The Acceleron Aerospace Journal (AAJ) (E-ISSN: 2583-9942) is an international, peer-reviewed, open-access scholarly platform dedicated to advancing innovative and interdisciplinary research in aerospace and allied scientific domains. The journal provides a distinctive publication avenue that supports emerging researchers, including undergraduate and graduate scholars, alongside established academics. AAJ publishes high-quality research articles, reviews, and technical papers across a broad spectrum of disciplines, including general sciences, aerospace engineering, aeronautics, astronautics, space science advancements, and next-generation engineering technologies. The journal emphasizes the integration of multidisciplinary approaches to address contemporary challenges and future developments in space exploration and related fields. Recognized for its academic contribution, AAJ is indexed in major databases such as Google Scholar, Scilit, NASA Astrophysics Data System (ADS), CORE, Semantic Scholar, ResearchGate, Directory of Research Journal Index (DRJI), Asian Science Citation Index (ASCI), WorldCat, Open Ukrainian Citation Index (OUCI), among others. The journal operates under a fully Open Access (OA) model, ensuring unrestricted and immediate access to all published content, thereby enhancing global knowledge dissemination. The editorial and peer-review processes are managed by an international board of experts from India, Germany, and Sweden, ensuring rigorous quality standards. The journal workflow is facilitated through the Open Journal Systems (OJS) platform developed by the Public Knowledge Project (PKP), Simon Fraser University. Aim and Focus: The Acceleron Aerospace Journal (AAJ) aims to promote innovative and high-impact research in aerospace and interdisciplinary scientific domains while providing a global platform for early-career researchers and students to disseminate their work. The journal encourages cross-disciplinary collaboration in emerging technological fields and supports the publication of cutting-edge advancements in space science, engineering, and related areas. It seeks to bridge the gap between theoretical research and practical applications, fostering advancements that contribute to both academic progress and industrial innovation. Scope of Coverage: The scope of AAJ encompasses a wide range of disciplines, including aerospace engineering and technology, aeronautical and astronautical sciences, space exploration and satellite systems, propulsion systems, advanced materials, artificial intelligence applications in aerospace, robotics, automation, avionics, and interdisciplinary engineering innovations. The journal also welcomes contributions in physical sciences related to space and atmospheric studies, as well as emerging technologies that intersect with aerospace and engineering domains, thereby promoting a comprehensive and inclusive research environment. Ethics and Publishing Policies Journal Ethics The journal strictly adheres to the ethical standards established by the Committee on Publication Ethics (COPE) and the DOAJ Principles of Transparency and Best Practice in Scholarly Publishing, covering authorship, plagiarism, conflict of interest, data integrity, complaints, corrections, and retractions. 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Highly Cited Articles [1] Advancements in Lightweight Materials for Aerospace Structures: A Comprehensive Review [DOI:10.61359/11.2106-2409] [2] Statistical Reliability Analysis of Interplanetary Spacecraft Operating at Different Interplanetary Extremity [DOI: 10.61359/11.2106-2419] [3] A Short Review on India’s Interplanetary Missions [DOI: 10.61359/11.2106-2403] [4] Challenges and Innovations in Electric Propulsion Systems for Space Transportation: A Comprehensive Review [DOI:10.61359/11.2106-2511] [5] Terraforming Mars: A Strategic Framework for Sustainable Colonization and Expansion [DOI: 10.61359/11.2106-2513] Most Read Articles [1] Review on Photometric Study of Variable Stars [DOI:10.61359/11.2106-2425] [2] A CatBoost-Based Approach for Aerosol Optical Depth Estimation Using Multi-Spectral Sentinel-2 Data [DOI: 10.61359/11.2106-2520] [3] Comparison of Propulsion Options for Interplanetary Missions [DOI:10.61359/11.2106-2459] [4] Design of 2-DOF Thrust Vector Control System for Rockets and Missiles [DOI:10.61359/11.2106-2505] [5] The Common Heritage of Mankind and the Rights of Future Generations in Outer Space Exploration: The Ethical Frontier [DOI:10.61359/11.2106-2432] Journal Metrics, Indexing, and Submission Categories [From 2023 to 2026] Metrics Details Major Indexing Submission Category Authors (From India & Abroad) 300+ Google Scholar Research Article Papers Received 350+ Scilit [MDPI] Review Article Papers Published 190+ NASA ADS Conceptual Paper Journal Acceptance Rate 82% CORE UK Conference Paper Average Review Time 45-60 Days IPI Index Student Paper Journal Indexation in Databases 40+ ROAD UG & PG Thesis Journal IF [23-24] 5.437 Semantic Scholar Comments
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Optimization of Air-Breathing Electric Hybrid Engines for Atmospheric-to-Orbit Vehicles
Air-breathing electric hybrid engines have emerged as a promising concept for future atmospheric-to-orbit (ATO) vehicles and very low Earth orbit (VLEO) missions. The primary advantage of this technology lies in its ability to reduce dependence on carried propellant by utilizing ambient atmospheric particles as the working fluid, thereby improving mission efficiency and extending operational lifespan. This review synthesizes the core principles of air-breathing propulsion, electric propulsion, hybrid engine architecture, and mission-level performance analysis, with emphasis on how these systems may enable next-generation space access. The review also examines the principal engineering challenges involved in realizing this concept. These include intake capture efficiency, aerothermal loading, onboard power availability, multi-mode transition stability, and system resilience across varying flight conditions. Performance enhancement strategies such as plasma-assisted combustion, magnetohydrodynamic (MHD) flow control, intake compression and shock optimization, and precooler thermal management are discussed as enabling technologies. In addition, thermodynamic analysis, multi-objective optimization frameworks, and mission-level design methodologies are addressed. The review concludes that air-breathing electric hybrid propulsion remains in an early but promising phase of development, offering a compelling research direction for efficient and reusable ATO systems.
