Taylor658/624-hektor-hohmann-transfer-orbit

Hektor-Hohmann Transfer Orbit Dataset Card

Author: ATaylor
Contact: hf.co/taylor658
License: Apache License 2.0
Rows: ~30,000

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Dataset Summary

This dataset contains a comprehensive set of synthetic data for an interplanetary mission to 624 Hektor, modeled using a Type II Hohmann transfer orbit. It features:

• LEO Departure and heliocentric trajectory phases.
• Jupiter gravity assist flyby.
• Electric propulsion thrust arcs.
• Final insertion at 624 Hektor on March 18, 2032.

The dataset is ideal for machine learning tasks related to orbital mechanics, low-thrust mission optimization, and multi-body transfer simulation.

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Mission Profile

1. LEO Departure: Initial departure from Earth's orbit using electric propulsion.
2. Heliocentric Transfer: Transitioning into an interplanetary trajectory.
3. Jupiter Gravity Assist: Utilizing Jupiter’s gravity for a velocity boost.
4. Arrival at 624 Hektor: Final insertion burn at the target asteroid 624 Hektor.

Final Event: March 18, 2032, orbit capture at 624 Hektor.

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Dataset Columns

Key Orbital Mechanics Parameters:

1. Timestamp_UTC: Universal Coordinated Time for each record.
2. Mission_Segment: Categorized mission phase (e.g., "LEO Departure," "Jupiter Flyby").
3. Central_Body: The celestial body being orbited (Earth/Sun/Hektor).
4. Orbital_Radius_km: Current orbital distance from the central body.
5. Semi_Major_Axis_km: Semi-major axis of the elliptical orbit.
6. Eccentricity: Shape of the orbit (0 for circular, <1 for elliptical).
7. Inclination_deg: Orbital plane tilt relative to the ecliptic plane.
8. True_Anomaly_deg: Orbital position relative to the periapsis.
9. Phase_Angle_deg: Angular alignment between the spacecraft and target.
10. Velocity_km_s: Spacecraft velocity relative to the central body.

Thrust and Propulsion Data:

11. Thrust_Level_N: Thrust output in Newtons.
12. Propellant_Mass_kg: Remaining propellant mass.
13. Specific_Impulse_s: Propulsion efficiency parameter.
14. Engine_Power_kW: Electric propulsion power.

Gravity Assist Parameters:

15. Jupiter_Encounter_DateTime_UTC: Timestamp for Jupiter gravity assist.
16. Closest_Approach_Dist_Jupiter_km: Minimum distance to Jupiter.
17. Inbound_Velocity_Rel_Jupiter_km_s: Velocity approaching Jupiter.
18. Outbound_Velocity_Rel_Jupiter_km_s: Velocity after gravity assist.
19. Gravity_Assist_DV_Eq_km_s: Equivalent velocity gain from the assist.

Arrival Data:

20. Hektor_Encounter_DateTime_UTC: Arrival time at 624 Hektor.
21. Relative_Velocity_at_Hektor_km_s: Velocity at 624 Hektor encounter.
22. Capture_Insertion_DV_km_s: Delta-V required for orbital capture.
23. Final_Orbit_SMA_km: Semi-major axis of the orbit around Hektor.
24. Final_Orbit_Inclination_deg: Inclination of the final orbit.

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Intended Usage

1. Foundation Model Training: Time-series or tabular input for a broad model (e.g., analyzing or predicting orbital mechanics states).
2. Synthetic Orbital Data Exploration: Demonstrating multi-body, low-thrust mission profiles.

Disclaimer: Values are not from real missions. They are randomly or linearly generated placeholders.

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Citation

@misc{hektor_hohmann_transfer_2024,
  title={{Hektor-Hohmann Transfer Orbit Dataset}},
  author={ATaylor},
  year={2024},
  note={Synthetic dataset for Jupiter-assisted transfer to 624 Hektor.},
  howpublished={Generated for research and simulation purposes.}
}

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