An evacuated or vacuum airship relies on the same principle of buoyancy used by standard balloons. However, unlike a balloon which uses a lighter than air gas to displace air and provide lift, the vacuum airship leverages a rigid structure to maintain a vacuum and displace air, thereby providing buoyancy. This method is similar to how a ship uses a rigid structure to displace water and fill the space with air; an evacuated airship uses the same mechanism, except air is displaced and the space remains vacant. Using this method, the evacuated airship is capable of utilizing the full potential of the displaced mass of air, which has interesting implications in the Martian atmosphere. Unlike other aerial vehicles, which are at a disadvantage in Martian atmospheric conditions, the evacuated airship benefits from the Martian atmosphere by virtue of the temperature and molecular composition. As a result, the evacuated airship offers an unprecedented payload capacity and, if implemented, may be used to transport current and future scientific instruments, other vehicles, rovers, and possibly even human habitations. A standard dirigible or balloon for Mars would have a severely limited span of operation and a very narrow field of study, nearly exclusively the atmosphere, but a vacuum airship can be used as a long term tool for many different missions: transportation, ground study, communications, atmospheric study, etcetera, thereby making it a far more economically sensible choice. This investigation illustrates development of several different approaches to the evacuated airship which are dictated by different enabling technologies as well as those viable with current technology. For current materials technology, this investigation has addressed and solved the most core feasibility aspects of the concept, laying the foundation for further development of the mission and design. The current design of the evacuated airship uses a tensegrity structure, which is a truss structure comprised of bars in pure compression and cables in pure tension, to support an outer membrane. Beams of the tensegrity structure themselves are comprised of more intricate tensegrity structures, which reduce the overall mass of the design, enabling payload capacity. As such, this design is fully capable of supporting the load from atmospheric pressure on Mars while remaining light enough to have useful payload capacity, which was testing using detailed, non-linear finite element simulations, accounting for non-linearities in displacement, global and local buckling, and membrane failure criteria. This was further improved by combining and extending several design methods to reduce the overall mass of the structure. As can be shown, the current payload of the design is 500 kilograms, with projections through further implementation of the developed design methods to have a payload over one ton, and even more payload can be expected from further development of the design and mission. There still remain many other avenues for further mass reduction of the structure and optimization of the design in general, which can be used in conjunction with the methods developed over this investigation. Additionally, protocols for the fundamentals of a mission implementing the evacuated airship on Mars are examined in this investigation. These protocols cover the transport, deployment, and planetary insertion of the evacuated airship on Mars, which are the main criteria for mission feasibility. Planetary insertion was analyzed using high fidelity numerical methods to observe the full scope of influences on the evacuated airship during entry into the atmosphere. As a result, the underlying analysis behind the installation of the evacuated airship on Mars has been covered sufficiently and provides a general framework which is fully capable of conforming to future changes and adaptations to the design. Overall, the evacuated airship represents an exciting and revolutionary concept for Mars and will enable missions which would otherwise be impossible. Not to mention, a vast majority of the structural methods and theory developed for the evacuated airship can be applied to many other projects which solicit high load bearing capability, low mass, and/or deployability—terrestrial, Martian, or otherwise. The results of this investigation are foundational and should not be considered final. There are still many aspects of the evacuated airship concept which need to be further developed, however, this research covers the main points of feasibility for the concept.