Report of the IAU/IAG Working Group on cartographic coordinates and rotational elements: 2006

Seidelmann, P. K.; Archinal, B. A.; A’Hearn, Michael F.; Conrad, Albert; Consolmagno, G. J.; Hestroffer, Daniel; Hilton, James L.; Krasinsky, G. A.; Neumann, Gregory A.; Oberst, J.; Stooke, P. J.; Tedesco, E. F.; Tholen, David J.; Thomas, P. C.; Williams, I. P.

doi:10.1007/s10569-007-9072-y

Cited by 255 publications

(171 citation statements)

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“…The ME system is recommended because nearly all cartographic products of the past and present have been aligned to it (Davies & Colvin 2000). The difference in the coordinates of a point on the surface of the Moon between these systems is approximately less than 1 km (Seidelmann et al 2007). Coordinates in the ME reference system are consistent with the IAU/IAG working group's definitions.…”

Section: Coordinate Transformations Between the Earth And The Moonmentioning

confidence: 88%

“…The E-EME2000 reference frame is often assumed to be identical to the International Celestial Reference Frame (ICRF) (Roncoli 2005). The recommended values for the direction of the north pole of rotation and the prime meridian of the Moon can be found in works by Roncoli (2005) and Seidelmann et al (2007). Using the IAU/IAG-defined approximate expressions, the Moon-centered Moon Mean Equator and IAU vector of epoch J2000 (M-MME2000) coordinate system can be easily derived.…”

Section: Coordinate Transformations Between the Earth And The Moonmentioning

confidence: 99%

“…Actually, the precise lunar gravity field was developed using the lunar orientation specified by the JPL planetary ephemeris series in the PA system. On the ephemeris, the orientation of the Moon with respect to the Earth-centered Earth Mean Equator of J2000 (EME2000) is given by three Euler angles and their rates for PA system as follows (Seidelmann et al 2007). The three Euler angles include ϕ , the angle along the ICRF equator, from the ICRF X-axis to the ascending node of the lunar equator; θ , the inclination of the lunar equator to the ICRF equator; and ψ , the angle along the lunar equator from the node to the lunar prime meridian.…”

Section: Coordinate Transformations Between the Earth And The Moonmentioning

confidence: 99%

See 2 more Smart Citations

Development of Precise Lunar Orbit Propagator and Lunar Polar Orbiter's Lifetime Analysis

Song¹,

Park²,

Kim³

et al. 2010

Journal of Astronomy and Space Sciences

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To prepare for a Korean lunar orbiter mission, a precise lunar orbit propagator; Yonsei precise lunar orbit propagator (YSPLOP) is developed. In the propagator, accelerations due to the Moon's non-spherical gravity, the point masses of the Earth, Moon, Sun, Mars, Jupiter and also, solar radiation pressures can be included. The developed propagator's performance is validated and propagation errors between YSPOLP and STK/Astrogator are found to have about maximum 4-m, in along-track direction during 30 days (Earth's time) of propagation. Also, it is found that the lifetime of a lunar polar orbiter is strongly affected by the different degrees and orders of the lunar gravity model, by a third body's gravitational attractions (especially the Earth), and by the different orbital inclinations. The reliable lifetime of circular lunar polar orbiter at about 100 km altitude is estimated to have about 160 days (Earth's time). However, to estimate the reasonable lifetime of circular lunar polar orbiter at about 100 km altitude, it is strongly recommended to consider at least 50 × 50 degrees and orders of the lunar gravity field. The results provided in this paper are expected to make further progress in the design fields of Korea's lunar orbiter missions.

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Section: Coordinate Transformations Between the Earth And The Moonmentioning

confidence: 88%

Section: Coordinate Transformations Between the Earth And The Moonmentioning

confidence: 99%

Section: Coordinate Transformations Between the Earth And The Moonmentioning

confidence: 99%

See 1 more Smart Citation

Development of Precise Lunar Orbit Propagator and Lunar Polar Orbiter's Lifetime Analysis

