Advanced Radioisotope Power Systems Research Articles

Impedance spectroscopy characterization of neutron irradiated thermoelectric modules for space nuclear power

The European Space Agency is currently supporting the research and development of advanced radioisotope power systems utilising thermoelectric modules. The performance of thermoelectric modules following exposure to neutron radiation is of significant interest due to the likely application of radioisotope thermoelectric generators in deep space exploration or planetary landers requiring prolonged periods of operation. This study utilises impedance spectroscopy to characterise the effects of neutron irradiation on the performance of complete thermoelectric modules, as opposed to standalone material. For a 50 We americium-241 radioisotope thermoelectric generator design, it is estimated that the TE modules could be exposed to a total integrated flux of approximately 5 × 1013 neutrons cm-2 (>1 MeV). In this study, an equivalent neutron dose was simulated experimentally via an acute 2-hour exposure in a research pool reactor. Bi2Te3-based thermoelectric modules with different leg aspect ratios and microstructures were investigated. Gamma-ray spectroscopy was initially used to identify activated radionuclides and hence quantify irradiation induced transmutation doping. To evaluate the thermoelectric properties pre- and post-irradiation, impedance spectroscopy characterization was employed. Isochronal thermal annealing of defects imparted by the irradiation process, revealed that polycrystalline based modules required significantly higher temperature than those with a monolithic microstructure. Whilst this may indicate a greater susceptibility to neutron irradiation, all tested modules demonstrated sufficient radiation hardness for use within an americium-241 radioisotope thermoelectric generator. Furthermore, the work reported demonstrates that impedance spectroscopy is a highly capably diagnostic tool for characterising the in-service degradation of complete thermoelectric devices.

RPS strategies to enable NASA's next decade robotic Mars missions

NASA's proposed roadmap for robotic Mars exploration over the next decade is influenced by science goals, technology needs and budgetary considerations. These requirements could introduce potential changes to the succession of missions, resulting in both technology feed forward and heritage. For long duration robotic surface missions at locations, where solar power generation is not feasible or limited, Radioisotope Power Systems (RPS) could be considered. Thus, RPSs could provide enabling power technologies for some of these missions, covering a power range from 10s of milliwatts to potentially a kilowatt or even higher. Currently, NASA and DoE with their industry partners are developing two RPSs, both generating about 110 W(e) at BOL. These systems will be made available as early as 2009. The Multi-Mission Radioisotope Thermoelectric Generator (MMRTG)—with static power conversion—was down-selected as a potential power source for the MSL mission. Development of small-RPSs is in a planning stage by NASA and DoE; potentially targeting both the 10s of milliwatts and 10s of watts power ranges. If developed, Radioisotope Heat Unit (RHU) based systems—generating 10s to 100s of milliwatts—could power small adjunct elements on larger missions, while the GPHS module-based systems—each generating 10s of watts—could be stacked to provide the required power levels on MER class surface assets. MMRTGs and Stirling Radioisotope Generators (SRGs) could power MSL class or larger missions. Advanced Radioisotope Power Systems (ARPS) with higher specific powers and increased power conversion efficiencies could enhance or even enable missions towards the second half of the next decade. This study examines the available power system options and power selection strategies in line with the proposed mission lineup, and identifies the benefits and utility of the various options for each of the next decade launch opportunities.

05/02503 Performance analysis of cascaded thermoelectric converters for advanced radioisotope power systems

05/02503 Performance analysis of cascaded thermoelectric converters for advanced radioisotope power systems

Tests results and performance comparisons of coated and un-coated skutterudite based segmented unicouples

Abstract Skutterudite based thermoelectric unicouples are being considered for use in Advanced Radioisotope Power Systems (ARPSs) to support NASA’s planetary exploration missions. For these systems, which would be much lighter than state of the art Radioisotope Thermoelectric Generators (RTGs), it is important to ensure minimal degradation in the performance of unicouples that may be caused by material sublimation. In this work, two unicouples, JAN-04 with a thin metallic coating on the legs near the hot junction to suppress antimony sublimation and SEP-03 without coating, are tested for >1000 and 3600 h, respectively. The legs in the two unicouples are of almost the same dimensions and compositions; the p-legs are made of CeFe 3.5 Co 0.5 Sb 12 and Bi 0.4 Sb 1.6 Te 3 segments and the n-legs are made of CoSb 3 and Bi 2 Te 2.95 Se 0.05 segments. SEP-03 is tested at average hot and cold junction temperatures of 961.5 ± 22.0 and 296.3 ± 5.7 K, respectively, in argon gas at ∼0.068 MPa, and JAN-04 is tested at 962.8 ± 20.5 and 294.5 ± 3.3 K, respectively, initially in argon gas at the same pressure for ∼26.5 h then in vacuum ∼9.0 × 10 −7 Torr for >973.5 h. The measured open circuit voltage V oc (240 mV) and peak electrical power (1.64 W e ) for SEP-03 at the beginning of test (BOT) are higher than those for JAN-04 (188 mV and 0.84 W e , respectively). Although the argon gas effectively decreased the antimony loss from the legs of SEP-03, marked degradations in performance occurred. The estimated peak efficiency for SEP-03 decreased from 13.8% at BOT to 5.8% at end of test (EOT), and the peak power decreased from 1.64 W e at BOT to 0.48 W e at EOT, however, V oc decreased by ∼14%. The latter for JAN-04 decreased only by ∼3%, the estimated peak efficiency (∼12%) changed very little and the peak power decreased by ∼20%. Unlike SEP-03, the measured total and contact resistances of the legs in JAN-04 changed very little.

