Solar Sail Body-Fixed Hovering over Elongated Asteroids

Zeng, Xia; Gong, Shengping; Li, Junfeng; Alfriend, Kyle T.

doi:10.2514/1.g001061

Cited by 71 publications

(21 citation statements)

References 24 publications

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“…But they were rarely used in space explorations due to the far distance away from the two primaries. However, triangular equilibrium points of an irregular gravitational field, especially linearly stable or close to stable state, should be expected as more ideal locations than collinear equilibrium points for bodyfixed hovering flights [29].…”

Section: Periodic Orbits Over Linearly Stable Triangular Libration Pomentioning

confidence: 99%

Periodic orbits in the Chermnykh problem

Zeng

Alfriend

2017

Astrodyn

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Periodic orbits in irregular gravitational fields are significant for an understanding of dynamical behaviors around asteroids as well as the engineering aspect for deep space explorations. The rotating mass dipole, referred to as the Chermnykh problem, is a good alternative model to study qualitative dynamical environments near elongated asteroids, like the asteroid 1620 Geographos, 216 Kleopatra, or 25143 Itokawa. In this paper a global searching method is adopted to search for periodic orbits around the dipole model

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Section: Periodic Orbits Over Linearly Stable Triangular Libration Pomentioning

confidence: 99%

Periodic orbits in the Chermnykh problem

Zeng

Alfriend

2017

Astrodyn

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“…is method is feasible on asteroids due to low nominal acceleration of the spacecraft [7,8,11]. Zeng proposed the solar sail spacecraft's hover over an asteroid, which greatly extended the hover time and hover range without fuel consumption [12]. It should be pointed out that the research on spacecraft hovering over an asteroid in the early stage mainly concentrated on the relative position control of the spacecraft and asteroid irrespective of the relative attitude control [7-9, 11, 13-15].…”

Section: Introductionmentioning

confidence: 99%

Robust Adaptive Relative Position and Attitude Control for Noncooperative Spacecraft Hovering under Coupled Uncertain Dynamics

Liu

Zhang

et al. 2019

Mathematical Problems in Engineering

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The control of body-fixed hovering over noncooperative target, as one of the key problems of relative motion control between spacecrafts, is studied in the paper. The position of the chaser in the noncooperative target’s body coordinate system is required to remain unchanged, and the attitude of the chaser and the target must be synchronized at the same time. Initially, a six-degrees-of-freedom-coupled dynamic model of a chaser relative to a target is established, and relative attitude dynamics is described through using modified Rodrigues parameters (MRP). Considering the model uncertainty and external disturbances of the noncooperative target system, an adaptive nonsingular terminal sliding mode (NTSM) controller is designed. Adaptive tuning method is used to overcome the effects of the model uncertainty and external disturbances. The upper bounds of the model uncertainty and external disturbances are not required to be known in advance. The actual control law is continuous and chatter-free, which is obtained by integrating the discontinuous derivative control signal. Finally, these theoretical results are verified by numerical simulation.

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“…Previous work has mainly focused on terminator orbits [16] and the existence of hovering points at an asteroid [16][17][18][19][20]. These hovering points originate when adding a solar sail (or any low-thrust propulsion system [21,22]) to a three-body system: any three-body system exhibits the well-known Lagrange points which can be extended to threedimensional surfaces of artificial equilibrium points through a correct selection of sail acceleration and attitude.…”

Section: Introductionmentioning

confidence: 99%

Solar-Sail Orbital Motion About Asteroids and Binary Asteroid Systems

Heiligers

Scheeres

2018

Journal of Guidance, Control, and Dynamics

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Solar radiation pressure (SRP) is a major orbital perturbation for missions to small bodies like asteroids and binary asteroid systems. This paper studies the utilization of SRP on a solar sail for asteroid mission applications, specifically to generate artificial equilibrium points (AEPs) and displaced periodic orbits in these systems. For the single asteroid case, contours of AEPs for constant sail acceleration magnitudes are found in the Hill + SRP problem as well as periodic orbits around these AEPs. The binary system is modeled by first adding a fourth-body perturbation to the Hill + SRP dynamics, demonstrating the effect of the smaller asteroid as an oscillatory motion superimposed on the unperturbed orbit. Truly periodic orbits are obtained in the bi-circular + SRP problem, showing the existence of socalled pole-sitter-like orbits above the binary system's orbital plane. Higher-fidelity dynamical effects are investigated for these pole-sitter-like orbits for binary system 1999 KW4, showing feasibility of the orbits around aphelion. All results are generated for nearterm sail technology and for a simple, fixed sail attitude relative to the Sun. They therefore = Denotes first order derivative with respect to time   = Denotes second order derivative with respect to time

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Solar Sail Body-Fixed Hovering over Elongated Asteroids

Cited by 71 publications

References 24 publications

Periodic orbits in the Chermnykh problem

Periodic orbits in the Chermnykh problem

Robust Adaptive Relative Position and Attitude Control for Noncooperative Spacecraft Hovering under Coupled Uncertain Dynamics

Solar-Sail Orbital Motion About Asteroids and Binary Asteroid Systems

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