By Zhuo Kang, Lishan Kang, Xiufen Zou, Minzhong Liu, Changhe Li, Ming Yang, Yan Li (auth.), Lishan Kang, Yong Liu, Sanyou Zeng (eds.)
This publication constitutes the refereed complaints of the second one overseas Symposium on Intelligence Computation and purposes, ISICA 2007, held in Wuhan, China, in September 2007. The seventy one revised complete papers have been rigorously reviewed and chosen from approximately 1000 submissions. the themes contain evolutionary computation, evolutionary studying, neural networks, swarms, trend attractiveness, info mining and others.
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Extra info for Advances in Computation and Intelligence: Second International Symposium, ISICA 2007 Wuhan, China, September 21-23, 2007 Proceedings
3-5 show the DLZ1 shape which algrithms obtained. For DLZ1 optimization DMOGA achieves the best distribution of solutions, and in this metric NSGA-II is the worst, SPEA2 is similar to DMOGA. In convengence metric NSGA-II is the best, and DMOGA follows. And about efficiency, the cpu time of DMOGA is faster than SPEA2, however slower than NSGA-II. 22 J. Zheng et al. Table 1. Comparision result of GD Table 4. 4776E-4 Table 2. 05854 Table 3. 13329 Table 5. 00207 Table 6. 2992 DLZ2 test problem We consider the three-objective test problem of DLZ2, the Pareto optimal front satisfying f12 + f 22 + f32 = 1 in DLZ2 .
We add an equivalent energy component in the launch velocity to take into account of not colliding with the swing-by planet. 3 Handling Using NSGA-II First, we discuss the representation scheme for the decision variables within the NSGAII framework . We fix a maximum of three swing-by planets, thereby leaving us with four options: (i) direct flight (no swing-by), (ii) one planet swing-by, (iii) two planet swing-by and (iv) three planet swing-by. We use a two-bit substring for representing these four options with 00, 01, 10 and 11, respectively.
The trajectory optimization problem involves a number of decision variables and constraints, a description of which requires us to first understand the transfer of spacecraft from one planet to another. The standard orbital mechanics  uses parameters like state vectors and velocity maneuvers for fixing a trajectory. For computing a transfer from one planet to another, a patched conic model  is usually employed. In this model, the motion takes place along a plane. In practice, the transfer can involve swingby planets or can be a direct one.
Advances in Computation and Intelligence: Second International Symposium, ISICA 2007 Wuhan, China, September 21-23, 2007 Proceedings by Zhuo Kang, Lishan Kang, Xiufen Zou, Minzhong Liu, Changhe Li, Ming Yang, Yan Li (auth.), Lishan Kang, Yong Liu, Sanyou Zeng (eds.)