Path: Orbit/OrbitMechanics
% Compute (VF,gammaF) at hF from (v0,gamma0) at h0. -------------------------------------------------------------------------- Form: [VF, gammaF, a, e, H] = OrbitVel2D( v0, gamma0, h0, hF, rE, mu ) ------------------------------------------------------------------------ ------ Inputs ------ v0 (1,:) Initial velocity (km/s) gamma0 (1,:) Initial flight path angle (rad) h0 (1,:) Initial altitude (km) hF (1,:) Final altitude for orbit (km) rE (1,1) Planet radius (km) (earth is the default) mu (1,1) Gravitational potential (km^3/s^2) (earth is the default) ------- Outputs ------- vF (1,:) Velocity at hF (km/s) gammaF (1,:) Flight path angle at hF (rad) a (1,:) Orbit semi major axis (km) e (1,:) Orbit eccentricity H (1,:) Orbit angular momentum, (km^2/s) ------------------------------------------------------------------------
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