The longitudinal dynamics of the aircraft is defined by:x = Ax+Bu, A=B=B₁ = [0B = BE = [0For measurementsC=C₁ = [1CaC=C₁ = [0O a.000000-0.0500.05-0.3With the thrust only input or the elevator only input, the corresponding B matrices are:unstable1 0 0 0],0 1 0 0]0.001 00010 0 -2 -0.1]C=C₂ = [0Is the uncontrolled, open loop system?d. unstable1-0.2000001−11of either the altitude, speed or pitch angle, the corresponding C matrices are:0 0 0 0],O b. not asymptotically stableO c. asymptotically stable-10.10-1-0.7"y = Cx

it is asked to check the open loop stability of given system

The longitudinal dynamics of the aircraft is defined by: x = Ax+Bu, A = 0 0 B=BT = [0 B = B =[ 0 0 0 0 0 -0.05 0 0.05 -0.3 0 0 1 -0.2 0 0 0 With the thrust only input or the elevator only input, the corresponding B matrices are: 0.001 0 0 0 1 -2 -0.1] 0 -1 0 0.1 1 0 -1 -1 1 -0.7 For measurements C=C₁ = [1 0 0 0 0], C=C₁ = [0 1 0 0 0], C=C₂ = [0 0 1 0 0] Is the uncontrolled, open loop system? O a. unstable O b. not asymptotically stable O c. asymptotically stable O d. unstable " y = Cx of either the altitude, speed or pitch angle, the corresponding C matrices are:

The longitudinal dynamics of the aircraft is defined by: x = Ax+Bu, A = 0 0 B=BT = [0 B = B =[ 0 0 0 0 0 -0.05 0 0.05 -0.3 0 0 1 -0.2 0 0 0 With the thrust only input or the elevator only input, the corresponding B matrices are: 0.001 0 0 0 1 -2 -0.1] 0 -1 0 0.1 1 0 -1 -1 1 -0.7 For measurements C=C₁ = [1 0 0 0 0], C=C₁ = [0 1 0 0 0], C=C₂ = [0 0 1 0 0] Is the uncontrolled, open loop system? O a. unstable O b. not asymptotically stable O c. asymptotically stable O d. unstable " y = Cx of either the altitude, speed or pitch angle, the corresponding C matrices are:

Introductory Circuit Analysis (13th Edition)

13th Edition

ISBN:9780133923605

Author:Robert L. Boylestad

Publisher:Robert L. Boylestad

Chapter1: Introduction

Section: Chapter Questions

Problem 1P: Visit your local library (at school or home) and describe the extent to which it provides literature...

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