Above is my attempt at writing the code which failed. Below is what you need to use to write the the code.

1. Rocket Trajectory Computation: MATLAB Implementation O solutions submitted (max: Unlimited) This problem is designed to help you achieve the following course objectives: Understand basic principles of computer programming for numerical computation. Perform each of the above using structured professional-standard code. Problem Description: Implement the algorithm you developed in Part 1 of HW3 in a MATLAB function. Function e Reset MATLAB Documentation 5 function [h, V, n] = RocketTrajectoryidt, te, tf, ti, mo, c_de, c_di, mfdoto, ue, af) Input dt: time step (scalar) 4 to: initial time (scalar) tf: final tine scalar) 6 ti: time when parachute is to be deployed (scalar) 7 m: initial mass of rocket including fuel (scalar) BSC_de: drag coefficient before parachute deployment (scalar) 9 c_d1: drag coefficient after parachute deployment (scalar) 10 % mfdot: fuel mass flow rate (before fuel is burned up) (scalar) 11 % ue: exhaust velocity (scalar) 12 % mf: initial mass of fuel (scalar) 13 Output 14 h: time history of rocket altitude from to to tf (1 x N vector) 15 v: time history of rocket velocity from to to tf (1 x N vector) 16 % m: time history of rocket mass from to to tf (1 x N vector) 17 - 18 19 % Initialization 20 t = t:dt:tf; define the time vector: from to to tf with increment dt. 21 h = zeros(size(t)); 22 (1) = 8.0; initial altitude of rocket is 0.8 23 v = zeros(size(t)); 24 v(1) = 8.0; initial velocity of rocket is 8.0 25 i = zeros(size(t)); 26 mil) = m; initial mass of the rocket is given as input: mo. 27 g = 9.81; gravitational acceleration (m/s^2) 29 % calculate N: dimension of vector t 30 N = numel(t); 32 Write your function here. for i=1:N-1; if t(i)sat1 c_d=c_d1; else c_d=c_do; end end if mi)-(m-af)c= Thrust=; phi=8; 44 else Thrust=phixue; phi-phi0; 47 end 46 dvdt=-9-c_d/m(1)-(1) abs((1)) Thrust/m(i); v(1-1)=v( 1 )+dvdt dt; 53 h(i+1)=h(i)+v(i) dt; 55 m(i+1)=m( i )-phi-dt; 57 end Complete the following flow chart by filling the missing parts with the appropriate task numbers. Input: dt, to, tf, t1, mo, c_do c_di, phio, ue, mf Initialize vectors I, h, v, and m as discrete time instances, altitude, velocity, and mass: define g=9.81 (m's 2) Input variables: dt: time step (At); to: initial time; tf. final time; tl: time when parachute is to be deployed mo: initial mass of rocket (including fuel); c_do: drag coeff. before parachute deployment; c_dl: drag coeff. after parachute deployment; phio: rate of fuel consumption (before fuel is burned up); ue: exhaust velocity; mf: initial mass of fuel. calculate N = length(t) | B 1 Yes 10 2012 mono Yes 7. Yes No F cinstvo for i=1 to N for i=1 to N-1 3. define c d = c_do define c_d = c_d1 is mi) - (m0 - mf) 0? compute m(i + 1) = m(i) - phi * dt compute dvdt = -9 - c_d/m(i) *V(i) * (vi) + Thrust/m(i); 9. define Thrust = phi0 * ue; phi = phi0; 10. define Thrust = 0; phi = 0; 11. compute h(i + 1) = h(i) +v(i) * dt compute V1+1 = 0 + dvdt.dt Output: h, v. m Best Solution My Solutions Test Results Solution 4: All tests passed Submitted on 16 Feb 2020 at 22:26 | ID: 19518059 | Size: 36 O A HNM + OO 000 IL LLLLLLL L O I H. 1 A = 2; B = 4; 3 C = 3; 4 D = 5; 5 E = 10; 6 F = 9; G = 8; 8 H = 11; 9 I = 7; 10 % Note: This is just a template. It will not pass the test. You should change the right-hand-sides. 