Momentum transfer from the DART mission kinetic impact on asteroid Dimorphos

Abstract

The NASA Double Asteroid Redirection Test (DART) mission performed a kinetic impact on asteroid Dimorphos, the satellite of the binary asteroid (65803) Didymos, at 23:14 UTC on 26 September 2022 as a planetary defence test¹. DART was the first hypervelocity impact experiment on an asteroid at size and velocity scales relevant to planetary defence, intended to validate kinetic impact as a means of asteroid deflection. Here we report a determination of the momentum transferred to an asteroid by kinetic impact. On the basis of the change in the binary orbit period², we find an instantaneous reduction in Dimorphos’s along-track orbital velocity component of 2.70 ± 0.10 mm s⁻¹, indicating enhanced momentum transfer due to recoil from ejecta streams produced by the impact^3,4. For a Dimorphos bulk density range of 1,500 to 3,300 kg m⁻³, we find that the expected value of the momentum enhancement factor, β, ranges between 2.2 and 4.9, depending on the mass of Dimorphos. If Dimorphos and Didymos are assumed to have equal densities of 2,400 kg m⁻³, ${\beta =3.61}_{-0.25}^{+0.19}\left(1\sigma \right)$. These β values indicate that substantially more momentum was transferred to Dimorphos from the escaping impact ejecta than was incident with DART. Therefore, the DART kinetic impact was highly effective in deflecting the asteroid Dimorphos.

The authors report on a determination of the momentum transferred to an asteroid by kinetic impact, showing that the DART kinetic impact was highly effective in deflecting the asteroid Dimorphos.

Main

Observations from the NASA Double Asteroid Redirection Test (DART) spacecraft on approach found Dimorphos to be an oblate spheroid with a boulder-strewn surface, and the spacecraft struck within 25 m of the centre of the figure¹. Ejecta from the DART impact were observed in situ by the Italian Space Agency’s Light Italian Cubesat for Imaging of Asteroids (LICIACube) spacecraft, which performed a flyby of Dimorphos with a closest approach about 168 s after the DART impact⁵. The impact ejecta were further observed by Earth- and space-based telescopes, revealing ejecta streams and dust tails similar to those seen in active asteroids thought to be triggered by natural impacts^3,6. Ground-based telescopes and radar determined that the DART impact reduced the binary orbit period by 33.0 ± 1.0 (3σ) min (ref. ²).

As a planetary defence test mission, a key objective of DART is to determine the amount of momentum transferred to the target body relative to the incident momentum of the spacecraft, quantified by the momentum enhancement factor β (for example, refs. ^4,7,8), which is defined by the momentum balance of the kinetic impact,

$$M\mathrm{\Delta }\mathbf{v}=m\mathbf{U}+m(\beta -1)(\hat{\mathbf{E}}\cdot \mathbf{U})\hat{\mathbf{E}}.$$ 1

Here, M is the mass of Dimorphos, $\mathrm{\Delta }\mathbf{v}$ is the impact-induced change in Dimorphos’s orbital velocity, m is DART’s mass at impact, $\mathbf{U}$ is DART’s velocity relative to Dimorphos at impact and $\hat{\mathbf{E}}$ is the net ejecta momentum direction. $M\mathrm{\Delta }\mathbf{v}$ is the momentum transferred to Dimorphos, $m\mathbf{U}$ is DART’s incident momentum and the final term in the equation is the ejecta’s net momentum written in terms of the spacecraft incident momentum. In this formulation, β is the ratio of actual imparted momentum to the impactor’s momentum in the direction of the net ejecta momentum. Although previous works have defined β using the impactor’s momentum in the surface normal direction^8,9, we elect to use the ejecta direction instead as our reference for the result to be independent of the surface topography. These definitions are equivalent in the case in which the ejecta direction is in the surface normal direction. A β value near 1 would indicate that ejecta recoil had made only a negligible contribution to the momentum transfer. A β > 2 would mean that the ejecta momentum contribution exceeded the incident momentum from DART.

