EXTREMA: SCP-Optimized Low-Thrust Interplanetary Trajectories

The present work, framed within the ERC-funded project EXTREMA (Engineering Extremely Rare Events in Astrodynamics for Deep-Space Mission in Autonomy) [1], provides a comprehensive collection of optimal low-thrust interplanetary trajectories. The dataset is designed to support research in trajectory design, algorithm validation, machine learning, and autonomous guidance. Each scenario within the dataset contains optimal solutions for transfers from Earth to Mars, Venus, and several asteroids. The scenarios are drawn from the dataset published in EXTREMA: Random autonomous interplanetary mission scenarios for EXTREMA Simulation Hub (ESH) hardware-in-the-loop simulations. The solutions are calculated using an optimization tool based on Sequential Convex Programming (SCP), developed for the autonomous guidance and control Pillar 2 (the algorithm [5] is a C++ modified version of the work presented in [2]).The dataset is provided in a structured JSON format. For every trajectory scenario, the data includes: Mission Parameters: Initial ephemeris times, target identifiers, spacecraft mass, maximum thrust, and specific impulse. SCP Solution: The raw output from the SCP algorithm, providing the state (position, velocity, mass) and control (thrust vectors) across optimized nodes. Thrust-Regularized (TR) Solution: A post-processed, flyable trajectory where thrust arcs are parameterized by third-order polynomials for direction angles. Propagated Verification: Numerical propagation of the regularized solution to verify boundary condition errors and mass fuel consumption accuracy. Simulation settings: Dynamics: Two-body heliocentric dynamics. Reference Frame: Equatorial J2000, Solar System Barycenter (SSB) origin. Integration: 8th-order Runge-Kutta method with non-dimensional time-stepping. Solvers: ECOS [3] for the SCP solution, SNOPT [4] for the TR solution. Departure states are time-shifted to avoid n-body integration singularities at Earth's center. The initial state is defined at et_0 + Δt, with Δt = +2 days (Mars) or -2 days (Venus/Asteroids). The detailed description of the solution structure is provided in README.md For additional information about the EXTREMA project visit the page extrema.polimi.it.