End-to-End Mission Design & Trajectory Optimization Year 2 of 3

EG proposes the continued integration of the Copernicus and Genesis trajectory design tools to incorporate an Initial Guess Generator for end-to-end mission design and optimization of all flight phases, including Earth ascent, lunar ascent, rendezvous, and lunar descent.

This proposed addition matures the existing Copernicus/Genesis integration from Year 1 by providing a better initial guesses for ascent/descent. Potential benefits: Cost savings for mission planning and analysis work (more efficient analysis and faster turnaround). Mass savings from better optimized solutions (e.g., higher payload delivery, or increased abort coverage for crewed missions due to more available prop). Improved mission availability (launch/landing opportunities). This capability is a critical component needed for prototyping an onboard autonomous abort system, paramount for mission safety in future complex human spaceflight design and operations (Orion, HLS, Gateway, Mars).

This is early/mid-stage (TRL 4) — the most realistic path in is NASA SBIR/STTR, which funds small businesses and research institutions to develop technology aligned with NASA's needs (equity-free, phased funding). Check whether a current SBIR/STTR solicitation topic overlaps with this project's technology area, or contact the project directly (above) to ask.

None of these are guaranteed paths for this specific project — TechPort itself doesn't have an "apply" button. Reaching out to the contact(s) above with a specific question is usually the fastest way to find out what's actually open.