SolidR:

Path: Propulsion/Rocket

% Computes the right hand side of the dynamical equations for a solid rocket engine
 The state vector is

   [pressure;volume;mass].

 In this model the burning area is assumed to be a function

   aB = cAB.*(mP.^nAB) 
 
 nAB is an array of exponents and cAB is an array of coefficients.

   mP = 1 - x(3)/mP0

 The initial pressure must be > 0. Any small number will do.
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   Form:
   [dX, dI] = SolidR( g, t0, aStar, a, n, R, sigmaP, dT, rhoP, mP0, cAB, nAB, rM, l, x )
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   ------
   Inputs
   ------
   g           (1,1)   Ratio of specific heats for the gas
   t0          (1,1)   Combustion temperature
   aStar       (1,1)   Throat area
   a           (1,1)   Burning rate coefficient
   n           (1,1)   Burning rate exponent
   R           (1,1)   Gas constant
   sigmaP      (1,1)   Burning rate temperature sensitivity coefficient
   dT          (1,1)   Change in temperature from nominal
   rhoP        (1,1)   Fuel density
   mP0         (1,1)   Total propellant mass
   cAB         (1,:)   Burning area coefficients
   nAB         (1,:)   Burning area exponents
   rM          (1,1)   Propellant radius
   l           (1,1)   Engine length
   x           (3,1)   State [pressure;volume;mass]

   -------
   Outputs
   -------
   dX          (3,1)   State derivative
   dI          (2,1)   Inertia derivatives [polar; transverse]

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