1. Rocket Trajectory Computation: MATLAB Implementation O solutions submitted (max: Unlimited) This problem is designed to help you achieve the following course objectives: Understand basic principles of computer programming for numerical computation. Perform each of the above using structured professional-standard code. Problem Description: Implement the algorithm you developed in Part 1 of HW3 in a MATLAB function. Function e Reset MATLAB Documentation 5 function [h, V, n] = RocketTrajectoryidt, te, tf, ti, mo, c_de, c_di, mfdoto, ue, af) Input dt: time step (scalar) 4 to: initial time (scalar) tf: final tine scalar) 6 ti: time when parachute is to be deployed (scalar) 7 m: initial mass of rocket including fuel (scalar) BSC_de: drag coefficient before parachute deployment (scalar) 9 c_d1: drag coefficient after parachute deployment (scalar) 10 % mfdot: fuel mass flow rate (before fuel is burned up) (scalar) 11 % ue: exhaust velocity (scalar) 12 % mf: initial mass of fuel (scalar) 13 Output 14 h: time history of rocket altitude from to to tf (1 x N vector) 15 v: time history of rocket velocity from to to tf (1 x N vector) 16 % m: time history of rocket mass from to to tf (1 x N vector) 17 - 18 19 % Initialization 20 t = t:dt:tf; define the time vector: from to to tf with increment dt. 21 h = zeros(size(t)); 22 (1) = 8.0; initial altitude of rocket is 0.8 23 v = zeros(size(t)); 24 v(1) = 8.0; initial velocity of rocket is 8.0 25 i = zeros(size(t)); 26 mil) = m; initial mass of the rocket is given as input: mo. 27 g = 9.81; gravitational acceleration (m/s^2) 29 % calculate N: dimension of vector t 30 N = numel(t); 32 Write your function here. for i=1:N-1; if t(i)sat1 c_d=c_d1; else c_d=c_do; end end if mi)-(m-af)c= Thrust=; phi=8; 44 else Thrust=phixue; phi-phi0; 47 end 46 dvdt=-9-c_d/m(1)-(1) abs((1)) Thrust/m(i); v(1-1)=v( 1 )+dvdt dt; 53 h(i+1)=h(i)+v(i) dt; 55 m(i+1)=m( i )-phi-dt; 57 end Complete the following flow chart by filling the missing parts with the appropriate task numbers. Input: dt, to, tf, t1, mo, c_do c_di, phio, ue, mf Initialize vectors I, h, v, and m as discrete time instances, altitude, velocity, and mass: define g=9.81 (m's 2) Input variables: dt: time step (At); to: initial time; tf. final time; tl: time when parachute is to be deployed mo: initial mass of rocket (including fuel); c_do: drag coeff. before parachute deployment; c_dl: drag coeff. after parachute deployment; phio: rate of fuel consumption (before fuel is burned up); ue: exhaust velocity; mf: initial mass of fuel. calculate N = length(t) | B 1 Yes 10 2012 mono Yes 7. Yes No F cinstvo for i=1 to N for i=1 to N-1 3. define c d = c_do define c_d = c_d1 is mi) - (m0 - mf) 0? compute m(i + 1) = m(i) - phi * dt compute dvdt = -9 - c_d/m(i) *V(i) * (vi) + Thrust/m(i); 9. define Thrust = phi0 * ue; phi = phi0; 10. define Thrust = 0; phi = 0; 11. compute h(i + 1) = h(i) +v(i) * dt compute V1+1 = 0 + dvdt.dt Output: h, v. m Best Solution My Solutions Test Results Solution 4: All tests passed Submitted on 16 Feb 2020 at 22:26 | ID: 19518059 | Size: 36 O A HNM + OO 000 IL LLLLLLL L O I H. 1 A = 2; B = 4; 3 C = 3; 4 D = 5; 5 E = 10; 6 F = 9; G = 8; 8 H = 11; 9 I = 7; 10 % Note: This is just a template. It will not pass the test. You should change the right-hand-sides