Taylor658/624-hektor-hohmann-transfer-orbit

🪨 Hektor-Hohmann Transfer Orbit Dataset

🛰️ ~30,000 synthetic time-series rows for an interplanetary mission to asteroid 624 Hektor: LEO departure, heliocentric transfer with electric propulsion thrust arcs, Jupiter gravity assist, and orbit capture at Hektor.

⚠️ Disclaimer: All values are synthetically generated placeholders, produced by random or linear interpolation over the mission timeline. They are not propagated trajectories and are not from any real or planned mission. Not suitable for mission analysis.

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📋 At a Glance

🔢 Rows	~30,000
📊 Documented Columns	24
🎯 Target Body	624 Hektor (Jupiter trojan)
🪐 Gravity Assist	Jupiter
🚀 Propulsion	Electric propulsion, low-thrust arcs
📅 Nominal Capture Date	March 18, 2032 (synthetic)
🧬 Generation	Synthetic, random and linear placeholders over a timeline
🌍 Language	English
📄 License	MIT
🏷️ Version	1.0

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📝 Dataset Summary

A synthetic time-series dataset for a mission to 624 Hektor, modeled as a Type II (transfer angle greater than 180°) heliocentric transfer with a Jupiter gravity assist and electric propulsion thrust arcs. It covers:

• 🌍 LEO departure and heliocentric trajectory phases
• 🪐 Jupiter gravity assist flyby
• ⚡ Electric propulsion thrust arcs
• 🪨 Orbit capture at 624 Hektor on a nominal date of March 18, 2032

The dataset provides the schema and timeline shape of a low-thrust, gravity-assisted mission for pipeline prototyping and tabular or time-series modeling exercises.

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🛸 Mission Profile

1. 🌍 LEO Departure: Departure from Earth orbit using electric propulsion
2. ☀️ Heliocentric Transfer: Transition to an interplanetary trajectory
3. 🪐 Jupiter Gravity Assist: Velocity boost from a Jupiter flyby
4. 🪨 Arrival at 624 Hektor: Capture insertion burn at the target asteroid

📅 Final Event: March 18, 2032, orbit capture at 624 Hektor (synthetic)

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🏗️ Dataset Structure

🧭 Orbital Mechanics Parameters

Column	Unit	Description
⏱️ Timestamp_UTC	datetime	UTC time of each record
📍 Mission_Segment	categorical	Mission phase (e.g., "LEO Departure," "Jupiter Flyby")
🌐 Central_Body	categorical	Body being orbited (Earth, Sun, Hektor)
📏 Orbital_Radius_km	km	Distance from the central body
📐 Semi_Major_Axis_km	km	Semi-major axis of the current orbit
🥚 Eccentricity	dimensionless	Orbit shape (0 = circular, <1 = elliptical)
📐 Inclination_deg	degrees	Orbital plane tilt relative to the ecliptic
🧭 True_Anomaly_deg	degrees	Position relative to periapsis
📐 Phase_Angle_deg	degrees	Angular alignment between spacecraft and target
💨 Velocity_km_s	km/s	Velocity relative to the central body

🚀 Thrust and Propulsion

Column	Unit	Description
🔥 Thrust_Level_N	N	Thrust output
⛽ Propellant_Mass_kg	kg	Remaining propellant mass
⚡ Specific_Impulse_s	s	Specific impulse
🔋 Engine_Power_kW	kW	Electric propulsion power

🪐 Gravity Assist

Column	Unit	Description
⏱️ Jupiter_Encounter_DateTime_UTC	datetime	Time of Jupiter gravity assist
🎯 Closest_Approach_Dist_Jupiter_km	km	Minimum distance to Jupiter
➡️ Inbound_Velocity_Rel_Jupiter_km_s	km/s	Velocity approaching Jupiter
⬅️ Outbound_Velocity_Rel_Jupiter_km_s	km/s	Velocity after the assist
⚡ Gravity_Assist_DV_Eq_km_s	km/s	Equivalent velocity gain from the assist

🪨 Arrival

Column	Unit	Description
⏱️ Hektor_Encounter_DateTime_UTC	datetime	Arrival time at 624 Hektor
💨 Relative_Velocity_at_Hektor_km_s	km/s	Velocity at Hektor encounter
⚡ Capture_Insertion_DV_km_s	km/s	∆v required for orbital capture
📐 Final_Orbit_SMA_km	km	Semi-major axis of the orbit around Hektor
📐 Final_Orbit_Inclination_deg	degrees	Inclination of the final orbit

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💡 Usage

🚀 Load the Dataset

from datasets import load_dataset

dataset = load_dataset("Taylor658/624-hektor-hohmann-transfer-orbit", split="train")
print(dataset[0])

🎯 Intended Usage

• 📈 Time-series and tabular modeling exercises over a multi-phase mission timeline
• 🧪 Pipeline prototyping: exercise ingestion, segmentation by Mission_Segment, and feature engineering on a realistic schema before connecting to propagated ephemerides
• 🔗 Companion resources: the titan-hohmann-transfer-orbit dataset, the Titan-Hohmann model, and the HohmannHET physics library

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⚠️ Limitations

🧬 Synthetic Placeholders

• Values are generated by random sampling or linear interpolation across the timeline
• Orbital elements are not the output of a propagator and will not satisfy orbital mechanics identities between columns

📏 No Dynamics

• No two-body, patched-conic, or n-body integration was performed
• The Jupiter gravity assist and Hektor capture figures are nominal, not computed from encounter geometry

📅 Dates

• The 2032 capture date and encounter timestamps are synthetic anchors for the timeline, not the result of a launch window analysis

🚫 Not for Mission Analysis

• Any trajectory, ∆v, or timing question must be answered with a validated astrodynamics toolchain, not from this data

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🙌 Citation

@misc{hektor_hohmann_transfer_2026,
  title={{Hektor-Hohmann Transfer Orbit Dataset}},
  author={Taylor, A.},
  year={2026},
  howpublished={\url{https://huggingface.co/datasets/Taylor658/624-hektor-hohmann-transfer-orbit}},
  note={Synthetic placeholder dataset for a Jupiter-assisted, low-thrust transfer to 624 Hektor.}
}

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🧑‍💻 Contributing

• 💬 Open a Discussion to propose additional mission segments, propagated replacements for placeholder columns, or other target bodies

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👨‍🚀 Author: A Taylor · 🤗 Hugging Face: hf.co/Taylor658 · 🐙 GitHub: ATaylorAerospace