The full $\mathrm{\Delta }\mathbf{v}$ cannot be determined with the available information¹⁰, but its component along Dimorphos’s orbital velocity direction, referred to as the along-track direction, can be estimated from available data including Dimorphos’s orbit period change. To express β in terms of the along-track component of $\mathrm{\Delta }\mathbf{v}$, we take the scalar product of (1) with the unit vector ${\hat{\mathbf{e}}}_{\mathrm{T}}$ in the along-track direction. Solving for β yields,

$$\beta =1+\frac{\frac{M}{m}\left(\mathrm{\Delta }\mathbf{v}\cdot {\hat{\mathbf{e}}}_{\mathrm{T}}\right)-\left(\mathbf{U}\cdot {\hat{\mathbf{e}}}_{\mathrm{T}}\right)}{\left(\hat{\mathbf{E}}\cdot \mathbf{U}\right)\left(\hat{\mathbf{E}}\cdot {\hat{\mathbf{e}}}_{\mathrm{T}}\right)}.$$ 2

For the remainder of this work, we refer to the along-track component of Dimorphos’s velocity change, $\mathrm{\Delta }\mathbf{v}\cdot {\hat{\mathbf{e}}}_{\mathrm{T}}$, as Δv_T. Figure 1 shows the geometry of the DART impact, including the nominal ellipsoidal shapes used for Didymos and Dimorphos in our analysis, and the nominal orientations of U, ${\hat{\mathbf{e}}}_{\mathrm{T}}$ and $\hat{\mathbf{E}}$ at the time of impact.

Fig. 1. Schematic of the DART impact geometry on Dimorphos.

The pre-impact orbit is shown with a solid line around Didymos. The dashed line sketches the orbit change due to the impact. Orbits are drawn roughly to scale. The positive pole direction of Didymos is $\hat{\mathbf{h}}$ (pointing down in the bottom panel). DART’s incident direction is $\hat{\mathbf{U}}$, the net ejecta momentum direction is $\hat{\mathbf{E}}$ (which points to a right ascension (RA) and declination (Dec) of 138° and +13°, respectively), and the direction of Dimorphos’s orbital motion, referred to as the along-track direction, is ${\hat{\mathbf{e}}}_{\mathrm{T}}$. The relative positions of the Sun and the Earth are also indicated. The upper panel shows the view from Didymos’s negative pole direction, whereas the lower panel provides a perspective view. Scale bar, 1 km.

The major unknowns in calculating β are Δv_T, M and $\hat{\mathbf{E}}$. We first use a Monte Carlo approach to produce a distribution for Δv_T consistent with the measured period change that incorporates the various uncertainties involved. We sample many possible combinations of Didymos system parameters, including the ellipsoid shape extents of the asteroids, pre-impact orbit separation distance between the two asteroids’ centres of mass (that is, Dimorphos’s pre-impact orbit radius), pre- and post-impact orbit periods, and net ejecta momentum direction $\hat{\mathbf{E}}$. We use the full two-body problem code (General Use Binary Asteroid Simulator (GUBAS)¹¹, Methods) that implements coupled rotational and orbital dynamics to numerically determine Δv_T for each sampled combination of input parameters. Coupled dynamics are necessary because of the non-spherical shapes of Didymos and Dimorphos and their close proximity relative to their sizes. A range of values for M is generated by combining the volumes of the sampled ellipsoid shape parameters with values for Dimorphos’s density. The Monte Carlo approach is summarized by Extended Data Fig. 1. As Dimorphos’s density has not been directly measured and has a large uncertainty, we treat it as an independent variable and uniformly sample a wide range of possible values between 1,500 and 3,300 kg m^–3, a range that encompasses the 3σ uncertainty¹. Using a technique modified from that of ref. ¹² (Methods), we apply observations of the ejecta by means of Hubble and LICIACube data to obtain a preliminary measurement of the axis of the ejecta cone geometry (Extended Data Figs. 2 and 3). The cone axis direction is identical to $\hat{\mathbf{E}}$ assuming the ejecta plume holds the momentum uniformly, and we find $\hat{\mathbf{E}}$ points towards a right ascension and declination (Dec) of 138° and +13°, respectively (Extended Data Fig. 2). We assign a conservative uncertainty of 15° around this direction. Finally, β also depends on DART’s mass and impact velocity, as well as Didymos’s pole orientation². Those quantities have negligibly small uncertainties relative to those of the other parameters discussed previously and are therefore treated as fixed values (not sampled). See Methods for additional details on the Monte Carlo analysis, Extended Data Table 1 for a list of parameters and uncertainties, and Extended Data Table 2 for the covariances that were used.

