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 ¯½º = J ŝ₁ŝ₁ + J ŝ₂§₂ + J §¸Ŝ3 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. 52 €3 3> 2t 55 Λ Из At the instant when Qt = 90°, the spacecraft S is oriented relative to the orbit such that 8₁ = 0° 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.
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 ¯½º = J ŝ₁ŝ₁ + J ŝ₂§₂ + J §¸Ŝ3 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. 52 €3 3> 2t 55 Λ Из At the instant when Qt = 90°, the spacecraft S is oriented relative to the orbit such that 8₁ = 0° 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.
Elements Of Electromagnetics
7th Edition
ISBN:9780190698614
Author:Sadiku, Matthew N. O.
Publisher:Sadiku, Matthew N. O.
ChapterMA: Math Assessment
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Transcribed Image Text: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
¯½º = J ŝ₁ŝ₁ + J ŝ₂§₂ + J §¸Ŝ3
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.
52
€3
3>
2t
55
Λ
Из
At the instant when Qt = 90°, the spacecraft S is oriented relative to the orbit such that
8₁ = 0°
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.
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