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

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

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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