I particularly only really need help making the simulink model

3. A satellite single-axis control system can be represented by the block diagram in Fig. The variables k, a, and b are controller parameters, and J is the spacecraft moment of inertia. Supposed the nominal moment of inertia is J = 10.8 x 108 slug ft2 and the controller parameters are k = 10.8 x 108, a=1, and b= 8. Controller Spacecraft o(t) + 04(0) Desired attitude k(s + a) s + b Jx2 Actual attitude Figure 2: A spacecraft single-axis attitude control block. (a) Develop a MATLAB script to compute the closed-loop transfer function ((s)/d(s). HINT: helpful commands in MATLAB to lookup are feedback and series (b) Compute and plot the step response to a 10 step input (c) Develop a Simulink model for the system and plot the response to a 20 step input 3. A satellite single-axis control system can be represented by the block diagram in Fig. The variables k, a, and b are controller parameters, and J is the spacecraft moment of inertia. Supposed the nominal moment of inertia is J = 10.8 x 108 slug ft2 and the controller parameters are k = 10.8 x 108, a=1, and b= 8. Controller Spacecraft o(t) + 04(0) Desired attitude k(s + a) s + b Jx2 Actual attitude Figure 2: A spacecraft single-axis attitude control block. (a) Develop a MATLAB script to compute the closed-loop transfer function ((s)/d(s). HINT: helpful commands in MATLAB to lookup are feedback and series (b) Compute and plot the step response to a 10 step input (c) Develop a Simulink model for the system and plot the response to a 20 step input