RoLaMGAS / GUIDE
Explore a route.
Keep the solution.
Robert’s Lambert Multi Gravity Assist Solver is free, open-source mission-design software by Robert Barthell Garay, B.S. Aerospace Engineering. The desktop solver uses JPL Horizons ephemerides and your computer’s CPU.
Browse and compare
Choose a destination and filter launch years, flight time, launch C3, arrival hyperbolic excess speed and cruise delta-v. Each graph color represents an assist sequence. Flight time stays on the horizontal axis; the vertical axis is C3 or arrival V-infinity.
Open a website trajectory in the app
Select a trajectory and choose Use in desktop app. Save the JSON file, then choose Import options / website trajectory in the desktop application. RoLaMGAS v0.2.4 loads the selected Lambert solution using its dates, branches and maneuver controls. It checks the solution against local JPL data without a new optimization search. Older clients can load the portable search settings.
Export for Celestia
Ideal Lambert coasts meet at planet centers. They are useful for analysis and broad previews, but their XYZV samples are unsuitable for close flyby renders. Use the desktop app’s Integrate & export action to construct finite-radius planetary passages. It uses the Sun outside encounter spheres of influence and the encounter planet inside, reports patch corrections, and exports CSV/XYZV. Check its clearance and burn reports before adopting the result. SOI join corrections arise from independently targeted arcs; they are not proven unavoidable mission costs. A joint flyby-and-leg optimizer would be needed to establish that.
Integrated concepts and saved patched-conic examples retain their original direct downloads and model notes. Their trajectories are separate from a new Lambert reconstruction.
Historical mission names
A calendar-date match compares every listed encounter against the published mission schedule. It does not validate the spacecraft’s flown trajectory, launch performance or burn budget. You can save your own mission label in the inspector; custom labels stay in that browser.
Launch vehicle capacity
Expand the NASA launch-vehicle panel to compare the selected C3 with saved NASA LSP high-energy capacities. Configurations and recovery modes remain separate. The website interpolates between cached samples and never extrapolates. The desktop app can query the exact C3 through NASA’s public form. Read the attached ground rules for adapters, reserves and launch-window assumptions.
Limits of the model
A flyby does not necessarily provide solar escape. A prograde Lambert leg can take the long way around the Sun and pass through the inner Solar System before reaching an outer target. Inspect the geometry as well as the encounter-speed checks.
Lambert searches use heliocentric two-body arcs and patched-conic flyby screening. Launch injection and terminal capture need separate budgets. The parking-orbit delta-v calculator is an ideal impulsive estimate. Saved candidates are design starting points, not operational navigation solutions.