Interaction between attitude libration and orbital motion of a rigid body in a near keplerian orbit of low eccentricity

Mohan, Swati; Lange, John V.; Lange, Benjamin

doi:10.1007/bf01229519

Cited by 13 publications

(7 citation statements)

References 2 publications

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“…In the literature related to this problem, there are studies of relative equilibria and quasi-periodic motions based on various approximate models of the coupling between orbital motion and attitude motion of earth satellites. We refer the reader to the work of Beletskii (1966), Duboshin (1958), Roberson (1970Roberson ( ), (1958, Longman (1971), Meirovitch (1968), Mohan, Breakwell and Lange (1972), Likins (1965), Sincarsin and Hughes (1983), Pascal (1985), and Sarychev (1975). The basic problem at hand is the dynamics of a rigid body or gyrostat in a central gravitational field.…”

Section: Introductionmentioning

confidence: 97%

Hamiltonian dynamics of a rigid body in a central gravitational field

Wang

Krishnaprasad

Maddocks

1990

Celestial Mech Dyn Astr

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Abstract. This paper concerns the dynamics of a rigid body of finite extent moving under the influence of a central gravitational field. A principal motivation behind this paper is to reveal the hamiltonian structure of the n-body problem for masses of finite extent and to understand the approximation inherent to modeling the system as the motion of point masses. To this end, explicit account is taken of effects arising because of the finite extent of the moving body. In the spirit of Arnold and Smale, exact models of spin-orbit coupling are formulated, with particular attention given to the underlying Lie group framework. Hamiltonian structures associated with such models are carefully constructed and shown to be non-canonical. Special motions, namely relative equilibria, are investigated in detail and the notion of a non-great circle relative equilibrium is introduced. Non-great circle motions cannot arise in the point mass model. In our analysis, a variational characterization of relative equilibria is found to be very useful.The reduced hamiltonian formulation introduced in this paper suggests a systematic approach to approximation of the underlying dynamics based on series expansion of the reduced hamiltonian. The latter part of the paper is concerned with rigorous derivations of nonlinear stability results for certain families of relative equilibria. Here Arnold's energyCasimir method and Lagrange multiplier methods prove useful.

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Section: Introductionmentioning

confidence: 97%

Hamiltonian dynamics of a rigid body in a central gravitational field

Wang

Krishnaprasad

Maddocks

1990

Celestial Mech Dyn Astr

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“…Lange and Mohan studied the orbit-attitude coupling of a conventional spacecraft which moves in the Earth's central field. The interdependence of the orbit and attitude motions is shown explicitly by expanding the differential gravitational force and torque in a Taylor series in the small parameter ε = ρ/R, where ρ is the characteristic of spacecraft size and R is the orbital radius [14,15]. Lange and Mohan neglected the terms which are higher than ε 2 .…”

Section: Introductionmentioning

confidence: 99%

Gravitational orbit–attitude coupling dynamics of a large solar power satellite

Liu

Zhang

et al. 2017

Aerospace Science and Technology

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“…The attitude-orbit coupling will also have a crucial impact on the recently announced Asteroid Retrieval Mission (ARM) (Mazanek et al, 2013), where the size of the exploring spacecraft is comparable to the small asteroid. Mohan et al (1972) and Pascal (1985) have studied attitude-orbit coupling for Earth orbiting spacecraft. Sanyal (2004) studied the coupled dynamics in context of multibody systems in a central gravitational field, and its uses for the design of new control techniques.…”

Section: Introductionmentioning

confidence: 99%

Coupled orbit–attitude dynamics and relative state estimation of spacecraft near small Solar System bodies

Misra

Izadi

Sanyal

et al. 2016

Advances in Space Research

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The effects of dynamical coupling between the rotational (attitude) and translational (orbital) motion of spacecraft near small Solar System bodies is investigated. This coupling arises due to the weak gravity of these bodies, as well as solar radiation pressure. The traditional approach assumes a pointmass spacecraft model to describe the translational motion of the spacecraft, while the attitude motion is considered to be completely decoupled from the translational motion. The model used here to describe the rigid-body spacecraft dynamics includes the non-uniform rotating gravity field of the small body up to second degree and order along with the attitude dependent terms, solar tide, and solar radiation pressure. This model shows that the second degree and order gravity terms due to the small body affect the dynamics of the spacecraft to the same extent as the orbit-attitude coupling due to the primary gravity (zeroth order) term. Variational integrators are used to simulate the dynamics of both the rigid spacecraft and the point mass. The small bodies considered here are modeled after Near-Earth Objects (NEO) Itokawa, and are assumed to be triaxial ellipsoids with uniform density. Differences in the numerically obtained trajectories of a rigid spacecraft and a point mass are then compared, to illustrate the impact of the orbit-attitude coupling on spacecraft dynamics in proximity of small bodies. Possible implications on the performance of model-based spacecraft control and on the station-keeping budget, if the orbit-attitude coupling is not accounted for in the model of the dynamics, are also discussed. An almost globally asymptotically stable motion estimation scheme based solely on visual/optical feedback that estimates the relative motion of the asteroid with respect to the spacecraft is also obtained. This estimation scheme does not require a model of the dynamics of the asteroid, which makes it perfectly suited for asteroids whose properties are not well known.

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Interaction between attitude libration and orbital motion of a rigid body in a near keplerian orbit of low eccentricity

Cited by 13 publications

References 2 publications

Hamiltonian dynamics of a rigid body in a central gravitational field

Hamiltonian dynamics of a rigid body in a central gravitational field

Gravitational orbit–attitude coupling dynamics of a large solar power satellite

Coupled orbit–attitude dynamics and relative state estimation of spacecraft near small Solar System bodies

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