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Path: Propulsion/Rocket
% Computes the thrust and exhaust velocity of a chemical rocket. Thrust is per unit area. The default is an H2/O2 rocket with f as the mixture raio. This was formerly called RocketH2. Type RocketChemical for a demo. qR must be the energy per unit mass of fuel + oxygen. Since version 8. -------------------------------------------------------------------------- Form: [thrust, uEQ] = RocketChemical( p0, pA, aStar, aE, qR, gamma, f ) -------------------------------------------------------------------------- ------ Inputs ------ p0 (1,1) Combustion pressure (N/m^2) pA (1,:) Exhaust pressure (N/m^2) aStar (1,1) Throat area (m^2) aE (1,1) Exit area (m^2) qR (1,1) Energy fuel (J/kg) gamma (1,1) Ratio of specific heats f (1,1) H2/O2 ratio (2 = stoichiometric) throttle (1,1) throttle value (0 < throttle < 1) ------- Outputs ------- thrust (1,:) Thrust (N) uEQ (1,:) Exhaust velocity (m/s) --------------------------------------------------------------------------
Common: Atmosphere/StdAtm Common: Graphics/Plot2D Propulsion: Chemical/QRHydrogen Propulsion: Gas/IsentropicExpansion Propulsion: Gas/MachFromAreaRatio Propulsion: Rocket/UEQR
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