Performance analysis of cascaded thermoelectric converters for advanced radioisotope power systems

Abstract Advanced radioisotope power systems (ARPSs) for future planetary missions require higher conversion efficiency than the state-of-the-art (SOA) SiGe thermoelectric converter in order to decrease system mass and reduce mission cost. The performance of three cascaded thermoelectric converters (CTCs) for potential use in ARPSs is investigated at heat rejection temperatures of 375, 475 and 575 K and input thermal powers of 1, 2 and 3 Wth. These CTCs have top SiGe unicouples that are thermally, but not electrically, coupled to bottom unicouples having one of the following compositions: (a) TAGS-85 (p-leg) and 2N–PbTe (n-leg); (b) CeFe3.5Co0.5Sb12 (p-leg) and CoSb3 (n-leg); and (c) segmented p-leg of CeFe3.5Co0.5Sb12 and Zn4Sb3 and n-leg of CoSb3. The top and bottom unicouples in the CTCs are of the same length (10 mm), but the optimized cross-sectional areas of the n- and p-legs for maximum efficiency are different. The nominal hot junction temperature of the top SiGe unicouples at their peak efficiencies is 1273 K and that of the cold junction is 780 K when the bottom unicouple is of composition (a) and 980 K for compositions (b) and (c). The hot junction temperatures of the bottom unicouples are taken 20 K lower than the cold junctions of the top unicouples, but the input thermal powers to the former are the same as those rejected by the latter. Assuming zero side heat losses and a contact resistance of 150 μΩ cm2 per leg in the top and bottom unicouples, the calculated peak efficiencies of the CTCs vary from 9.43% to 14.35%. These efficiencies are 40–113% higher, respectively, than that of SOA SiGe (∼6.5%) when operating at the cold junction temperature of 566 K and the same hot junction temperature (1273 K) and contact resistance per leg. Decreasing this resistance to a realistic value of 50 μΩ cm2 per leg increases the peak efficiencies of the CTCs by 0.5–0.9 percentage points to 9.93–15.25%.

An analysis of coated particles fuel compact-general purpose heat source (CPFC-GPHS)

The C oated P articles F uel C ompact (CPFC) offers performance advantages for use in the Radioisotope Heater Unit (RHU) and General Purpose Heat Source (GPHS) for Advanced Radioisotope Power Systems (ARPSs), generating a few milliwatts or a few hundred watts of electrical power, respectively, for future planetary exploration. It comprises 238PuO 2 fuel kernels with 5-μm thick PyC inner coating and a strong ZrC outer coating, dispersed in a graphite matrix. The fuel kernels in the compact could be either of a single size (≤ 1200 μm) or binary sizes (300 and 1200 μm) for particles' volume compaction of 62.5% and 72%, respectively. The ZrC coating serves as a pressure vessel for containing the fuel kernels and the helium gas generated by the radioactive decay of 238Pu during storage time before launch and the mission lifetime (15–25 years). The thickness of the ZrC coating and hence, the specific thermal power of the CPFC depend on the estimated maximum fuel temperature during reentry following a launch accident, the storage time before launch and mission duration, and the helium release fraction from the fuel kernels. This paper investigates, the advantage of replacing the four iridium-clad 238PuO 2 fuel pellets, the two floating graphite membranes, and the two graphite impact shells in current State-Of-the-Art (SOA) GPHS with CPFC. The mass, thermal power, and specific thermal power of the CPFC-GPHS are calculated as functions of the helium release fraction from the fuel kernels, up to a full release, and the maximum compact temperature during reentry, from 1500 K to 2400 K. For the same mass and volume, the single-size particles CPFC-GPHS could generate 260 W at Beginning-Of-Mission (BOM), following 10 years of storage, versus 231 W for SOA GPHS. For an additional 10% higher mass, the CPFC-GPHS could generate 340 W at BOM at a specific thermal power of 214 W/kg, which are 47% and 34% higher than those of SOA GPHS, respectively.