This paper describes an architectural concept for a Small Lunar Exploration and Delivery System to operate as a platform for emplacing payloads into lunar orbit and onto the lunar surface, while providing mobility for surface exploration, science, and infrastructure. The concept leverages emerging services that are capable of delivering payloads to Low Earth Orbit (LEO), while utilizing new and old technologies to build a platform for transfer to Low Lunar Orbit (LLO). Advances and miniaturization in avionics, navigation, power, and propulsion systems enable a unique opportunity to develop a system that is both capable of landing on the lunar surface and providing surface mobility with the same system. Nomenclature deltaV = change in velocity, m/s Isp = specific impulse, s
This paper summarizes the final results of a study analyzing different Guidance, Navigation and Control (GN&C) architectural approaches for fault tolerance in National Aeronautics and Space Administration's (NASA's) crewed and robotic exploration space systems. GN&C systems were decomposed into simple building block subunits of sensors, computers, and actuators and various forms of subunit interconnection were defined for investigation. The resulting subunit/interconnection construct was used as a top-level abstraction for building candidate GN&C system architectures. This model was implemented using Massachusetts Institute of Technology's (MIT's) Object Process Network (OPN) modeling language in order to more easily enumerate possible architectures and ultimately identify which of these architectures have optimal properties. Dual and triple redundant GN&C system architectures, employing different classes of components, were modeled using the OPN language. The model assumed perfect coverage -100-percent accuracy in detecting and isolating a failure. Within the constraints of the model, all possible architectures were rigorously enumerated and the weight/reliability trade-offs of crossstrapping components and using more than one type of component were assessed. The study results indicate it is possible to produce nearly all potentially optimal GN&C architectures using generic connections between low-reliability components. The identified optimal architectures reveal a preference to increase GN&C system redundancy of lighter, less reliable components rather than using smaller numbers of more reliable, heavy components.T the core of NASA's future space exploration is a return to the Moon, where we will build a sustainable longterm human presence. As the Space Shuttle approaches retirement and the International Space Station nears completion, NASA's Constellation Program (CxP) is designing and developing the next fleet of American spacefaring vehicles to bring astronauts back to the Moon, and possibly to Mars and beyond. In order to meet their exploration goals, NASA's CxP will have to acquire and operate a number of new human-rated systems, such as the Orion Crew Exploration Vehicle (CEV), the Ares-1 Crew Launch Vehicle (CLV), and the Altair Lunar Lander, along with other elements for crew transportation (e.g., in-space propulsion stages), lunar habitation, and mobility. Robotic systems will include lunar robotic orbiter vehicles and robotic lunar landers. Commonality in exploration system hardware, and software elements offers the opportunity to significantly increase sustainability by reducing, both nonrecurring and recurring cost and/or risk. In particular the potential benefit of common GN&C avionics and flight software is considerable, not only in the initial development effort, but in validation and verification, and more importantly in the ongoing maintenance efforts and incremental upgrades that will occur over the life cycle of these exploration spacecraft. With commonality of the onboard components of this...
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