metadata
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
Credit: NASA/JPL-Caltech
Part of a dataset collection on Hugging Face.
Dataset description
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
| Column | Description |
|---|---|
epoch_tdb |
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 |
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 |
y_km |
Geocentric Y position in km (J2000 ecliptic frame); orthogonal to X in the ecliptic plane |
z_km |
Geocentric Z position in km (J2000 ecliptic frame); positive toward ecliptic north pole; small for near-ecliptic trajectories |
vx_km_s |
X velocity component in km/s (J2000 geocentric frame); Orion reaches ~10.8 km/s at TLI and ~11 km/s at entry interface |
vy_km_s |
Y velocity component in km/s (J2000 geocentric frame) |
vz_km_s |
Z velocity component in km/s (J2000 geocentric frame) |
distance_earth_km |
Distance from Earth's center in km, derived as sqrt(x^2+y^2+z^2); peaks near 450,000 km during the lunar flyby; Earth's surface is at 6,371 km |
speed_km_s |
Scalar speed in km/s, derived as sqrt(vx^2+vy^2+vz^2); peaks at TLI burn (~10.8 km/s) |
distance_moon_km |
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 mismatched row counts |
mission_phase |
Mission segment label: earth_orbit, transit_outbound, lunar_approach, lunar_flyby, transit_return, or entry |
Crew schema
| Column | Description |
|---|---|
name |
Full name of the crew member |
role |
Role on the mission: Commander, Pilot, Mission Specialist 1, or Mission Specialist 2 |
agency |
Space agency: NASA or CSA (Canadian Space Agency) |
nationality |
Nationality of the crew member |
birth_date |
Date of birth in YYYY-MM-DD format |
birth_place |
City and state/province of birth |
selection_year |
Year selected as astronaut/candidate by their space agency |
military_rank |
Military rank and branch if applicable; null for civilian astronauts |
previous_missions |
Previous spaceflight missions with dates; null if first flight |
previous_flight_days |
Total days spent in space on previous missions; 0 for rookie astronauts |
eva_count |
Number of previous extravehicular activities (spacewalks); 0 if none |
eva_hours |
Total hours of previous EVA time; 0.0 if no EVAs |
notable |
Notable achievements or distinctions of the crew member |
Timeline schema
| Column | Description |
|---|---|
met |
Mission Elapsed Time in T+DD:HH:MM format (or T-HH:MM:SS for pre-launch events); referenced from booster ignition/liftoff at T+00:00:00 |
phase |
Mission phase label: terminal_countdown, ascent, earth_orbit, transit_outbound, lunar_flyby, transit_return, or entry |
event |
Free-text description of the mission event or milestone |
Payloads schema
| Column | Description |
|---|---|
name |
Name of the CubeSat or experiment (e.g. 'TACHELES', 'Proximity Ops Demo') |
type |
Payload type: 'CubeSat' for secondary spacecraft or 'experiment' for onboard demonstrations |
provider_country |
Country providing the payload (e.g. 'Germany', 'USA') |
provider_agency |
Space agency or organization providing the payload (e.g. 'DLR', 'NASA') |
mass_kg |
Payload mass in kg; null for experiments without a discrete mass |
objective |
Primary scientific or technology demonstration objective of the payload |
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
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 -- spacecraft
-1024("Integrity Orion EM-2") - Timeline & crew: NASA Artemis II Press Kit and launch blog
- 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
Citation
@dataset{artemis_ii,
title = {Artemis II Mission Data},
author = {juliensimon},
year = {2026},
url = {https://huggingface.co/datasets/juliensimon/artemis-ii},
publisher = {Hugging Face}
}