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Baiocco, P., and Ch Bonnal. "Technology demonstration for reusable launchers." Acta Astronautica 120 (March 2016): 43–58. http://dx.doi.org/10.1016/j.actaastro.2015.11.032.
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Lobanovsky, Yu I. "Efficiency analysis of reusable aerospace launchers." Aerospace Science and Technology 1, no. 1 (1997): 37–46. http://dx.doi.org/10.1016/s1270-9638(97)90022-5.
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Chelaru, Teodor-Viorel, Valentin Pană, and Costin Ene. "Performance Evaluation for Launcher Testing Vehicle." Aerospace 9, no. 9 (2022): 504. http://dx.doi.org/10.3390/aerospace9090504.
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The paper’s purpose is to present a calculus model for a testing vehicle that can be used to validate guidance, navigation and control systems for reusable launchers in all flight phases. The technical solution is based on a throttleable engine with thrust vectoring control and a reaction control system (RCS) used for roll. For calculus, we will develop a nonlinear model with six degrees of freedom, based on quaternion, extended with nonlinear equations that use pulse modulation in order to control roll. In order to synthesize the controller, we also develop a linear model similar to the launcher model. The paper analyzes two basic scenarios, first with the ascending and the descending flight phases and the second having a horizontal flight interleaved between ascending and descending flight phases, both scenarios being specific for reusable launchers. Based on these scenarios, the paper evaluates some performances of the proposed vehicle, namely flight envelope and guidance accuracy.
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Simplício, Pedro, Andrés Marcos, and Samir Bennani. "Guidance of Reusable Launchers: Improving Descent and Landing Performance." Journal of Guidance, Control, and Dynamics 42, no. 10 (2019): 2206–19. http://dx.doi.org/10.2514/1.g004155.
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D’Angelo, Salvatore, Edmondo Minisci, Daniele Di Bona, and Luciano Guerra. "Optimization Methodology for Ascent Trajectories of Lifting-Body Reusable Launchers." Journal of Spacecraft and Rockets 37, no. 6 (2000): 761–67. http://dx.doi.org/10.2514/2.3648.
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Musso, Girolamo, Iara Figueiras, Héléna Goubel, et al. "A Multidisciplinary Optimization Framework for Ecodesign of Reusable Microsatellite Launchers." Aerospace 11, no. 2 (2024): 126. http://dx.doi.org/10.3390/aerospace11020126.
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The commercial space launch sector is currently undergoing a significant shift, with increasing competition and demand for launch services, as well as growing concerns about the environmental impact of rocket launches. To address these challenges, within the New Space Portugal project scope, a multidisciplinary framework for designing and optimizing new launch vehicles is proposed. Creating a more resilient and responsible space industry can be achieved by combining technological innovation and environmental sustainability, as emphasized by the framework. The main scope of the framework was to couple all the disciplines relevant to the space vehicle design in a modular way. Significant emphasis was placed on the infusion of ecodesign principles, including Life Cycle Assessment (LCA) considerations. Optimization techniques were employed to enhance the design and help designers conduct trade-off studies. In general, this multidisciplinary framework aims to provide a comprehensive approach to designing next-generation launch vehicles that meet the demands of a rapidly changing market while also minimizing their environmental impact. A methodology that leverages the strengths of both genetic and gradient-based algorithms is employed for optimizations with the objectives of maximizing the apogee altitude and minimizing the Global Warming Potential (GWP). Despite only being tested at the moment for sounding rockets, the framework has demonstrated promising results. It has illuminated the potential of this approach, leading to the identification of three optimal designs: one for maximizing the apogee, another for minimizing GWP, and a compromise design that strikes a balance between the two objectives. The outcomes yielded a maximum apogee of 6.41 km, a minimum GWP of 9.06 kg CO2eq, and a balanced compromise design featuring an apogee of 5.75 km and a GWP of 25.64 kg CO2eq.
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Duparcq, J. L., E. Hermant, and D. Scherrer. "Turbojet-type engines for the airbreathing propulsion of reusable winged launchers." Acta Astronautica 29, no. 1 (1993): 41–50. http://dx.doi.org/10.1016/0094-5765(93)90068-8.
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Gulczyński, Mateusz T., Robson H. S. Hahn, Jan C. Deeken, and Michael Oschwald. "Turbopump Parametric Modelling and Reliability Assessment for Reusable Rocket Engine Applications." Aerospace 11, no. 10 (2024): 808. http://dx.doi.org/10.3390/aerospace11100808.
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The development of modern reusable launchers, such as the Themis project with its LOX/LCH4 Prometheus engine, CALLISTO—a reusable VTVL-launcher first-stage demonstrator with a LOX/LH2 RSR2 engine, and SpaceX’s Falcon 9 with its Merlin 1D engine, underscores the need for advanced control algorithms to ensure reliable engine operation. The multi-restart capability of these engines imposes additional requirements for throttling, necessitating an extended controller-validity domain to safely achieve low thrust levels across various operating regimes. This capability also increases the risk of component failure, especially as engine parameters evolve with mission profiles. To address this, our study evaluates the dynamic reliability of reusable rocket engines (RREs) and their subcomponents under different failure modes using multi-physics system-level modelling and simulation, with a particular focus on turbopump components. Transient condition modelling and performance analysis, conducted using EcosimPro-ESPSS software (version 6.4.34), revealed that turbopump components maintain high reliability under nominal conditions, with turbine blades demonstrating significant fatigue life even under varying thermal and mechanical loads. Additionally, the proposed predictive model estimates the remaining useful life of critical components, offering valuable insights for improving the longevity and reliability of turbopumps in reusable rocket engines. This study employs deterministic, thermally dependent structural simulations, with key control objectives including end-state tracking of combustion chamber pressure and mixture ratios and the verification of operational constraints, exemplified by the LUMEN demonstrator engine and the LE-5B-2 engine class.
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Simplício, Pedro, Andrés Marcos, and Samir Bennani. "Reusable Launchers: Development of a Coupled Flight Mechanics, Guidance, and Control Benchmark." Journal of Spacecraft and Rockets 57, no. 1 (2020): 74–89. http://dx.doi.org/10.2514/1.a34429.
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Bonnal, Ch, and M. Caporicci. "Future reusable launch vehicles in europe: the FLTP (Future Launchers Technologies Programme)." Acta Astronautica 47, no. 2-9 (2000): 113–18. http://dx.doi.org/10.1016/s0094-5765(00)00050-3.
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Pezzella, Giuseppe. "Preliminary Aerodynamic and Aerothermodynamic Assessment of the VTO Hopper Booster." ISRN Mechanical Engineering 2011 (May 4, 2011): 1–15. http://dx.doi.org/10.5402/2011/215785.
