日韩欧美一 , 欧美午夜激情视频 , 国产精品一二三 , 日韩av电影一区二区三区,av官网在线,少妇高潮在线,国产精品亚洲综合色区韩国

Satellite Constellation Design with

時間:2023-04-30 01:03:33 航空航天論文 我要投稿
  • 相關(guān)推薦

Satellite Constellation Design with Adaptively Continuous Ant System Algorithm

The ant system algorithm (ASA) has proved to be a novel meta-heuristic algorithm to solve many multivariable problems. In this paper, the earth coverage of satellite constellation is analyzed and a (n + 1)-fold coverage rate is put forward to evaluate the coverage performance of a satellite constellation. An optimization model of constellation parameters is established on the basis of the coverage performance. As a newly developed method, ASA can be applied to optimize the constellation parameters. In order to improve the ASA,a rule for adaptive number of ants is proposed, by which the search range is obviously enlarged and the convergence speed increased.Simulation results have shown that the ASA is more quick and efficient than other methods.

作 者: He Quan Han Chao   作者單位: School of Astronautics, Beijing University of Aeronautics and Astronautics, Beijing 100083, China  刊 名: 中國航空學(xué)報(英文版)  ISTIC 英文刊名: CHINESE JOURNAL OF AERONAUTICS  年,卷(期): 2007 20(4)  分類號: V2  關(guān)鍵詞: ant system algorithm   satellite constellation   optimization design   coverage performance   adaptive adjusting  

【Satellite Constellation Design with 】相關(guān)文章:

Knowledge Fusion Design Method: Satellite Module Layout04-26

Chinas Meteorological Satellite Application System04-26

Change-1 Satellite Completed Its Preset Objectives04-27

Optimum municipal wastewater treatment plant design with consideration of uncertainty04-26

英文求職信-Design / Creative - Production Artist04-26

Ivar asteroid rendezvous mission system scenario and trajectory design04-26

英文求職信-Design / Creative - Senior Graphic Designer04-26

Chuangxin-1-02 And Shiyan Satellite 3 Launched Atop A LM-2D04-27

A Quasi-equipotential Field Simulation for Preform Design of P/M Superalloy Disk04-26

Design of Neural Network Variable Structure Reentry Control System for Reusable Launch Vehicle04-26