juliensimon/artemis-ii
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--- license: cc-by-4.0 pretty_name: "Artemis II Mission Data" language: - en description: "NASA Artemis II crewed lunar flyby mission: trajectory state vectors from JPL Horizons, crew manifest, mission timeline, and payload inventory." task_categories: - time-series-forecasting - tabular-regression tags: - space - artemis - nasa - moon - lunar - orion - trajectory - orbital-mechanics - sls - deep-space - open-data - tabular-data - parquet size_categories: - 1K<n<10K configs: - config_name: trajectory data_files: - split: train path: data/trajectory.parquet default: true - config_name: crew data_files: - split: train path: data/crew.parquet - config_name: timeline data_files: - split: train path: data/timeline.parquet - config_name: payloads data_files: - split: train path: data/payloads.parquet --- # Artemis II Mission Data <div align="center"> <img src="banner.jpg" alt="Voyager spacecraft artist concept" width="400"> <p><em>Credit: NASA/JPL-Caltech</em></p> </div> *Part of the [Space Probe & Mission Datasets](https://huggingface.co/collections/juliensimon/space-probe-and-mission-datasets-69c3fe82d410a42b1e313167) collection on Hugging Face.*  Comprehensive dataset for NASA's **Artemis II** mission — the first crewed flight beyond low Earth orbit since Apollo 17 (1972). Covers the ~10-day crewed lunar flyby aboard the Orion spacecraft *Integrity*, launched April 1, 2026 on SLS Block 1. ## Configs This dataset has four configs (tables): | Config | Records | Description | |--------|---------|-------------| | `trajectory` | **1,284** | State vectors at 10-min intervals (position, velocity, distances) | | `timeline` | **47** | Mission events from terminal countdown through splashdown | | `crew` | **4** | Crew manifest with biographical data | | `payloads` | **8** | CubeSats and onboard experiments | ## Trajectory schema Geocentric J2000 ecliptic state vectors from [JPL Horizons](https://ssd.jpl.nasa.gov/horizons/) (spacecraft ID `-1024`). | Column | Type | Description | |--------|------|-------------| | `epoch_tdb` | datetime | Timestamp of the state vector in Barycentric Dynamical Time (TDB), sampled at 10-minute intervals throughout the mission; TDB differs from UTC by a slowly varying offset (≈69 s during 2026) | | `x_km` | float | Geocentric X position in km in the J2000 mean ecliptic and equinox frame; origin at Earth's center; X-axis points toward vernal equinox; typical range ±450,000 km (Earth–Moon distance ≈384,400 km) | | `y_km` | float | Geocentric Y position in km (J2000 ecliptic frame); orthogonal to X in the ecliptic plane | | `z_km` | float | Geocentric Z position in km (J2000 ecliptic frame); positive toward ecliptic north pole; small for near-ecliptic trajectories | | `vx_km_s` | float | X velocity component in km/s (J2000 geocentric frame); Orion reaches ~10.8 km/s at TLI and decelerates to ≈11 km/s at entry interface | | `vy_km_s` | float | Y velocity component in km/s (J2000 geocentric frame) | | `vz_km_s` | float | Z velocity component in km/s (J2000 geocentric frame) | | `distance_earth_km` | float | Distance from Earth's center in km, derived as √(x²+y²+z²); peaks near 450,000 km during the lunar flyby; Earth's surface is at 6,371 km, LEO at ~400 km | | `speed_km_s` | float | Scalar speed in km/s, derived as √(vx²+vy²+vz²); peaks at TLI burn (≈10.8 km/s), reaches minimum near maximum Earth distance, then increases again during return; entry interface speed ≈11 km/s | | `distance_moon_km` | float | Distance from the Moon's center in km from selenocentric Horizons query; minimum occurs at closest lunar approach (~8,900 km); null if Horizons returned a different number of rows than geocentric query | | `mission_phase` | string | Mission segment label assigned by event timestamps: `earth_orbit` (launch through ICPS separation burn), `transit_outbound` (TLI through lunar sphere-of-influence entry), `lunar_approach` (SOI entry through closest approach), `lunar_flyby` (closest approach through SOI exit), `transit_return` (SOI exit through entry interface), `entry` (entry interface through splashdown) | ## Quick stats - **1,284** trajectory vectors (2026-04-02 02:00 to 2026-04-10 23:50 TDB) - Maximum distance from Earth: **413,143 km** (256770 statute miles) - Closest lunar approach: **8,283 km** at 2026-04-06 23:00 TDB - Maximum speed: **10.57 km/s** (38068 km/h) - Crew: **4** (3 NASA + 1 CSA) — first crewed mission beyond LEO in 54 years - CubeSats: **4** secondary payloads from Germany, South Korea, Saudi Arabia, Argentina ## Usage ```python from datasets import load_dataset # Trajectory data (default config) ds = load_dataset("juliensimon/artemis-ii", split="train") df = ds.to_pandas() # Plot distance from Moon over time import matplotlib.pyplot as plt plt.figure(figsize=(12, 4)) plt.plot(df["epoch_tdb"], df["distance_moon_km"]) plt.xlabel("Time (TDB)") plt.ylabel("Distance from Moon (km)") plt.title("Artemis II — Distance to Moon") plt.tight_layout() plt.show() # Find closest lunar approach idx = df["distance_moon_km"].idxmin() print(f"Closest approach: {df.loc[idx, 'distance_moon_km']:,.0f} km at {df.loc[idx, 'epoch_tdb']}") # Load other configs crew = load_dataset("juliensimon/artemis-ii", "crew", split="train").to_pandas() timeline = load_dataset("juliensimon/artemis-ii", "timeline", split="train").to_pandas() payloads = load_dataset("juliensimon/artemis-ii", "payloads", split="train").to_pandas() ``` ## Data source - **Trajectory:** [JPL Horizons](https://ssd.jpl.nasa.gov/horizons/) — spacecraft `-1024` ("Integrity Orion EM-2"), geocentric and selenocentric vectors - **Timeline & crew:** [NASA Artemis II Press Kit](https://www.nasa.gov/wp-content/uploads/2026/01/artemis-ii-press-kit.pdf) and [launch blog](https://www.nasa.gov/blogs/missions/2026/04/01/live-artemis-ii-launch-day-updates/) - **Payload data:** NASA, DLR, KARI, KACST, CONAE public announcements ## Update schedule Updated during the mission as JPL Horizons trajectory data is refined. Will switch to as-flown ephemeris after splashdown. ## Related datasets - [space-track-tle-history](https://huggingface.co/datasets/juliensimon/space-track-tle-history) — Orbital element history for tracked objects - [donki-space-weather-events](https://huggingface.co/datasets/juliensimon/donki-space-weather-events) — Space weather events (relevant for crew radiation exposure) - [dst-index](https://huggingface.co/datasets/juliensimon/dst-index) — Geomagnetic storm index ## Pipeline Source code: [juliensimon/space-datasets](https://github.com/juliensimon/space-datasets) ## Support If you find this dataset useful, please give it a ❤️ on the [dataset page](https://huggingface.co/datasets/juliensimon/artemis-ii) and share feedback in the Community tab! Also consider giving a ⭐️ to the [space-datasets](https://github.com/juliensimon/space-datasets) repo. ## Citation ```bibtex @dataset{artemis_ii, author = {Simon, Julien}, title = {Artemis II Mission Data}, year = {2026}, publisher = {Hugging Face}, url = {https://huggingface.co/datasets/juliensimon/artemis-ii}, note = {Trajectory from JPL Horizons; mission data from NASA press kit} } ``` ## License [CC-BY-4.0](https://creativecommons.org/licenses/by/4.0/)
