|
SUPPORT SITE |
|
|
|
SUPPORT SITE |
|
Path: Orbit/Interplanetary
% Generate elements and orbit state for the asteroid Apophis. Utilizes an ephemeris point from 2009. -------------------------------------------------------------------------- Form: [elA, rA, vA, jD] = ApophisOrbit -------------------------------------------------------------------------- ------ Inputs ------ None ------- Outputs ------- elA (1,6) [a i Omega omega e M] rA (3,1) Heliocentric position (km) vA (3,1) Heliocentric velocity (km) jD (1,1) Julian day number of epoch --------------------------------------------------------------------------
Common: Database/Constant Common: Time/Date2JD SC: BasicOrbit/RV2El SC: BasicOrbit/RVFromKepler
Back to the Orbit Module page