Extended Data Fig. 1. Outline of algorithm used to calculate β.

The Monte Carlo variables are outlined by dashed lines and are defined as follows: pre-impact orbit period P_pre; pre-impact orbit semimajor axis a_pre; Didymos ellipsoid extents A_x, A_y, A_z; Dimorphos ellipsoid extents B_x, B_y, B_z; Dimorphos density ρ_B; post-impact orbit period P_post; and net ejecta momentum direction $\hat{E}$. First, a secant algorithm iterates Didymos density ρ_A to match P_pre. Next, another secant algorithm iterates the along-track change in Dimorphos’s velocity Δv_T to match P_post. Finally, M is calculated using the ellipsoid extents and density of Dimorphos, and then combined with Δv_T and $\hat{E}$ to calculate β.

Extended Data Fig. 2. Ejecta cone orientation lies in the swaths of sky (black lines) defined by HST and LICIACube observations.

The light-blue envelope outlines the axis position uncertainty in the direction measured in the sky plane. Red lines divide the along-plane swaths into regions that are excluded based on cone morphology in LICIACube images: 1) and 2) are excluded because the ejecta cone would point in the opposite direction from what is observed; 3) is excluded because the axis would lie too close to the sky plane; 4) is excluded because the axis would lie too close to the line-of-sight; and 5) is the expected region for the axis orientation. The yellow dot denotes the best solution (RA,Dec) = [138°,+13°] with the dark-blue envelope showing the extent of possible solutions. The red square is the direction of the incoming DART trajectory [128°,+18°] and the green triangle shows Dimorphos’s velocity vector [134°,+5°]. The LICIACube swath is defined for the +175 s image shown in Extended Data Fig. 3.

Extended Data Fig. 3. Two LICIACube LUKE images showing the ejecta morphology that were used to reduce the possible axis orientation solutions.

The left panel shows an approach observation, 156 s after impact, with the ejecta in front of and partially obscuring Dimorphos. The right panel shows the ejecta morphology after close approach, 175 s after impact, with Dimorphos silhouetted against the ejecta cone. The images show the red channel from frames LICIACUBE_LUKE_L2_1664234220_00005_01 and LICIACUBE_LUKE_L2_1664234239_01003_01. The bright object in the upper corner of each image is Didymos.

Extended Data Table 1.

Values and uncertainties used for numerical simulations

All vectors are reported in the Earth Mean Equator J2000 (EME J2000) coordinate frame, at the impact time of September 26, 2022, 23:14:24.183 UTC¹. For Gaussian uncertainties we report the 1σ uncertainties. For uniform uncertainties we report the median and the range of possible values.

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.

We find that $\mathrm{\Delta }{v}_{\mathrm{T}}=-2.70\pm 0.10\left(1\sigma \right)$ mm s⁻¹, on the basis of the observed impact-induced period change of −33.0 ± 1.0 (3σ) minutes and the shapes and separation of Didymos and Dimorphos^1,2. Figure 2 shows the distribution of Δv_T values from the Monte Carlo analysis, along with the fitted mean and standard deviation. The resulting spread of β values as a function of Dimorphos’s density, calculated by means of equation (2), is presented in Fig. 3, along with linear fits for the mean β versus density trend and its 1σ confidence intervals. The linear-fit slope is expressed as a scale factor on the ratio of density to the nominal value of 2,400 kg m⁻³ (ref. ¹). For that nominal Dimorphos density, at which Dimorphos and Didymos would have roughly equal densities, ${\beta =3.61}_{-0.25}^{+0.19}$ with 1σ confidence. The mean β ranges between 2.2 and 4.9 as a function of density across the range of 1,500 to 3,300 kg m⁻³ and, overall, β ranges between 1.9 and 5.5 with 3σ confidence.

