------------------------------------------------------------------------------- Computes the flight path angle from eccentricity and true anomaly. This is the angle between the tangent to r and the velocity vector for any orbit. ------------------------------------------------------------------------------- Form: [gamma, cgamma, sgamma] = FPA( e, nu ) ------------------------------------------------------------------------------- ------ Inputs ------ e Eccentricity nu True anomaly ------- Outputs ------- gamma The flight path angle cgamma Cosine of gamma sgamma Sine of gamma -------------------------------------------------------------------------------