Path: Propulsion/Rocket
% Determines performance of a cold gas rocket. Thrust and mDot are functions of (p0,e). All inputs are mks. You need to compute p0 and t0 from the volume of the tank, mass of fuel and temperature. Type ColdGas for a demo. -------------------------------------------------------------------------- Form: [thrust, iSP, rho, mDot] = ColdGas( s, aStar, p0, pA, t0, e ) -------------------------------------------------------------------------- ------ Inputs ------ s (1,:) Gas to be used. aStar (1,1) Throat area (m^2) p0 (n) Chamber pressure after heating (N/m^2) pA (1,1) Ambient pressure (N/m^2) t0 (1,1) Temperature after heating (deg-K) e (1,1) Area ratio ------- Outputs ------- thrust (n,m) Thrust level (N) iSP (m) Specific impulse (sec) rho (n) Gas density (kg/m^3) mDot (n) Mass flow (kg/sec) --------------------------------------------------------------------------
Propulsion: Rocket/IdealRkt Propulsion: Rocket/TCoeff Propulsion: Rocket/V2Isp SC: Environs/MolWt2R Common: CommonData/SwooshWatermark Common: General/CellToMat Common: General/DeBlankLT Common: General/MatToCell Common: General/StrMtch Common: General/Watermark Common: Graphics/Mesh2 Common: Graphics/NewFig Common: Graphics/Plot2D Common: Graphics/PltStyle Common: Graphics/XLabelS Common: Graphics/YLabelS Common: Graphics/ZLabelS Common: Materials/GasProperties
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