關鍵字查詢 | 類別:期刊論文 | | 關鍵字:Sun-synchronous satellite orbit determination

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序號 學年期 教師動態
1 92/2 航太系 馬德明 教授 期刊論文 發佈 Low Altitude Sun-Synchronous Satellite Orbit Determination , [92-2] :Low Altitude Sun-Synchronous Satellite Orbit Determination期刊論文Low Altitude Sun-Synchronous Satellite Orbit DeterminationMa, Der-Ming; Zhai, Shen-You淡江大學航空太空工程學系Kidlington: Pergamon PressActa Astronautica 54(4), pp.245–251The linearized dynamic equations used for on-board orbit determination of Sun-synchronous satellite are derived. Sun-synchronous orbits are orbits with the secular rate of the right ascension of the ascending node equal to the right ascension rate of the mean sun. Therefore the orbit is no more a closed circle but a tight helix about the Earth. In the paper, instead of treating the orbit as a closed circle, the actual helix orbit is taken as nominal trajectory. The details of the linearized equations of motion for the satellite in the Sun-synchronous orbit are derived. The linearized equations are obtained by perturbing the Keplerian motion with the J2 correction and the effect of sun's attraction being neglected. Combined with the GPS navigation equations, the Kalman
2 92/2 航太系 馬德明 教授 期刊論文 發佈 Sun-synchronous satellite orbit determination , [92-2] :Sun-synchronous satellite orbit determination期刊論文Sun-synchronous satellite orbit determinationMa, Der-Ming; Zhai, Shen-You淡江大學航空太空工程學系Algorithms; Global positioning system; Kalman filtering; Navigation; Orbits; Perturbation techniques; Sun; Trajectories; Keplerian motion; Sun-synchronous satellites; SatellitesKidlington: PergamonActa Astronautica 54(4), pp.245-251The linearized dynamic equations used for on-board orbit determination of Sun-synchronous satellite are derived. Sun-synchronous orbits are orbits with the secular rate of the right ascension of the ascending node equal to the right ascension rate of the mean sun. Therefore the orbit is no more a closed circle but a tight helix about the Earth. In the paper, instead of treating the orbit as a closed circle, the actual helix orbit is taken as nominal trajectory. The details of the linearized equations of motion for the satellite in the Sun-synchronous orbit are derived. The linearized equations are obtained by perturbing the Ke
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