This chapter is focused upon use of the three major families of thin-film solar cell (TFSC) materials for space applications: amorphous silicon (a-Si), cadmium telluride (CdTe), and copper indium gallium selenide (CIGS). Clearly, there are distinct advantages to be realized through use of thin III-V and perovskite hybrid materials for photovoltaics (PV) for space power generation. However, studies of inorganic TFSC materials have yielded several potential space applications as well as numerous scientific and technological insights over the past 50 years. A short discussion of the difference between space (air mass zero, AM0) and terrestrial (AM1.0 or AM1.5) solar radiation begins the chapter. After contrasting crystalline and TFSCs, we explore the key components of TFSC devices; performance and technical challenges of the main inorganic absorber materials are then considered. We examine, in context, several unique stressors in the space environment, varying with location, that challenge TFSC devices. Thermal issues in space, including cycling and thermal load, are more extreme than those encountered by terrestrial installations; other issues include atomic oxygen and various types of radiation (alpha, beta, gamma, and cosmic rays). Device structure(s), including mass specific power and processing details, as well as testing relevant to use of TFSCs for space missions are examined. A brief summary of past, present, and future applications for space exploration concludes the chapter. Finally, we highlight several examples of technology transfer to other PV devices and related technologies.

We provide an overview of the results of several patent and literature searches that focus on (or address) single-source precursor (SSP) chemistry, materials processing, and nanotechnology aspects. Important inorganic material classes fabricated include carbides, pnictides, chalcogenides, and mixed anion materials. A cross-section of example applications of SSP-processed materials includes: energy conversion and storage, (micro)electronics, sensor, environmental, surface modification, and (bio)medicine. We also summarize past efforts in our laboratories to develop practical applications of SSPs and address issues related to the transfer and commercialization of SSP processing, materials technologies, with potential applications. We conclude with insights into our own personal experiences with technology transfer, including some examples of public and private entities to potentially facilitate such endeavors, and offer some practical advice for the reader.

Silicon, being the second most abundant element on the earth's crust with the theoretical specific capacity of 4200 mAh g− 1, can serve as a cost-effective and environmentally benign anode material for next generation LIBs. The practical application of Si-based anode is, however, mostly hindered by its low electronic conductivity, colossal volume changes during lithiation/delithiation, and unstable nature of the SEI. Even though significant progress has been achieved in Si-based hybrid materials from the viewpoint of fundamental research, the commercial viability of Si-based anode demands low first cycle irreversible capacity loss, better capacity retention, good tap density, high Si content, simple and scalable manufacturing process, and most importantly low manufacturing cost. Additionally, an efficient, simple, low-cost, easily scalable synthesis methodology is desired which can assure an excellent electrochemical performance of Si-based anode materials. Herein, we have outlined the progress achieved in making a hybrid material with silicon as composite anodes, specifically carbon-silicon hybrid, oxide-silicon hybrid, silicon-metal hybrid, and silicide for LIBs. Further, this chapter covers several topics that pertain to practical considerations such as alternative and low-cost processing methods. The successful implementation of suitable alternative raw materials and processing methods are very essential for the production of Si-based anode, especially when approaching the industrial facility.

Rechargeable batteries are ideal for numerous applications: electronics, electric vehicles, stationary energy storage, and aerospace systems. Over the past several decades, our research groups and collaborators have examined aspects of advanced (nano)materials, including Si alloys for Li-ion batteries (LIBs) for aerospace power applications. These applications present unique challenges such as temperature fluctuations, rapid gravitational fluctuations, high-energy particles and radiation environments, atomic oxygen, hard-ultraviolet light, thermal management and the necessity or weight- and space savings. This chapter covers several topics that pertain to practical considerations for integrated power devices (and systems) and microsatellites (i.e., CubeSats); we address their applicability to future space exploration. Integrated power technologies that involve energy storage and energy conversion address several concerns about limitations imposed upon space flight hardware and systems related to power, space, and mass limitations. An integrated power device was successfully demonstrated in low-Earth orbit on the Starshine 3 microsatellite in late 2001/early 2002. We review efforts by numerous other researchers to develop batteries integrated with solar cells and other technologies. We outline the four basic types of integrated power devices (or systems), address potential applications and discuss advantages, challenges, and practical considerations. We discuss a variety of battery technologies (with a focus on LIBs) for CubeSats. Commercial LIBs have been successfully demonstrated for numerous exploration missions over the past 20 years, including a remarkable successful combined lander/CubeSat mission (insight/MarCO) to Mars during the past several years. It is important to note that while a variety of battery technologies could be employed, Li-ion batteries with Si-containing anodes may be the optical choice for certain missions.

