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. -------------------------------------------------------------------------- Form: [dX, dI] = SolidR( g, t0, aStar, a, n, R, sigmaP, dT, rhoP, mP0, cAB, nAB, rM, l, x ) -------------------------------------------------------------------------- ------ 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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