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How do I find the "effective" yaw, pitch and roll from a rotated Inertial Measurement Unit?

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Consider a right-hand coordinate system, N with basisvectors ${hat{x_N},hat{y_N},hat{z_N}}$ where:

  • the x-axis is pointing north
  • the y-axis is pointing east

Consider an airplane with a right-hand coordinate system, B with basis vectors ${hat{x_B},hat{y_B},hat{z_B}}$ where:

  • the x-axis is pointing towards the nose of the plane
  • the y-axis is pointing towards the right wing

Looking at an online Euler Angle Visualization Tool
it seems that the definition of roll, pitch and yaw of the plane is ?:

  • the N basisvectors are first rotated yaw around the the z-axis
  • the new basisvectors are rotated pitch around the new y-axis
  • the new basisvectors are rotated roll around the new x-axis and the result is the B basis vectors:

$$
begin{bmatrix} hat{x_B} \ hat{y_B} \ hat{z_B} end{bmatrix}
=R_{BN}*begin{bmatrix} hat{x_N} \ hat{y_N} \ hat{z_N} end{bmatrix}
$$

where
$$
R_{BN}=RX_{BN}(roll)*RY_{BN}(pitch)*RZ_{BN}(yaw)
$$

enter image description here

I find that
$$
RZ_{BN} = RZ^T
$$

$$
RY_{BN} = RY^T
$$

$$
RX_{BN} = RX^T
$$

$$
R=RZ*RY*RX=R_{BN}^T
$$

where RX, RY RZ and R are the standard rotation matrices used to convert a position from a rotated coordinate system to an unrotated:
enter image description here
Is this correct?

Next let us assume that roll, pitch and yaw is measured by an instrument (an Inertial Measurement Unit).
We introduce a coordinate system for the instrument, I with basisvectors ${hat{x_I},hat{y_I},hat{z_I}}$.

The instrument is rotated wrt to the airplane:
$$
begin{bmatrix} hat{x_I} \ hat{y_I} \ hat{z_I} end{bmatrix}
=R_{IB}*begin{bmatrix} hat{x_B} \ hat{y_B} \ hat{z_B} end{bmatrix}
$$

Given a known $R_{IB}$ and a measurement from the instrument: $(yaw_i, pitch_i,roll_i)$ how can I find $(yaw, pitch,roll)$ of the airplane?

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