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The coming decades of planetary science and deep space exploration will likely have a combination of more ambitious missions and ever more constrained budgets. The outer solar system, in particular, poses a challenge for lower mission cost as the principal need for a robotic craft — a source of energy — is difficult to supply through conventional means (solar energy). Even as far from the Sun as Saturn, the solar energy density is only 1% of that at Earth. Not viewed typically as a power source for low-cost missions, radioisotope power systems (RPS) may well fill that role by providing power to small spacecraft in the outer solar system. And the outer solar system beckons with extremely compelling science. The rich dynamics of the atmospheres of the gas giants are continuously operating laboratories of extreme weather processes, examples of which in miniaturized scale may become more familiar here on Earth. Enceladus, a small moon of Saturn, has been seen by the Cassini mission to be a site of continuous high geologic activity, with plumes of water vapor and particles pumped hundreds of kilometers above the surface, indeed into Saturn orbit. The internal heating mechanisms of this activity beg for explanation, and more importantly, initial measurements by the Cassini spacecraft give tantalizing clues that the geo-thermal source of the heating is, in fact, maintaining a global sub-surface ocean, which in combination could provide a habitat for life. This paper will explore how existing and currently available RPS elements may make mission concepts to explore the intriguing science of Enceladus economically tractable, and at the same time provide a generic platform for other small but highly capable spacecraft to explore the outer solar system.

At the request of the Satellites Panel of the National Research Council (NRC) Planetary Science Decadal Survey, a Rapid Mission Architecture (RMA) study of possible missions to Saturn's moon Enceladus was conducted at the Jet Propulsion Laboratory in January and February of 2010. This was one of many studies commissioned by this NRC Decadal Survey. In this study, 15 Enceladus mission architectures were examined that spanned a broad range of potential science return and total estimated mission cost.

The JPL Rapid Mission Architecture (RMA) capability is a novel collaborative team-based approach to generate new mission architectures, explore broad trade space options, and conduct architecture-level analyses. RMA studies address feasibility and identify best candidates to proceed to further detailed design studies. Development of RMA first began at JPL in 2007 and has evolved to address the need for rapid, effective early mission architectural development and trade space exploration as a precursor to traditional point design evaluations. The RMA approach integrates a small team of architecture-level experts (typically 6–10 people) to generate and explore a wide-ranging trade space of mission architectures driven by the mission science (or technology) objectives. Group brainstorming and trade space analyses are conducted at a higher level of assessment across multiple mission architectures and systems to enable rapid assessment of a set of diverse, innovative concepts. This paper describes the overall JPL RMA team, process, and high-level approach. Some illustrative results from previous JPL RMA studies are discussed. 1 2

In 2007 a JPL Rapid Mission Architecture (RMA) analysis team identified and evaluated a broad set of mission architecture options for a suite of scientific exploration objectives targeting the Saturnian moon Enceladus. Primary science objectives were largely focused on examination of the driving mechanisms and extent of interactions by the plumes of Enceladus recently discovered by Cassini mission science teams. Investigation of the architectural trade space spanned a wide range of options, from high-energy flybys of Enceladus as a re-instrumented expansion on the Cassini mission, to more complex, multi-element combinations of Enceladus orbiters carrying multiple variants of in-situ deployable systems. Trajectory design emerged as a critical element of the mission concepts, enabling challenging missions on Atlas V and Delta IV-Heavy class launch vehicles. Various Enceladus Flagship-class mission concepts identified were analyzed and compared against several first-order figures of merit, including mass, cost, risk, mission timeline, and associated science value with respect to accomplishment of the full set of science objectives. Results are presented for these comparative analyses and the characterization of the explored trade space.

This paper describes the results of a recent Titan exploration mission study aimed at investigating optimal methods for scientific observation of the atmosphere and surface of this veiled moon. During the course of this study a mission design concept was evolved which involves sending a two element mission to Titan, consisting of an orbiter for global observations and data relay, and an aerial vehicle which would drift in the atmosphere for more detailed surface study. The type of aerial vehicle proposed is a hot air balloon, or montgolfiere, which would use the Titan atmosphere, heated using the waste heat from its radioisotope power system to provide long term buoyancy. Once deployed, the montgolfiere would ride with the easterly winds, occasionally changing altitude to take advantage of possible reverse wind directions and even descending to the surface to physically sample sites of interest as they come up. Seasonal and tidal north-south winds would allow the mission to explore different latitudes, which Cassini data have shown to be amazingly diverse in geologic nature. Communication from the montgolfiere would be relayed through the accompanying orbiter spacecraft, as well as directly to Earth, providing the potential for data return from Titan's surface equivalent to that provided by many comparable orbiter missions at much closer destinations.

The National Research Council's solar system exploration decadal survey identified Jupiter's moon Europa as its highest-priority destination for near-term exploration. Voyager and Galileo missions to the Jupiter system provided evidence consistent with a subsurface ocean on Europa, which is of great interest as a potential abode for extraterrestrial life. This paper describes a conceptual flagship-class Europa orbiter concept that was assumed to launch as early as 2012, arriving at Europa approximately 8 years later using inner solar system gravity assists to reach Jupiter. Jupiter's intense radiation environment limits the mission duration at Europa to 30 days for this study, though the duration is a result of multiple trades and is by no means fixed. The Europa subgroup of the outer planets assessment group identified six primary science objectives for this concept. An /spl sim/150-kg instrument suite selected for the study addresses those objectives. Large heliocentric distances, high power levels required, and especially the harsh Jovian radiation environment drove the selection of radioisotope thermoelectric generators (RTGs) for all onboard electrical power, with the excess heat aiding spacecraft thermal control. Mass and architecture trades were performed using different spacecraft trajectories, launch vehicle types, radioisotope power systems, and mission durations. The study shows that new mission constraints allow a scientifically compelling Europa orbiter mission that might also deliver a Europa lander.