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A launch condition optimization with genetic algorithm (GA) for spacecraft rendezvous is presented. Impulsive increment velocity at the ideal boost point on the initial trajectory can be obtained by Lambert's theorem and Keplerian equations. Relative to the centroid-time method, optimization methods for the launch condition by a standard genetic algorithm (SGA) and an adaptive genetic algorithm (AGA) are also considered. In these GA cases, the launch condition is encoded as a binary string, and a fitness function is constructed with the miss distance. Simulations with three degree-of-freedom models are designed, which consider perturbing force and the time-varying mass. The result shows that GAs can prominently reduce the miss distance comparing with the centroid-time method. Furthermore the AGA has more rapid astringency than SGA.