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Within the framework of the Future Launchers Preparatory Program, carried out by the European Space Agency, the VTO-Hopper reusable launcher is investigated. This concept is a winged sub orbital vehicle designed for vertical take-off with an expendable upper stage, able to deliver a payload up to 8 Mg in geostationary transfer orbit. After the staging, the reusable booster will re-enter the Earth's atmosphere, and then perform a downrange landing. In this paper the current design activities are described. The goal has been to define the preliminary booster aerodynamic and aerothermodynamic databases. Therefore, the aerothermal environment that the vehicle will encounter along its lifting reentry has been provided and analyzed. Different design approaches have been addressed. In fact, aerodynamic and aerothermodynamic analyses have been performed by using both engineering and numerical methods. For instance, a 3D Panel Methods code, typical for hypersonics, has been employed; the heat flux distributions have been evaluated by means of improved boundary layer methods. Increasing the order of complexity, a number of detailed 3D CFD analyses have been performed for different flight conditions along the descent trajectory. Results show that the aerodynamics and aerothermodynamics derived from engineering design approach are valid only for preliminary analysis purposes.
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Dumon, Jéromine, Yannick Bury, Nicolas Gourdain, and Laurent Michel. "Numerical and experimental investigations of buffet on a diamond airfoil designed for space launcher applications." International Journal of Numerical Methods for Heat & Fluid Flow 30, no. 9 (2019): 4203–18. http://dx.doi.org/10.1108/hff-07-2018-0353.
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Purpose The development of reusable space launchers requires a comprehensive knowledge of transonic flow effects on the launcher structure, such as buffet. Indeed, the mechanical integrity of the launcher can be compromised by shock wave/boundary layer interactions, that induce lateral forces responsible for plunging and pitching moments. Design/methodology/approach This paper aims to report numerical and experimental investigations on the aerodynamic and aeroelastic behavior of a diamond airfoil, designed for microsatellite-dedicated launchers, with a particular interest for the fluid/structure interaction during buffeting. Experimental investigations based on Schlieren visualizations are conducted in a transonic wind tunnel and are then compared with numerical predictions based on unsteady Reynolds averaged Navier–Stokes and large eddy simulation (LES) approaches. The effect of buffeting on the structure is finally studied by solving the equation of the dynamics. Findings Buffeting is both experimentally and numerically revealed. Experiments highlight 3D oscillations of the shock wave in the manner of a wind-flapping flag. LES computations identify a lambda-shaped shock wave foot width oscillations, which noticeably impact aerodynamic loads. At last, the experiments highlight the chaotic behavior of the shock wave as it shifts from an oscillatory periodic to an erratic 3D flapping state. Fluid structure computations show that the aerodynamic response of the airfoil tends to damp the structural vibrations and to mitigate the effect of buffeting. Originality/value While buffeting has been extensively studied for classical supercritical profiles, this study focuses on diamond airfoils. Moreover, a fluid structure computation has been conducted to point out the effect of buffeting.
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De Oliveira, Alice, and Michèle Lavagna. "Coupling of Advanced Guidance and Robust Control for the Descent and Precise Landing of Reusable Launchers." Aerospace 11, no. 11 (2024): 914. http://dx.doi.org/10.3390/aerospace11110914.
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This paper investigates the coupling of successive convex optimization guidance with robust structured H∞ control for the descent and precise landing of Reusable Launch Vehicles (RLVs). More particularly, this Guidance and Control (G&C) system is foreseen to be integrated into a nonlinear six-degree-of-freedom RLV controlled dynamics simulator which covers the aerodynamic and powered descent phase until vertical landing of a first-stage rocket equipped with a thrust vector control system and steerable planar fins. A cost function strategy analysis is performed to find out the most efficient one to be implemented in closed-loop with the robust control system and the vehicle flight mechanics involved. In addition, the controller synthesis via structured H∞ is thoroughly described. The latter are built at different points of the descent trajectory using Proportional-Integral-Derivative (PID)-like structures with feedback on the attitude angles, rates, and lateral body velocities. The architecture is verified through linear analyses as well as nonlinear cases with the aforementioned simulator, and the G&C approach is validated by comparing the performance and robustness with a baseline system in nominal conditions as well as in the presence of perturbations. The overall results show that the proposed G&C system represents a relevant candidate for realistic descent flight and precise landing phase for reusable launchers.
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Ashford, D. M., and P. Q. Collins. "The prospects for European aerospace transporters - Part 1: The derivation of a first order parametric method for estimating the development cost of aerospace transporters." Aeronautical Journal 93, no. 921 (1989): 1–10. http://dx.doi.org/10.1017/s0001924000016638.
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SummaryManned spacecraft cost typically ten times as much to develop as advanced technology prototype aeroplanes of similar weight. For example, the Hermes spaceplane, which is designed to be launched into orbit by the expendable Ariane 5, has an estimated development cost of $4 billion, which is about ten times greater than the cost of the Experimental Aircraft Programme (EAP) demonstrator of the European Fighter Aircraft ($350 million). The Hermes spaceplane and the EAP are of comparable size and weight and both use very advanced technology. The EAP is already more mature than Hermes would become because, although the EAP is only a prototype, it has made more flights than are planned for Hermes over its entire operational career.This part of the paper attempts to identify the factors which explain this difference in cost and then to determine which of them would apply to fully reusable, piloted, aeroplane-like launchers, i.e. aerospace transporters.
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Singh, Sunayna, Martin Sippel, and Sven Stappert. "Full-scale simulations of ‘In-Air Capturing’ return mode for winged reusable launch vehicles." Journal of Physics: Conference Series 2526, no. 1 (2023): 012114. http://dx.doi.org/10.1088/1742-6596/2526/1/012114.
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Abstract The recent success of reusable launchers has become a driving force for sustainable launch technologies. An innovative approach proposed by DLR, involves winged rocket stages captured mid air and towed back to the launch site by an aircraft. This recovery concept known as ‘In-Air Capturing (IAC)’, shows potential for substantial cost reduction, when compared to existing return modes. In the light of the Horizon 2020 project FALCon, full-scale simulations and sub-scale flight testing were carried out for further development of the technology. The paper summarizes the full-scale studies performed within FALCon. The full-scale test cases are introduced and the simulation framework for analysis of trajectories is presented. Then, the IAC maneuver is analyzed through trajectory simulations. Major external disturbances coming from the wake of the aircraft and flexibility of the rope connecting the rocket stage to the aircraft (after capture) are also addressed.
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Piacquadio, Stefano, Dominik Pridöhl, Nils Henkel, et al. "Comprehensive Comparison of Different Integrated Thermal Protection Systems with Ablative Materials for Load-Bearing Components of Reusable Launch Vehicles." Aerospace 10, no. 3 (2023): 319. http://dx.doi.org/10.3390/aerospace10030319.
