Path: Propulsion/Rocket
% Computes the thrust and exhaust velocity as a function of pressure. Utilizes the engine data measured at vacuum and a specified reference pressure. Type RocketFromUEAndT for a demo of the Shuttle Main Engine (SME). -------------------------------------------------------------------------- Form: [t, uE] = RocketFromUEAndT( uE0, uEA, t0, tA, pA, p ) -------------------------------------------------------------------------- ------ Inputs ------ uE0 (1,1) Exhaust velocity in vacuum uEA (1,1) Exhaust velocity at pressure pA t0 (1,1) Thrust in vacuum tA (1,1) Thrust at pressure pA pA (1,1) Reference pressure p (1,:) Pressure ------- Outputs ------- t (1,1) Thrust uE (1,1) Exhaust velocity --------------------------------------------------------------------------
Common: Graphics/Plot2D
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