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.
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Form:
[thrust, uEQ] = RocketChemical( p0, pA, aStar, aE, qR, gamma, f )
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Inputs
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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)
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Outputs
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thrust (1,:) Thrust (N)
uEQ (1,:) Exhaust velocity (m/s)
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References: Martinez-Sanchez, M. "16.53 Course Notes"
M.I.T. 1979.
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Propulsion: Chemical/QRHydrogen Propulsion: Gas/IsentropicExpansion Propulsion: Gas/MachFromAreaRatio Propulsion: Rocket/UEQR Common: Atmosphere/StdAtm Common: Graphics/Plot2D
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