The longitudinal dynamics of the aircraft is defined by: x = Ax+Bu, A= B=BT = [0 B=BE = [0 0 0 0 0 0 a. b. 0 -0.05 0 0.05 -0.3 unstable With the thrust only input or the elevator only input, the corresponding B matrices are: 0 0 For measurements C=C₁ = [1 0 0 0 0], C=C₁ = [0 1 0 0 o], C=C₂ = [0 0 1 0 0] Is the uncontrolled, open loop system? 1 -0.2 0 0 0 0.001 000 -2 -0.1] asymptotically stable 0 -1 0 0.1 1 0 -1 -1 1 -0.7 C. not asymptotically stable d. unstable o 1 > of either the altitude, speed or pitch angle, the corresponding C matrices are: y = Cx

The longitudinal dynamics of the aircraft is defined by: x = Ax+Bu, A= B=BT = [0 B=BE = [0 0 0 0 0 0 a. b. 0 -0.05 0 0.05 -0.3 unstable With the thrust only input or the elevator only input, the corresponding B matrices are: 0 0 For measurements C=C₁ = [1 0 0 0 0], C=C₁ = [0 1 0 0 o], C=C₂ = [0 0 1 0 0] Is the uncontrolled, open loop system? 1 -0.2 0 0 0 0.001 000 -2 -0.1] asymptotically stable 0 -1 0 0.1 1 0 -1 -1 1 -0.7 C. not asymptotically stable d. unstable o 1 > of either the altitude, speed or pitch angle, the corresponding C matrices are: y = Cx

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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