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Journal articles on the topic 'Reusable Launchers'

Author: Grafiati

Published: 23 November 2024

Last updated: 19 July 2025

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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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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. Initially, the field of rocketry was characterized by rudimentary designs and limited payload capacities, primarily driven by military objectives during the mid-20th century. The transition to space exploration catalyzed the development of more sophisticated launch systems, exemplified by the introduction of the Saturn V rocket, which facilitated human exploration of the Moon. This era marked a significant leap in engineering capabilities, setting the stage for subsequent advancements in launch technology. The advent of the Space Shuttle program in the 1980s introduced a paradigm shift in satellite deployment, allowing for the transportation of multiple payloads and the servicing of existing satellites in orbit. However, the high operational costs and complexity of the Shuttle system prompted the search for more economical and efficient launch solutions. This led to the emergence of commercial launch providers, such as Space X and Blue Origin, which have revolutionized the industry with the development of reusable rocket technology. The Falcon 9, for instance, has demonstrated the feasibility of reusing first-stage boosters, significantly reducing launch costs and increasing the frequency of satellite deployments. Moreover, the evolution of launchers has been closely linked to advancements in satellite technology. Modern satellites are equipped with sophisticated instrumentation and capabilities, necessitating launch vehicles that can accommodate larger payloads and deliver them to precise orbits. The integration of small satellite technology has further diversified the launch market, leading to the proliferation of dedicated small satellite launchers and rideshare missions.

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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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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 market. Europe aims to double its space transportation market share by 2030 by developing low-cost propulsion and launch routes for SMEs. Over 100 projects worldwide are developing light-lift and micro-lift rockets, with consideration for geographically closer spaceports. Challenges like space debris are addressed through innovative solutions. Recommendations emphasize reusable technologies and greener propulsion systems. The COVID-19 pandemic highlighted vulnerabilities but also spurred innovation and resilience. This paper discusses the multifaceted aspects influencing the space launching market evolution, including market dynamics, European initiatives, external factors, innovation, and future potential.

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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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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 the required height of hypersonic speed. The integrated launch vehicle consists of three solid propellant stages connecting to the side. An integrated launch vehicle is placed under the unmanned aerial vehicle and separates when it reaches a required height and speed. The technical and economic substantiation of the parameters was carried out according to the criterion of minimizing the costs of the aerospace system, which combines the costs of the development and operation of the aerospace system and shows the number of launches to achieve a reduction in the cost of removing the payload to a given indicator. The results obtained made it possible to determine the performance characteristics of the Ukrainian air-launched aerospace system. The paper presents a comparative analysis of the obtained characteristics. The comparisons were made in terms of overall performance, aerodynamic performance, flight performance, and cost performance. The comparison was made with the main analogs: the projects Spiral (USSR), Molot (Russia), GT RASCAL (United States), Sänger-2, and ELAC (Germany). Based on the comparison of the obtained ASS with existing systems, a rationale was provided for the parameters of the air-launched aerospace system.

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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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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 given to design choices in the guidance optimization problem and the control definition for each phase, which were made to enhance the harmonization of the guidance and control (G&C) system. The proposed GNC is integrated in a high-fidelity Functional Engineering Simulator (FES) and its robustness is assessed in a real-world scenario, considering a downrange landing mission of the RETALT1 (RETro propulsion Assisted Landing Technologies Two-Stage-To-Orbit vehicle) rocket.

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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 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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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 widerdisruption caused by these technologies at the governmental and private levels, new opportunities through satellitedeployment, space tourism, and interplanetary missions. Strategic approaches followed by aerospace companies areinnovation with iterative testing for cost optimizations. Results focused on demonstrating potential for inside-outinnovation to achieve space or economic feasibility, making the space accessible for human beings. As such, strategicmodels in this research may also be applied in other sectors of high-tech industries as they look to break through into newinnovations

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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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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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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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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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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 that the adaptive cooling structure optimization design method could optimize the cooling structure of complex shapes; for different optimization schemes, there were corresponding cooling channel distributions and optimal number of channels to make the objective function optimal. For the optimization case 3, the optimal number of cooling channels is 62. Compared with the regular cooling channel design, the cooling structure’s average temperature drops from 672 K to 656 K, and the temperature unevenness decreases from 151 K to 140 K at the cost of increasing the pressure drop from 0.092 MPa to 0.1436 MPa.

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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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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 standardised protocols at regular and specified intervals and sequenced in large six-monthly batches at a centralised sequencing facility. The use of standard operating procedures (SOPs) during data collection, library preparation and sequencing aims to provide uniformity amongst the data collected from the sites. Coupled with strict adherence to open and FAIR (Findable, Accessible, Interoperable, Reusable) data principles, this ensures maximum comparability amongst samples and enhances reusability and interoperability of the data with other data sources. The observatory network was launched in June 2021, when the first sampling campaign took place.

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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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