Fig. 2. Probability distribution of Δv_T, the along-track component of the change in Dimorphos’s velocity induced by DART’s impact, generated by our Monte Carlo analysis that samples over input parameter uncertainties.

The histogram consists of 100,000 Monte Carlo samples and is normalized to an area of unity. A Gaussian fit to the distribution indicates a mean Δv_T of −2.70 mm s⁻¹ with a standard deviation of 0.10 mm s⁻¹.

Fig. 3. β as a function of Dimorphos’s bulk density ρ_B, from the dynamical Monte Carlo analysis.

Individual samples are plotted as points, whereas the linear fit for the mean β is plotted as the solid line and the dotted lines show the 1σ confidence interval. The colour bar indicates the mass of Dimorphos corresponding to each Monte Carlo sample, which is determined by bulk density and the volume. The density range shown corresponds to the 3σ range of the Didymos system density, whereas the shaded region highlights the 1σ range¹. If the density of Dimorphos were 2,400 kg m⁻³, the densities of Didymos and Dimorphos would be the same as the system density, and β = ${3.61}_{-0.25}^{+0.19}$ (1σ). For context, the densities of three other S-type near-Earth asteroids are in the range shown: 433 Eros³² at 2,670 ± 30 kg m⁻³; 25143 Itokawa³³ at 1,900 ± 130 kg m⁻³ and 66391 Moshup³⁴ at 1,970 ± 240 kg m⁻³.

Our result for β is consistent with numerical simulations^13–23 and laboratory experiments^24–29 of kinetic impacts, which have consistently indicated that β is expected to fall between about 1 and 6. However, non-unique combinations of asteroid mechanical properties (for example, cohesive strength, porosity and friction angle) can produce similar values of β in impact simulations²⁰. Future studies that combine estimates of β with additional constraints from the DART impact site geology¹ and ejecta observations^3,5 will provide greater insight into Dimorphos’s material properties. In addition, ESA’s Hera mission³⁰ is planned to arrive at the Didymos system in late 2026. By measuring Dimorphos’s mass and other orbital properties, Hera will allow us to significantly improve the accuracy and precision of the β determination.

DART’s impact demonstrates that the momentum transfer to a target asteroid can substantially exceed the incident momentum of the kinetic impactor, validating the effectiveness of kinetic impact for preventing future asteroid strikes on the Earth. The value of β from a kinetic impact is key to informing the strategy of a kinetic impactor mission (or missions) to mitigate a future asteroid impact threat to Earth³¹. Should β turn out to be greater than two across a wide range of asteroid types, it would mean important performance improvements for kinetic impactor asteroid deflection missions. If β > 2, as opposed to β ≅ 1, then the same sized kinetic impactor could deflect a given asteroid with less warning time, or deflect a larger asteroid with a given warning time than it otherwise could.

Methods

Numerical determination of Δv_T and β

Several parameters affect the value of β as presented in equation (2): Δv_T, M and $\hat{\mathbf{E}}$. The along-track velocity change, Δv_T depends on orbit period change, pre-impact semimajor axis and the shapes of Didymos and Dimorphos, whereas M depends on Dimorphos’s shape and bulk density (which was not measured). $\hat{\mathbf{E}}$ is the only parameter that is directly observed, but it still has considerable uncertainty. Thus, there are 12 total unknown input parameters: three axis lengths for Didymos’s ellipsoidal shape (A_x, A_y, A_z), three axial lengths for Dimorphos’s ellipsoidal shape (B_x, B_y, B_z), Dimorphos’s bulk density ρ_B, the pre-impact orbit semimajor axis a_pre, pre-impact orbit period P_pre and post-impact orbit period P_post, and two angles to define the ejecta momentum direction vector ($\hat{\mathbf{E}}$). Extended Data Table 1 lists these input parameter values and their uncertainties, along with additional known quantities needed to calculate β. To account for this large set of input uncertainties, we use a Monte Carlo approach in which 100,000 possible cases are generated by randomly sampling the input parameters within their uncertainties. We assume the DART spacecraft mass, DART impact velocity vector and Dimorphos’s orbital velocity direction (referred to as the along-track direction) are all known precisely because their uncertainties are negligibly small compared to the uncertainties of the other input parameters.