Copyright (c) 2026 Acceleron Aerospace Journal https://creativecommons.org/licenses/by/4.0
Engineering Feasibility Analysis of a Surface-Based Mars Habitat Using Integrated Structural, Thermal, Solar, and Aerodynamic Models
Human habitation on the Martian surface presents significant engineering challenges due to low atmospheric pressure, extreme thermal conditions, solar radiation exposure, and wind-induced environmental loads. Surface habitat systems must therefore maintain structural integrity, thermal stability, and aerodynamic robustness under combined Martian conditions. This study presents an integrated numerical assessment of a conceptual surface-based Mars habitat addressing these key design requirements. Structural performance is evaluated under the pressure differential between a pressurized interior and the Martian atmosphere for different habitat geometries. Thermal behavior is investigated through steady-state heat transfer analysis of a multilayer wall system comprising an aluminum structural shell, Martian regolith, and a low-conductivity insulation layer. Solar radiation effects are examined using date-specific solar flux conditions for multiple representative Martian years. Aerodynamic response under Martian wind conditions is analyzed to assess external flow behavior and wind-induced loading. The results demonstrate that habitat geometry and wall configuration play a decisive role in overall performance. Curved configurations exhibit significantly reduced deformation and lower aerodynamic drag compared to cylindrical forms. The multilayer wall system effectively limits heat loss and moderates temperature variations, with insulation identified as critical for maintaining thermal stability. Overall, the study highlights the importance of integrated structural, thermal, solar, and aerodynamic analysis in guiding early-stage design of surface-based Mars habitats under realistic environmental conditions.
Comparative Assessment of Space-Based Solar Power and Terrestrial Photovoltaic Systems
Sunlight in geostationary orbit arrives at approximately 1,361 W/m², unfiltered by atmosphere, uninterrupted by weather, and available for roughly 99% of the year. On Earth's surface, the same resource averages 150–300 W/m² at mid-latitudes after accounting for atmosphere, cloud, and the diurnal cycle. That gap, nearly an order of magnitude, is the central premise of Space-Based Solar Power (SBSP): collect energy where it is abundant, transmit it wirelessly to where it is needed. This paper quantifies that premise, challenges it economically, and asks whether it survives scrutiny. Using data from NASA, JAXA, ESA, IRENA, and NREL, we show that GEO SBSP concepts could deliver 6–10 times more annual energy per unit collector area than utility-scale terrestrial PV. The cost gap, however, is just as dramatic, NASA's 2024 baseline LCOE for SBSP sits at $0.61–$1.59/kWh, against a global weighted average of $0.043/kWh for terrestrial PV per IRENA's latest figures. The paper also examines two issues the existing literature tends to treat briefly: the specific debris and collision risks posed by deploying large structures in LEO and GEO, and the cost and power expectations for SBSP systems at different scales. A comparative assessment against conventional and modern generation technologies closes the paper, establishing what, precisely, makes SBSP unique and under what conditions it could become competitive.
Conceptual Design and Analysis of Rotating Skyhook Orbital Tether System (RSOTS)
The Rotating Skyhook Orbital Tether System (RSOTS) is a proposed space-launch-assistance architecture in which a tethered station in low Earth orbit (LEO) rotates a high-tensile cable so that its lower tip periodically sweeps to approximately 280–320 km altitude. A payload launched by a conventional rocket or hypersonic carrier vehicle to this rendezvous altitude is captured by the rotating tip, carried through the tether's arc, and released at higher velocity into a target orbit. The net result is a reduction in the rocket delta-V requirement of 30–50%, translating directly into smaller, cheaper, and more frequently reusable launch vehicles. This paper presents a comprehensive technical analysis of the RSOTS concept: orbital mechanics derivations, tether load analysis, materials selection, system mass budgets, economic modelling, identified engineering challenges with proposed mitigations, expansion scenarios including interplanetary applications, and a structured five-phase development roadmap from simulation to commercial operations. The key enabling technology, carbon nanotube (CNT) composite tether material, is advancing rapidly; however, the baseline architecture using currently available Zylon (PBO) fibre is sufficient for demonstration missions and yields a deployable system mass of approximately 23,000 kg, compatible with a single Falcon Heavy launch.
How Can Local Regolith Be Used to Create Self-Sustaining Agriculture Zones Without Relying on Full Planetary Terraforming?
Establishing sustainable agricultural systems is essential for long-duration human habitation in extraterrestrial environments. This study investigates the feasibility of utilizing lunar regolith as a foundational resource for developing localized, self-sustaining agricultural zones without requiring full planetary terraforming. By integrating regolith-derived materials with hydroponic cultivation, closed-loop waste recycling, and modular habitat design, the research demonstrates how in-situ resource utilization (ISRU) can support food production, oxygen generation, and habitat sustainability. The findings indicate that regolith can serve multiple roles, including structural support, radiation shielding, and resource extraction, while hydroponics and waste-recycling systems provide efficient nutrient cycling. These integrated systems present a scientifically realistic pathway toward sustainable lunar habitation.
