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- W2364973889 abstract "The dynamical equations for a kind of elliptic orbit rendezvous are presented.The differences of the semi major axes and inclinations between the chaser spacecraft and the target spacecraft are small,and their eccentricities are small too.With the reference frame built on a suitable circular orbit,dimensionless and linear time-invariant dynamical equations are deduced,and the relative states are obtained.Then,the dynamical equations are applied to two-impulse elliptic orbit rendezvous.Simulations for testing the equations and guidance laws are carried out,and the results are compared with that of CW equations and corresponding guidance laws.The simulation results show that the precisions of these new dynamical equations are better than that of CW equations,and can solve such kind elliptic orbit rendezvous problems." @default.
- W2364973889 created "2016-06-24" @default.
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- W2364973889 date "2008-01-01" @default.
- W2364973889 modified "2023-09-28" @default.
- W2364973889 title "Dynamical Equations for a Kind of Elliptic Orbit Rendezvous" @default.
- W2364973889 hasPublicationYear "2008" @default.
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