The pre-impact orbit semimajor axis, pre-impact orbit period and post-impact orbit period are sampled as a multivariate Gaussian distribution using the mean values and covariance matrix from the ‘N22+’ solution (refs. ³⁵ and ³⁶ of ref. ²; Extended Data Tables 1 and 2). This accounts for the small correlations between those three parameters. The physical extents of Didymos and Dimorphos from ref. ¹ are sampled uniformly, as those uncertainties are not Gaussian (Extended Data Table 1). β depends strongly on Dimorphos’s mass, but the mass is poorly constrained because Dimorphos’s bulk density has not been directly measured¹. Therefore, we treat density as the independent variable, sample it uniformly and report β as a function of Dimorphos’s density.

For each Monte Carlo sample for the Didymos system, a secant search algorithm (a finite-difference Newton’s method) described in ref. ³⁷ is first used to compute the density of Didymos required to reproduce the sampled pre-impact orbit period, given the sampled pre-impact orbit semimajor axis, body shapes and Dimorphos’s density. Then, a second secant search algorithm is used to determine the Δv_T required to achieve the sampled post-impact orbit period. We match the pre- and post-impact orbit periods because these are directly measured by ground-based observations and are thus the best-constrained parameters of the system². Given the non-Keplerian nature of the Didymos system, we use the GUBAS to numerically propagate the binary asteroid dynamics. GUBAS is a well-tested full two-body problem (F2BP) code that can model the mutual gravitational interactions between two arbitrarily shaped rigid bodies with uniform mass distributions^11,38. GUBAS has been benchmarked against other F2BP codes³⁹ and used extensively in previous dynamical studies of the Didymos system (for example, refs. ^10,37,40). Finally, the mass of Dimorphos is calculated from its ellipsoidal shape and Dimorphos’s density. This mass, along with the computed Δv_T and sampled net ejecta momentum direction, are provided as inputs to equation (2) to calculate the value of β corresponding to each of the 100,000 realizations of the system. For a discussion on estimating $\hat{\mathbf{E}}$, see the Ejecta plume direction section below. The process described herein is summarized graphically in Extended Data Fig. 1.

The convergence criteria on both secant algorithms are set such that the simulated orbit period matches the desired orbit period to an accuracy ten times better than the uncertainty on the measurements themselves. The numerical simulations measure the average orbit period of Dimorphos in an inertial frame over 30 days to account for small fluctuations in the mutual orbit period resulting from spin-orbit coupling⁴⁰. Our selection of 100,000 as the number of samples to use in the Monte Carlo analysis was informed by calculating an estimated minimum necessary number of samples from the Central Limit Theorem and then testing sample sizes near that estimated value. The β estimate results are well converged with 100,000 samples.

In the numerical simulations, both Didymos and Dimorphos are modelled as triaxial ellipsoids with physical extents from ref. ¹. Images from DRACO and LICIACube showed that both Didymos and Dimorphos have an oblate spheroid shape¹. There is no advantage to using more sophisticated shape models while the internal mass distributions of the bodies are unknown. Instead, the ellipsoidal approximation allows for easy sampling of a range of plausible moments of inertia as a proxy for different internal density distributions. For example, given the current uncertainties in Didymos’s physical extents¹, sampling over the given range of ellipsoidal shapes results in a range of plausible second-order gravity terms (analogous to the spherical harmonic terms J₂, C₂₂ and so on), which play an important role in the system’s dynamics due to the tight separation of the binary components. Neglecting their shapes and assuming Keplerian dynamics results in $\mathrm{\Delta }{v}_{\mathrm{T}}=-2.86\pm 0.095\left(1\sigma \right)$, whereas GUBAS’s second-order gravity model finds $\mathrm{\Delta }{v}_{\mathrm{T}}=-2.70\pm 0.10\left(1\sigma \right)$. Although fourth-order dynamics influence higher-order dynamical effects^37,40, we find that it comes with a significantly higher computational cost yet plays a negligible role in determining Δv_T. A smaller batch (due to increased computational cost) of roughly 4,000 runs was conducted with fourth-order dynamics, which resulted in $\mathrm{\Delta }{v}_{\mathrm{T}}=-2.68\pm 0.10\left(1\sigma \right)$, indicating the second-order dynamics model is appropriate for determining Δv_T given the current uncertainties in the orbit solution and body shapes. This result was also independently verified using analytical models, accounting for Didymos’s gravitational quadrupole, which agreed within a few percent of the second-order numerical results, as expected given their dynamical approximations.

