Path: Orbit/OrbitCoord
% Compute (VF,gammaF) at hF from (V0,gamma0) at h0. Given the initial velocity, altitude and flight path angle, compute the angular momentum, semi-major axis and eccentricity, as well as velocity and flight path angle at a second altitude. -------------------------------------------------------------------------- Form: [H,a,e,V2,fpa2] = VelAltFpaToHAE( V, h, fpa, h2, mu, R ) -------------------------------------------------------------------------- ------ Inputs ------ V (1,1) Velocity magnitude (km/s) h (1,1) Altitude (km) fpa (1,1) Flight path angle (rad) h2 (1,1) Second altitude to compute V2,fpa2 for (rad) mu (1,1) Gravitational constant R (1,1) Planet equatorial radius ------- Outputs ------- H (1,1) Angular momentum (km^2/s) a (1,1) Semi-major axis (km) e (1,1) Eccentricity V2 (1,1) Velocity at altitude h2 (km/s) fpa2 (1,1) Flight path angle at altitude h2 (rad) --------------------------------------------------------------------------
AC: ACData/ACTConstants SC: SCData/sCTConstants Common: CommonData/Constants Common: CommonData/xSplashSmall Common: Database/Constant Common: General/DeleteCell
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