Engineered Biopolymer Delivery Platforms for Space Nutrition: Food Encapsulation, Stability and Controlled Nutrient Release Strategies - A Review
Long duration space missions pose a special problem of ensuring the quality of nutritional value, safety, and stability of food systems because radiation, micro-gravity, and prolonged storage conditions are exposed. As a developing area of food, this review seeks to evaluate the promise of food grade biopolymers like proteins, polysaccharides (chitosan, alginate, pectin, cellulose) and pseudocereals as enhanced carriers of sensitive Nutrients like vitamins, probiotics and unsaturated fatty acids in harsh conditions of space nutrition systems. Current developments in food encapsulation technologies including nano-encapsulation technology, complex coacervation technology, hydrogel-based delivery systems and others are presented in terms of improvements in shelf life, oxidation prevention, and bioavailability enhancement. Also, the controlled release systems, such as pH-responsive and enzyme trigger responsive delivery systems, are discussed as the possible ways to enhance the efficiency of nutrient intake during the altered physiological conditions. Present due to food safety and scaling, material constraints issues are also brought into the limelight. The end of the review represents the future opportunities of developing functional and stable food systems to aid in feeding humanity during space exploration in the long-duration.
EM Topology Stability and Active Field Governance for High Power Hall Thrusters
The in-flight checkout of the Psyche spacecraft's SPT-140 Hall thrusters (Oh et al., Journal of Spacecraft and Rockets, 2026) documents five classes of transient and quasi-steady behaviour: burn-in thrust decay, extended mode-hopping, sensitivity to magnet-current settings, ground-to-space performance differences, and thrust variability during calibration. This Technical Comment reinterprets these observations within a unified electromagnetic-topology framework, demonstrating that each behaviour is a manifestation of one of four underlying EM-topology mechanisms, sheath evolution, magnetic-topology drift, ionisation-driven oscillations, and environment-dependent discharge equilibria, rather than an isolated anomaly. The analysis establishes that these instabilities are structural features of passive-topology Hall-thruster architectures and will become increasingly consequential as mission lifetimes and power levels grow. The Psyche dataset is further examined for its relevance to active electromagnetic field-governance research. A one-to-one correspondence is identified between the five observed behaviours and the stabilisation functions of the Rotating Electromagnetic Nozzle (REMN), an external field-governance architecture designed to suppress mode transitions, damp harmonics, lock B-field topology, and compensate for environmental boundary-condition changes in real time. The Psyche checkout data is presented as a valuable real-flight reference for evaluating next-generation active field-governance approaches in high-power electric propulsion.
The Griffiths ISRU-Powered Plasma Hopper (IMPH)A Shear-Stabilized Electromagnetic Surface Hopper with ISRU Propellant Generation and Kelvin-Helmholtz Bounded Operation
The Griffiths ISRU-Powered Plasma Hopper (IMPH) is a disc-shaped surface lander and hopper vehicle designed for planetary exploration on bodies where in-situ resources are accessible at or near the surface. The IMPH harvests local feedstock (CO2 from the Martian atmosphere, H2O ice from polar deposits, CH4 from Titan surface lakes), cracks it via an integrated GNMT microwave power module, generates plasma through electromagnetic confinement coils, and fires a burst-mode plasma plume downward through the electromagnetic edge to execute surface hops of 10 to 500 km range. The architecture eliminates dependence on Earth-supplied propellant: the planetary surface itself is the fuel source. The plasma drive employs shear-stabilized electromagnetic confinement addressing fundamental instability limitations in high-power plasma thrusters. Traditional systems including VASIMR, helicon thrusters, and magnetoplasmadynamic accelerators suffer from Kelvin-Helmholtz instabilities, anomalous cross-field transport, and erosion from plasma-wall interactions. The IMPH resolves these through engineered shear-layer stabilization where controlled velocity gradients create viscous dissipation exceeding instability growth rates, maintaining stable operation without active feedback control or complex magnetic field topologies. The vehicle operates in three modes. Mode A provides low-power plasma conditioning and precision landing at 10 to 50 kW, 5 to 15 N, Isp 1,500 to 2,500 s. Mode B executes primary hop ascent and descent burns at 50 to 200 kW, 20 to 60 N, Isp 2,500 to 3,500 s. Mode C enables high-performance long-range hops at 200 to 500 kW, 60 to 150 N, Isp 3,500 to 5,000 s with Kelvin-Helmholtz stability margins exceeding factors of 3 to 5 over critical thresholds. Mode transitions occur through software control of magnetic field strength, propellant flow rate, and microwave power allocation without hardware reconfiguration.
