Space-based solar power (SSP) generation is being touted as a solution to our ever-increasing energy consumption and dependence on fossil fuels. Satellites in Earth's orbit can capture solar energy through photovoltaic cells and transmit that power to ground based stations. Solar cells in orbit are not hindered by weather, clouds, or night. The energy generated by this process is clean and pollution-free. Although the concept of space-based solar power was initially proposed nearly 40 years ago, the level of technology in photovoltaics, power transmission, materials, and efficient satellite design has finally reached a level of maturity that makes solar power from space a feasible prospect. Furthermore, new strategies in methods for solar energy acquisition and transmission can lead to simplifications in design, reductions in cost and reduced risk.
This paper presents a comparative analysis of launch and Earth departure strategies for human Mars missions. A variety of Earth departure architectures are analyzed with regard to their trans-Mars injection capabilities (performance surrogate metric) and equipment and operational requirements (cost surrogate metric); it is assumed that aerocapture and chemical propulsion are used for all maneuvers in Mars vicinity for all architectures. The architectures are based on chemical propulsion (custom stages or Ares V Earth Departure Stage) as well as nuclear thermal propulsion. Consideration is also given to the impact of different Earth departure options on Mars aerocapture and Mars entry, descent and landing. The comparative aspect of the analysis consists of an iso-TMI mass analysis for the different options. Results of the set of architectures indicate that while chemical Earth departure strategies results in a 30-50 % increase in the number if Ares V launches required per mission, the associated additional marginal cost may be outweighed by the cost of developing and maintaining a nuclear thermal propulsion capability, as well as the increased marginal cost of nuclear thermal propulsion stages. In addition, chemical Earth departure strategies side-step the sensitive issue of space nuclear applications that would be associated with nuclear thermal propulsion.
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