Path: Orbit/OrbitMechanics
% Approximate the acceleration due to drag over an orbit arc, h0 to hF. Uses AtmDens2. -------------------------------------------------------------------------- Form: [a,t,rho] = OrbitDrag( v0, gamma0, h, BC ); ------------------------------------------------------------------------ ------ Inputs ------ v0 (1,:) Initial velocity at h (km/s) gamma0 (1,:) Initial flight path angle at h0 (rad) h (1,:) Altitude (km) bC (1,1) Ballistic coefficient (kg/m^2) ------- Outputs ------- a (1,:) Acceleration over arc (km/s/s) t (1,:) Time (monotonic from 0) over arc (s) rho (1,:) Atmospheric density over arc (kg/m^3) ------------------------------------------------------------------------
AerospaceUtils: AtmosphericCalculations/AtmDens2 Orbit: OrbitMechanics/OrbitVel2D Common: General/DeBlankLT Common: Graphics/NewFig Common: Graphics/PltStyle Common: Graphics/TitleS Common: Graphics/XLabelS Common: Graphics/YLabelS
Back to the Orbit Module page