RocketChemical:

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.
--------------------------------------------------------------------------
   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)

--------------------------------------------------------------------------
   References: Martinez-Sanchez, M. "16.53 Course Notes"
               M.I.T. 1979.
--------------------------------------------------------------------------

Children:

Propulsion: Chemical/QRHydrogen
Propulsion: Gas/IsentropicExpansion
Propulsion: Gas/MachFromAreaRatio
Propulsion: Rocket/UEQR
Common: Atmosphere/StdAtm
Common: Graphics/Plot2D

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