Consider a satellite moving in a torque-free environment. The inertial frame and satellite body-fixed frame are represented by N-frame and B-frame, where {₁, 2, ñ3} and {b₁, 62, 63} are right-handed vector bases fixed in N-frame and B-frame, respectively. {b;} is aligned with the principal axis of inertia, where ₁ and 63 are associated with the minimum and maximum moments of inertia, respectively. Denote the satellite angular velocity by w = wibi; and the inertia tensor about the CoM by Ic. Suppose that I at time t = 0 is given by: Ic(t = 0) = 2ñ₁ñ₁ +2.25ñ₂ŵ₂ +2.25 3ñ3 -0.75 n₂n3 -0.75 n3n2 (dimensionless) (a): First, let us characterize the inertia property of the satellite from the given information. (a.1): Express the satellite inertia tensor about the CoM in B-frame. Sketch the inertia ellipsoid of this body with B-frame
Consider a satellite moving in a torque-free environment. The inertial frame and satellite body-fixed frame are represented by N-frame and B-frame, where {₁, 2, ñ3} and {b₁, 62, 63} are right-handed vector bases fixed in N-frame and B-frame, respectively. {b;} is aligned with the principal axis of inertia, where ₁ and 63 are associated with the minimum and maximum moments of inertia, respectively. Denote the satellite angular velocity by w = wibi; and the inertia tensor about the CoM by Ic. Suppose that I at time t = 0 is given by: Ic(t = 0) = 2ñ₁ñ₁ +2.25ñ₂ŵ₂ +2.25 3ñ3 -0.75 n₂n3 -0.75 n3n2 (dimensionless) (a): First, let us characterize the inertia property of the satellite from the given information. (a.1): Express the satellite inertia tensor about the CoM in B-frame. Sketch the inertia ellipsoid of this body with B-frame
Elements Of Electromagnetics
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![Consider a satellite moving in a torque-free environment. The inertial frame and satellite body-fixed frame
are represented by N-frame and B-frame, where {^₁, ñ2, ñ3} and {b₁, 62, 63} are right-handed vector bases
fixed in N-frame and B-frame, respectively. {b} is aligned with the principal axis of inertia, where 6₁ and
63 are associated with the minimum and maximum moments of inertia, respectively.
Denote the satellite angular velocity by w = wibį and the inertia tensor about the CoM by Ie. Suppose
that I at time t = 0 is given by:
Ic(t = 0) = 2ñ₁ñ₁ +2.25 ñ₂n₂ +2.25 ñ3ñ3 -0.75 n₂n3 -0.75 n3n2 (dimensionless)
(a): First, let us characterize the inertia property of the satellite from the given information.
(a.1):
Express the satellite inertia tensor about the CoM in B-frame. Sketch the inertia ellipsoid of
this body with B-frame.](/v2/_next/image?url=https%3A%2F%2Fcontent.bartleby.com%2Fqna-images%2Fquestion%2Fad0d55fe-d83b-4711-86a1-cee8ecea510f%2F89fde7ca-dd30-4d61-985d-1b877eedb376%2Fxyiz49_processed.png&w=3840&q=75)
Transcribed Image Text:Consider a satellite moving in a torque-free environment. The inertial frame and satellite body-fixed frame
are represented by N-frame and B-frame, where {^₁, ñ2, ñ3} and {b₁, 62, 63} are right-handed vector bases
fixed in N-frame and B-frame, respectively. {b} is aligned with the principal axis of inertia, where 6₁ and
63 are associated with the minimum and maximum moments of inertia, respectively.
Denote the satellite angular velocity by w = wibį and the inertia tensor about the CoM by Ie. Suppose
that I at time t = 0 is given by:
Ic(t = 0) = 2ñ₁ñ₁ +2.25 ñ₂n₂ +2.25 ñ3ñ3 -0.75 n₂n3 -0.75 n3n2 (dimensionless)
(a): First, let us characterize the inertia property of the satellite from the given information.
(a.1):
Express the satellite inertia tensor about the CoM in B-frame. Sketch the inertia ellipsoid of
this body with B-frame.
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