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Article Citation - WoS: 6Citation - Scopus: 6Optimized Porous Carbon Particles From Sucrose and Their Polyethyleneimine Modifications for Enhanced Co2 Capture(Mdpi, 2024) Ari, Betul; Inger, Erk; Sunol, Aydin K.; Sahiner, NurettinCarbon dioxide (CO2), one of the primary greenhouse gases, plays a key role in global warming and is one of the culprits in the climate change crisis. Therefore, the use of appropriate CO2 capture and storage technologies is of significant importance for the future of planet Earth due to atmospheric, climate, and environmental concerns. A cleaner and more sustainable approach to CO2 capture and storage using porous materials, membranes, and amine-based sorbents could offer excellent possibilities. Here, sucrose-derived porous carbon particles (PCPs) were synthesized as adsorbents for CO2 capture. Next, these PCPs were modified with branched- and linear-polyethyleneimine (B-PEI and L-PEI) as B-PEI-PCP and L-PEI-PCP, respectively. These PCPs and their PEI-modified forms were then used to prepare metal nanoparticles such as Co, Cu, and Ni in situ as M@PCP and M@L/B-PEI-PCP (M: Ni, Co, and Cu). The presence of PEI on the PCP surface enables new amine functional groups, known for high CO2 capture ability. The presence of metal nanoparticles in the structure may be used as a catalyst to convert the captured CO2 into useful products, e.g., fuels or other chemical compounds, at high temperatures. It was found that B-PEI-PCP has a larger surface area and higher CO2 capture capacity with a surface area of 32.84 m(2)/g and a CO2 capture capacity of 1.05 mmol CO2/g adsorbent compared to L-PEI-PCP. Amongst metal-nanoparticle-embedded PEI-PCPs (M@PEI-PCPs, M: Ni, Co, Cu), Ni@L-PEI-PCP was found to have higher CO2 capture capacity, 0.81 mmol CO2/g adsorbent, and a surface area of 225 m(2)/g. These data are significant as they will steer future studies for the conversion of captured CO2 into useful fuels/chemicals.Article Citation - WoS: 1Citation - Scopus: 1Mass Driver Design Traveling Earth to the Moon(Ieee-inst Electrical Electronics Engineers inc, 2019) Inger, Erk; Inger, ErkIn this article, the flight of a mass driver was designed for launch from the Earth with Electro Magnetic Space Launching System (EMSLS). Then the orbit exit from the Earth at 185 km and orbit entry the Moon at 100kmwere examined with respect to change of trajectories by using chemical fuel and the engine in the mass driver. Electromagnetically launched mass drivers should orbit with a specified orbital velocity at a designated altitude. In this paper, the energy is transferred externally to a mass driver throughout the flight path the electromagnetic coil system called multistage (EMSLS) designated in order to achieve the specified orbital velocity. The mass driver is synchronously accelerated by a voltage through the capacitors which are used for storing energy. This energy is transferred through a switching inductor to the circuit of the mass driver so that the mass driver is launched into the orbit with a muzzle velocity. However, this fact creates high air drag energy losses due to atmospheric conditions and high velocity obtained in EMSLS. Thus, in the mass driver at 21km altitude an engine starts to increase the velocity of the system to reach orbital velocity. The final aim of this article is to capture the transfer of $\Delta \text{v}$ cost for traveling to the Moon. At any given arrival time in order to guide the system, designers only consider the gravity of the Earth and gravity of the Moon by using a Direct Lunar Transfer Trajectory for the Earth to the Moon approach. Finally, EMSLS was evaluated as a more advantageous and complimentary alternative to chemical propulsion systems for space transportation.
