Outer Natural Satellites Orbits Ephemerides. ... Choose type of the ephemeride: . ... Values of the orbital elements [ output e sin( ), e cos( ), sin(i) sin( ), sin(i) cos( ) ] . Distances between the osculating orbits . ... Choose Second Satellite (for the distances) U17 - Sycorax U18 - Prospero U19 - Setebos U20 - Stephano U21 - Trinculo U22 - Francisco U23 - Margaret U24 - Ferdinand . ... Enter initial date (years) . Enter final date (years) . ... Enter upper limit of frequency deg/year . ...

... Format of the orbital elements | Estimation of the extrapolation errors | Version 1" of the orbital elements collection, determined by KIAM during flight and used for operations planning . Version 2" of the of the orbital elements collection, modified by IKI during flight and recommended for the orbital calculations during scientific data processing . ... Three kinds of the INTERBALL Auroral probe (IB_AUR) orbital elements' collections are presented here. ... IKI RAN | SSC IKI RAN | ...

. Computer Ephemeris. Elements of osculating planetary orbits. Explanations. Each row contains at 0h of Time Dynamical Terrestrial of specified date in system of mean equator and ecliptic J2000.0 the ecliptic osculating elements of heliocentric orbit: inclination of orbital plane (degrees), longitude of ascending node (degrees), argument of perigelion (degrees), semimajor axis (astronomical units), mean motion (degrees per day), eccentricity (dimensionless), mean anomaly (degrees).

Next: RSOG Pre-Observation Products . ... Mission Elements . ... The main mission elements (ME) are: . The RSOG, based at ASC, which is responsible for the science operation of the RadioAstron Mission. ... The Main Ballistic(Navigation) Center (MBC) belonging to Lavochkin Association coordinates preparation and exchange of orbit determination and orbit reconstraction ptoducts. ... Experiment codes of five characters are used in naming GRT related files. ... RSOG . ... Corr (GTS?) ... Corr (RSOG?) ...

... Abstract Determine the state (position, velocity) of an orbiting body from a set of elliptic, hyperbolic, or parabolic orbital elements. ... The difference between this state and the state predicted by the nominal orbit at the same epoch can be computed as follows. conics_c ( elts, later, nominal ); vsubg_c ( nominal, state, 6, diff ); printf( "Perturbation in x, dx/dt = %f %f", diff[0], diff[3] ); printf( " y, dy/dt = %f %f", diff[1], diff[4] ); printf( " z, dz/dt = %f %f", diff[2], diff[5] ); . ...

... Contents . ... Sidereal time . ... Mean longitude of the Moon, mean elements of the Moon's orbit and equator . ... Ephemeris for physical observations of the Sun . ... Ephemeris for physical observations of the Moon . ... Matrix elements for conversion to CIRS . ... Conversion of mean time to sidereal time (with accuracy 0.01 s ) . ... Conversion of sidereal time to mean time (with accuracy 0.01 s ) . ... Conversion of mean time to sidereal time (with accuracy 0.001 s and 0.0001 s ) . ...

... xmmtrack . ... xmmtrack is an interactive IDL application that visualizes the orbit and attitude data in an ODF in the form of a 3-D animation sequence. The presented scenery includes an astronomically accurate simulation of the Earth-Sun system plus the actual and predicted trajectory of the XMM satellite on its path around the Earth. ... Please note: XMM's orbit is highly time variable and the predicted orbit will significantly deviate from the actual trajectory if the reference epochs differ. ...

JSC History . ... NASA History . ... Space Shuttle: 1981 to 2011 . NASA's Space Shuttle orbiters were the first spacecraft capable of routinely launching into orbit like rockets and then returning to Earth as gliders. ... http://www.nasa.gov/agency/crm/shuttle/index.html . ... http://www.jsc.nasa.gov/history/oral_histories/sts-r.htm . ... http://www.jsc.nasa.gov/history/shuttle_pk/pk/Flight_001_STS-001_Press_Kit.pdf . ... http://www.jsc.nasa.gov/history/shuttle_pk/shuttle_press.htm . ...

Orbital elements of binary components in a hierachical system can be fit to either the visibility data directly or to the separation and position angle data. ... Then use Data|Astrometry to read a previously prepared file ("zetuma.psn") containing the positional data. ... Semi-major axis = 8.4214471 . Semi-minor axis = 4.7663976 . ... We can now use the Thiele-Innes method to estimate the orbital elements from this apparent ellipse and the data, as implemented with the Util|Orbit button. ...