Aerocapture Mission Analysis Tool (AMAT)


AMAT idesigned to provide rapid mission analysis capability for aerocapture and atmospheric Entry, Descent, and Landing (EDL) mission concepts to the planetary science community.

See Jupyter notebooks to get started or refer to examples in the GitHub repository.

If you find AMAT useful in your work, please consider citing us: Girija et al., (2021). AMAT: A Python package for rapid conceptual design of aerocapture and atmospheric Entry, Descent, and Landing (EDL) missions in a Jupyter environment. Journal of Open Source Software, 6(67), 3710, DOI 10.21105/joss.03710

AMAT allows the user to simulate atmospheric entry trajectories, compute deceleration and heating loads, compute aerocapture entry corridors and simulate aerocapture trajectories. AMAT supports analysis for all atmosphere-bearing destinations in the Solar System: Venus, Earth, Mars, Jupiter, Saturn, Titan, Uranus, and Neptune. AMAT allows the calculation of launch performance for a set of launch vehicles. AMAT allows the calculation of V-inf vector from a Lambert arc for an interplanetary transfer. AMAT allows calculation of planetary approach trajectories for orbiters and entry systems from a given V_inf vector, B-plane targeting, and deflection maneuvers. AMAT allows the calculation of visibility of landers to Earth and relay orbiters and compute telecom link budgets.


For sub-routine documentation, see Module Index