Path: Propulsion/Electric
% Computes the thrust and specific impulse of an electric thruster. The exhaust velocity is computed from the element data and temperature. Computes the jet power from the mass flow and efficiency. -------------------------------------------------------------------------- Form: [iSP, power, mdot, AStar] = TElec( T, molWt, gamma, eff, TC, p ) -------------------------------------------------------------------------- ------ Inputs ------ T (1,:) Thrust (N) molWt (1,1) Molecular weight (kg/mole) gamma (1,1) Ratio of specific Heats eff (1,1) Efficiency TC (1,1) Chamber Temperature (°K) p (1,1) Chamber Pressure (N/m^2) ------- Outputs ------- iSP (1,:) Specific Impulse (sec) power (1,:) Power Consumption (watts) mdot (1,:) Mass flow (kg/sec) AStar (1,:) Throat area (m^2) --------------------------------------------------------------------------
Propulsion: Rocket/V2Isp SC: Environs/MolWt2R Common: CommonData/SwooshWatermark Common: General/CellToMat Common: General/MatToCell Common: General/Watermark Common: Graphics/NewFig Common: Graphics/Plot2D Common: Graphics/PltStyle
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