Problem Description A simple formula to estimate the upward velocity of a rocket (neglecting the aerodynamic drag) is: 0 mo -qt where t = time, v= upward velocity, u = the velocity at which fuel is expelled relative to the rocket, mo = the initial mass of the rocket at time t 0,q- the fuel consumption rate, andg the downward acceleration of gravity Develop a MATLAB function which, for given parameters u, mo, q, and g, and a specified velocity v', computes the time t" that the rocket reaches this velocity Hint: (1) Formulate this problem into a root-finding problem, and solve it using the MATLAB built-in function "fzero". (2) The initial bracketing interval (or initial guess) for "fzero" must be within the domain of the root-finding function. Note that the above function v(t) has a bounded domain (due to "In"). Solution MATLAB Documentation 1 function tstar-fzero-rocket-example ( u, g, q, m0, vstar) 2 Input 3/% 41 % 5/% 61 % 71 % 81 % 9 %% Output m0: initial mass of rocket at time t-0 g gravitational constant q fuel consumption rate u velocity at which fuel expelled relative to rocket vstar: upward velocity value for which tstar is to be determined % tstar: the time that the rocket reaches the specified velocity, vstar. (scalar) 12%% Write your code here 14 15 end Problem Description A simple formula to estimate the upward velocity of a rocket (neglecting the aerodynamic drag) is: 0 mo -qt where t = time, v= upward velocity, u = the velocity at which fuel is expelled relative to the rocket, mo = the initial mass of the rocket at time t 0,q- the fuel consumption rate, andg the downward acceleration of gravity Develop a MATLAB function which, for given parameters u, mo, q, and g, and a specified velocity v', computes the time t" that the rocket reaches this velocity Hint: (1) Formulate this problem into a root-finding problem, and solve it using the MATLAB built-in function "fzero". (2) The initial bracketing interval (or initial guess) for "fzero" must be within the domain of the root-finding function. Note that the above function v(t) has a bounded domain (due to "In"). Solution MATLAB Documentation 1 function tstar-fzero-rocket-example ( u, g, q, m0, vstar) 2 Input 3/% 41 % 5/% 61 % 71 % 81 % 9 %% Output m0: initial mass of rocket at time t-0 g gravitational constant q fuel consumption rate u velocity at which fuel expelled relative to rocket vstar: upward velocity value for which tstar is to be determined % tstar: the time that the rocket reaches the specified velocity, vstar. (scalar) 12%% Write your code here 14 15 end