Use MatLab or Python:

A rocket is launched from sea level on a purely vertical trajectory. Accelerometers in the rocket

yield the following for the vertical acceleration of the rocket:

For $t>35sec,a_{\text{v}\text{e}\text{r}\text{t}\text{i}\text{c}\text{a}\text{l}}=-11\mathrm{.}5\frac{m}{s^2}P,TT,P0$

For $t>35sec,a_{\text{v}\text{e}\text{r}\text{t}\text{i}\text{c}\text{a}\text{l}}=-11\mathrm{.}5\frac{m}{s^2}$

The rocket $is$ also capable $of$ measuring the temperature, pressure, and density $of$ the atmosphere

$asit$ moves through $it.$ Assuming a "Standard Atmosphere" write a program which will

determine the $P,T,$ and $as$ a function $of$ time until the maximum rocket altitude $is$ attained.

You are $to$ submit $6$ plots along with your code:

Altitude $vs$ time

Velocity $vs$ time

Density $vs$ time

Pressure $vs$ time

Temperature $vs$ time

Altitude $vs$ temperature $(the$ standard atmosphere plot$)$

I would suggest writing a standard atmosphere calculator that can take a single altitude $asan$

input and return $T,P,$ and $as$ outputs. Call this function within the larger code that $is$ flying this

rocket through the atmosphere.

You are $to$ submit a short report describing the problem, your approach $to$ the problem, and your

analysis $of$ your results. You should discuss the positive and negative aspects $of$ this simple

model and discuss how $it$ can $be$ improved. What would make this a more realistic proUblem?

What would $it$ take $to$ allow this rocket $to$ land gently $on$ the surface?