To summarize, we have made good progress on all the individual tasks outlined in the Phase-I schedule. Task1: Level 1 Requirements of the Venus Probe: We have formulated requirements for the Venus probe, which include: Power of 2 kWh, payload of 150 kg, hydrogen as the lifting gas, altitude cycling between 55-65 and 10-15 km from the surface and longevity for the balloon and probe. Task 2: Select suitable component Technologies: Selected suitable components technologies for the fuel cells (SOFC) in the regeneration mode to function as fuel cell and electrolyzer. Task 3: Design Electrolyzer cell and select PVs: Estimated the durations for harvesting hydrogen from the in-situ resources. SOA solar arrays with good thermal stability will be utilized. Task 4: Identify suitable metal hydrides for 25-350oC: Based on the analyses, magnesium based metal hydrides (Mg2Ni and Mg2Fe) as well as Fe-Ti seem to be suitable or these environments. A dual hydrogen storage system will be used to cater to the wide range of temperatures and pressures. Task 5: Design the Intermediate Temp Fuel Cell (350 oC): Instead of a low-TRL Intermediate Temperature Fuel Cell (at 350 oC), it appears that a solid oxide fuel cell would be a better option due to its high TRL and proven stability at high temperatures. Task 6: Identify compatible materials for balloon: Suitable materials have been identified for the Zero-pressure balloon with hydrogen as the lifting gas. Task 7: Generate performance data on electrolyzer, hydrides, fuel cell and balloon by test or analysis: Detailed analysis have been performed on the electrolyzer, hydrogen storage materials, fuel cells and balloon ascent and descent modes. Task 8: Integrate the components and assess system-level compatibility, analyze test data and assess the tech maturity of the probe and submit Final Report: A detailed model has been performed to determine the viability of the overall system. Quantitative estimates were made on the hydrogen transfer in and out of the balloon for its ascent and descent. Also, the probe is being designed for payload of 150 kg and a low-altitude power of 2 kWh. This report will be updated after a completion of the Phase I.