Song¹,

Park²,

Kim³

et al. 2010

Journal of Astronomy and Space Sciences

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“…ρ static and p static are functions only of r. This is justified by the fact that the dynamics are a perturbation to the mean hydrostatic state, and the planet's deviation from spherical geometry is small (the equatorial radius is larger than the polar radius by 2.3% and 1.7% for Uranus and Neptune respectively [33]), and therefore we can to good approximation calculate the dynamical contribution to the gravity harmonics (∆J dyn n ) in spherical geometry. This approximation retains density anomalies ρ associated with the velocity field u, but does not retain the dynamical density distortions associated with overall planetary oblateness which we discuss in detail below.…”

Section: Supplementary Information Researchmentioning

confidence: 99%

“…For cases with no core the density at β = 0 is not constrained, and its derivative at β = 0 is set to zero. Table S1: Uranus and Neptune planet characteristics [32,14,15,33]. The gravity field values correspond to a reference equatorial radius of 26,200 km for Uranus and 25,225 km for Neptune following the convention in [32].…”

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confidence: 99%

Atmospheric confinement of jet streams on Uranus and Neptune

Kaspi

Showman

Hubbard

et al. 2013

Nature

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Supplementary Informationvalues we use a suite of core/envelope internal structure models, with a wide range of core depths, core densities and envelope density profiles.The core is taken to be of constant density with the core density ranging between 0.8 × 10 4 < ρ core < 1.2 × 10 4 kg m −3 , and core radius extending up to 30% of the planetary radius on Neptune (0 < r core < 0.3 R, where R is the mean planetary radius), and 20% on Uranus, following the widest possible range of core densities given by [16, 17, 19]. We systematically explore this parameter space where for each case of ρ core and r core we then match an envelope represented by a 6th order polynomial with a monotonic density distribution so that ρ static = ρ core for 0 < r < r core (S1)where β = r/R is the normalized radius. The coefficients (a n ) are determined by constraints on the static density (ρ static ). The first constraint on the static density is that the density is zero at the surface, satisfied by setting the sum of the six polynomial coefficients to zero at β = 1. The second constraint is that the integrated density over the entire volume must equal to the planetary mass.The third constraint is that the density derivative at β = 1 equals the derivative of the density at the 1 bar pressure level (equal to -0.1492 and -0.2425 kg m −4 for Uranus and Neptune respectively,[31]). The first degree term in Eq. S2 is missing so that the derivative of the density goes to zero at the center for models with no core, and another constraint sets this value to zero at the core-envelope boundary for models with cores. The last constraint limits the value of J 2 to within the error estimates of the observed value of 3341.29 ± 0.72 × 10 −6 and 3408.43 ± 4.50 × 10 −6 for 1 Uranus and Neptune respectively [14, 15]. Since we are interested in determining the resulting J 4 we do not impose any constraints on J 4 , as done in most studies where the J 4 is constrained to within the observed values of J 4 (e.g., [13]). For cases with no core the density at β = 0 is not constrained, and its derivative at β = 0 is set to zero.Uranus Neptune 25

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The long‐term steady motion of Saturn's hexagon and the stability of its enclosed jet stream under seasonal changes

Sánchez‐Lavega

Río‐Gaztelurrutia

Hueso

et al. 2014

Geophysical Research Letters

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We investigate the long-term motion of Saturn's north pole hexagon and the structure of its associated eastward jet, using Cassini imaging science system and ground-based images from 2008 to 2014. We show that both are persistent features that have survived the long polar night, the jet profile remaining essentially unchanged. During those years, the hexagon vertices showed a steady rotation period of 10 h 39 min 23.01 ± 0.01 s. The analysis of Voyager 1 and 2 (1980)(1981) and Hubble Space Telescope and ground-based (1990-1991) images shows a period shorter by 3.5 s due to the presence at the time of a large anticyclone. We interpret the hexagon as a manifestation of a vertically trapped Rossby wave on the polar jet and, because of their survival and unchanged properties under the strong seasonal variations in insolation, we propose that both hexagon and jet are deep-rooted atmospheric features that could reveal the true rotation of the planet Saturn.

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Report of the IAU/IAG Working Group on cartographic coordinates and rotational elements: 2006

Cited by 255 publications

References 28 publications

Development of Precise Lunar Orbit Propagator and Lunar Polar Orbiter's Lifetime Analysis

Development of Precise Lunar Orbit Propagator and Lunar Polar Orbiter's Lifetime Analysis

Atmospheric confinement of jet streams on Uranus and Neptune

The long‐term steady motion of Saturn's hexagon and the stability of its enclosed jet stream under seasonal changes

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