Consider the vertical motion of a rocket. Initially, its altitude, velocity, and mass are 0.0 m, 0.0 m/s, and m0 kg, respectively. After it is launched, the rocket has altitude ( h ), velocity ( v ), and mass ( m ) .

Note:

1. the rate of fuel consumption phi is a non-zero constant ( phi0 ) before the fuel is completely burned, and zero afterward.

2. The rocket carries a parachute which is programmed to deploy at time t1. The value of drag coefficient c_d is cd_0 before time t1, and increases to cd_1 afterwards.

Complete the following flow chart by filling the missing parts with the appropriate task numbers.

The answers I've tried and failed:

A = 1, B = 4, C = 3, D = 5, E = 10, F = 9, G = 8, H = 7, I = 11

A = 1, B = 4, C = 3, D = 5, E = 10, F = 9, G = 8, H = 11, I = 7

A = 1, B = 4, C = 3, D = 6, E = 9, F = 10, G = 8, H = 7, I = 11

A = 1, B = 4, C = 3, D = 6, E = 9, F = 10, G = 8, H = 11, I = 7

Input Input variables: dt: time step (At); to initial time; final time; tl: time when parachute is to be deployed m0: initial mass of rocket (including fuel); c_do: drag coeff. before parachute deployment; c dl: drag coeff. after parachute deployment; phi0: rate of fuel consumption (before fuel is burned up); ue: exhaust velocity; mf initial mass of fuel Initialize vectors t, h, v, and m as discrete time instances, altitude, velocity, and mass: define g 9.81 (m's 2 calculate N = length() Yes for i-1 to N for i-1 to N-1 define c-d = c_d0 define cd cd! is m(i) - (m0 - mf) s 0? is mf 0? compute m(1 + 1) = m(i) _ phi * dt compute dvdt =-g-c-d/m(i) * v(i) * Ir(i)| + Thrust/m(1); define Thrust = phi0 * ue; phi = phi0; define Thrust=0; phi=0; compute h (i + 1) = h(i) + u(i) * dt Yes No - - compute v+1-vt dvdt dt 10. 11, Output: h, v, m Input Input variables: dt: time step (At); to initial time; final time; tl: time when parachute is to be deployed m0: initial mass of rocket (including fuel); c_do: drag coeff. before parachute deployment; c dl: drag coeff. after parachute deployment; phi0: rate of fuel consumption (before fuel is burned up); ue: exhaust velocity; mf initial mass of fuel Initialize vectors t, h, v, and m as discrete time instances, altitude, velocity, and mass: define g 9.81 (m's 2 calculate N = length() Yes for i-1 to N for i-1 to N-1 define c-d = c_d0 define cd cd! is m(i) - (m0 - mf) s 0? is mf 0? compute m(1 + 1) = m(i) _ phi * dt compute dvdt =-g-c-d/m(i) * v(i) * Ir(i)| + Thrust/m(1); define Thrust = phi0 * ue; phi = phi0; define Thrust=0; phi=0; compute h (i + 1) = h(i) + u(i) * dt Yes No - - compute v+1-vt dvdt dt 10. 11, Output: h, v, m