June F. Zakrajsek

Exploration Rover Concepts and Development Challenges

*† ‡ § ** This paper presents an overview of exploration rover concepts and the various development challenges associated with each as they are applied to exploration objectives and requirements for missions on the Moon and Mars. A variety of concepts for surface exploration vehicles have been proposed since the initial development of the Apollo-era lunar rover. These concepts range from small autonomous rovers to large pressurized crewed rovers capable of carrying several astronauts hundreds of kilometers and for weeks at a time. This paper provides a brief description of the rover concepts, along with a comparison of their relative benefits and limitations. In addition, this paper outlines, and investigates a number of critical development challenges that surface exploration vehicles must address in order to successfully meet the exploration mission vision. Major development challenges investigated in this paper include: mission and environmental challenges, design challenges, and production and delivery challenges. Mission and environmental challenges include effects of terrain, extreme temperature differentials, dust issues, and radiation protection. Mission profiles envisioned for Lunar and Mars surface exploration is also investigated. Design methods are discussed that focus on optimum methods for developing highly reliable, long-life and efficient systems. Design modularity and its importance to inexpensive and efficient tailoring for specific missions is also investigated. Notional teaming strategies are discussed, including benefits of tapping into traditionally non-space oriented manufacturers. In addition, challenges associated with delivering a surface exploration system is explored and discussed. Based on all the information presented, modularity will be the single most important factor in the development of a truly viable surface mobility vehicle. To meet mission, reliability, and affordability requirements, surface exploration vehicles, especially pressurized rovers, will need to be modularly designed and deployed across all projected Moon and Mars exploration missions. The modular concept should start as unmanned teleoperated rovers, and grow into a variety of manned vehicles by upgrading and adding additional modules.

Hydrogen therapy may reduce the risks related to radiation-induced oxidative stress in space flight

Cosmic radiation is known to induce DNA and lipid damage associated with increased oxidative stress and remains a major concern in space travel. Hydrogen, recently discovered as a novel therapeutic medical gas in a variety of biomedical fields, has potent antioxidant and anti-inflammatory activities. It is expected that space mission activities will increase in coming years both in numbers and duration. It is therefore important to estimate and prevent the risks encountered by astronauts due to oxidative stress prior to developing clinical symptoms of disease. We hypothesize that hydrogen administration to the astronauts by either inhalation or drinking hydrogen-rich water may potentially yield a novel and feasible preventative/therapeutic strategy to prevent radiation-induced adverse events.

Dynamic Radioisotope Power System development for space exploration

Dynamic power conversion offers the potential to produce Radioisotope Power Systems (RPS) that generate higher power outputs and utilize the available heat source plutonium fuel more efficiently than Radioisotope Thermoelectric Generators. Additionally, dynamic systems offer the potential of producing generators with significantly reduced power degradation over the course of deep space missions so that more power would be available at the end of the mission, when it is needed most for both powering science instruments and transmitting the resulting data. The development of dynamic generators involves addressing technical issues not typically associated with traditional thermoelectric generators. Developing long-life, robust, and reliable dynamic conversion technology is challenging yet essential to building a suitable flight-ready generator. Considerations include working within existing hardware-handling infrastructure, where possible, so that development costs can be kept low, and integrating dynamic generators into spacecraft, which may be more complex than integration of static thermoelectric systems. Methods of interfacing to and controlling a dynamic generator must also be considered, and new potential failure modes must be taken into account. This paper will address some of the key issues of dynamic RPS design, development, and adaption.

Enabling Future Low-Cost Small Spacecraft Mission Concepts Using Small Radioisotope Power Systems

For more than five decades, Radioisotope Power Systems (RPS) have played a critical role in the exploration of space, enabling missions of scientific discovery to destinations across the solar system by providing electrical power to explore remote and challenging environments - some of the hardest to reach, darkest, and coldest locations in the solar system. In particular, RPS has met the demand of many long-duration mission concepts for continuous power to conduct science investigations independent of change in sunlight or variations in surface conditions like shadows, thick clouds, or dust.

NASA's Radioisotope Power Systems Program Status

NASAs Radioisotope Power Systems (RPS) Program began formal implementation in December 2010. The RPS Programs goal is to make available RPS for the exploration of the solar system in environments where conventional solar or chemical power generation is impractical or impossible to meet mission needs. To meet this goal, the RPS Program manages investments in RPS system development and RPS technologies. The current keystone of the RPS Program is the development of the Advanced Stirling Radioisotope Generator (ASRG). This generator will be about four times more efficient than the more traditional thermoelectric generators, while providing a similar amount of power. This paper provides the status of the RPS Program and its related projects. Opportunities for RPS generator development and targeted research into RPS component performance enhancements, as well as constraints dealing with the supply of radioisotope fuel, are also discussed in the context of the next ten years of planetary science mission plans.

Radioisotope Power Systems Program Status and Expectations

The NASA Radioisotope Power Systems (RPS) Program’s goal is to make RPS available for the exploration of the solar system in environments where conventional solar or chemical power generation is impractical or impossible to use to meet mission needs. To meet this goal, the RPS Program manages investments in RPS system development and RPS technologies. The RPS Program exists to support NASA’s Science Mission Directorate (SMD). The RPS Program provides strategic leadership for RPS, enables the availability of RPS for use by the planetary science community, successfully executes RPS flight projects and mission deployments, maintains a robust technology development portfolio, coordinates RPS related National Environmental Policy Act (NEPA) and Nuclear Launch Safety (NLS) approval processes for SMD, maintains insight into the Department of Energy (DOE) implementation of NASA funded RPS production infrastructure operations, including implementation of the NASA funded heat-source plutonium production restart efforts. This paper will provide a status of recent RPS activities and accomplishments.

