Solar radiation pressure on (99942) Apophis

PurposeThe purpose of this paper is to assess the orbital perturbation caused by the gravitational orbit–attitude coupling of spacecraft in the proximity of asteroids.Design/methodology/approachThe gravitational orbit–attitude coupling perturbation (GOACP), which has been neglected before in the close-proximity orbital dynamics about asteroids, is investigated and compared with other orbital perturbations. The GOACP has its origin in the fact that the gravity acting on a non-spherical extended body is actually different from that acting on a point mass located at the body’s center of mass, which is the approximated model in the orbital dynamics. Besides, a case study of a tethered satellite system is given by numerical simulations.FindingsIt is found that the ratio of GOACP to the asteroid’s non-spherical gravity is the order of ρ/ae, where ρ is the spacecraft’s characteristic dimension and ae is the asteroid’s mean radius. It can also be seen that as ρ increases, GOACP will also increase but the solar radiation pressure (SRP) will decrease due to the decreasing area-to-mass ratio. The GOACP will be more significant than SRP at small orbital radii for a large-sized spacecraft. Based on the results by analyses and simulations, it can be concluded that GOACP needs to be considered in the orbital dynamics for a large-sized spacecraft in the proximity of a small asteroid.Practical implicationsThis study is of great importance for the future asteroids missions for scientific explorations and near-Earth objects mitigation.Originality/valueThe GOACP, which has been neglected before, is revealed and studied.

<p>The Yarkovsky and YORP effects originate due to the light pressure recoil force acting on the surface of an asteroid. The Yarkovsky effect changes the asteroid's orbit, whereas the YORP effect changes its rotation state. Both effects appear to be crucially important for the long-term evolution of kilometer-sized asteroids.</p><p>The talk will review the recent successes and difficulties in the theoretical modeling of these effects, the growing body of their observational confirmations, and how these effects can alter asteroids' shapes, create binary asteroids and asteroid pairs, spread asteroid families and help asteroids to migrate from the main belt to the near-Earth orbits.</p>

No AccessEngineering NoteGeneral Solar Radiation Pressure Model for Global Positioning System Orbit DeterminationJay McMahon and Daniel J. ScheeresJay McMahonAerospace Engineering Sciences, University of Colorado, Boulder, Colorado 80309*Research Associate, Aerospace Engineering Sciences, 431 UCB. Member AIAA.Search for more papers by this author and Daniel J. ScheeresAerospace Engineering Sciences, University of Colorado, Boulder, Colorado 80309†A. Richard Seabass Endowed Professor, Aerospace Engineering Sciences, 429 UCB. Member AIAA.Search for more papers by this authorPublished Online:10 Jan 2014https://doi.org/10.2514/1.61113SectionsRead Now ToolsAdd to favoritesDownload citationTrack citations About References [1] Ziebart M., “Generalized Analytical Solar Radiation Pressure Modeling Algorithm for Spacecraft of Complex Shape,” Journal of Spacecraft and Rockets, Vol. 41, No. 5, 2004, pp. 840–848. doi:https://doi.org/10.2514/1.13097 JSCRAG 0022-4650 LinkGoogle Scholar[2] Fliegel H. F. and Gallini T. E., “Solar Force Modeling of Block IIR Global Positioning System Satellites,” Journal of Spacecraft and Rockets, Vol. 33, No. 6, 1996, pp. 863–866. doi:https://doi.org/10.2514/3.26851 JSCRAG 0022-4650 LinkGoogle Scholar[3] Springer T., Beutler G. and Rothacher M., “A New Solar Radiation Pressure Model for GPS Satellites,” GPS Solutions, Vol. 2, No. 3, 1999, pp. 50–62.doi:https://doi.org/10.1007/PL00012757 1080-5370 CrossrefGoogle Scholar[4] Bar-Sever Y. E., “New and Improved Solar Radiation Pressure Models for GPS Satellites Based on Flight Data,” Jet Propulsion Lab., California Inst. of Technology TR 80-4193, Pasadena, CA, 1997. Google Scholar[5] McMahon J. and Scheeres D., “Secular Orbit Variation due to Solar Radiation Effects: A Detailed Model for BYORP,” Celestial Mechanics and Dynamical Astronomy, Vol. 106, No. 3, 2010, pp. 261–300.doi:https://doi.org/10.1007/s10569-009-9247-9 0923-2958 CrossrefGoogle Scholar[6] McMahon J. W. and Scheeres D. J., “A New Solar Radiation Pressure Force Model for Navigation,” Journal of Guidance, Control, and Dynamics, Vol. 33, No. 5, 2010, pp. 1418–1428. doi:https://doi.org/10.2514/1.48434 JGCDDT 0162-3192 LinkGoogle Scholar[7] Bar-Sever Y. E. and Kuang D., “New Empirically Derived Solar Radiation Pressure Model for Global Positioning System Satellites,” Interplanetary Network Progress Report, Vol. 42, No. 159, Nov. 2004, pp. 1–11. Google Scholar[8] Bar-Sever Y. E. and Kuang D., “New Empirically Derived Solar Radiation Pressure Model for Global Positioning System Satellites During Eclipse Seasons,” Interplanetary Network Progress Report, Vol. 42, No. 160, Feb. 2005, pp. 1–4. Google Scholar[9] Sibthorpe A., Weiss J., Harvey N., Kuang D. and Bar-Sever Y., “Empirical Modeling of Solar Radiation Pressure Forces Affecting GPS Satellites,” Abstract G54A-04, Presented at 2010 Fall Meeting, AGU, San Francisco, CA, 13–17 Dec. 2010. Google Scholar[10] Kouba J., “A Simplified Yaw-Attitude Model for Eclipsing GPS Satellites,” GPS Solutions, Vol. 13, No. 1, 2009, pp. 1–12.doi:https://doi.org/10.1007/s10291-008-0092-1 1080-5370 CrossrefGoogle Scholar Previous article Next article