Aerospace power applications present unique challenges such as temperature fluctuations, rapid gravitational fluctuations, high-energy particles and radiation environments, atomic oxygen, hard-ultraviolet light, thermal management, and the necessity of weight- and space savings. We review a variety of battery technologies for current aeronautics applications, including electric aircraft, high-altitude solar aircraft, and airships. A summary of energy storage options and issues for space exploration missions is also provided to introduce this intriguing topic. Batteries have been successfully demonstrated for numerous exploration missions to several classes of solar system destinations over the past 50 years. Given the broad technology space of battery types and materials, the final sections of this chapter focused on a discussion of several instructive representative missions and practical aspects of batteries (with a focus on rechargeable technologies) for space exploration. The discussion of recent successful and upcoming exploration missions is followed by a brief survey of appropriate battery technologies for specific destinations, a consideration of unique aspects of future missions to asteroids, and ocean worlds, including off-world atmospheric flight exploration, and Venus mission concepts, and ended with some comments on the long-term prospects for humanity to explore and possibly settle in habitable regions of our solar system. The use of local resources may one day enable off-world production of consumables, power components, and structural materials to facilitate the construction of settlements and the exploration of the farthest regions of the solar system. An important take-home lesson is the need to develop energy storage technologies and power systems that can withstand the radiation fluxes and temperature extremes encountered in the solar system; this will be critical for electronic devices, advanced instrumentation, and (small) off-world exploration vehicles.

We have discovered a novel two-phase synthesis of CuInSe2 at 25 deg C from Cu2Se and (C5H5)3In in 4-methylpyridine (4-MePy). An analogous reaction to produce CuInS2 must be run at 140 deg C in refluxing 4-MePy in the presence of 2-mercaptopyridine. Microscopy of CuInSe2 produced at 25 deg C shows it to be platelet-shaped crystallites with an approximate particle size of 10 microns, less than 2 percent C and H, with a small amount of unidentified crystalline impurity. Our results demonstrate that it is possible to produce from solution a material that is ordinarily synthesized in bulk or films at much higher temperatures or using extraneous reagents and/or electrons.

US 2013/02098.69 A1 Aug. 15, 2013 Related U.S. Application Data Continuation-in-part of application No. 13/725,969, filed on Dec. 21, 2012, and a continuation-in-part of application No. 12/392,525, filed on Feb. 25, 2009, now Pat. No. 8,420,258, application No. 13/779,409, which is a continuation-in-part of application No. 12/904,113, filed on Oct. 13, 2010, now Pat. No. 8,481,214. Provisional application No. 61/578,545, filed on Dec. 21, 2011, provisional application No. 61/254,090, filed on Oct. 22, 2009, provisional application No. 61/603,833, filed on Feb. 27, 2012, provisional application No. 61/615,179, filed on Mar. 23, 2012, provisional application No. 61/667,876, filed on Jul. 3, 2012, provisional application No. 61/667,317, filed on Jul. 30, 2012, provisional application No. 61/752,437, filed on Jan. 14, 2013. Int. C. HOLM 4/13 (2010.01) HOLM 4/58 (2010.01) HOLM 4/62 (2006.01) HOLM 6/04 (2006.01) HOIG II/68 (2013.01) HOLM 4/70 (2006.01) HOLM 4/13 (2010.01) HOLM 4/33 (2010.01) (Continued)

Single-crystal X-ray structures of four nickel dithiocarbamate complexes, the homoleptic mixed-organic bis-dithiocarbamates Ni[S2CN(isopropyl)(benzyl)](2), Ni[S2CN(ethyl)(n-butyl)](2), and Ni[S2CN(phenyl)(benzyl)](2), as well as the heteroleptic mixed-ligand complex NiCl[P(phenyl)(3)][(S2CN(phenyl)(benzyl)], were determined. A slightly distorted square-planar nickel coordination environment was observed for all four complexes. The organic residues adopt conformations to minimize steric interactions. Steric effects also may determine puckering, if any, about the nickel and nitrogen atoms, both of which are planar or nearly so. A trans-influence affects the Ni-S bond distances. Nitrogens interact with the CS2 carbons with a bond order near two; the other substituents on nitrogen display transoid conformations. There are no strong intermolecular interactions, consistent with prior observations of the volatility of nickel dithiocarbamate complexes. A preliminary thermolysis study of the homoleptic species results in production of 1:1 nickel sulfide phases, indicating the potential utility of these species as single-source precursors.[GRAPHICS].