A Unified Electromagnetic-Topology Framework and Augmentation Collar for Ion, Hall, Chemical, and Thermal Propulsion Plumes
Plume-generating propulsion systems, including ion engines, Hall thrusters, chemical rockets, and nuclear- or microwave-thermal systems, share common stability limitations arising from electromagnetic-topology effects. These include plume divergence, oscillatory modes, space-charge spreading, and sensitivity to environmental boundary conditions. This paper introduces a universal rotating electromagnetic augmentation collar (REMN/GREMN) designed to stabilise, collimate, and enhance plumes across all propulsion types. The REMN architecture generates controlled azimuthal shear layers and a rotating electromagnetic envelope that suppresses instabilities, improves plume alignment, and increases effective exhaust velocity. Performance gains include space-charge relief in ion engines (+8–15% thrust, +5–10% Isp), breathing-mode suppression in Hall thrusters (40–70% reduction, +18–28% thrust, +10–18% Isp), and pre-ionisation-driven improvements in chemical rockets (+8–15% Isp). Nuclear and microwave-thermal systems benefit from burst-mode plume stiffening and Kelvin–Helmholtz suppression. A unified EM-topology framework is presented to explain why all plumes, charged, partially charged, or neutral, respond to downstream electromagnetic shaping. An experimental pathway is outlined for bench-top validation using a plasma jet and rotating EM coil stack. The results position REMN as a propulsion-agnostic augmentation technology with broad applicability to next-generation spacecraft.
The Griffiths Free-Flying EVA Logistics Sled (NGLS)
As deep-space habitats, propulsion modules, and distributed construction platforms grow in scale and operational complexity, existing EVA mobility systems are no longer adequate to meet the increasing logistical demands on human crews. Conventional astronaut maneuvering units, such as SAFER and the historical MMU, were primarily designed for personal mobility and emergency self-rescue, rather than for transporting heavy equipment, structural components, or modular payloads across expansive spacecraft and habitat exteriors. The Griffiths Free-Flying EVA Logistics Sled (NGLS) addresses this critical gap by introducing a dedicated logistics-focused EVA architecture. It features dual high-pressure cold-gas propellant tanks, vectorable thruster assemblies, full six-degree-of-freedom control, autonomous stabilization, and modular cargo interfaces integrated into a lightweight composite frame. Designed for both piloted and autonomous operation, the system incorporates multiple redundant safety mechanisms, including fail-closed valves, dead-man stabilization, collision-avoidance sensors, and autonomous return-to-base capability, ensuring safe operation in proximity to complex, rotating, or thermally active structures. Performance modelling indicates that the NGLS can achieve an operational Δv of 50–150 m/s, transport payloads of 50–200 kg, and sustain sortie durations of 10–45 minutes, enabling logistics operations that extend well beyond the physiological limits of a suited astronaut. Furthermore, the architecture integrates seamlessly within the broader Griffiths ecosystem, supporting external maintenance of the Dual-Ring Habitat, inspection of propulsion modules such as the GNMT-Drive and MSH-Drive, and last-mile delivery of DIMDCP-fabricated components. Overall, the NGLS represents a practical, manufacturable, near-term solution that formalizes EVA logistics as a distinct and essential operational domain.
EM-Driven Underwater Power Generation Plants (EM-UPGPs)
EM Driven Underwater Power Generation Plants present a new architectural approach to tidal and current based energy generation. Rather than introducing new physics, EM UPGPs apply proven direct drive electromagnetic generation within a modular subsea plant structure designed to eliminate the dominant mechanical and operational burdens of traditional tidal turbines and offshore wind systems. Each plant integrates a slow turning hydrodynamic rotor, a sealed electromagnetic generator, and autonomous control systems into a single replaceable pod that can be installed, recovered, or swapped using standard ROV operations. The EM UPGP architecture replaces pitch systems, yaw drives, gearboxes, and tower structures with governed electromagnetic loading and distributed electronic control. This enables millisecond scale response to grid conditions, reduces maintenance requirements, and removes the need for heavy lift vessels or weather dependent surface access. When deployed in arrays, EM UPGPs operate as intelligent, cooperative nodes capable of balancing load, isolating faults, and maintaining stable output even when individual units are offline. This document defines the baseline EM UPGP design, introduces an optional superconducting variant for high capacity applications, and provides detailed analysis of system performance, installation methods, environmental considerations, and comparative economics. A reference two megawatt unit is used to establish realistic mass, power, and cost parameters. The analysis demonstrates that EM UPGPs can achieve energy conversion efficiency comparable to modern tidal turbines while offering significantly lower operational expenditure and a credible pathway to sub fifty dollars per megawatt hour levelised cost of energy. The architecture provides a practical, scalable, and grid compatible foundation for next generation underwater power generation.
Electro Magnetic Curvature Theory – Working Summary
We present a governed, falsifiable experimental framework for probing whether quantum-coherent electromagnetic systems can generate measurable spacetime curvature. The proposed apparatus consists of a counter-rotating toroidal stack of high-temperature superconducting rings (YBCO/BSCCO, 10–15 cm diameter, 500–1000 A, 1–5 T), an axial superconducting electromagnetic lens for directional field bias, and a cryogenic high-vacuum environment operating below 10⁻⁶ torr. This configuration is designed to produce an anisotropic stress–energy distribution topologically analogous to the boundary structure of warp-metric solutions in the weak-field, linearized regime, without invoking exotic matter or modifications to established physics. The detection framework employs dual-channel readout, a high-precision interferometer (phase sensitivity ~10⁻¹⁵ rad) and a torsion balance (torque resolution ~10⁻¹² N·m), to search for gravitomagnetic and frame-dragging-like signatures with effective angular velocity sensitivity in the range 10⁻¹⁶ to 10⁻¹⁸ rad/s. The experiment is structured so that both positive detections and null results yield publishable outcomes: either revealing previously unmeasured electromagnetic–gravity coupling in quantum-coherent systems, or establishing the strongest laboratory bounds to date on such interactions. The complete apparatus is estimated at USD 300,000–500,000, with a construction and commissioning timeline of 12–18 months.