Ray-tracing solar radiation pressure modeling for QZS-1

Developing the “Precessing Inclined Bi-Elliptical Four-Body Problem with Radiation Pressure” to search for orbits in the triple asteroid 2001SN263

The direct measurement of Earth's radiative Energy Imbalance (EEI) from space is a challenge for state-of-the-art radiometric observing systems. Current spaceborne radiometers measure the individual shortwave (Solar incoming and Earth reflected solar radiation) and longwave (Earth emitted thermal radiation) components of Earth's energy balance with unprecedented stability, but with calibration errors that are too large to determine the absolute magnitude of global mean EEI or net radiative flux, respectively, as the components' residual. Best estimates of multi-year (2005–2020) EEI are derived from temporal changes in planetary heat content, predominantly ocean heat content, and amount to ~0.9 Wm <sup xmlns:mml="http://www.w3.org/1998/Math/MathML" xmlns:xlink="http://www.w3.org/1999/xlink">−2</sup> . To monitor EEI directly from space, we propose an independent approach based on accelerometry that measures non-gravitational radial accelerations induced by radiation pressure. To provide requirements for a near-spherical "Space Balls" spacecraft and mission design, we develop a simulation environment using JPL's Mission Analysis, Operations, and Navigation Toolkit Environment (MONTE) software libraries and present-day radiative fluxes from the Clouds and Earth's Radiant Energy System (CERES). At its current initial stage, the toolset allows us to simulate accelerations acting on a spherical spacecraft due to solar radiation pressure, Earth's reflected shortwave (albedo) and emitted longwave radiation, as well as due to aerodynamic force. Induced accelerations as well as their sensitivity to mean orbit altitude and spacecraft absorptivity agree well with back-of the-envelope calculations and previous simulations that assess the role of radiation pressure accelerations for orbital drift. Future investigations will expand the MONTE-based simulation environment with additional shape and confounding force models. Preliminary simulations with an integrated spacecraft dynamics model suggest that the main confounding accelerations for a non-perfect, faceted sphere are related to Yarkovsky, aerodynamic force and relativistic effects, which will have to be mitigated to facilitate a high-accuracy EEI measurement from space.

