Extended Data Table 2.

Covariance matrix

The covariances used to sample semimajor axis, a_pre, and pre- and post-impact orbit periods. The orbital solution from refs. ^2,36 fits the pre-impact mean motion at the impact epoch, n_pre, and the change in mean motion due to the DART impact, Δn. Once these parameters are sampled, they are turned into a pre- and post-impact orbit period by the relation $P_{\mathit{pre}}=2\pi /n_{\mathit{pre}}$ and $P_{\mathit{post}}=2\pi /(n_{\mathit{pre}}+\Delta n)$. The covariance matrix is constructed using units of km for a_pre and rad/s for n_pre and Δn.