DEMO

Bennu to Ryugu Asteroid Transfer

Asteroid-to-asteroid transfer mission between two NEAs

This is demonstration data showing the capabilities of ADAM's transfer trajectory service.

Status

SUCCESS

Job complete.

Job ID

7ea2dc77-4784-4602-9f49-a933f3d230ec

Created

August 29, 2025 at 06:28:42 PM UTC

Departure Body

bennu

Source: JPL Small Body Database

Launch Window

MJD 62742 - 63107

2030-08-29 to 2031-08-29

Arrival Body

ryugu

Source: JPL Small Body Database

Arrival Window

MJD 63473 - 63838

2032-08-29 to 2033-08-29

Transfer Direction

Prograde

Step Size

8 days

Max C3 Departure

200 km²/s²

Porkchop Plot

Interactive Plot:Porkchop Plot: Click on any point in the plot above to see detailed trajectory optimization information and visualize the 3D trajectory. You can also use the dropdown above to browse solutions or hover over points for quick previews. Click and drag to zoom or use the pan tool. Use the dropdown above to browse solutions or tap the button above to view the full interactive plot in landscape mode.

Transfer Details

Loading optimal C3 solution...

Download Raw Data

File Format Information: All data files were generated using the adam_core library.

Transfer data is provided in CSV format containing all computed Lambert transfer solutions with trajectory details, orbital elements, and launch directions. The accompanying CSV-W metadata file contains detailed schema information including column descriptions, units, coordinate frames, and byte-level indexing for efficient data access.

For data analysis, we recommend the parquet format, which provides the most efficient access to the complete dataset with built-in schema information and is optimized for high-performance analysis with adam_core, pyarrow, pandas, dask, or spark.

Ephemeris files are provided in OEM format (Orbit Ephemeris Message), a CCSDS standard.

Lambert Solutions (CSV)

CSV file with all computed transfer trajectories and ra/dec

CSV Metadata (CSVW)

Schema and indexing metadata for the CSV file

Lambert Solutions Parquet (Recommended)

Recommended: Parquet format with optimized schema for efficient data analysis to be used with adam_core.

Plot (HTML)

Standalone HTML file with porkchop plot

Departure Body Ephemeris

OEM file with departure body orbital data

Arrival Body Ephemeris

OEM file with arrival body orbital data

Explore Data with adam_core

Python Analysis: You can load and analyze the trajectory optimization data directly in Python using the adam_core library. The code below shows how to access C3 values, V-infinity, time of flight, and orbital elements.

# Install adam_core if needed

!pip install adam_core

from adam_core.missions.porkchop import LambertSolutions

# Load the Lambert solutions dataset

solutions = LambertSolutions.from_parquet("gs://asteroid-institute-public/production/transfer-trajectory/7ea2dc77-4784-4602-9f49-a933f3d230ec/lambert_solutions.parquet")

# Get C3 departure energy (au²/d²)

solutions.c3_departure()[0]

# Get V-infinity at arrival (au/d)

solutions.vinf_arrival()[0]

# Get time of flight (days)

solutions.time_of_flight()[0]

# Get solution departure orbit (spacecraft at departure)

solution_orbit = solutions.solution_departure_orbit()

solution_orbit.coordinates.to_keplerian().to_dataframe()

Note: The gs:// URI format is required for loading data from Google Cloud Storage. See the adam_core documentation for more examples and API reference.

About This Demo

This demonstration showcases ADAM's Trajectory Optimizer service using real computational results from an Earth-Mars transfer analysis. The service uses Lambert's problem solver to compute optimal transfer trajectories between solar system bodies.

To run your own trajectory analysis with custom parameters,create an account..