Nuclear Microwave-Thermal Propulsion: Megawatt-Class NM with Rotating Electromagnetic Nozzles
The capability gap between low-thrust electric propulsion and high-thrust chemical propulsion limits deep-space mission architecture. No current system achieves thrust ≥30 N, specific impulse ≥2,500 s, and power >1 MW simultaneously for crewed outer solar system transit. GNMT v7. 0 is a Nuclear Microwave-Thermal propulsion architecture resolving this gap through a megawatt-class nuclear electric system combining a Prometheus-lineage fast-spectrum fission reactor with twin Rotating Electromagnetic Nozzle (REMN) stacks. The REMN couples helicon radiofrequency plasma heating (13. 56–27. 12 MHz, η_RF = 0. 70–0. 85) with rotating permanent magnet nozzles (100–300 Hz), combining magnetic mirror thermal conversion (η_mirror = 0. 90–0.97) with J×B Lorentz acceleration to achieve η_noz = 0. 85–0. 92. At 1. 0 MW RF input and 1. 2 mg/s water propellant flow, exhaust velocity reaches 38 km/s (Iₛₚ = 3,880 s) and thrust is 46 N. A spine-mounted dual-use water-tank pod architecture provides directional crew radiation shielding (20–40 cm water-equivalent, GCR dose reduction 2–4×) and propellant storage, eliminating separate shielding mass and saving 20–30 tonnes. Mission analysis predicts Jupiter transit in 18–24 months (40–60% shorter than chemical), Saturn in 36–42 months, and Pluto in 48–60 months for a 100-tonne vehicle. All subsystems are grounded in validated laboratory physics; a four-phase validation pathway targets TRL.
How SETI Uses Machine Learning for Analyzing Radio Signals
There are more stars in the universe than the number of grains of sand on Earth. And orbiting each of these are more worlds than we could ever visit, more chances than we could ever count. And yet, we have heard nothing - no messages, no signals, no signs. Just absolute silence, stretching across billions of years and light years alike. But as Carl Sagan himself says, "The absence of evidence is not evidence of absence". Maybe they don't know we're here. Maybe they're too far to reach us. Maybe they're choosing not to speak. Or even wilder - they've been speaking all along, and we haven't known how to listen. So, we built ears as wide as continents and tuned our them to the language of numbers - with structured signals, repeating patterns, the rhythms hidden in randomness, the fingerprints of thought etched in the static. And this brings us to SETI, the Search for Extraterrestrial Intelligence.
Gravitational Wave Astronomy of Binary Black Hole Mergers: Observations, Fundamental Physics, and Cosmological Implications
Gravitational wave (GW) astronomy has opened a transformative window into the study of black holes by allowing direct observations of binary black hole mergers and providing unprecedented insights into their formation, dynamics, and role in the universe. This review presents a comprehensive overview of the field with a focus on black hole mergers as powerful sources of gravitational radiation. We begin by tracing the historical development of GW detection, highlighting key milestones such as the first direct observation of GW150914. Theoretical modeling of merger dynamics including inspiral, merger, and ringdown phases is discussed alongside waveform generation techniques that underpin parameter estimation and event classification. We then examine recent observational discoveries from LIGO-Virgo-KAGRA catalogs, analyzing statistical trends in masses, spins, and redshifts. The paper also explores how GW data are used to test general relativity in strong-field regimes and to constrain exotic alternatives to black holes. From a cosmological perspective, we review applications such as standard sirens for measuring the Hubble constant and the role of black hole mergers in tracing cosmic structure formation. Finally, we discuss prospects enabled by next-generation ground- and space-based detectors, and the growing importance of multi-messenger synergies. Together, these developments mark the beginning of a new era in astrophysics, where gravitational waves are not just a confirmation of theory but a primary tool for discovery.
Electric Propulsion for Space Exploration: Principles, Technologies, Challenges, and Future Directions
Electric propulsion (EP) represents a transformative alternative to conventional chemical propulsion by utilizing electrical energy to accelerate propellant to extremely high exhaust velocities. This results in significantly higher specific impulse (Isp) and reduced propellant mass requirements, making EP particularly suitable for long-duration and deep-space missions. This review provides a comprehensive overview of major EP technologies, including ion thrusters, Hall-effect thrusters, and magnetoplasmadynamic thrusters. It examines their operating principles, performance characteristics, historical evolution, and current state-of-the-art developments. Additionally, the paper discusses system-level integration challenges, particularly in power generation and thermal management. Emerging innovations, mission design considerations, and future research directions are also analyzed. The potential of EP in enabling interplanetary cargo transport, sustained lunar operations, and human missions beyond Earth orbit is critically assessed.
High Fidelity Simulation Based Optimization of Aircraft Fuselage Structure
Aircraft Fuselage must be designed to achieve low structural weight while maintain adequate strength and stability under critical loading conditions. Conventional Global Finite Element Models (GFEM), typically composed of beam and shell elements, provide computational efficiency but may not capture detailed panel-level structural behavior. In this study, a high-fidelity finite element model of fuselage model is analyzed under Load Case to generate structural response data. A design of experiments (DOE) approach is used to explore the design space, and surrogate models are developed using polynomial regression for mass and box-cox regression for stress estimation. Structural Optimization is performed to minimize weight under strain constraints using Particle Swarm Optimization and brute-force search. The optimized configuration is further verified using a detailed finite element model (DFEM) of fuselage panel through eigenvalue buckling analysis, ensuring a buckling factor greater than 1.0.