We do not sample the rotation period of Dimorphos, as it is assumed to be equal to the pre-impact orbit period before the impact, with reasoning as follows. A measured orbit semimajor axis drift directed inwards⁴¹ indicates the system is evolving under the influence of the binary Yarkevsky–O’Keefe–Radzievskii–Paddack effect⁴², which requires a secondary in near-synchronous rotation. Furthermore, radar images constrain Dimorphos’s spin period to be within 3 h of the synchronous rate³⁵. Recent models for tidal dissipation in binary asteroids suggest that any free libration would dissipate on 100-year timescales⁴³, making any substantial free libration unlikely given the timescales for excitation mechanisms such as close planetary encounters and natural impacts¹⁰. Furthermore, Dimorphos’s pre-impact eccentricity is constrained to be less than 0.03 (refs. ^35,41), putting the maximum possible forced libration amplitude⁴⁴ at around 0.5°. Although Dimorphos’s rotation state is not precisely determined by DART, this body of evidence suggests that Dimorphos was probably in near-synchronous rotation and on a nearly circular orbit before the DART impact.

Our model further assumes all momentum is transferred instantaneously, because earlier work showed the time duration of the momentum transfer has a negligible effect on the resulting dynamics¹⁰. The instantaneous torque on Dimorphos due to DART’s slightly off-centre impact¹ is also neglected as the corresponding change in Dimorphos’s rotation state is small compared to that arising from exciting Dimorphos’s eccentricity and libration by the impact^10,37,45. Finally, the effects of reshaping and mass loss due to cratering and ejecta are also neglected, as these effects are expected to be smaller in magnitude than the current roughly 1 min uncertainty on the post-impact orbit period⁴⁶ and will remain poorly constrained until the Hera mission characterizes the Didymos system in 2027 (ref. ³⁰). We leave these higher-order effects for future work once the post-impact orbit solution is refined further.

Ejecta plume direction

We use observations of the ejecta plume to determine the ejecta momentum direction $\hat{\mathbf{E}}$. The conical ejecta plume was imaged by the LICIACube LUKE camera⁵ and the Hubble Space Telescope (HST)³. We apply a technique used to derive cometary spin poles¹² to estimate the orientation of the ejecta cone axis. Although it is possible to have an asymmetric distribution of ejecta momentum (mass and velocity) within the cone, we assume the cone to be axially symmetric. The approach applies the ejecta cone’s bright edges (if captured in an image) to compute the apparent direction of the cone axis projected onto the sky, which is assumed to be the middle of the edges.

For a LICIACube observation, the projected cone axis defines the LICIACube-axis plane in inertial space that contains the line-of-sight and the projected axis. The cone axis can lie anywhere in this plane. The analogous plane HST axis is defined from early HST images of the plume (those taken within 2 h after the impact) that show similar radial velocity to the ejecta in the LICIACube images, indicating it is probably the same ejecta material observed on a larger spatial scale. The intersection of these planes defines the cone axis orientation in three dimensions, but unfortunately the LICIACube- and HST-axis planes are nearly parallel. Thus, these observations do not provide a unique solution but they constrain the axis orientation to a narrow swath of the sky (Extended Data Fig. 2). However, LICIACube LUKE images resolved the ejecta cone and the cone morphology over a large range of viewing angles during the flyby, further constraining the cone axis orientation³. During the approach to Dimorphos, the cone was pointed towards LICIACube, with the ejecta obscuring parts of Dimorphos. During recession from Dimorphos, the cone pointed away from Dimorphos and revealed it in silhouette (Extended Data Fig. 3). The tightest constraint on cone orientation would have come from closest-approach images, with the cone axis in the plane-of-sky, as the cone transitioned from pointing towards the observer to pointing away. Unfortunately, Dimorphos and the ejecta cone were outside the LUKE field of view for 13 s around closest approach, and we lack images from the transition.

