converting a state vector to C3, RLA and DLA - Printable Version +- HP Forums ( https://www.hpmuseum.org/forum)+-- Forum: HP Software Libraries ( /forum-10.html)+--- Forum: HP Prime Software Library ( /forum-15.html)+--- Thread: converting a state vector to C3, RLA and DLA ( /thread-19142.html) |

converting a state vector to C3, RLA and DLA - cdeaglejr - 11-14-2022 06:13 PM
This HP Prime program, named demo_rv2hyper, can be used to calculate C3 (twice the specific (per unit mass) orbital energy), RLA (the right ascension) and DLA (declination) of the asymptote of a hyperbolic trajectory. This computer program assumes that the hyperbolic targets, state vector and classical orbital elements are all in the same Earth-centered-inertial (ECI) coordinate system. This demo program uses "hard-wired" x, y and z components of the position and velocity vectors of a typical hyperbolic orbit. For this example // eci position vector (kilometers) r(1) := -6.28143245744413e3; r(2) := -1.71886519445504e3; r(3) := -8.16419427413681e2; // eci velocity vector (kilometers/second) v(1) := 3.30316298967422; v(2) := -9.56155991173246; v(3) := -5.28351302498913; The zipped archive for this program and its documentation can be downloaded from https://www.dropbox.com/s/blb21vpcr5jszig/demo_rv2hyper.zip?dl=0 |