This is the Final Report from Global Aerospace Corporation on this NIAC effort (Grant Nos.: NNX17AJ71G and 80NSSC18K0062) to develop the Pluto Hop, Skip, and Jump mission concept. We sought out to establish the feasibility of using a large inflatable drag device to decelerate and land on Pluto from interplanetary speed (~14 km/s) using only the Pluto atmosphere and just a few kilograms of propellant. The design and analysis efforts in Phase I indicated that this is feasible. Aerodynamic heating and loads were found to be orders of magnitude less than typical planetary entries due to the ultra-low ballistic coefficient craft and the low density and large scale height of the Pluto atmosphere. The deceleration system is capable of delivering a 200-kg lander-hopper to the surface or inserting an orbiter of a similar mass using aerocapture. Mission analysis work led to a reference mission with Earth launch in 2029, Jupiter assist in 2030, and Pluto arrival in 2040. Global Aerospace Corporation and its research partner, ILC Dover, have documented in this report the results of the design and analytical modeling efforts during the contract period (9 May 2017 – 9 February 2018). Key accomplishments include:1. Refined atmospheric models using the most recent New Horizons measurements and established the system-level requirements for a reference mission design, 2. Performed interplanetary trajectory analysis to select a reference launch and arrival condition and analyzed Pluto arrival approach conditions to enable a lander mission,3. Used planetary aeroassist simulations to study the Pluto entry environment conditions including convective heating, g-loads, dynamic pressures, and evaluated the effect of atmospheric variation on the decelerator performance,4. Performed approach and landing analysis to determine the possible Pluto landing site locations based on the arrival geometry, and also performed an aerocapture analysis to evaluative feasibility of orbit insertion,5. Performed static structural, dynamic aeroelastic, CFD aerothermodynamics, and thermal analysis leading to a conceptual decelerator design, 6. Developed a feasible materials solution for the decelerator envelope using conventional materials and softgoods fabrication techniques, generated an envelope patterning design, developed a load-distribution scheme, and generated an envelope system mass breakdown,7. Designed a lander-hopper payload, selected science payload components, evaluated hop performance at the surface, and generated a mass breakdown, 8. Developed the integrated system conceptual design and mass breakdown.