System Dynamics
3rd Edition
ISBN: 9780073398068
Author: III William J. Palm
Publisher: MCG
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Chapter 5, Problem 5.4P
Draw a block diagram for the following equation. The output is X (s); the inputs are F(s) and G(s).
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Problem 3: A cube-shaped spacecraft is in a circular Earth orbit. Let N (n,) be inertial
and the spacecraft is denoted S (ŝ₁). The spacecraft is described such that
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Location of the spacecraft in the orbit is determined by the orbit-fixed unit vectors ê, that
are oriented by the angle (Qt), where is a constant angular rate.
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At the instant when Qt = 90°, the spacecraft S is oriented relative to the orbit such that
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Space-three 1-2-3 angles 0₂ = 60°
and
ES = $₂ rad/s
0₁ = 135°
(a) At this instant, determine the direction cosine matrix that describes the orientation of
the spacecraft with respect to the inertial frame N.
Chapter 5 Solutions
System Dynamics
Ch. 5 - Prob. 5.1PCh. 5 - Obtain the transfer function Xs/Fs from the block...Ch. 5 - Obtain the transfer function Xs/Fs from the block...Ch. 5 - Draw a block diagram for the following equation....Ch. 5 - Draw a block diagram for the following model. The...Ch. 5 - Referring to Figure P5.6, derive the expressions...Ch. 5 - Prob. 5.7PCh. 5 - Prob. 5.10PCh. 5 - Obtain the state model for the reduced-form model...Ch. 5 - Obtain the state model for the reduced-form model...
Ch. 5 - Prob. 5.13PCh. 5 - Obtain the state model for the transfer-function...Ch. 5 - Obtain the state model for the two-mass system...Ch. 5 - Prob. 5.16PCh. 5 - Put the following model in standard state-variable...Ch. 5 - Given the state-variable model...Ch. 5 - Given the following state-variable models, obtain...Ch. 5 - Prob. 5.20PCh. 5 - The transfer function of a certain system is...Ch. 5 - Prob. 5.22PCh. 5 - Prob. 5.23PCh. 5 - Use MATLAB to obtain a state model for the...Ch. 5 - Use MATLAB to obtain a state-variable model for...
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