The resolved LICIACube images are used to eliminate portions of the swath in Extended Data Fig. 2 where the observed cone morphology is inconsistent with those axis orientations. For example, half of the swath is rejected because the axis would be pointed in the opposite direction of what was observed. We also exclude orientations in which the cone would point too close to the line-of-sight during the approach or recession of LICIACube. We find the axis orientation to be (right ascension, Dec) = (138°, +13°). We assign conservative uncertainties of roughly 15° in all directions based on the angular extents of region 5 in Extended Data Fig. 2.

Online content

Any methods, additional references, Nature Portfolio reporting summaries, source data, extended data, supplementary information, acknowledgements, peer review information; details of author contributions and competing interests; and statements of data and code availability are available at 10.1038/s41586-023-05878-z.

Author contributions

A.F.C. led the overall conception and writing of the study. H.F.A. contributed the GUBAS dynamical simulations for the Monte Carlo analysis. B.W.B. contributed the Monte Carlo analysis. A.J.M. validated the GUBAS dynamical simulations. T.L.F. and M.H. determined the ejecta cone orientation. S.D.R. contributed to discussions of β determination and implications. A.F.C., H.F.A., B.W.B., A.J.M., T.L.F. and D.C.R. wrote most of the manuscript text. E.D. led the LICIACube investigation as Principal Investigator. A.Z. led production of LICIACube imaging data. V.D.C. led the calibration of the LICIACube imagers. T.S.S. helped with verification of the GUBAS results and provided comments on the manuscript. S.C. and S.P.N. provided the Dimorphos orbital velocity vector direction, DART velocity vector at impact and the covariance matrix for the pre-impact orbit semimajor axis, mean motion and change in mean motion. J.-Y.L. helped with efforts to estimate the ejecta momentum direction from HST and LICIACube observations. S.E., O.S.B., N.L.C., S.C., G.S.C., R.T.D., T.M.D., M.E.D., C.M.E., F.F., D.M.G., S.A.J., M.J., K.M.K., J.-Y.L., R.L., P.M., N.M., R.N., E.P., A.S.R., D.J.S., A.M.S., J.M.S., J.M.T.-R., J.-B.V., J.D.W., K.W. and Y.Z. provided useful inputs and/or comments on the manuscript. J.R.L. assisted with verification efforts for the numerical simulations. E.D., V.D.C., E.M.E., A.R., I.G., P.J.D.D., P.H.H., I.B., A.Z., S.L.I., J.R.B., G.P., A.L., M.P., G.Z., M.A., A.C., G.C., M.D.O., S.I., G.I., M.L., D.M., P.P., D.P., S.P., P.T. and M.Z. contributed to the development and operation of LICIACube, in addition to provision of LICIACube imaging data.

Peer review

Peer review information

Nature thanks the anonymous reviewer(s) for their contribution to the peer review of this work. Peer reviewer reports are available.

Data availability

The dynamical simulations were carried out using GUBAS, which is publicly available on Github (https://github.com/meyeralexj/gubas). The Dimorphos orbital velocity direction vector components presented in Extended Data Table 1 were computed using the dimorphos_s501.bsp and sb-65803-198.bsp (Didymos) data files available at https://dart.jhuapl.edu/SPICE_kernels/spk. The DART incident velocity vector components presented in Extended Data Table 1 were computed using those two files in combination with the DART_2022_269_1241_ops_v01_impact.bsp data file, available at the same URL. Data availability at that URL is planned until summer 2023, after which those data may be found at https://naif.jpl.nasa.gov/naif/data.html.

Competing interests

The authors declare no competing interests.

Extended data

is available for this paper at 10.1038/s41586-023-05878-z.

Supplementary information

The online version contains supplementary material available at 10.1038/s41586-023-05878-z.