Design and Development of a Morphing-Fin Hybrid Rocket-Powered Loitering Interceptor
The rise of the agile and low-signature aerial threats such as UAVs necessitates the development of advanced and flexible air defence systems. Conventional Surface-to-Air Missiles (SAMs) are often limited by the very low engagement time, while existing loitering munitions are unable to provide the high energy performance needed for intercept. The paper presents the conceptual design and critical analysis of a new type of loitering intercept weapon that combines a throttleable hybrid rocket propulsion system with a mission-adaptive airframe utilizing morphing fins. The methodology for the design consists of the theoretical design of a GOX/HTPB-based hybrid rocket propulsion system capable of high-thrust boost mode (50 N) and low-thrust loiter mode (5 N). The paper also includes the use of Computational Fluid Dynamics (CFD) to assess the aerodynamic performance of the missile in both stowed and deployed fin configurations, validating the aerodynamic feasibility of the low-speed loiter mode. The paper extends the conceptual design by including a critical analysis of the technical challenges.
Short Commentary: Human Exploration of Mars: Concepts, Missions, and Technological Evolution (1960–2025)
Human exploration of Mars has long been a central objective of planetary science and aerospace engineering. Since the early space age, researchers and space agencies have proposed numerous mission architectures, technologies, and strategies aimed at enabling crewed missions to the Red Planet. Over the past six decades, advancements in propulsion systems, spacecraft design, robotics, and planetary science have significantly improved the feasibility of human Mars exploration. This article reviews the conceptual and technological evolution of human Mars exploration from 1960 to 2025. It examines early mission proposals, robotic exploration efforts, technological constraints, habitat concepts, transportation systems, and lessons learned from past missions. The study highlights the critical engineering challenges associated with long-duration space travel, planetary environments, and mission reliability. It also discusses emerging concepts such as in-situ resource utilization, underground habitats, and integrated interplanetary transportation systems. By synthesizing developments over several decades, this article provides a broad perspective on the progress and remaining challenges in achieving sustainable human exploration of Mars.
Copyright (c) 2025 Acceleron Aerospace Journal https://creativecommons.org/licenses/by/4.0
Numerical Study on the Change of Aerodynamic Characteristics of Rotors Due to Ice Accretion Depending on the Sectional Shapes
Aircraft are frequently exposed to various atmospheric conditions during ascent, where they encounter supercooled droplets within clouds. These droplets can freeze upon contact with the aircraft surface, leading to ice accretion at temperatures below the freezing point. This ice formation alters the aircraft's shape, adversely affecting its aerodynamic properties, flight efficiency, and stability. This study investigates the effects of icing on airfoil geometries, focusing on the aerodynamic characteristics and robustness of rotor blades in icing conditions through two-dimensional simulations and the Blade Element Momentum (BEM) method. Our findings indicate that an increase in the thickness ratio within the same camber series leads to reduced maximum droplet collection efficiency and broadens the range of the impingement limit for supercooled droplets. This effect is pronounced as thicker airfoils show lesser ice accumulation, enhancing aerodynamic stability under icing conditions. Conversely, airfoils with a lower camber ratio exhibit decreased maximum collection efficiency and a milder slope of droplet collection efficiency, resulting in reduced thrust loss. This suggests that selecting airfoil profiles with a lower camber ratio and greater thickness can significantly improve the robustness against icing conditions.
The Griffiths Dual-Ring Superconducting Artificial-Gravity Habitat Architecture: Counter-Rotating Magnetic Levitation Design for Long-Duration Deep-Space Habitation
Long-duration human habitation beyond Earth's magnetosphere requires artificial gravity to prevent the progressive musculoskeletal, cardiovascular, and neurovestibular deterioration observed in sustained microgravity exposure. Existing artificial gravity concepts tethered systems, single-ring centrifuges, and rotating drums each exhibit fundamental limitations in gyroscopic stability, physiological adequacy, structural scalability, or integration with active propulsion and defence architectures. This paper presents the Griffiths Dual-Ring Superconducting Artificial-Gravity Habitat Architecture: a counter-rotating, magnetically levitated habitat system providing 0.8 g at the outer habitation ring (100 m outer diameter, 50 m radius) and 0.6 g at the inner laboratory ring (75 m outer diameter, 37.5 m radius), both at a common rotation rate of 3.78 RPM (ω = 0.396 rad/s). Counter-rotation eliminates net angular momentum, removing gyroscopic coupling with attitude control systems and enabling free reorientation of the combined habitat. Superconducting toroidal coils provide magnetic levitation, structural rigidity, and electromagnetic bearing functionality with field stability maintained at ±0.01 T through closed-loop flux feedback. The governing framework quantifies centripetal acceleration, hoop stress in the ring structure, magnetic levitation force balance, thermal radiative equilibrium, and angular momentum cancellation conditions. Coriolis acceleration at walking speed (1 m/s) is 0.79 m/s² (8.1% of local gravity), within published adaptation limits. The gravity gradient across a 1.8 m crew height is 3.6%, negligible relative to physiological thresholds. The architecture integrates with the Griffiths Reactive-Field Framework (GRFF) four-layer defence envelope, GNMT propulsion, NGLS EVA logistics, and the DIGSP governance protocol, forming a complete deep-space habitation system within the Griffiths Canon. The habitat architecture is now explicitly integrated with the GNMT v7.0 Nuclear Microwave‑Thermal propulsion system and its Rotating Electromagnetic Nozzle (REMN) stacks, providing a unified propulsion–habitation interface. Dedicated EVA logistics ports support the Griffiths Free‑Flying EVA Logistics Sled (NGLS) for external maintenance, cargo movement, and distributed construction. Two experimental bays in the central spine are reserved for compact superconducting EM‑curvature test modules, leveraging shared REBCO‑class coil technology while maintaining full isolation from the levitation system. These integrations align the habitat with the broader Griffiths Canon and its propulsion, logistics, and experimental frameworks.
