This paper demonstrates quaternion-based variational integration for spacecraft dynamics, suggesting improvements in simulation and real-time control applications.
This paper presents the application of discrete variational mechanics to spacecraft attitude dynamics using quaternion state variables. A general method is introduced for spacecraft dynamic system by deriving a variational integrators and quaternion state variables. The designed integrators demonstrate the behaviour of momentum and realistic energy which is comparable computational cost and less than a low order Runge-Kutta methods, it is suggestable for both real- time estimation and simulation of control application. The performance of integrators exemplifies rigid bodies with momentum actuators, internal viscous damping. In addition, Extended Kalman Filter (EKF) is presented for the purpose of attitude determination and on-orbit manufacturing operations.
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Gianmarco Radice (2025) studied this question.
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