Evolution of angular velocity for defunct satellites as a result of YORP: An initial study

Albuja, Antonella A.; Scheeres, Daniel J.; McMahon, Jay W.

doi:10.1016/j.asr.2015.04.013

Cited by 16 publications

(6 citation statements)

References 23 publications

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“…Leveraging studies of asteroid dynamics, Albuja et al [9,10] investigated the influence of solar radiation and thermal re-emission torques on defunct satellite spin states. The combined influence of these torques on a body's spin state is called the Yarkovsky-O'Keefe-Radzievskii-Paddack (YORP) effect [11].…”

Section: Introductionmentioning

confidence: 99%

“…A number of authors have investigated spin-averaged attitude dynamics models. Albuja et al [9] extended the uniform spin-averaged asteroidal YORP work of Scheeres [14] to defunct satellites. These models are not applicable to tumbling satellites as the motion is driven by two generally incommensurate periods rather than one for the uniform case [15].…”

Section: Introductionmentioning

confidence: 99%

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Averaged Solar Torque Rotational Dynamics for Defunct Satellites

Benson

Scheeres

2021

Journal of Guidance, Control, and Dynamics

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Spin state predictions for defunct satellites in geosynchronous earth orbit (GEO) are valuable for active debris removal and servicing missions as well as material shedding studies and attitude-dependent solar radiation pressure (SRP) modeling. Previous studies have shown that solar radiation torques can explain the observed spin state evolution of some GEO objects via the Yarkovsky-O'Keefe-Radzievskii-Paddack (YORP) effect. These studies have focused primarily on uniform rotation. Nevertheless, many objects are in non-principal axis rotation (i.e. tumbling). Recent exploration of the tumbling regime for the family of retired GOES 8-12 satellites has shown intriguing YORP-driven behavior including spin-orbit coupling, tumbling cycles, and tumbling period resonances. To better explore and understand the tumbling regime, we develop a semi-analytical tumbling-averaged rotational dynamics model. The derivation requires analytically averaging over the satellite's torquefree rotation, defined by Jacobi elliptic functions. Averaging is facilitated by a second order Fourier series approximation of the facet illumination function. The averaged model is found to capture and explain the general long-term behavior of the full dynamics while reducing computation time by roughly three orders of magnitude. This improved computation efficiency promises to enable rapid exploration of general long-term rotational dynamics for defunct satellites and rocket bodies.

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Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Averaged Solar Torque Rotational Dynamics for Defunct Satellites

Benson

Scheeres

2021

Journal of Guidance, Control, and Dynamics

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“…It expresses the influence of thermal radiation force on asymmetric rotating bodies, provoking torques able to influence spin velocity and spin axis direction. Mainly analyzed for its capability of affecting spin period of small asteroids, its effect on defunct satellites in GEO has been investigated by Albuja et al [16]. In this work, the YORP effect model derived in [17] is leveraged.…”

Section: Yorp Effect Modelmentioning

confidence: 99%

YORP Effect on Long-Term Rotational Dynamics of Debris in GEO

Cuomo

2022

Aerotec. Missili Spaz.

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The Yarkovsky–O’Keefe–Radzievskii–Paddack (YORP) effect describes the torque induced on space objects produced by solar radiation and thermal re-emission. Previous analyses have demonstrated its influence on long-term rotational dynamics of space debris objects in Geostationary Orbit (GEO), where YORP becomes predominant with respect to other external perturbations (e.g., atmospheric drag, gravity gradient, eddy current torque), leading to a wide variety of possible behaviors. The capability of forecasting time windows of slow uniform rotation, if any, would bring significant advantages in operations of Active Debris Removal and on-orbit servicing, especially in the detumbling phase. Also, a non-negligible impact of the End-of-Life configuration, in terms of movable surfaces orientation and center of mass location, could lead to guidelines for future satellites to be easier targets in the disposal phase. In this work, a previously derived semi-analytical tumbling-averaged YORP rotational dynamics model is leveraged. Exploiting an averaged model, computational time is strongly reduced while maintaining sufficient accuracy compared to propagation of Euler’s equations of motion. First, a satellite of the Geostationary Operational Environmental Satellite (GOES) family is analyzed and compared to previous studies to verify the correct implementation of the model. A wider analysis is performed on simple geometric models, such as a box-wing satellite, a 3U CubeSat, and a rocket body. The impact of object size, surface optical properties, and center of mass position on long-term rotational behavior is investigated, providing a general insight into these phenomena with a possible future application to existing objects in GEO.

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“…This method was developed by Scheeres [11] to model the dynamical evolution of asteroids' motion due to the Yarkovsky-O'Keefe-Raszievskii-Paddack or "YORP" effect [21,22]. It was later expanded to represent the SRP effects on spacecraft [23][24][25][26][27].…”

Section: Trp Fourier Series Representationmentioning

confidence: 99%

Precise Model for Small-Body Thermal Radiation Pressure Acting on Spacecraft

Hesar

Scheeres

McMahon

et al. 2017

Journal of Guidance, Control, and Dynamics

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A precise representation of small body surface thermal radiation pressure effects acting on orbiting spacecraft is discussed. The proposed framework takes advantage of a general Fourier series expansion to compute small body surface thermal radiation pressure. Fourier series expansion has been used before for the precise representation of solar radiation pressure effects on spacecraft orbiting small bodies. This framework takes into account the surface thermal parameters of small bodies, geometric relationship of orbiting spacecraft with the small body surface, and the shape and surface properties of spacecraft allowing for the computation of thermal radiation pressure, which may also be used for the generation of precise orbit determination solutions.After presenting the general model, we provide an example application of the model for the OSIRIS-REx spacecraft in orbit about Asteroid (101955) Bennu. Via simulation studies, we evaluate the effect of mis-modeling the thermal radiation pressure on the spacecraft and study the utilization of the proposed method for generating precise orbit determination solutions.

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Evolution of angular velocity for defunct satellites as a result of YORP: An initial study

Cited by 16 publications

References 23 publications

Averaged Solar Torque Rotational Dynamics for Defunct Satellites

Averaged Solar Torque Rotational Dynamics for Defunct Satellites

YORP Effect on Long-Term Rotational Dynamics of Debris in GEO

Precise Model for Small-Body Thermal Radiation Pressure Acting on Spacecraft

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