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A Matlab®/Simulink® non-linear simulator for orbital spacecraft rendezvous applications.

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Academic year: 2021

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Figure 1: These blocks compute the inertial state of the spacecrafts by integrating equation (2.15) from t 0 to t f and making the conversion between orbital elements and inertial state.
Figure 4: Computes the derivative of the orbital elements via equation (2.15). To initialize the integrator, performs the variable change (2.6).
Figure 6: Computes the relative state between the satellites in the LVLH coordinates system of the leader spacecraft via the transformations presented in subsection 2.2.5.
Figure 9: Relative trajectory obtained after running the simulation

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