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TOPEX/Poseidon orbit acquisition maneuver designThe current baseline injection orbit for the jointly sponsored NASA/CNES TOPEX/Poseidon mission is near-circular, approximately 30 km below the desired operational orbit altitude and at the operational orbit inclination. A baseline maneuver sequence to retarget from this injection orbit to the desired operational orbit has been designed based upon the expected worst-case 3-sigma injection and maneuver execution errors. The sequence requires seven maneuvers, including an initial calibration burn, and achieves the operational orbit with the desired ground track pattern in 30 days. A delay sensitivity analysis has been conducted to estimate the allowable operational delay for each maneuver without increasing the total orbit acquisition period. The baseline sequence provides back-ups for a one-revolution delay for each maneuver and one-day delay for most maneuvers. It is also shown that a higher injection orbit allows the maneuver sequence to achieve the operational orbit in 26 days under a worst-case scenario.
Document ID
19920060692
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Bhat, Ramachandra S.
(JPL Pasadena, CA, United States)
Date Acquired
August 15, 2013
Publication Date
January 1, 1992
Subject Category
Astrodynamics
Report/Patent Number
AAS PAPER 91-514
Meeting Information
Meeting: AAS/AIAA Astrodynamics Conference
Location: Durango, CO
Country: United States
Start Date: August 19, 1991
End Date: August 22, 1991
Accession Number
92A43316
Distribution Limits
Public
Copyright
Other

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