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Economic viability of small launch vehicles, i.e., microlaunchers, is impaired by several factors, one of which is a higher dry to wet mass ratio as compared to conventional size launchers. Although reusability may reduce launch cost, it can drive dry and/or wet mass to unfeasibly high levels. In particular, for load-bearing components that are exposed to convective heating during the aerothermodynamic phase of the re-entry, the mass increase due to the presence of a thermal protection system (TPS) must be considered. Examples of such components are aerodynamic drag devices (ADDs), which are extended during the re-entry. These should withstand high mechanical loading, be thermally protected to avoid failure, and be reusable. Ablative materials can offer lightweight thermal protection, but they represent an add-on mass for the structure and they are rarely reusable. Similarly, TPS based on ceramic matrix composite (CMC) tiles represent an additional mass. To tackle this issue, so-called integrated thermal protection systems (ITPS) composed of CMC sandwich structures were introduced in the literature. The aim is to obtain a load-bearing structure that is at the same time the thermally protective layer. However, a comprehensive description of the real lightweight potential of such solutions compared to ablative materials with the corresponding sub-structures is, to the authors’ knowledge, not yet presented. Thus, based on the design of an ADD, this work aims to holistically describe such load bearing components and to compare different TPS solutions. Both thermal and preliminary mechanical designs are discussed. Additionally, a novel concept is proposed, which is based on the use of phase change materials (PCMs) embedded within a metallic sandwich structure with an additively manufactured lattice core. Such a solution can be beneficial due to the combination of both the high specific stiffness of lattice structures and the high mass-specific thermal energy storage potential of PCMs. The study is conducted with reference to the first stage of the microlauncher analysed within the European Horizon-2020 project named Recovery and Return To Base (RRTB).
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Shubov, Mikhail. "Electric Rocket Launcher Aircraft—Drone-Launched Short Range Rocket System." Aerospace 10, no. 6 (2023): 514. http://dx.doi.org/10.3390/aerospace10060514.
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This paper is concerned with the idea of a significant improvement of state-of-the-art short-range rockets by means of using rocket artillery systems. Such a system consists of a rocket launcher aircraft (RLA) and a drone-launched short range rocket (DLSRR). An RLA is a reusable first stage of a military rocket. A DLSRR is the expendable second stage, which flies to the target. RLA-DLSRR systems have not yet been built, but they have been described in previous works by the author. State-of-the-art rocket systems are completely expendable and, hence, extremely expensive. No rocket artillery system with a reusable first stage has been built so far. Civilian spaceships with reusable first stages have been successful since 2015. In an electrically pumped rocket engine, the fuel and oxidizer are pumped into a combustion chamber by an electric-motor-driven pump. The electric motor is powered by a battery bank. Electrically pumped rocket engines would further decrease the cost of RLA-DLSRR systems. These engines are less expensive and more reliable then conventional rocket engines. In the present paper, it is shown that commercially available lithium polymer battery banks, as well as high specific power electric motors, provide sufficient power for the rocket engines needed for RLA-DLSRR systems. In the example given, it is calculated that an ERLA–DLSRR system with a liftoff mass of 15 tons can deliver a 210 kg payload to a range of up to 567 km with an impact velocity of up to 2415 m/s.
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DUMONT, Etienne, Shinji ISHIMOTO, Pascal TATIOSSIAN, et al. "CALLISTO: A Demonstrator for Reusable Launcher Key Technologies." TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN 19, no. 1 (2021): 106–15. http://dx.doi.org/10.2322/tastj.19.106.
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Guadagnini, Jacopo, Michèle Lavagna, and Paulo Rosa. "Model predictive control for reusable space launcher guidance improvement." Acta Astronautica 193 (April 2022): 767–78. http://dx.doi.org/10.1016/j.actaastro.2021.10.014.
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Zhong, Ya, Danghui Liu, and Chen Wang. "Research Progress of Key Technologies for Typical Reusable Launcher Vehicles." IOP Conference Series: Materials Science and Engineering 449 (November 29, 2018): 012008. http://dx.doi.org/10.1088/1757-899x/449/1/012008.
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Bergström, Rasmus, Daniele Pilori, Miguel Pinheiro, et al. "Iterative design development of a reusable micro-launcher within the RRTB project." Journal of Physics: Conference Series 2526, no. 1 (2023): 012117. http://dx.doi.org/10.1088/1742-6596/2526/1/012117.
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Abstract The Recovery and Return-To-Base European Reusable Micro-Launcher project, part of the European Commission’s H2020 programme, intends to develop a novel reusable micro launcher system to bring independent and cost-effective access-to-space for the European small satellite market. The multi-disciplinary project focuses on the optimization of aerospike tail-first atmospheric re-entry of the MESO vehicle, together with the design and manufacturing of reusable cryogenic tanks, and the effort is divided into two design loops, where each design loop starts from establishing early design decisions and assumptions so that dedicated subsystem work may progress immediately. The multiple design loop approach allows for unsuitable design decisions, or risky and speculative assumptions to be revised or excluded at the project half-way point, thereby acting as a form of risk management. Throughout the work performed in the first design loop several conclusions were reached. The design presented both novel design features, but also critical issues which became better understood as the fidelity of the subsystem designs and mission analysis increased. These issues ultimately lead to the overall system design and CONOPS to be updated for the second loop, with several of the early design choices being modified, especially through the removal of the EDF landing system, based on the results of the first loop. For the second design loop, the design is updated to alleviate the most critical problem drivers, and to improve the system’s ability to fulfil the top-level requirements and objectives. The updated design uses a Mid-Air Catch approach, and leverages on the heritage of the previous design loop, implementing tailored changes based on the outcome of the trade-offs performed at mission and system levels.
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Trabandt, Ulrich, Burkhard Esser, Dietmar Koch, Ralf Knoche, and Giorgio Tumino. "Ceramic Matrix Composites Life Cycle Testing Under Reusable Launcher Environmental Conditions." International Journal of Applied Ceramic Technology 2, no. 2 (2005): 150–61. http://dx.doi.org/10.1111/j.1744-7402.2005.02017.x.
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Bizzarri, D., P. Hendrick, G. Heyen, and P. Ngendakumana. "Propulsion vehicle integration for reusable launcher using in-flight oxygen collection." Aerospace Science and Technology 12, no. 6 (2008): 429–35. http://dx.doi.org/10.1016/j.ast.2007.10.012.
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Trifa, Panagiotis, Dimitrios Rellakis, and Georgia Psoni. "Structural efficiency evaluation of innovative reusable launch vehicles." Journal of Physics: Conference Series 2526, no. 1 (2023): 012116. http://dx.doi.org/10.1088/1742-6596/2526/1/012116.
