The aircraft turboprop engine is controlled by a closed-loop system with block diagram shown below. The engine is modeled as a multivariable system with input vector E(s), which contains the fuel rate and propeller blade angle, and output vector Y(s), consisting of the engine speed and turbine-inlet temperature. The transfer function matrices are given as 2 10 1 0 H(s) = s(s + 2) G,(s) =| 5 1 R(s) Y(s) 3) H(S) Find the closed-loop transfer function matrix +G,(s)H(s)G,(s) for the multivariable system.