Analysis of the Impact of Orbit-Attitude Coupling at Higher-Degree Potential Models on Spacecraft Dynamics

McCann, Brennan S.; Nazari, Morad

doi:10.1007/s40295-022-00335-x

Cited by 5 publications

(3 citation statements)

References 28 publications

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“…Note that (i = 1, 2, 3) for the three-body problem. For details of higher order gravitational terms, the reader is referred to [27]. Furthermore, defining a 1 ≡ 1/∥r i ∥, a 2 ≡ 1/∥r i ∥ 3 , and…”

Section: Gravitational Potential In Fnbpmentioning

confidence: 99%

Framework for the full N-body problem in SE(3) and its reduction to the circular restricted full three-body problem

Nazari

Canales

McCann

et al. 2023

Celest Mech Dyn Astron

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A novel, compact formalism of rigid body motion dynamics is presented in a general reference frame based on the geometric mechanics framework. This formalism, proposed on the special Euclidean space (SE(3)) of the Lie group, naturally accounts for the orbit/attitude coupling due to the gravitational moments and forces. It is demonstrated that the structure of the rigid body dynamics equations is preserved in different coordinate frames. Then, using the expression of gravitational potential, this global framework is applied to the circular restricted full three-body problem (CRF3BP) of a near-rectilinear halo orbit (NRHO) similar to that of Gateway, where the equations are uniquely provided in the body frame of the spacecraft and the barycentric rotating frame. For the sake of propagation and consistency with the classical circular restricted three-body problem (CR3BP), the equations of the CRF3BP Full N-Body Problem in SE(3) and its Reduction to CRF3BP are also presented in a non-dimensional form. Trajectories computed with different inertia tensors are compared with those obtained using the traditional equations of motion of a point-mass spacecraft subject to the gravitational fields of two larger primaries. The comparison between CRF3BP and CR3BP suggests: (a) the need for computation of customized families of halo orbits considering inertia properties of each spacecraft; and (b) the use of attitude-only control for station-keeping in future NRHO missions to reduce station-keeping costs which would otherwise be relatively large if the point-mass approximation were used.

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Section: Gravitational Potential In Fnbpmentioning

confidence: 99%

Framework for the full N-body problem in SE(3) and its reduction to the circular restricted full three-body problem

Nazari

Canales

McCann

et al. 2023

Celest Mech Dyn Astron

Self Cite

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show abstract

“…In the research of spacecraft proximity collaborative tasks, such as rendezvous and docking, precision formation, space manipulation, and on-orbit assembly, many scholars have proposed the necessity of attitude-orbit coupling modeling [1][2][3][4][5]. Some scholars have applied the attitude-orbit coupling results to spacecraft guidance, navigation and control (GNC) [6,7].…”

Section: Introductionmentioning

confidence: 99%

“…The viewpoint proposed in Refs. [1][2][3][4][5] conflicts with the engineering application research in Refs. [10][11][12], which makes scientific aerospace engineers to wonder whether the research work on attitude-orbit coupling relative dynamic model is necessary, or under what circumstances it is necessary.…”

Section: Introductionmentioning

confidence: 99%

Mechanism and Application of Attitude and Orbit Coupling Dynamics for Spacecraft Proximity Relative Motion

Hao,

Jin,

Tianzhe

et al. 2024

International Journal of Aerospace Engineering

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This paper analyzes the root causes of attitude-orbit coupling effects of spacecraft proximity relative motion in space precision collaborative tasks from three aspects: mathematical representation, physical definition, and engineering applications. At first, taking mathematical representation as the context, spacecraft proximity relative motion representations such as particle relative dynamic model, extended particle relative dynamic model, and dual-spiral-based relative dynamic model are investigated in detail. On this basis, the mechanism of attitude-orbit coupling effects originating from different mathematical representations is further investigated. Second, spiral theory–based attitude-orbit coupling relative dynamics is developed. The innovation of this work is extending the dual number representation from rigid body to flexible body, which makes it possible to describe the proximity relative motion between two rigid-flexible coupling spacecraft. Third, the application value of attitude-orbit coupling relative dynamic model in precision collaborative mission such as precision formation, rendezvous and docking, space manipulation, and on-orbit assembly is provided. Finally, simulation results verify the engineering significance of the attitude-orbit coupling relative dynamic model.

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Circular restricted full three-body problem with rigid-body spacecraft dynamics in binary asteroid systems

McCann,

Anderson,

Nazari

et al. 2024

Celest Mech Dyn Astron

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Analysis of the Impact of Orbit-Attitude Coupling at Higher-Degree Potential Models on Spacecraft Dynamics

Cited by 5 publications

References 28 publications

Framework for the full N-body problem in SE(3) and its reduction to the circular restricted full three-body problem

Framework for the full N-body problem in SE(3) and its reduction to the circular restricted full three-body problem

Mechanism and Application of Attitude and Orbit Coupling Dynamics for Spacecraft Proximity Relative Motion

Circular restricted full three-body problem with rigid-body spacecraft dynamics in binary asteroid systems

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