Case Study on Detecting Anomalies in CubeSat Telemetry Using Machine Learning Approach
The increasing complexity of CubeSat missions and the volume of telemetry data they generate has heightened the need for advanced anomaly detection systems capable of identifying faults before they escalate into mission failures. Traditional threshold-based monitoring approaches fall short in capturing subtle, multivariate, and time-dependent anomalies inherent in satellite telemetry. This case study explores the application of machine learning (ML) techniques for anomaly detection in CubeSat telemetry, with a focus on evaluating recent research supported by publicly released benchmark datasets: OPSSAT‑AD and ESA‑ADB. These datasets provide real-world, labelled telemetry from operational ESA missions and have enabled systematic benchmarking of over 30 machine learning models. The study synthesises model performance across metrics such as F1-score and AUC, highlighting that temporal models like LSTMs and temporal convolutional networks (TCNs) consistently outperform classical methods in time-series tasks. Limitations in dataset continuity, anomaly sparsity, and generalisability are discussed, along with the need for explainable and resource-efficient models suitable for onboard deployment. The case concludes with a call for expanded benchmark datasets, real-time validation, and cross-disciplinary collaboration to ensure robust, interpretable, and mission-ready anomaly detection systems for future CubeSat applications.
A Critical Review of Aerodynamic Lift: Widespread Misconceptions and Physical Origins
The science behind how airplanes generate lift remains a topic of ongoing debate and controversy. Over the years, numerous theories, such as the Equal Transit Time Theory, Skipping Stone Theory, and Venturi Effect, have been proposed, yet none fully capture the true mechanism of lift generation. Despite the availability of advanced mathematical models and aerodynamic analyses, confusion persists, even among pilots and aircraft manufacturers, due to the widespread dissemination of misleading explanations. This paper aims to clarify these misconceptions by first examining the flawed theories, then presenting a more accurate and physically grounded explanation of lift, supported by real- world examples and calculations. Understanding the correct principles is crucial for both scientific accuracy and practical application in aviation.
Target Detection Techniques in Radar Systems: Introduction, Challenges, Opportunities and Applications
Target detection technique is one of the foremost important aspects for surveillance and tracking system in aerospace. This review paper delves in detail with covering the major concerns on the conceptual as well as theoretical concepts required for the suitable space mission requirements. It also highlights the challenges, opportunities and applications for the radar system in aerospace sector. Overall, the detailed review summary has been provided to understand the working aspects of radar tracking systems about its types and other major concepts.
SOLARAS S2: An Overview of India’s Private Solar CubeSat Mission
The frequent development of small satellite technology has made access to space more reliable and flexible for scientific research for educational and technology testing mission purposes. SOLARAS S2 is 1U CubeSat satellite developed by Grahaa space as part of its early nanosatellite development works. The main goal of the mission is to test key spacecraft subsystems while carrying out experimental studies related to solar radiation and satellite communication performance. The satellite is scheduled for launch as a rideshare payload aboard South Korea’s HANBIT-NANO, operated by Innospace, from the Alcântara Space Center by end of December 2025, and is intended to be placed into a low Earth orbit at an altitude of about 300 km. SOLARAS S2 operates an open and non-commercial technology illustration mission, by continually transmitting telemetry and beacon signals in the UHF and VHF bands around the world to receive and analyze the signals, supporting satellite health monitoring, signal behaviour studies, and leaning activities. The spacecraft follows standard 1U CubeSat design, featuring a small structure, limited power availability, and modular subsystems suited for early in-orbit testing. Although with technical and scientific goals, the mission emphasized regulatory compliance through formal registration with international telecommunication union, ensuring official use of radio-frequency spectrums for mission. Overall, SOLARAS S2 shows smaller size satellites can provide affordable and sustainable missions while supporting future nanosatellite and constellation development.
Aerodynamics of Re-entry Vehicles on Mars: Balancing Heat Shield Design and Efficiency
The design of re-entry vehicles for Mars is one of the toughest challenges in aerospace engineering. It requires careful integration of aerodynamic efficiency and thermal protection. Unlike Earth, Mars has a thin atmosphere made mostly of carbon dioxide. This atmosphere offers limited aerodynamic braking while still generating intense heat during hypersonic entry. This unique environment requires balancing the need to minimize heat shield mass with ensuring enough thermal resilience. Systems that are overdesigned reduce payload capacity, while those that are underdesigned risk mission failure. This paper looks at the aerodynamics of Mars re-entry vehicles, focusing on blunt-body and lifting-body shapes. It analyzes how entry trajectory affects peak heating and total thermal load, showing the trade-offs between shallow and steep descent profiles. The study also reviews thermal protection materials, including phenolic impregnated carbon ablators (PICA), ultra-high temperature ceramics (UHTCs), and new porous carbon ablators that improve radiation scattering. The paper examines innovative design approaches like deployable and inflatable heat shields, hypercone decelerators, and additive manufacturing of thermal protection systems. These methods could boost efficiency and reduce structural mass. Furthermore, it explores aerothermal interactions such as localized heating from surface protrusions and risks linked to boundary-layer transition in flexible shields. These aspects underline the importance of aerodynamic-thermal coupling in designing next-generation systems. By combining advancements in material science, aerodynamic improvement, and deployable designs, this research highlights a comprehensive approach to re-entry vehicle design. The findings suggest that future Mars missions will need hybrid solutions that blend ablative, ceramic, and flexible thermal protection systems to achieve safety and efficiency. Ultimately, achieving this balance will be crucial for reliably delivering larger payloads, supporting robotic missions, and paving the way for human exploration of the Martian surface.