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An approach is proposed to solve a real-world complex multiple-impulse, multiple-revolution rendezvous problem which concerns orbital perturbations such as non-central force of the earth, the attracting forces of the sun and the moon, atmospheric drag and solar radiation pressure. A generalized multiple-revolution Lambert algorithm combined with a feasible iteration rendezvous approach is developed to transform the engineering rendezvous problem to a nonlinear programming problem. A reasonable approximation method is developed to greatly simplify the computation of the earth orbit perturbations which can save much time in the resulting optimization. A two-step method, which first uses a J2J3J4 analytical orbit model and then uses a Bulirsh-Stoer integration method to integrate simplified orbital model, with a high efficient Social Cognition Optimization (SCO) algorithm are used to solve such problem. A two-day rendezvous problem is solved to demonstrate the efficiency and effectiveness of the developed approach. The method shows that SCO algorithm which is inspired by human cognitive ability can be successfully used to optimize real-word engineering problem.

The Yarkovsky effect in generalized photogravitational 3-body problem

The task of creating a stable orbit of the Apophis asteroid satellite as a homogeneous triaxial ellipsoid is investigated. The simulation of the motion of the spacecraft around the asteroid was performed taking into account the main perturbations: from the attraction of celestial bodies, asteroids non-sphericity and solar radiation pressure, and taking into account the asteroids own rotation. It is shown that it is possible to create a stable orbit of an asteroid satellite. This orbit can be used for a detailed study of the characteristics of the asteroid and the refinement of its orbit using ground radio measurements of the motion of a satellite equipped with a radio beacon.

Although the forces of radiation pressure have been well known to physicists, 1 for a long time it has been difficult to study them in the laboratory due to the presence of temperature gradients causing thermal forces which could obscure the radiation pressure. It has only been since 1970, after the advent of suitable laser sources, that practical applications could be investigated, beginning with the experimental demonstration by A. Ashkin of acceleration and trapping of micron-sized particles using the force of radiation pressure from a cw visible laser.2 Additional steps were made in the following years, 3–6 but a major practical advancement was achieved in 1986 when Ashkin and coworkers demonstrated optical trapping of dielectric particles (in the size range from about 25 nm up to 10 μm) in water solution by a single-beam gradient force radiation-pressure trap. 7 An year later, Ashkin and Dziedzic coined the term «optical tweezers» when reporting the demonstration of the optical trapping and manipulation of individual viruses and bacteria in aqueous solution by laser radiation pressure. They «have used the trap as an optical tweezers for moving live single and multiple bacteria while being viewed under a high-resolution optical microscope».8 During the last decade there has been increased attention to the use of optical tweezers: this occurred mainly in microbiology, but optical tweezers are expected to play an important role in the future development of nanometric-scale technology for manipulation, control and analysis of ultra-small structures.

Modeling approaches for precise relativistic orbits: Analytical, Lie-series, and pN approximation

We investigate the surface thermophysical properties (thermal emissivity, thermal inertia, roughness fraction and geometric albedo) of asteroid (99942) Apophis, using the currently available mid-infrared observations from CanariCam on Gran Telescopio CANARIAS and far-infrared data from PACS on Herschel, based on the Advanced Thermophysical Model. We show that the thermal emissivity of Apophis should be wavelength dependent from 8.70 μm to 160 μm, and the maximum emissivity may appear around 20 μm, similar to that of Vesta. Moreover, we further derive the thermal inertia, roughness fraction, geometric albedo and effective diameter of Apophis within a possible 1 scale of , , and , and 3 scale of , , and . The derived low thermal inertia but high roughness fraction may imply that Apophis could have regolith on its surface, where stronger space weathering but weaker regolith migration has happened in comparison with asteroid Itokawa. Our results show that small-size asteroids could also have fine regolith on the surface, and further infer that Apophis may have been delivered from the Main Belt by the Yarkovsky effect.