Coupled Dynamics and Integrated Control for Position and Attitude Motions of Spacecraft: A Survey

Zhang, Feng; Duan, Guangren

doi:10.1109/jas.2023.123306

Cited by 3 publications

(2 citation statements)

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“…Then, U EB xx can be represented as Equation (21). H EB can be calculated by taking Equation ( 24), thus we can then yield u 4,12 x and ∑ 3 n=1 u n,12…”

Section: Appendix B2 Proof Of Example 2 (Extended Body Model)mentioning

confidence: 99%

“…When modeling the orbit-attitude coupled motion of an S/C, many studies have separately modeled orbit and attitude dynamics and combined them for simplicity of analysis, or they have employed mutual potentials. Most common is the former approach, which does not require any attitude information for analyzing S/C orbital motion but does require S/C positions to calculate gravitational torques [12]. This approach is applicable when the primary body significantly outweighs the S/C, as the contribution of the S/C volume to the gravitational force is negligible.…”

Section: Introductionmentioning

confidence: 99%

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Modelling Rigid Body Potential of Small Celestial Bodies for Analyzing Orbit–Attitude Coupled Motions of Spacecraft

Lee,

Park

2024

Aerospace

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The present study aims to propose a general framework of modeling rigid body potentials (RBPs) suitable for analyzing the orbit–attitude coupled motion of a spacecraft (S/C) near small celestial bodies, regardless of gravity estimation models. Here, ‘rigid body potential’ refers to the potential of a small celestial body integrated across the finite volume of an S/C, assuming that the mass of the S/C has no influence on the motion of the small celestial body. First proposed is a comprehensive formulation for modeling the RBP including its associated force, torque, and Hessian matrix, which is then applied to three gravity estimation models. The Hessian of potential plays a crucial role in calculating the RBP. This study assesses the RBP via numerical simulations for the purpose of determining proper gravity estimation models and seeking modeling conditions. The gravity estimation models and the associated RBP are tested for eight small celestial bodies. In this study, we utilize distance units (DUs) instead of SI units, where the DU is defined as the mean radius of the given small celestial body. For a given specific distance in Dus, the relative error of the gravity estimation model at this distance has a similar value regardless of the small celestial body. However, the difference value between the potential and RBP depends on the DU; in other words, it depends on the size of the small celestial body. This implies that accurate gravity estimation models are imperative for conducting RBP analysis. The overall results can help develop a propagation system for orbit–attitude coupled motions of an S/C in the vicinity of small celestial bodies.

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“…Then, U EB xx can be represented as Equation (21). H EB can be calculated by taking Equation ( 24), thus we can then yield u 4,12 x and ∑ 3 n=1 u n,12…”

Section: Appendix B2 Proof Of Example 2 (Extended Body Model)mentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%