converting a state vector to C3, RLA and DLA

11142022, 06:13 PM
Post: #1




converting a state vector to C3, RLA and DLA
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 Earthcenteredinertial (ECI) coordinate system.
This demo program uses "hardwired" 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/blb21vpcr5jszi...r.zip?dl=0 

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