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Abstract This work is focused on evaluating the structural design of the innovative reusable micro launcher MESO, originated from the RRTB, a funded project by EU. The structural efficiency of MESO is evaluated in association with its mass budget, which is based on project’s early adopted requirements. In this particular design loop, the reusability concept is intergraded by implementing the fail-safe design approach, considering the exclusive use of high TRL aluminum alloys. The main objective of this work is achieved by developing a global Finite Element Model (FEM), comprising a set of sub-models, which represent the primary structure, the secondary structures, the equipment and their interfaces as well. The paper proceeds with the description of the modelling approach regarding mesh development and the connections created between the sub-models for assembling the integrated Global FEM of the launcher. The first iteration of the load analysis loop resulted in the extraction of the Design Limit Loads (DLL). The DLL investigated in both ground and flight cases, which comprise the most severe combination of quasi-static loads. The FEM is verified and subjected to various types of preliminary structural analysis, taking into consideration the required ECSS design and safety factors for static strength and stability assessment. The analyses results indicated the order of magnitude and the location of all weak areas of the launcher. Subsequently a preliminary sizing procedure is performed in order to prevent all failure modes according to the structural design requirements. The conclusions derived from the structural analysis of the first design loop influence the design modifications to be considered for the next design loop, where the same steps are going to be followed until the structural design requirements are satisfied once again.
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Putra, Dicky Ramadhan, and Yuliana Riana Prasetyawati. "Faktor-faktor yang Mempengaruhi Minat Beli Ulang Green Product Starbucks." Jurnal METRIS 22, no. 01 (2021): 49–56. http://dx.doi.org/10.25170/metris.v22i01.2664.
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The growth of coffee consumption in the community has a negative impact on the increase in the amount of plastic waste from coffee drinks. This condition is the focus of Starbuck's attention to produce green product reusable Color changing cups. Therefore, this study aims to determine the factors that influence buying interest in green product reusable color changing cups. The research method used is survey and the data analysis technique used is path analysis. Primary data was obtained through a questionnaire distributed to 80 respondents who are Instagram followers @starbucksindonesia who use reusable color changing cups at the Sahid Sudirman Center. The results showed that Green Product had a positive effect on repurchase intention through green advertising. This research also shows that the innovation of reusable color changing cups as a green product launched by Starbucks, was received positively and in accordance with the needs of people who have started to care about environmentally friendly products. Starbucks consumers will reuse reusable color changing cups as containers or glasses when purchasing drinks.
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Martinez Torio, A., J. M. Bahu, D. Delorme, V. Guenard, and H. Poussin. "Near range safety analysis for a reusable launcher concept based on toss-back." Journal of Space Safety Engineering 4, no. 1 (2017): 29–35. http://dx.doi.org/10.1016/j.jsse.2017.02.006.
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De Oliveira, Alice, and Michèle Lavagna. "Development of a Controlled Dynamics Simulator for Reusable Launcher Descent and Precise Landing." Aerospace 10, no. 12 (2023): 993. http://dx.doi.org/10.3390/aerospace10120993.
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This paper introduces a Reusable Launch Vehicle (RLV) descent dynamics simulator coupled with closed-loop guidance and control (G&C) integration. The studied vehicle’s first-stage booster, evolving in the terrestrial atmosphere, is steered by a Thrust Vector Control (TVC) system and planar fins through gain-scheduled Proportional–Integral–Derivative controllers, correcting the trajectory deviations until precise landing from the reference profile computed in real time by a successive convex optimisation algorithm. Environmental and aerodynamic models that reproduce realistic atmospheric conditions are integrated into the simulator for enhanced assessment. Comparative performance results were achieved in terms of control configuration (TVC-only, fins-only, and both) for nominal conditions as well as with external disturbances such as wind gusts or multiple uncertainties through a Monte Carlo analysis to assess the G&C system. These studies demonstrated that the configuration combining TVC and steerable planar fins has sufficient control authority to provide stable flight and adequate uncertainties and disturbance rejection. The developed simulator provides a preliminary assessment of G&C techniques for the RLV descent and landing phase, along with examining the interactions that occur. In particular, it paves the way towards the development and assessment of more advanced and robust algorithms.
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Relangi, Naresh, Lakshmi Narayana Phaneendra Peri, Caio Henrique Franco Levi Domingos, Amalia Fossella, Julia Meria Leite Henriques, and Antonella Ingenito. "Design of Supersonic and Hybrid engine based Advanced Rocket (SHAR)." IOP Conference Series: Materials Science and Engineering 1226, no. 1 (2022): 012031. http://dx.doi.org/10.1088/1757-899x/1226/1/012031.
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Abstract The paper deals with the design of a two-stage to orbit rocket launcher loaded with a solid rocket booster, scramjet, and hybrid rocket for delivering a 100kg payload in 200 km circular orbit. The possibility of implementing a cavity-based axisymmetric circular combustor in a scramjet is proposed. Computational analysis on various injector locations in a circular combustor and their validation with the test bench results were performed. The utilisation of a hybrid rocket in the final stage of the launcher to deliver the payload is discussed and the performance characteristics of the circular scramjet combustor and the hybrid rocket are shown. The overall mission proposed based on the sustainable and reusable characteristics.
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Okuda, Haruyuki. "Observations of Diffuse Infrared Radiation by a Small Cryogenical Telescope, IRTS." Symposium - International Astronomical Union 139 (1990): 435–39. http://dx.doi.org/10.1017/s0074180900241235.
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A small, cryogenically cooled infrared telescope named IRTS (Infrared Telescope in Space) is under development. The telescope is equipped with spectrometers and a photometer with medium spatial and spectral resolution covering the wavelength range from 1 to 1000 μm. The instrument is specially designed for observations of the cosmic background radiation and galactic infrared radiation. It will be flown on board a Japanese reusable free-flyer called SFU (space flyer unit) to be launched in 1994.
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Dreus, A. U., V. V. Yemets, M. M. Dron, V. P. Malaychuk, and L. G. Dubovik. "PREREQUISITES FOR CREATING ULTRA-LIGHT LAUNCH VEHICLES WITH POLYMER BODIES." System design and analysis of aerospace technique characteristics 32, no. 1 (2023): 25–40. http://dx.doi.org/10.15421/472303.
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The relevance of the problem of creating new light and ultra-light launch vehicles from the point of view of the development of the modern space industry is shown. First of all, this problem is related to the expansion of the market and the scope of use of small satellites, most of which are now launched into orbit as passing load by medium and heavy launch vehicles, which is not at all prompt and too expensive. The estimated forecast of the small satellite launch market, which is presented herein, indicates a growing demand for their launch services. A low-cost launch vehicle for the launch of small satellites would greatly expand their use, development, and production. This indicates the need for creation of special-purpose cheap transport vehicles for the operative decision of tasks of launching such satellites into orbit. It is shown that the main directions for increasing the efficiency and reducing the cost of launches are reducing the cost of making a transport space system, increasing of mass the payload, increasing the multiplicity of reusable uses, and reducing one-time costs per start. World trends in solving this problem are connected with the solution problem of creating ultra-light launch vehicles. The historical review of studies on prototype rockets that use the principle of reducing the mass of a launch vehicle during flight by burning spent structural elements indicates the possibility of creating launch vehicles on this principle by using complex hydrocarbon polymers as structural materials. It is shown that polymer materials, in particular polyethylene, can become the main material for the manufacture of fuel tanks for solid rockets, which use the new principle of burning the design during flight. The use of fuel tanks as fuel will give a possibility to reduce the cost of the propulsion system, which is one of the most expensive parts of the launch vehicle. The development of such launch vehicles and the commercialization of scientific research will allow domestic aerospace companies to occupy a niche in the market of small satellite launches.
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Das, Anup Kumar. "A brief overview of recently launched digital libraries of India." Library Hi Tech News 39, no. 2 (2022): 18–20. http://dx.doi.org/10.1108/lhtn-11-2021-0085.
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Purpose This paper evaluates the different digital libraries (DLs) in India developed in the past two decades. These DLs help advance scholarship and facilitate the reading habits of their users. Many of these DLs have a rich collection of vernacular literature depicting India’s diverse cultural heritages and traditions. DLs in India also help in outreaching global researchers and knowledge seekers. Many diaspora communities use these DLs frequently and other stakeholders such as the international scholars interested in Indic civilization. This paper finally suggests a way forward to make operational DL initiatives discoverable to humans and machines with the adaptation of FAIR principles that make e-resources findable, accessible, interoperable and reusable for their discovery beyond respective DL portals. Design/methodology/approach This study used a desk survey of DL initiatives in India. Their salient features are obtained from their respective Web portals and social media profiles. Findings This study identified twelve operational DL initiatives in India. Out of them, the newest five DL initiatives are described in this paper. Originality/value This study reflects original findings on the newest five DL initiatives of India. These findings were not earlier reported in a journal article.
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Berry, W., and H. Grallert. "Performance and technical feasibility comparison of reusable launch systems: A synthesis of the ESA winged launcher studies." Acta Astronautica 38, no. 4-8 (1996): 333–47. http://dx.doi.org/10.1016/0094-5765(96)00049-5.
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Murata, Renato, Julien Marzat, Hélène Piet-Lahanier, Sandra Boujnah, and Pierre Belleoud. "Residual Selection for Observer-Based Fault Detection and Isolation in a Multi-Engine Propulsion Cluster." PHM Society European Conference 8, no. 1 (2024): 9. http://dx.doi.org/10.36001/phme.2024.v8i1.4056.
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For complex systems, the number of residual candidates generated by Structural Analysis could be in the order of tens of thousands, and implementing all candidates is infeasible. This paper addresses the residual generator candidate selection problem from a state-observer perspective. First, the most suitable candidates to derive state-observers are selected based on two criteria related to the state-space form and a low number of equations. Then, a novel algorithm finds the minimal subset of residual generator candidates capable of detecting and isolating all faults. A procedure is introduced to compare the fault sensitivity of the selected candidates. This residual selection method is applied to the multi-engine propulsion cluster of a reusable launcher to illustrate its benefits.
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Karukayil, Johan, and Henry Love. "Optimal Leg Height of Landing Legs to Reduce Risk of Damage from Regolith Ejecta by Retrorocket Exhausts." Hyperscience International Journals 3, no. 3 (2023): 17–23. http://dx.doi.org/10.55672/hij2023pp17-23.
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Over the past decade, there has been a rapid increase in rocket launches. 2022 was a record-breaking year for the aerospace industry, with 180 successful rocket launches into orbit, 44 more than the previous year. Reducing as many risks as possible is essential as interplanetary rocket launches and reusable booster landings become more frequent. One such risk occurs when a rocket/booster lands. During the landing process, the retrorockets spray debris from the loose ground, which may damage the rocket/landing module. Retrorockets are rocket engines that provide a thrust opposing the spacecraft’s motion, causing it to decelerate. This paper studies the effect of landing leg height on ejecta velocity, the volume of debris ejected, and ground surface temperature change. Four landing leg heights were tested with an Estes® E-16 consumer model rocket motor: 0 mm, 50 mm, 75 mm, and 100 mm. The experiment suggests that the optimal height above the ground’s surface for a simulated landing module based on the volume and velocity of the ejecta is 50 mm. Landing legs that elevate a model rocket this height create an average crater volume of 610.5 mL and a max crater diameter of 10.34 cm. After determining the optimal height, a landing leg system was developed. This system was attached to an Aerodactyl TS® model rocket and utilized landing legs that elevated the rocket to a height of 50 mm above the ground at landing.
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Murata, Renato, Louis Thioulouse, Julien Marzat, Helene Piet-Lahanier, Marco Galeotta, and Rancois Farago. "Diagnosis and Fault-Tolerant Control for a Multi-Engine Cluster of a Reusable Launcher with Sensor and Actuator Faults." PHM Society European Conference 7, no. 1 (2022): 583–85. http://dx.doi.org/10.36001/phme.2022.v7i1.3296.
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A possible way to increase the reliability and availability of a system is to apply an Active Fault Tolerant Control (AFTC) algorithm. This thesis aims to use this algorithm in a multiengine propulsive cluster with sensor and actuator faults. First, a Health Monitoring System (HMS) will be developed to monitor the entire propulsive cluster. The HMS will use model-based fault diagnosis techniques. Then, in case of actuator faults, the cluster will be reconfigured to minimize its effects. The reconfiguration can be made by using control allocation or modifying the control law of the engine. A simulation model of the entire cluster is under development. The model simulates the whole system, including the propellant feeding system, engines, and mechanical system. It will be used to study the effect of different faults on the system and compare different reconfiguration strategies.
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Noble, Gordon, and Kenneth Brophy. "Ritual and remembrance at a prehistoric ceremonial complex in central Scotland: excavations at Forteviot, Perth and Kinross." Antiquity 85, no. 329 (2011): 787–804. http://dx.doi.org/10.1017/s0003598x00068319.
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Aerial photography and excavations have brought to notice a major prehistoric ceremonial complex in central Scotland comparable to Stonehenge, although largely built in earth and timber. Beginning, like Stonehenge, as a cremation cemetery, it launched its monumentality by means of an immense circle of tree trunks, and developed it with smaller circles of posts and an earth bank (henge). A change of political mood in the Early Bronze Age is marked by one of Scotland's best preserved dagger-burials in a stone cist with an engraved lid. The perishable (or reusable) materials meant that this great centre lay for millennia under ploughed fields, until it was adopted, by design or by chance, as a centre of the Pictish kings.
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Sullivan, Sheila. "Are Bioplastics a Sustainable Alternative to Single-Use Plastic? A Pilot Project at the University of South Florida." SustainE 1, no. 1 (2023): 53–61. http://dx.doi.org/10.55366/suse.v1i1.4.
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Campaigns to ban single-use plastics have spread globally, increasing awareness about plastic pollution and driving consumer demand for bioplastics alternatives. Consumer perception is that plastics derived from plants are compostable. Biodegradable and compostable products are not the same. Arguably, everything will eventually biodegrade. Compostable, however, signifies that the product will decompose into the soil within a timeframe. A University of South Florida (USF) pilot research study has launched investigating the efficacy of single-use bioplastics in a home compost environment. The results will provide consumers with green product recommendations, call attention to the interdependence between bioplastics and Industrial Composting Facilities, and encourage behavior supportive of sustainable, reusable alternatives aligned with the SDG’s.
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Cai, Jiajing, Zhenxuan Liu, Zihang Su, and Gang Wang. "SpaceX's Network Effects and Innovation Strategy Analysis." Highlights in Business, Economics and Management 30 (April 10, 2024): 234–38. http://dx.doi.org/10.54097/yhe5sj83.
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The core competitiveness of an enterprise refers to the unique capabilities and resources of an enterprise that stand out in the market and surpass its competitors. This competitiveness is a key factor for the long-term survival and development of enterprises. Business leaders need to carefully analyze and develop the company's core competencies to ensure that the company has a lasting competitive advantage in the market. This paper deeply discusses the core competitiveness of Space X, including product innovation, competitors and differentiated competition, business space, innovation strategy, network effect, and positive feedback loop. The SWOT analysis of SpaceX reveals its strengths in brand reach and technological innovation but also highlights some challenges, such as the lack of products for everyday users. The company's innovative strategies, including reusable rocket launches and Starlink satellite networks, make it a leader in the private space industry. SpaceX The vision for the future transcends commercial space activities to explore and colonize multiple planets, demonstrating its commitment to a sustainable space civilization.
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Bayarri, Genís, Pau Andrio, Josep Lluís Gelpí, Adam Hospital, and Modesto Orozco. "Using interactive Jupyter Notebooks and BioConda for FAIR and reproducible biomolecular simulation workflows." PLOS Computational Biology 20, no. 6 (2024): e1012173. http://dx.doi.org/10.1371/journal.pcbi.1012173.
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Interactive Jupyter Notebooks in combination with Conda environments can be used to generate FAIR (Findable, Accessible, Interoperable and Reusable/Reproducible) biomolecular simulation workflows. The interactive programming code accompanied by documentation and the possibility to inspect intermediate results with versatile graphical charts and data visualization is very helpful, especially in iterative processes, where parameters might be adjusted to a particular system of interest. This work presents a collection of FAIR notebooks covering various areas of the biomolecular simulation field, such as molecular dynamics (MD), protein–ligand docking, molecular checking/modeling, molecular interactions, and free energy perturbations. Workflows can be launched with myBinder or easily installed in a local system. The collection of notebooks aims to provide a compilation of demonstration workflows, and it is continuously updated and expanded with examples using new methodologies and tools.
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Gao, Huayu, Zheng Wei, Xiang Zhang, et al. "Optimum Design of a Reusable Spacecraft Launch System Using Electromagnetic Energy: An Artificial Intelligence GSO Algorithm." Energies 16, no. 23 (2023): 7717. http://dx.doi.org/10.3390/en16237717.
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Due to its advantages of high acceleration, reusability, environmental protection, safety, energy conservation, and efficiency, electromagnetic energy has been considered as an inevitable choice for future space launch technology. This paper proposes a novel three-level orbital launch approach based on a combination of a traditional two-level orbital launch method and an electromagnetic boost (EMB), in which the traditional two-level orbital launch consists of a turbine-based combined cycle (TBCC) and a reusable rocket (RR). Firstly, a mathematical model of a multi-stage coil electromagnetic boost system is established to develop the proposed three-level EMB-TBCC-RR orbital launch approach, achieving a horizontal take-off–horizontal landing (HTHL) reusable launch. In order to optimize the fuel quality of the energy system, an artificial intelligence algorithm parameters-sensitivity-based adaptive quantum-inspired glowworm swarm optimization (AQGSO)is proposed to improve the performance of the electromagnetic boosting system. Simulation results show that the proposed AQGSO improves the global optimization precision and convergence speed. By using the proposed EMB-TBCC-RR orbital launch system and the optimization approach, the required fuel weight was reduced by about 13 tons for the same launch mission, and the energy efficiency and reusability of the spacecraft was greatly improved. The spacecraft can be launched with more cargo capacity and increased payload. The proposed novel three-level orbital launch approach can help engineers to design and optimize the orbital launch system in the field of electromagnetic energy conversion and management.
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Holt, Marilyn E., Kathleen F. Mittendorf, Michele LeNoue-Newton, et al. "My Cancer Genome: Coevolution of Precision Oncology and a Molecular Oncology Knowledgebase." JCO Clinical Cancer Informatics, no. 5 (September 2021): 995–1004. http://dx.doi.org/10.1200/cci.21.00084.
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PURPOSE The My Cancer Genome (MCG) knowledgebase and resulting website were launched in 2011 with the purpose of guiding clinicians in the application of genomic testing results for treatment of patients with cancer. Both knowledgebase and website were originally developed using a wiki-style approach that relied on manual evidence curation and synthesis of that evidence into cancer-related biomarker, disease, and pathway pages on the website that summarized the literature for a clinical audience. This approach required significant time investment for each page, which limited website scalability as the field advanced. To address this challenge, we designed and used an assertion-based data model that allows the knowledgebase and website to expand with the field of precision oncology. METHODS Assertions, or computationally accessible cause and effect statements, are both manually curated from primary sources and imported from external databases and stored in a knowledge management system. To generate pages for the MCG website, reusable templates transform assertions into reconfigurable text and visualizations that form the building blocks for automatically updating disease, biomarker, drug, and clinical trial pages. RESULTS Combining text and graph templates with assertions in our knowledgebase allows generation of web pages that automatically update with our knowledgebase. Automated page generation empowers rapid scaling of the website as assertions with new biomarkers and drugs are added to the knowledgebase. This process has generated more than 9,100 clinical trial pages, 18,100 gene and alteration pages, 900 disease pages, and 2,700 drug pages to date. CONCLUSION Leveraging both computational and manual curation processes in combination with reusable templates empowers automation and scalability for both the MCG knowledgebase and MCG website.
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Sustkova, Hana Pergl, Kristina Maria Hettne, Peter Wittenburg, et al. "FAIR Convergence Matrix: Optimizing the Reuse of Existing FAIR-Related Resources." Data Intelligence 2, no. 1-2 (2020): 158–70. http://dx.doi.org/10.1162/dint_a_00038.
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The FAIR principles articulate the behaviors expected from digital artifacts that are Findable, Accessible, Interoperable and Reusable by machines and by people. Although by now widely accepted, the FAIR Principles by design do not explicitly consider actual implementation choices enabling FAIR behaviors. As different communities have their own, often well-established implementation preferences and priorities for data reuse, coordinating a broadly accepted, widely used FAIR implementation approach remains a global challenge. In an effort to accelerate broad community convergence on FAIR implementation options, the GO FAIR community has launched the development of the FAIR Convergence Matrix. The Matrix is a platform that compiles for any community of practice, an inventory of their self-declared FAIR implementation choices and challenges. The Convergence Matrix is itself a FAIR resource, openly available, and encourages voluntary participation by any self-identified community of practice (not only the GO FAIR Implementation Networks). Based on patterns of use and reuse of existing resources, the Convergence Matrix supports the transparent derivation of strategies that optimally coordinate convergence on standards and technologies in the emerging Internet of FAIR Data and Services.
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Jozič, Zidanšek, and Repnik. "Fuel Conservation for Launch Vehicles: Falcon Heavy Case Study." Energies 13, no. 3 (2020): 660. http://dx.doi.org/10.3390/en13030660.
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Space exploration has recently been growing at an increasing pace and has caused a significant burden to the environment, in particular, during the launch of rockets, when a large amount of fuel is burned and the exhaust gases are released in the air. For this case study, we selected the SpaceX Falcon Heavy reusable heavy-lift launch vehicle, which is one of the most promising rockets for the low-cost lifting of heavy payloads into orbit and beyond. We evaluated several strategies for optimisation of fuel consumption and for minimisation of environmental impact during launch through the atmosphere for the case of its first launch on February 6, 2018, when the rocket carried a red Tesla Roadster with a “Starman” in the direction toward Mars. In addition to the flight plan and Newtonian equations of motion, we have taken into account the thermodynamic properties of the rocket engines. Results are similar but slightly different if one minimises the total fuel consumption for the desired flight plan or if one minimises the environmental pollution during the initial stage of the launch through the atmosphere. The same methodology can be extended for launches in other directions including the Earth orbit and the Moon.
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Delikoura, Eirini, and Dimitrios Kouis. "Open Research Data and Open Peer Review: Perceptions of a Medical and Health Sciences Community in Greece." Publications 9, no. 2 (2021): 14. http://dx.doi.org/10.3390/publications9020014.
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Recently significant initiatives have been launched for the dissemination of Open Access as part of the Open Science movement. Nevertheless, two other major pillars of Open Science such as Open Research Data (ORD) and Open Peer Review (OPR) are still in an early stage of development among the communities of researchers and stakeholders. The present study sought to unveil the perceptions of a medical and health sciences community about these issues. Through the investigation of researchers‘ attitudes, valuable conclusions can be drawn, especially in the field of medicine and health sciences, where an explosive growth of scientific publishing exists. A quantitative survey was conducted based on a structured questionnaire, with 179 valid responses. The participants in the survey agreed with the Open Peer Review principles. However, they ignored basic terms like FAIR (Findable, Accessible, Interoperable, and Reusable) and appeared incentivized to permit the exploitation of their data. Regarding Open Peer Review (OPR), participants expressed their agreement, implying their support for a trustworthy evaluation system. Conclusively, researchers need to receive proper training for both Open Research Data principles and Open Peer Review processes which combined with a reformed evaluation system will enable them to take full advantage of the opportunities that arise from the new scholarly publishing and communication landscape.
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dos Remedios, Nick, Marie-Elise Lecoq, David Martin, and Sophia Ratcliffe. "The Living Atlases community in action: the NBN Atlas Spatial Portal and “Explore Your Region” module." Biodiversity Information Science and Standards 2 (May 21, 2018): e25486. http://dx.doi.org/10.3897/biss.2.25486.
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Atlas of Living Australia (ALA) (https://www.ala.org.au/) is the Global Biodiversity Information Facility (GBIF) node of Australia. Since 2010, they have developed and improved a platform for sharing and exploring biodiversity information. All the modules are publicly available for reuse and customization on their GitHub account (https://github.com/AtlasOfLivingAustralia). The National Biodiversity Network, a registered charity, is the UK GBIF node and has been sharing biodiversity data since 2000. They published more than 79 million occurrences from 818 datasets. In 2016, they launched the NBN Atlas Scotland (https://scotland.nbnatlas.org/) based on the Atlas of Living Australia infrastructure. Since then, they released the NBN Atlas (https://nbnatlas.org/), the NBN Atlas Wales (https://wales.nbnatlas.org/) and soon the NBN Atlas Isle of Man. In addition to the occurrence/species search engine and the metadata registry, they put in place several tools that help users to work with data published in the network: the spatial portal and "explore your region" module. Both elements are based on Atlas of Living Australia developments. Because the Atlas of Living Australia platform is really powerful an reusable, we want to show you these two applications used to make geographical analyses. In order to perform this, we will present you the specificities of each component by giving examples of some functionalities.
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Nazarova, Yulia A., and Vladimir A. Tikhonov. "Comparative analysis of the economic feasibility of using ultra-small spacecrafts." RUDN Journal of Engineering Researches 22, no. 1 (2021): 43–53. http://dx.doi.org/10.22363/2312-8143-2021-22-1-43-53.
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The relevance of the issue under consideration is associated with the evolution of existing technologies, due to which the functionality increases and the mass of the payload decreases, as a result of which the question of the use of cost-effective launch vehicles is raised. The purpose of this work is to carry out a comparative analysis of the feasibility of using ultra-light launch vehicles to provide services for the delivery of small spacecraft to low-earth orbit. The article is written within the framework of socio-economic research methods. Retrospective analysis and comparative approach are combined with the use of quantitative methods. The theoretical significance of the study consists in the analysis of the modern operation of small spacecraft and the state of the world rocket and space industry, analysis of the existing strategy of the State Corporation Roscosmos in the development of a new line of reusable launch vehicles and consideration of promising projects of domestic private companies involved in the creation of ultra-light launch vehicles. The practical significance lies in the possibility of using the results of studying the intensity of space launches when making strategic decisions on the use of ultra-light launch vehicles. Based on the assessment of existing forecasts for the development and creation of small-sized spacecraft, it is concluded that the world space market is interested in the types of satellites and classes of launch vehicles for their launch.
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Bénichou, Laurence, Marcus Guidoti, Isabelle Gérard, Donat Agosti, Tony Robillard, and Fabio Cianferoni. "European Journal of Taxonomy: a deeper look into a decade of data." European Journal of Taxonomy 782 (December 17, 2021): 173–96. http://dx.doi.org/10.5852/ejt.2021.782.1597.
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The European Journal of Taxonomy (EJT) is a decade-old journal dedicated to the taxonomy of living and fossil eukaryotes. Launched in 2011, the EJT published exactly 900 articles (31 778 pages) from 2011 to 2021. The journal has been processed in its entirety by Plazi, liberating the data therein, depositing it into TreatmentBank, Biodiversity Literature Repository and disseminating it to partners, including the Global Biodiversity Information Facility (GBIF) using a combination of a highly automated workflow, quality control tools, and human curation. The dissemination of original research along with the ability to use and reuse data as freely as possible is the key to innovation, opening the corpus of known published biodiversity knowledge, and furthering advances in science. This paper aims to discuss the advantages and limitations of retro-conversion and to showcase the potential analyses of the data published in EJT and made findable, accessible, interoperable and reusable (FAIR) by Plazi. Among others, taxonomic and geographic coverage, geographical distribution of authors, citation of previous works and treatments, timespan between the publication and treatments with their cited works are discussed. Manually counted data were compared with the automated process, the latter being analysed and discussed. Creating FAIR data from a publication results in an average multiplication factor of 166 for additional access through the taxonomic treatments, figures and material citations citing the original publication in TreatmentBank, the Biodiversity Literature Repository and the Global Biodiversity Information Facility. Despite the advances in processing, liberating data remains cumbersome and has its limitations which lead us to conclude that the future of scientific publishing involves semantically enhanced publications.
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Reddy, D. Yamini, K. Hari Hruthvik, M. Harsha Vardhan Reddy, and Dr Vyomal Naishadhkumar Pandya. "Simulating an LTE Network Using OMNeT++." International Journal for Research in Applied Science and Engineering Technology 10, no. 3 (2022): 219–34. http://dx.doi.org/10.22214/ijraset.2022.40528.
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Abstract: Long Term Evolution emerged from the previous 3GPP system known as the Universal Mobile Telecommunication System. This technology is an entire IP-based network that provides an IP-based mobile content called the Evolved Packet Core. The main goals of LTE are to increase data rates, provide lower latency on the Radio Access Network, improve bandwidth and optimal performance. The LTE architecture combines a new basic channel called eNodeB with a single core called the Evolved Packet Core that provides access to both voice and IP data resources. Long Term Evolution (LTE) talks about a promising new invention that gives broadband internet access to the universe. Therefore, many test groups are trying to simplify their show. Shockingly, from now on, apparently, there are no open source simulation systems, which can be used to emulate high-density user platforms like India, which are unrestricted. Lack of a standard reference system for use by assessment students and researchers is a loss. To overcome this, we came up with a project that not only imitates LTE but can also be used to replicate any OFDM package programs such as LTE pro advanced, and was launched to provide a comprehensive presentation of the LTE environment. Our simulation project has been contemplated to reproduce uplink and downlink editing methods in multi-cell / multi-user environments, considering customer portability, radio asset development, reusable strategies, flexible balance and coding module, and various ideas that work best for aspiring students. researchers. Using simulation software and framework,After researching many simulation software we concluded that OMNet ++ would be the best suit for our project. We have used the Inet 4.3 framework in the required modules.
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Chudoba, B., G. Coleman, X. Huang, and P. A. Czysz. "Conceptual design assessment of a suborbital tourist space access vehicle." Aeronautical Journal 112, no. 1135 (2008): 523–35. http://dx.doi.org/10.1017/s0001924000002487.
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Abstract Space transportation remains in the pioneering stages. What might this century bring if we had a ‘railroad to space’ that embodied the characteristics of the transcontinental undertaking? The X-33 and Venture Star projects were one attempt to achieve the characteristics of that transcontinental railroad. There are others, here and in other countries, but perhaps we need to begin with a smaller first step, a small, commercial reusable rocket with ballistic ascent to space altitude with a hypersonic glider return? Our challenge in space today is to develop vehicles that are in continuous use, maintained and operated on a fixed schedule despite weather or environmental hazards, which move payloads not only into space but back again. The X PRIZE was a $10 million prize awarded to Scaled Composites as the first privately financed spaceship that launched the equivalent of three persons to an altitude of at least 100 kilometers on two consecutive flights within two weeks. What about an analogous vehicle that flies two or three times a week, every week for a number of years? A major difference is that this challenge is to be accomplished without government support or government developed vehicles. The aerospace vehicle design (AVD) Laboratory team at the University of Texas at Arlington is developing a generic space access vehicle (SAV) design synthesis environment with focus on the conceptual design phase. The AVD Lab has applied elements of this toolbox to the study of a tourist aerospace vehicle under a grant from Rocketplane Limited, Inc. The development of a low-cost tourist vehicle based on the adaptation of a Learjet 25/35/45 series aircraft is the focus of this paper.
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Ștefan, Elena Emilia. "The Deposit-Return System in the Current European Background." Athens Journal of Law 10, no. 3 (2024): 331–44. http://dx.doi.org/10.30958/ajl.10-3-5.
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Nowadays, given the background of the global climate change, the issue of responsible conduct towards society and nature, must concern us all. Current trends at European level are converging towards a growing legal awareness of the obligations we all have towards nature: public authorities, states, but also citizens. The situation of abandoned waste often leads public authorities to resort to public-private partnerships in order to offer possible solutions to protect the planet, preserve and improve the quality of the environment and mitigate man-made damage. The pretext of our paper is the introduction by the Romanian executive of the deposit-return system, as a legal novelty. It was adopted in October 2021 and launched on November 30, 2023. Therefore, the purpose of this study is to learn as much as possible about the implementation of this legal mechanism in our country, which aims to increase the collection and recycling of non-reusable primary packaging. In this regard, our analysis will investigate from an interdisciplinary perspective, on the one hand, the applicable legal framework and, on the other hand, will capture European trends regarding the deposit-return system. We believe that the topic is of general interest, which makes it important not only for public authorities but also for private individuals. Using scientific research methods specific to law, we will emphasize the conclusion of the paper, namely that it is our responsibility to protect the environment in which we live and to contribute to a better quality of life through community involvement, so that we have a cleaner environment. Keywords: deposit-return system; administrative acts; state responsibility; central public authority for environmental protection