Computational Flow Investigation on NACA 16-006 Airfoil at Varying Angle of Attack using Ansys Fluent
The aerodynamic performance of thin, symmetric airfoils remains critical for applications requiring low drag and stable behaviour across a wide range of operating conditions. This study represents a detailed computational investigation of the NACA 16-006 airfoil with a 1 m chord length operating at a freestream velocity of 100 m/s under constant atmospheric conditions. Numerical simulations were performed using ANSYS Fluent to evaluate aerodynamic characteristics across angles of attack ranging from 0° to 10°. Steady-state analyses employing the SST k–ω steady and turbulence model were initially conducted for 0°, 2°, 4°, and 6°, where the flow remained predominantly attached and produced stable convergence. However, significant fluctuations in aerodynamic coefficients observed at 6° indicated the onset of unsteady flow phenomena, prompting the transition to transient simulations for 6°, 8°, and 10°. At large angle of attack i.e., 10° the initial reflection of boundary layer separation occurs due of adverse pressure gradients and increased turbulence intensity. This study contributes to improved understanding of the NACA 16-006 airfoil’s performance and provides a validated numerical framework for analysing thin airfoils under mixed steady-unsteady flow regimes.
Mean Aerodynamic Flow Field of an Impinging Jet Issuing from a Convergent Nozzle with Varying Nozzle to Plate Distance
Jet impinging on a flat surface draws a lot of attention among the researchers working in the area of aerodynamics not only because of its complex flow physics, but also due to its wide range of applications. Starting from launch vehicles during lift-off to aircraft during vertical take-off and landing, jets impinge on the surfaces (inclined as well as flat surface) has wide range of applications. Due to these impingements, high thermal and pressure loads acts on the surface where jets are impinging. Besides these high acoustic levels as well as loss of lift also generates during this impingement. Numerical flow simulations are carried out using commercial CFD code to understand the flow physics of an impinging jet on a flat surface. Simulations are carried out at a nozzle pressure ratio of 5.0 with varying distance between the nozzle to plate. The results so obtained are analyzed in detail and are brought out in this paper.
The Impact of Zero Gravity on Human Bone Density - A Literature Review of Spaceflight Data
Spending months in space without gravity takes a serious toll on the human skeleton because without the constant pull of gravity, bones especially in the spine, hips, and legs, lose strength fast, breaking down at a rate of 1–2% per month. This review looks at decades of spaceflight research, from Skylab and Mir to the International Space Station and NASA’s Twins Study, to understand why this happens, how fast it occurs, and what can be done about it. The problem starts with the lack of mechanical loading, which signals bone cells to stop building new tissue while continuing to break down old bone. Changes in calcium balance, hormones, and other body systems make things worse, and recovery after returning to Earth is often incomplete. Astronauts currently rely on intense exercise, bone-protecting drugs, and carefully planned diets, but these are known to only slow down the losses. New ideas like creating artificial gravity, redesigning spacecraft for better loading, using personalized health plans, and monitoring bone health in real time could help protect future crews on missions to Mars or the Moon, and even space tourists. Ultimately, solving this problem is the key for space exploration and improving bone health here on Earth.
Design, Implementation, and Flight Validation Strategy of AkSat U2 and ViskanSat Sub-Orbital Picosatellite Platforms aboard the Rhumi-1 Sounding Rocket
This study presents the design rationale, subsystem implementation, and comparative evaluation of two sub-orbital picosatellite demonstrators, AkSat U2 and ViskanSat, developed as ultra-compact, low-cost platforms for near-space technology validation aboard the Space Zone Aerospace’s Rhumi-1 sounding rocket. Both systems employ an identical mechanical form factor, avionics architecture, and power subsystem to enable controlled performance comparison under the same flight conditions. Each demonstrator integrates a 3D-printed structural enclosure, an ESP32-based microcontroller, a high-resolution MS5611 barometric pressure sensor, and an MPU6050 inertial measurement unit to support autonomous data logging of altitude, inertial dynamics, and thermal variations during ascent, coast, and descent. The Rhumi-1 sub-orbital trajectory, reaching altitudes of approximately 30–75 km, provides a relevant test environment for evaluating sensor fidelity, structural robustness, and low-power operational strategies under rapidly changing atmospheric and dynamic conditions. Pre-flight characterization and comparative analysis indicate strong performance consistency between the two platforms, demonstrating manufacturing repeatability and subsystem reliability. The results reinforce the effectiveness of low-cost picosatellite demonstrators as scalable technology-readiness tools for future balloon-borne, aerial, and femtosatellite orbital missions.