• 主题
高级搜索  >
历史搜索 清空历史
首页> 外文期刊>Journal of Spacecraft and Rockets >Design Exploration of Low-Thrust Space Trajectory Problem for DESTINY Mission
【24h】

Design Exploration of Low-Thrust Space Trajectory Problem for DESTINY Mission

机译：DESTINY任务低推力空间弹道问题的设计探索

获取原文
获取原文并翻译 | 示例
           
页面导航
  • 摘要
  • 著录项
  • 相似文献
  • 相关主题

摘要

The present study focuses on exploring optimal transfer solutions for the Demonstration and Experiment of Space Technology for INterplanetary voYage (DESTINY) mission, which was proposed as an Institute of Space and Astronautical Science (ISAS) Epsilon-class small program in 2013 based on the "Space Science & Exploration Roadmap" proposed by the ISAS and later approved by the government committee on space policy. During the DESTINY mission, the spacecraft will first be injected into a low elliptical orbit by an Epsilon rocket, and its altitude will then be increased to approach the Moon using an ion engine system. Next, the spacecraft will be injected via a transfer orbit to the L2 Halo orbit of the Sun-Earth system by way of gravity assist from the Moon. As the spacecraft revolves around the Earth several hundred times, it gradually increases its altitude. Thus, the launch time and thrust profile must be chosen properly. Note that there are several conflicting requirements, including the reduction of fuel consumption, total flight time, and maximum eclipse time, that must be taken into consideration. To satisfy these requirements, many-objective evolutionary computation is applied to find better orbital designs.
机译：本研究的重点是探索用于行星际航行（DESTINY）任务的空间技术演示和实验的最佳转移解决方案，该方案是在2013年作为“空间与宇航科学研究所（ISAS）Epsilon级小计划”提出的，由ISAS提出并随后获得政府空间政策委员会批准的《空间科学与探索路线图》。在DESTINY任务期间，该航天器将首先由Epsilon火箭注入低椭圆轨道，然后使用离子引擎系统将其高度增加以接近月球。接下来，飞船将通过月球的引力辅助，通过转移轨道被注入到太阳地球系统的L2 Halo轨道。随着航天器绕地球旋转数百次，它逐渐增加了高度。因此，必须适当选择发射时间和推力曲线。请注意，有几个相互矛盾的要求，包括减少油耗，总飞行时间和最大日食时间，必须予以考虑。为了满足这些要求，应用了多目标进化计算来找到更好的轨道设计。

著录项

  • 来源
    《Journal of Spacecraft and Rockets》 |2017年第4期|796-807|共12页
  • 作者

    Watanabe Takeshi; Tatsukawa Tomoaki; Yamamoto Takayuki; Oyama Akira; Kawakatsu Yasuhiro;

  • 作者单位

    Japan Aerosp Explorat Agcy, Dept Space Flight Syst, Inst Space & Astronaut Sci, Sagamihara, Kanagawa 2525210, Japan;

    Tokyo Univ Sci, Dept Management Sci, Fac Engn, Div 1, Tokyo 1258585, Japan;

    Japan Aerosp Explorat Agcy, Res Unit 1, Res & Dev Directorate, Inst Space & Astronaut Sci, Sagamihara, Kanagawa 2525210, Japan;

    Japan Aerosp Explorat Agcy, Dept Space Flight Syst, Inst Space & Astronaut Sci, Sagamihara, Kanagawa 2525210, Japan;

    Japan Aerosp Explorat Agcy, Dept Space Flight Syst, Inst Space & Astronaut Sci, Sagamihara, Kanagawa 2525210, Japan;

  • 收录信息 美国《科学引文索引》(SCI);美国《工程索引》(EI);
  • 原文格式 PDF
  • 正文语种 eng
  • 中图分类
  • 关键词

相似文献

  • 外文文献
  • 中文文献
  • 专利
获取原文

客服邮箱：kefu@zhangqiaokeyan.com

京公网安备：11010802029741号 ICP备案号：京ICP备15016152号-6 六维联合信息科技 (北京) 有限公司©版权所有

  • 客服微信

  • 服务号