NASA's Radioisotope Power Systems planning and potential future systems overview

The goal of NASAs Radioisotope Power Systems (RPS) Program is to make RPS ready and available to support the exploration of the solar system in environments where the use of conventional solar or chemical power generation is impractical or insufficient to meet the needs of the missions. To meet this goal, the RPS Program, working closely with the Department of Energy, performs mission and system studies (such as the recently released Nuclear Power Assessment Study), assesses the readiness of promising technologies to infuse in future generators, assesses the sustainment of key RPS capabilities and knowledge, forecasts and tracks the Programs budgetary needs, and disseminates current information about RPS to the community of potential users. This process has been refined and used to determine the current content of the RPS Programs portfolio. This portfolio currently includes an effort to mature advanced thermoelectric technology for possible integration into an enhanced MultiMission Radioisotope Generator (eMMRTG), sustainment and production of the currently deployed MMRTG, and technology investments that could lead to a future Stirling Radioisotope Generator (SRG). This paper describes the program planning processes that have been used, the currently available MMRTG, and one of the potential future systems, the eMMRTG.

NASA's Radioisotope Power Systems and Technologies - A Forward Look

For 50 years, the use of radioisotope power systems for spacecraft applications has continued to evolve and mature. Advances in energy conversion component technologies as well as in flight generators continue to this day. In 2008, an effort to consolidate management of these related efforts was initiated, and the formation of a NASA Radioisotope Power Systems Program began. NASA has now completed consolidation of its investments in Radioisotope Power Systems (RPS) through the approval of a single program office structure. The RPS Program’s goal is to make RPS available for the exploration of the solar system in environments where conventional solar or chemical power generation is impractical or impossible. While historical use of RPS dates back fifty years to the launch of a 2.7 watt generator, this program overview provides an integrated look into recent progress by the DOE-NASA team on the Advanced Stirling Radioisotope Generator (ASRG) system development and its preparation for potential mission applications on the current Discovery mission competition. The overview also explores technology maturation of thermoelectric and thermo-photovoltaic technology as well as systems development status and plans. Possible RPS-based missions and destinations that were discussed as part of the recently completed Planetary Science Decadal Survey are identified and placed in context of the program implementation. Opportunities for RPS generator development and targeted research into RPS component performance enhancements as well as constraints dealing with the supply of radioisotope heat sources are also discussed in the context of the next 10 years of Planetary Science mission plans.

NASA's Radioisotope Power Systems program overview — A focus on RPS users

The goal of NASAs Radioisotope Power Systems (RPS) Program is to make RPS ready and available to support the exploration of the solar system in environments where the use of conventional solar or chemical power generation is impractical or impossible to meet potential future mission needs. To meet this goal, the RPS Program manages investments in RPS technologies and RPS system development, working closely with the Department of Energy. This paper provides an overview of the RPS Program content and status, its collaborations with potential RPS users, and the approach employed to maintain the readiness of RPS to support future NASA mission concepts.

Science instrument sensitivities to Radioisotope Power System environment

Radioisotope Power Systems (RPS) have been and will be enabling or significantly enhancing for many missions, including several concepts identified in the 2011 Planetary Science Decadal Survey. Some mission planners and science investigators might have concerns about possible impacts from RPS-induced conditions upon the scientific capabilities of their mission concepts. To alleviate these concerns, this paper looks at existing and potential future RPS designs, and examines their potential radiation, thermal, vibration, electromagnetic interference (EMI), and magnetic fields impacts on representative science instruments and science measurements. Radiation impacts from RPS on science instruments are of potential concern for instruments with optical detectors and instruments with high-voltage electronics. The two main areas of concern are noise effects on the instrument measurements, and long-term effects of instrument damage. While RPS by their nature will contribute to total radiation dose, their addition for most missions should be relatively small. For example, the gamma dose rate from one Multi-Mission Radioisotope Thermoelectric Generator (MMRTG) would be an order of magnitude lower than the environmental dose rate at Mars, and would have a correspondingly lower contribution to instrument noise and to any permanent damage to payload sensors. Increasing the number of General Purpose Heat Source (GPHS) modules used in an RPS would be expected to increase the generated radiation proportionally; however, the effect of more GPHS modules is mitigated from a strictly linear relationship by self-shielding effects. The radiation field of an RPS is anisotropic due to the deviation of the modules from a point-source-geometry. For particularly sensitive instruments, the total radiation dose could be mitigated with separation or application of spot shielding. Though a new, higher-power RPS could generate more heat per unit than current designs, thermal impact to the flight system could be mitigated with shading and pointing if required by the mission. Alternatively, excess heat could prove beneficial in providing needed heat to spacecraft components and instruments in some thermal environments. Vibration for a new higher-power Stirling Radioisotope Generator (SRG) would be expected to be similar to the recent Advanced Stirling Radioisotope Generator (ASRG) design. While vibration should be low, it must be considered and addressed during spacecraft and instrument design. EMI and magnetic fields for new RPS concepts are expected to be low as for the current RPS, but must be considered and addressed if the mission includes sensitive instruments such as magnetometers. The assessment conducted for this paper focused on orbiter instrument payloads for two representative mission concepts - a Titan Saturn System Mission (TSSM) and a Uranus Orbiter and Probe (UOP) - since both of these Decadal Survey concepts would include many diverse instruments on board. This paper describes how the potential impacts of the RPS on science instruments and measurements were assessed and which impacts were addressed. Then, this paper suggests mitigation strategies against those impacts, and provides an overview of several topics that would benefit from further work.