關鍵字查詢 | 類別:期刊論文 | | 關鍵字:Analytic theory of optimal plane change by low aerodynamic forces

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序號 學年期 教師動態
1 85/2 航太系 馬德明 教授 期刊論文 發佈 Analytic theory of optimal plane change by low aerodynamic forces , [85-2] :Analytic theory of optimal plane change by low aerodynamic forces期刊論文Analytic theory of optimal plane change by low aerodynamic forcesMa, Der-Ming; Wu, Chi-Hang; Vinh, Nguyen X.淡江大學航空太空工程學系Aerodynamics; Approximation theory; Computational methods; Computer simulation; Equations of state; Integration; Maneuverability; Nonlinear equations; Optimization; Reentry; Variational techniques; Lifting bodies; Multi pass maneuvers; Optimal plane change; OrbitsSpringfield: American Astronautical SocietyJournal of The Astronautical Sciences 45(3), pp.329-347The properites of the optimal and sub-optimal solutions to multiple-pass aeroassisted plane change were previously studied in terms of the trajectory variables. The solutions show the strong orbital nature. Then, it is proposed to obtain the variational equations of the orbital elements. We shall use these equations and the approximate control derived in Vinh and Ma (1990) to calculate the trajectories. In this respect, the approximate control l
2 81/2 航太系 馬德明 教授 期刊論文 發佈 Analytic theory of optimal plane change by low aerodynamic forces , [81-2] :Analytic theory of optimal plane change by low aerodynamic forces期刊論文Analytic theory of optimal plane change by low aerodynamic forcesMa, Der-Ming; Wu, Chi-Hang; Vinh, Nguyen X.淡江大學航空太空工程學系Aerodynamics; Approximation theory; Computational methods; Computer simulation; Equations of state; Integration; Maneuverability; Nonlinear equations; Optimization; Reentry; Variational techniques; Lifting bodies; Multi pass maneuvers; Optimal plane change; OrbitsSan Diego: Univelt Inc.Advances in the Astronautical Sciences 82(2), pp.1139-1154The properites of the optimal and sub-optimal solutions to multiple-pass aeroassisted plane change were previously studied in terms of the trajectory variables. The solutions show the strong orbital nature. Then, it is proposed to obtain the variational equations of the orbital elements. We shall use these equations and the approximate control derived in Vinh and Ma (1990) to calculate the trajectories. In this respect, the approximate control law and the transv
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