کد مقاله | کد نشریه | سال انتشار | مقاله انگلیسی | نسخه تمام متن |
---|---|---|---|---|
1767265 | 1020184 | 2007 | 10 صفحه PDF | دانلود رایگان |
عنوان انگلیسی مقاله ISI
On-orbit performance of Gravity Probe B drag-free translation control and orbit determination
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کلمات کلیدی
موضوعات مرتبط
مهندسی و علوم پایه
علوم زمین و سیارات
علوم فضا و نجوم
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چکیده انگلیسی
The Gravity Probe B (GP-B) Relativity Mission is a fundamental physics experiment to test Einstein's theory of General Relativity based on observations of spinning gyroscopes onboard a satellite in a near-polar, near-circular orbit at an altitude of about 640Â km around the Earth. The GP-B mission was designed to test two predictions of Einstein's theory, the geodetic effect and the frame-dragging effect, to an accuracy better than 5Â ÃÂ 10â4Â arcsec/yr. Drag-free control technology is implemented in the GP-B translation control system to minimize support forces and support induced torques on the gyroscopes. A Global Positioning System (GPS) receiver onboard the GP-B satellite provides real-time position, velocity and timing data. The GP-B orbit is determined on the ground based on the 3-axis GPS position data and verified independently with ground-based laser ranging measurements. This paper describes the design and implementation of the drag-free translation control and orbit determination system of the GP-B satellite. The on-orbit performance of the drag-free translation control system satisfies the requirements of the GP-B science experiment. The residual accelerations from the gyroscope control efforts are less than 4Â ÃÂ 10â11Â m/s2 (along the satellite roll axis) and less than 2Â ÃÂ 10â10Â m/s2 (transverse to the satellite roll axis) between 0.01Â mHz and 10Â mHz in inertial space. The non-gravitational acceleration along the satellite roll axis, including a nearly constant component (which is kept below 1Â ÃÂ 10â7Â m/s2) and a sinusoidal component (whose amplitude varies from about 5Â ÃÂ 10â7Â m/s2 to less than 1Â ÃÂ 10â8Â m/s2), causes the gyroscope spin axis to drift less than 9Â ÃÂ 10â5Â arcsec/yr. The orbit determination system is found to provide overlapping orbit solution segments having RMS (root mean square) position and velocity errors of a few meters and a few mm/s, well within the RMS mission requirements of 25Â m and 7.5Â cm/s.
ناشر
Database: Elsevier - ScienceDirect (ساینس دایرکت)
Journal: Advances in Space Research - Volume 40, Issue 1, 2007, Pages 1-10
Journal: Advances in Space Research - Volume 40, Issue 1, 2007, Pages 1-10
نویسندگان
J. Li, W.J. Bencze, D.B. DeBra, G. Hanuschak, T. Holmes, G.M. Keiser, J. Mester, P. Shestople, H. Small,