Spacecraft Motion About Slowly Rotating Asteroids

Hu, Weiduo; Scheeres, Daniel J.

doi:10.2514/2.4944

Cited by 67 publications

(43 citation statements)

References 14 publications

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“…[12], paying attention to the averaging condition. It is also interesting to give a comparison of the slow and fast rotating cases.…”

Section: Averaging Analysismentioning

confidence: 99%

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Averaging analyses for spacecraft orbital motions around asteroids

Scheeres

2014

Acta Mech Sin

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This paper summarizes a few cases of spacecraft orbital motion around asteroid for which averaging method can be applied, i.e., when central body rotates slowly, fast, and when a spacecraft is near to the resonant orbits between the spacecraft mean motion and the central body's rotation. Averaging conditions for these cases are given. As a major extension, a few classes of near resonant orbits are analyzed by the averaging method. Then some resulted conclusions of these averaging analyses are applied to understand the stability regions in a numerical experiment. Some stability conclusions are obtained. As a typical example, it is shown in detail that near circular 1 : 2 resonant orbit is always unstable.

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“…[12], paying attention to the averaging condition. It is also interesting to give a comparison of the slow and fast rotating cases.…”

Section: Averaging Analysismentioning

confidence: 99%

“…Spacecraft secular motion around asteroids has been studied extensively in Refs. [11,12] when an asteroid does not rotate or rotates slowly and rotates fast [13,14]. This paper studies the averaging condition for secular motion for these different cases.…”

Section: Introductionmentioning

confidence: 98%

Averaging analyses for spacecraft orbital motions around asteroids

Scheeres

2014

Acta Mech Sin

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“…In this work, it is assumed that the asteroid is an ellipsoid with semi-axes a I , b I , c I defined in the body fixed reference frame − − i j k (principal axes of inertia) as shown The gravity field of the asteroid is expressed as the sum of a spherical field plus a second-degree and second-order field (Hu, 2002):…”

Section: Proximity Motion Dynamics and Controlmentioning

confidence: 99%

Asteroid rotation and orbit control via laser ablation

Vetrisano

Colombo

Vasile

2016

Advances in Space Research

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This paper presents an approach to control the rotational motion of an asteroid while a spacecraft is deflecting its trajectory through laser ablation. During the deflection, the proximity motion of the spacecraft is coupled with the orbital and rotational motion of the asteroid. The combination of the deflection acceleration, solar radiation pressure, gravity field and plume impingement will force the spacecraft to drift away from the asteroid. In turn, a variation of the motion of the spacecraft produces a change in the modulus and direction of the deflection action which modifies the rotational and orbital motion of the asteroid. An on-board state estimation and control algorithm is then presented that simultaneously provides an optimal proximity control and a control of the rotational motion of the asteroid. It will be shown that the simulataneous control of the rotational and proximity motions of asteroid and spacecraft has a significant impact on the required deflection time.

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“…3) and that the asteroid rotates around the z-axis with angular velocity w a . The gravity field of the asteroid is expressed as the sum of a spherical field plus a second-degree and second-order field (Hu and Scheeres 2002;Rossi et al 1999),…”

Section: Mirror Dynamics and Controlmentioning

confidence: 99%