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

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Consider a satellite moving in a torque-free environment. The inertial frame and satellite body-fixed frame are represented by \( \mathcal{N}\)-frame and \( \mathcal{B}\)-frame, where \( \{\hat{n}_1, \hat{n}_2, \hat{n}_3\} \) and \( \{\hat{b}_1, \hat{b}_2, \hat{b}_3\} \) are right-handed vector bases fixed in \( \mathcal{N}\)-frame and \( \mathcal{B}\)-frame, respectively. \( \{\hat{b}_i\} \) is aligned with the principal axis of inertia, where \( \hat{b}_1 \) and \( \hat{b}_3 \) are associated with the minimum and maximum moments of inertia, respectively.

Denote the satellite angular velocity by \( \omega = \omega_i \hat{b}_i \) and the inertia tensor about the CoM by \( \bar{I}_c \). Suppose that \( \bar{I}_c \) at time \( t = 0 \) is given by:

\[
\bar{I}_c(t = 0) = 2 \hat{n}_1 \hat{n}_1 + 2.25 \hat{n}_2 \hat{n}_2 + 2.25 \hat{n}_3 \hat{n}_3 - 0.75 \hat{n}_2 \hat{n}_3 - 0.75 \hat{n}_3 \hat{n}_2 \quad \text{(dimensionless)}
\]

(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 \( \mathcal{B}\)-frame. Sketch the inertia ellipsoid of this body with \( \mathcal{B}\)-frame.**
Transcribed Image Text:Consider a satellite moving in a torque-free environment. The inertial frame and satellite body-fixed frame are represented by \( \mathcal{N}\)-frame and \( \mathcal{B}\)-frame, where \( \{\hat{n}_1, \hat{n}_2, \hat{n}_3\} \) and \( \{\hat{b}_1, \hat{b}_2, \hat{b}_3\} \) are right-handed vector bases fixed in \( \mathcal{N}\)-frame and \( \mathcal{B}\)-frame, respectively. \( \{\hat{b}_i\} \) is aligned with the principal axis of inertia, where \( \hat{b}_1 \) and \( \hat{b}_3 \) are associated with the minimum and maximum moments of inertia, respectively. Denote the satellite angular velocity by \( \omega = \omega_i \hat{b}_i \) and the inertia tensor about the CoM by \( \bar{I}_c \). Suppose that \( \bar{I}_c \) at time \( t = 0 \) is given by: \[ \bar{I}_c(t = 0) = 2 \hat{n}_1 \hat{n}_1 + 2.25 \hat{n}_2 \hat{n}_2 + 2.25 \hat{n}_3 \hat{n}_3 - 0.75 \hat{n}_2 \hat{n}_3 - 0.75 \hat{n}_3 \hat{n}_2 \quad \text{(dimensionless)} \] (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 \( \mathcal{B}\)-frame. Sketch the inertia ellipsoid of this body with \( \mathcal{B}\)-frame.**
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