 Direct Transfer Let us now explain how to compute the motion between a pair of planets. Say, the spacecraft moves from first planet to the second planet. This involves knowing the location of both planets at the start and at the end when the spacecraft reaches the second planet. Moreover, assume that we fix a transfer time t for reaching second planet from the first one and investigate if such a transfer is possible from the location information of both planets. The Lambert’s approach [8] helps us determine the velocity vectors required at the first (v1 ) and second (v2 ) planet in order to materialize such a transfer time.

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