I propagate the attitude of a satellite in a free-floating, torque free environment from $t_k$ to $t_{k+1}$ by integrating Euler's equation of motion:

$$ \dot{\omega} = [J]^{-1}([\omega]_{\times}[J]\:\omega)$$

with $[J]\in\mathbb{R}^{3\times3}$ being the (full) inertia matrix and $\omega \in \mathbb{R}^3$ the angular velocity vector, and $[\cdot]_{\times}$ being the skew-symmetric operator.

If we consider an Euler integration step of $dt$, we can therefore write:

$$ \omega_{k+1} = \dot{\omega}_k\cdot dt = [J]^{-1}([\omega_k]_{\times}[J]\:\omega_k)\cdot dt$$

I would like to compute the analytical Jacobian $\textbf{F}_\omega = \frac{\partial\omega_{k+1}}{\partial \omega_k}$, or an approximation of it, in order to propagate the covariance from $t_k$ to $t_{k+1}$. Is there any known closed-form solution? With the cross-product, I really don't know how to tackle the problem.

Any help is welcome. Thank you.

  • $\begingroup$ Based on the comment you make near the end of your question: does it help that the derivative of (a cross b) is a’ cross b + a cross b’ ? $\endgroup$
    – SteveO
    Commented May 25, 2021 at 17:21
  • $\begingroup$ It does, thank you very much! $\endgroup$
    – Maltergate
    Commented May 26, 2021 at 8:39

1 Answer 1


$$\frac{\partial\dot\omega}{\partial\omega} = [J]^{-1}\frac{\partial([\omega]_{\times}[J]\omega)}{\partial\omega}$$

$$= [J]^{-1} \frac{\partial(\omega\times[J]\omega)}{\partial\omega}$$

$$= [J]^{-1} \left (\frac{\partial\omega}{\partial\omega}\times[J]\omega + \omega \times [J]\frac{\partial\omega}{\partial \omega}\right)$$

$$ = [J]^{-1} \left (1\times[J]\omega + [\omega]_\times[J] \right) $$

Using the two definitions:

  1. $a \times b = [a]_{\times}b = [b]^{\intercal}_{\times}a$
  2. $[x]^{\intercal}_{\times} = -[x]_{\times}$

on the term $1\times[J]\omega$, we find the correct answer: $$ \frac{\partial\dot\omega}{\partial\omega} = [J]^{-1} \left ( [\omega]_{\times}[J] - \left [[J]\omega \right]_{\times} \right )$$


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