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Summary of Test Results: Thermal Vacuum: The Canon R5 (mirrorless) and Nikon D6 (DSLR) showed similar operational characteristics from -30C to +40C in a vacuum. Both cameras survived thermal vacuum testing. (Nikon Z9 was not available at the time vacuum testing occurred). Radiation: Read capability of 4 CFExpress cards was tested in proton environment.
The Small Spacecraft Technology (SST) program within NASA’s Space Technology Mission Directorate, expands the ability to execute unique missions through rapid development and demonstration of capabilities for small spacecraft applicable to exploration, science and the commercial space sector. Through targeted development and frequent in space testing, the program: • Enables execution of missions at much lower cost than previously possible • Substantially reduces the time required for development of spacecraft • Enables new mission architectures through the use of small spacecraft • Expands the reach of small spacecraft to new destinations and challenging new environments • Enables the augmentation of existing assets and future missions with supporting small spacecraft. The program achieves its objectives through: • Identification and investment in the development of new subsystem technologies to enhance or expand the capabilities of small spacecraft • Sponsorship of flight demonstrations of new technologies, capabilities and applications for small spacecraft • Promotion of the use of small spacecraft as platforms for testing and demonstrating technologies and capabilities that might have more general applications in larger-scale spacecraft and systems Technologies funded by the program that are key to advancing the utility and capability of small spacecraft were demonstrated in 2022 and 2023. Notable on-orbit demonstrations include the following. • The Cislunar Autonomous Positioning System Technology Operations and Navigation Experiment’s (CAPSTONE) navigation technology that was demonstrated for the first time in 2023 could provide autonomous onboard navigation information for future lunar missions, minimizing or eliminating human-in-the-loop mission operations. • The optical communications technology also demonstrated in 2023 by the TeraByte InfraRed Delivery (TBIRD) payload that launched on Pathfinder Technology Demonstrator-3, achieved 200 gigabit per second (Gbps) throughput on a space-to-ground optical link between a satellite in orbit and Earth, the highest data rate ever achieved by optical communications technology. • The precision laser pointing performance of NASA’s CubeSat Infrared CrossLink A (CLICK) spacecraft’s fine steering mirror control system was successfully demonstrated. This element of the laser communications system will be used to demonstrate two-way crosslink communication in low-Earth orbit by CLICK B/C anticipated to launch in late 2024. Investments in subsystem technology development through funding to university, industry, and other government partners in a number of areas will be discussed. Among others, topic areas include propulsion, autonomous swarm technology, edge computing, and thermal control. Additionally, the status of the CubeSat-alternative platform, DiskSat, strategies for accelerating the demonstration of technology payloads via the Realizing Rapid, Reduced-cost high-Risk Research (R5) project, and the status of recently completed and upcoming on-orbit demonstrations will also be presented.
A 10-step, 9-species reduced mechanism for methane/oxygen combustion is evaluated and optimized for use in rotating detonation rocket engine (RDRE) simulations at an operating pressure of 10 bar. The mechanism is assessed against GRI-Mech 3.0 for ignition delay times, adiabatic equilibrium temperature and species, Chapman-Jouguet (CJ) detonation parameters, and laminar flame speed. A sequential Nelder–Mead optimization procedure is applied to the rate constants of reactions R1, R4, and R5, targeting ignition delay agreement over the equivalence ratio range φ = 1.0–1.4 and temperature range T = 1400–2000 K. The optimized mechanism achieves ignition delay agreement within 28% of GRI-Mech 3.0 for the temperature range relevant to RDRE operation (τ ≥ 5 μs). Adiabatic equilibrium temperatures and CJ detonation parameters are reproduced within 0.15% of GRI-Mech 3.0 values, confirming thermodynamic consistency of the mechanism. Laminar flame speed predictions deviate significantly from GRI-Mech 3.0, which is attributed to the absence of HO₂ chemistry in the reduced mechanism; this limitation does not affect RDRE simulation fidelity since laminar flame propagation is of secondary importance in RDREs.
The present invention is directed to methods of preparing metal sulfide, metal selenide, or metal sulfide/selenide nanoparticles and the products derived therefrom. In various embodiments, the nanoparticles are derived from the reaction between precursor metal salts and certain sulfur- and/or selenium-containing precursors each independently having a structure of Formula (I), (II), or (III), or an isomer, salt, or tautomer thereof, where Q1, Q2, Q3, R1, R2, R3, R5, and X are defined within the specification.
The present disclosure relates to a composition that includes a first repeat unit defined by where R includes a first hydrocarbon chain that includes at least one olefinic bond, R5 includes a second hydrocarbon chain, the second hydrocarbon chain may be saturated, and n may be between 2 and 1,000.
Described herein are bacteriochlorins comprising an annulated isocyclic ring such as a compound Formula I: or a metal conjugate thereof, wherein: R1, R2, R3, R4, R5, R6, R7, R8, R9, R10, R11, R12, R13, R14, R15, R16, and Z are each as defined herein. Also described are methods and intermediates for the synthesis of bacteriochlorins comprising an annulated isocyclic ring, and methods of using such bacteriochlorins for, among other things, diagnostic and therapeutic purposes such as, e.g., luminescent compounds in flow cytometry, and/or as active agents in photodynamic therapy (PDT).
The present disclosure relates to a composition that includes a repeat unit defined by where each of R1, R2, R3, R4, R5, R6, R7, and R8 includes at least one of a hydrogen atom, a fluorine atom, and/or a first hydrocarbon chain having between 1 and 20 carbon atoms, inclusively, where each of A1, A2, A3 and A4 are either a carbon atom or a nitrogen atom, when A1 is a nitrogen atom, A2 is a carbon atom, when A2 is a nitrogen atom, A1 is a carbon atom, when A3 is a nitrogen atom, A4 is a carbon atom, when A4 is a nitrogen atom, A3 is a carbon atom, either A1 or A2 form a covalent bond, x, with a carbon atom, a, either A3 or A4 form a covalent bond, y, with a carbon atom, b, L is a linker group that includes an aromatic ring, and n is between 1 and 20, inclusively.
A method for extracting rare earth metals (e.g., lanthanides and/or actinides) from aqueous solution, the method comprising: (i) acidifying an aqueous solution containing said rare earth metals with sulfuric acid to result in an acidified aqueous solution containing 1-12 M concentration of sulfuric acid; and (ii) contacting the acidified aqueous solution with an aqueous-insoluble hydrophobic solution comprising a rare earth extractant molecule dissolved in an aqueous-insoluble hydrophobic solvent to result in extraction of one or more of the rare earth metals into the aqueous hydrophobic solution, wherein the rare earth extractant molecule has the following structure: wherein R1, R2, R3, and R4 are independently selected from hydrocarbon groups containing 1-20 carbon atoms, provided that the total carbon atoms in R1, R2, R3, and R4 is at least 12; and R5 and R6 are independently selected from hydrogen atom and hydrocarbon groups containing 1-3 carbon atoms.
The present disclosure relates to a composition that includes a first repeat unit defined by where R includes a first hydrocarbon chain that includes at least one olefinic bond, R5 includes a second hydrocarbon chain, the second hydrocarbon chain may be saturated, and n may be between 2 and 1,000.