SOHO Mission Halo Orbit Recovery from the Attitude SOHO任务的晕轨道恢复从态度课件.ppt

下载文档 降价啦

10
0
约1.42万字
约 36页
2018-06-22 发布于贵州
举报
版权申诉
保障服务

SOHO Mission Halo Orbit Recovery from the Attitude SOHO任务的晕轨道恢复从态度课件.ppt

1、本文档共36页，可阅读全部内容。
2、有哪些信誉好的足球投注网站（book118）网站文档一经付费（服务费），不意味着购买了该文档的版权，仅供个人/单位学习、研究之用，不得用于商业用途，未经授权，严禁复制、发行、汇编、翻译或者网络传播等，侵权必究。
3、本站所有内容均由合作方或网友上传，本站不对文档的完整性、权威性及其观点立场正确性做任何保证或承诺！文档内容仅供研究参考，付费前请自行鉴别。如您付费，意味着您自己接受本站规则且自行承担风险，本站不退款、不进行额外附加服务；查看《如何避免下载的几个坑》。如果您已付费下载过本站文档，您可以点击这里二次下载。
4、如文档侵犯商业秘密、侵犯著作权、侵犯人身权等，请点击“版权申诉”（推荐），也可以打举报电话：400-050-0827(电话支持时间：9:00-18:30)。

SOHO Mission Halo Orbit Recovery from the Attitude SOHO任务的晕轨道恢复从态度课件

C. E. Roberts The SOHO Mission Halo Orbit Recovery from the Attitude Control Anomalies of 1998Craig E. RobertsComputer Sciences CorporationFlight Dynamics FacilityGoddard Space Flight Center Libration Point Orbits and Applications 10 - 14 June 2002 Parador d’Aiguablava Girona, Spain Contents Introduction to SOHO and its Halo Orbit SOHO Stationkeeping Technique June 1998 Anomaly and Recovery December 1998 Anomaly and Recovery Conclusion Solar Heliospheric Observatory (SOHO) Spacecraft SOHO Mission Overview Launched 3 December 1995; Sun-Earth/Moon L1 Halo Orbit Insertion (HOI) March 1996 Joint ESA/NASA mission; second NASA mission dedicated to Sun-Earth L1 halo orbit Purpose: Sun and solar wind science 3-axis stabilized; closed loop attitude system with momentum wheels, gyros (formerly), Sun sensors, FHSTs Steering laws keep S/C X-axis and instrument boresights Sun-pointing; Z-axis nods to stay aligned with Sun’s spin axis over course of year Hydrazine blowdown propulsion for translational control, momentum management and backup attitude control Two fully redundant strings of 8 4.5 N thrusters per string SOHO’s Halo: View from NEP SOHO’s Class 2 Halo: Side View SOHO’s Halo: Looking Sunward from Earth SOHO Halo Orbit Stationkeeping Technique Single-axis control Thrust vectors aligned with S/C body X-axis (X-axis always Sun-pointed) Thrust/?V then parallel or anti-parallel to S/C-Sun line Upshot: ?V basically along Earth-Sun line (GSE X-axis) Trajectory propagated to a candidate SK epoch; ?V applied and differentially corrected as trajectory propagated toward a target goal (RLP VX = 0) in subsequent RLP XZ-plane crossing; repeated until two halo revolutions are achieved ?V toward the Sun increases orbital energy, preventing halo decay back toward Earth ?V away from Sun decreases orbital energy, preventing escape into free heliocentric orbit Stationkeeping Realities LPO correction costs increase exponentially from epoch of last impulse; doubling constant ? 16 days