Abstract
The state transition matrix (STM) is a part of the onboard orbit determination system. It is used to control the satellite’s orbital motion to a predefined reference orbit. Firstly in this paper a simple orbit model that captures the secular behavior of the orbital motion in the presence of all perturbation forces is derived. Next, an approximate STM to match the secular effects in the orbit due to oblate earth effect and later in the presence of all perturbation forces is derived. Numerical experiments are provided for illustration.
Highlights
Autonomous orbit control in satellites is possible with the present onboard technological advancements
When we include the complete dynamics as reference orbit we have to use continuous control
The present note brings out a State transition matrix (STM) that is in Cartesian frame as an alternative to [6] and considers only secular effects
Summary
Autonomous orbit control in satellites is possible with the present onboard technological advancements. Using the receiver orbit solution the absolute orbit control system ensures the satellite motion to this reference orbit model in the earth centered fixed Cartesian reference frame. When we include the complete dynamics as reference orbit we have to use continuous control. The present note brings out a STM that is in Cartesian frame as an alternative to [6] and considers only secular effects. We note in the literature that the STM that is in Cartesian frame is derived in [7] and it includes secular and periodic effects.
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