We describe the structures of two indium complexes obtained during the attempted syntheses of solid-state materials precursors. The geometries of mer-InBr3(pic)(3) 1 and [In(mu-OH)Br-2(pic)(2)center dot 2pic](2) (pic = 4-methylpyridine) are distorted octahedra about the metal atoms. Two molecules which differ mainly with respect to the relative orientation of the gamma-picoline planes are present in the asymmetric unit of I, and a trans influence is observed for the ligands. Two indium atoms and two hydroxyl groups form a four atom ring in 2, with the four bromine atoms not coplanar. A two-fold rotational symmetry axis is present with the two indium atoms occupying special positions. A trans influence is also observed. Two nonequivalent gamma-picolines not coordinated to the metals are present, one of which forms a hydrogen bond to the hydroxyl group while the other exhibits no strong intermolecular associations. (C) 2015 Elsevier B.V. All rights reserved.

Three copper–indium bimetallic compounds, (PPh3)2CuIn(ER)4 [R=CH3, E=S and R=Ph, E=S and Se], potentially useful as single-source precursors for the lower temperature (<400°C) synthesis of ternary chalcopyrite photovoltaic materials, contain an inorganic core structure consisting of two triphenylphosphine ligands attached to Cu(I), two thiolate or selenolate ligands attached to In(III), and an additional two bridging S or Se anion ligands. The metal and bridging chalcogen atoms form planar rings. The ligands adopt geometries to minimize steric interactions, and the intramolecular Cu…In nonbonded distances (3.285–3.500Å) depend on the stereoelectronic demands of the ligands.

An entry from the Cambridge Structural Database, the world’s repository for small molecule crystal structures. The entry contains experimental data from a crystal diffraction study. The deposited dataset for this entry is freely available from the CCDC and typically includes 3D coordinates, cell parameters, space group, experimental conditions and quality measures.

As humanity begins to reach out into the solar system, it has become apparent that supporting a human or robotic presence in transit and/or on station requires significant expendable resources including consumables (to support people), fuel, and convenient reliable power. Transporting all necessary expendables is inefficient, inconvenient, costly, and, in the final analysis, a complicating factor for mission planners and a significant source of potential failure modes. Over the past twenty-five years, beginning with the Space Exploration Initiative, researchers at the NASA Glenn Research Center (GRC), academic collaborators, and industrial partners have analyzed, researched, and developed successful solutions for the challenges posed by surviving and even thriving in the resource limited environment(s) presented by near-Earth space and non-terrestrial surface operations. In this retrospective paper, we highlight the efforts of the co-authors in resource simulation and utilization, materials processing and consumable(s) production, power systems and analysis, fuel storage and handling, propulsion systems, and mission operations. As we move forward in our quest to explore space using a resource-optimized approach, it is worthwhile to consider lessons learned relative to efficient utilization of the (comparatively) abundant natural resources and improving the sustainability (and environment) for life on Earth. We reconsider Lunar (and briefly Martian) resource utilization for potential colonization, and discuss next steps moving away from Earth.

The phenol photocatalytic degradation was investigated using heterogeneous catalyst Ag-doped ZnO nanowires under UV irradiation. Ag-ZnO nanowires were immobilized on borosilicate glass via a simple hydrothermal technique. Preliminary photodegradation studies were performed with Ag-ZnO nanowires at various concentrations of phenol (10 - 60 mg/L) at undiluted pH. After determination of the optimal initial concentration (30 mg/L), additional parameters including pH and light intensity were investigated to optimize photodegradation of phenol for large-scale application. The experimental results illustrate that the kinetics of degradation of phenol are pseudo-first order. Based on the relationship, experimental model and empirical correlation were generated and compared for validity. The experimental data were found to fit a cubic model (linear in UV irradiation intensity, I, and cubic in pH), over ranges of 10 - 60 W (UV lamp power) and 2.7 - 11.0 (pH) with a coefficient of determination (R2) of 0.9934. This model, of the form K(I, pH) = c00 + c10I + c01pH + c11IpH + c02pH2 + c12IpH2 + c03pH3 was found to yield a better fit than simpler (quadratic) or more complex (quartic) polynomial-based models considered. The model parameters cij and corresponding 95% confidence intervals were obtained.