$($Use MATLAB for all parts$($A$,$ B$,$ C$,$ D$)$ of the question. Show code and make sure it works$)$

g$=32\mathrm{.}17405[$f$($t$)/($s$^(2))]($gravitational

acceleration on Earth$)$

h$=0[$ft$]($sea level$)$

U$\_(1)=169\mathrm{.}98[$f$($t$)/($s$)]$

$\backslash$Theta $\_(1)=5[$deg$]$

L$\_($p$)=-0\mathrm{.}3751[(1)/($s$)]$

L$\_(\backslash$beta $)=-1\mathrm{.}6639[(1)/($s$^(2))]$

L$\_($r$)=0\mathrm{.}4329[(1)/($s$)]$

I$\_(\backslash$delta $\_($r$))=0\mathrm{.}1347[(1)/($s$^(2))]$

I$\_(\backslash$delta $\_($a$))=1\mathrm{.}4331[(1)/($s$^(2))]$

Y$\_($p$)=0[$f$($t$)/($s$)]$

Y$\_(\backslash$beta $)=-14\mathrm{.}2686[$f$($t$)/($s$^(2))]$

Y$\_($r$)=0\mathrm{.}7819[$f$($t$)/($s$)]$

Y$\_(\backslash$delta $\_($r$))=2\mathrm{.}7364[$f$($t$)/($s$^(2))]$

Y$\_(\backslash$delta $\_($a$))=0[$f$($t$)/($s$^(2))]$

N$\_($p$)=-0\mathrm{.}0742[(1)/($s$)]$

N$\_(\backslash$beta $)=0\mathrm{.}8555[(1)/($s$^(2))]$

N$\_($r$)=-0\mathrm{.}1483[(1)/($s$)]$

N$\_(\backslash$delta $\_($r$))=-0\mathrm{.}4220[(1)/($s$^(2))]$

N$\_(\backslash$delta $\_($a$))=-0\mathrm{.}2852[(1)/($s$^(2))]$

Department of Aerospace Engineering

The full lateral$-$directional state$-$space system for this aircraft is given as:

Write a MATLAB$-$Simulink program to complete the following tasks: