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Journal articles on the topic 'Reusable Launchers'

Author: Grafiati

Published: 23 November 2024

Last updated: 31 July 2025

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1

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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2

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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3

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 launc

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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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6

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

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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 comp

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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 dat

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12

Tolasa, Diriba. "From Earth to Orbit: The Evolution of Launchers and Their Impact on Satellite Deployment." American Journal of Aerospace Engineering 10, no. 1 (2025): 11–23. https://doi.org/10.11648/j.ajae.20231001.12.

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The advancement of launch vehicles has been pivotal in shaping the landscape of space exploration and satellite deployment. This abstract examines the historical evolution of launchers, from early ballistic rockets to contemporary reusable systems, and their profound impact on the deployment and operational capabilities of satellites. The development of launch technology has paralleled the increasing complexity and functionality of satellites, enabling a diverse array of applications ranging from telecommunications and Earth observation to scientific research and interplanetary exploration. In

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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/structu

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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 efficien

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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 b

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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

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Prisăcariu, Emilia Georgiana. "NAVIGATING THE FUTURE: EUROPEAN SPACE PROPULSION INNOVATIONS AND MARKET DYNAMICS IN THE SMALL SATELLITE INDUSTRY." Aerospace Research in Bulgaria 37 (2025): 175–82. https://doi.org/10.3897/arb.v37.e17.

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The small satellite market is set for rapid growth, driven by the need for independent space access. While current options involve ridesharing, dedicated small satellite launchers offer customized access, with nanosatellites taking as little as 8 months from concept to launch. Europe invests significantly in space transportation R&D through programs like HORIZON SPACE, aiming to boost competitiveness and reduce reliance on external providers. ESA initiatives like FLPP and BOOST! focus on technological advancements and commercial services. Despite efforts, the USA dominates the space launch

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18

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 e

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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 sys

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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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22

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 deci

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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-

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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 us

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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 co

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KALYNYCHENKO, D. S., and T. A. MANKO. "ANALYSIS OF PERFORMANCE CHARACTERISTICS OF AEROSPACE SYSTEMS." Kosmìčna nauka ì tehnologìâ 30, no. 6 (2024): 15–19. https://doi.org/10.15407/knit2024.06.015.

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The paper discusses the solution to the crucial problem of analyzing the performance characteristics of an air-launched aerospace system (ASS) made in Ukraine as compared with similar foreign ASS. A feasibility study of the parameters of the air-launched aerospace system for the Ukrainian ASS, consisting of a reusable hypersonic unmanned aerial vehicle and an expendable launch vehicle, has been carried out. At the same time, two different types of air engines are used as part of a hypersonic unmanned aerial vehicle: a turbojet engine for takeoff from the runway and a ramjet engine for reaching

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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 c

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Guadagnini, Jacopo, Pietro Ghignoni, Fabio Spada, Gabriele De Zaiacomo, and Afonso Botelho. "End-to-End GNC Solution for Reusable Launch Vehicles." Aerospace 12, no. 4 (2025): 339. https://doi.org/10.3390/aerospace12040339.

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This paper presents an autonomous end-to-end guidance, navigation, and control (GNC) solution for a reusable launcher, addressing the challenges of precision pinpoint landing and reusability. The proposed GNC system integrates advanced onboard trajectory optimization and H∞ control to ensure robust performance across re-entry, aerodynamics, and landing phases. This work discusses the GNC design and definition and introduces the strategies adopted both for the guidance and the control design to handle rapidly varying dynamic environments and strict landing requirements. Particular attention is

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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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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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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 o

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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 oper

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Ishita Prakash and Niraj Pandey. "Strategies for Success in Aerospace: The Innovative and Disruptive Power of Reusable Rockets." COMMERCE RESEARCH REVIEW 2, no. 1 (2025): 44–56. https://doi.org/10.21844/crr.v2i01.1121.

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Rocket reusability will be a revolution in the aerospace industry, compelling new models of fabrication of launch vehiclesand outer-space exploration. This paper explores the transformative nature of reusable rocket technology as innovational,cost-cutting, and sustainable. A reusable rocket can be launched multiple times without necessitating the use of a differentrocket. The cost has come down to the kilogram when it goes into space. Companies like Space-X and Blue Origin havebrought this within the range carried by such rockets. Such research is also taken to a deeper level to look into the

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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

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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 si

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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 s

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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

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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 re

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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

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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,

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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 b

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Wu, Shujie, Xuan Li, Haosu Wang, Xin Li, Liming Xiao, and Wenyong Zhou. "The adaptive optimization design of nozzle cooling structure." Journal of Physics: Conference Series 3026, no. 1 (2025): 012038. https://doi.org/10.1088/1742-6596/3026/1/012038.

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Abstract Reusable rockets can reduce the cost of rocket launches. To maximize the time, the nozzle can be reused, and the cooling design of the nozzle is particularly critical. Based on the regenerative cooling method, an adaptive cooling structure optimization design method is proposed. It gets rid of human factors and can more freely take the cooling structure average temperature, temperature unevenness, and cooling channel pressure drop as the objective function and use as many objective functions as possible for more comprehensive and practical optimization. The calculation results showed

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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 scalabilit

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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 implem

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Pavloudi, Christina, Ioulia Santi, Iñigo Azua, et al. "First release of the European marine omics biodiversity observation network (EMO BON) shotgun metagenomics data from water and sediment samples." Biodiversity Data Journal 13 (March 12, 2025): e143585. https://doi.org/10.3897/BDJ.13.e143585.

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The European Marine Omics Biodiversity Observation Network (EMO BON) is an initiative of the European Marine Biological Resource Centre (EMBRC) to establish a persistent genomic observatory amongst designated European coastal marine sites, sharing the same protocols for sampling and data curation. Environmental samples are collected from the water column and, at some sites, soft sediments and hard substrates (Autonomous Reef Monitoring Structures - ARMS), together with a set of mandatory and discretionary metadata (including Essential Ocean Variables - EOVs). Samples are collected following st

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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 atmosp

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