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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Ahead of Print Policy Accepted manuscripts are published online as Ahead of Print articles and assigned a DOI prior to formal issue assignment, ensuring the earliest possible availability of research to the scholarly community. Content Registration and DOI Policy All peer-reviewed articles are registered with Crossref and assigned a unique Digital Object Identifier (DOI) to ensure permanent identification, discoverability, and citability across global scholarly databases. 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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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.
Copyright (c) 2026 Acceleron Aerospace Journal https://creativecommons.org/licenses/by/4.0
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.
Computational Outcome Validation & Evaluation of a Transport Aircraft Analysis
The results of a computational study that was carried out to examine Euler flow over a traditional transport aircraft are covered in this paper. At Mach 0.15, the analysis has been carried out for a range of angles of attack and sideslip combinations. CFD ACE+ Navier Stokes solver is used for analysis and simulation. The angle of attack has been changed in 6-degree increments from 0 to 18 degrees for sideslip values of 0, 6, and 12. The computations are performed using the Origin 3000, an SGI server. A recent study on grid independence demonstrated that a mesh size of 2,079,082 cells was optimal for achieving accurate computational results in fluid dynamics simulations. This determination was based on a systematic refinement approach, where various mesh configurations were evaluated for their impact on solution convergence and accuracy. The analysis revealed that this specific cell count effectively balanced computational efficiency with numerical precision, as further refinement yielded diminishing returns with respect to error reduction. Additionally, the use of this ideal mesh size minimized resource consumption while ensuring that key flow characteristics were captured without significant artifacts or discrepancies often associated with coarser grids. Ultimately, the findings underscore the importance of meticulous grid selection in simulation practices to enhance robustness and reliability in predictive modeling across engineering applications.
Life In Space, Beyond Earth: Habitability In Question – Between Astrobiology and Aerospace Medicine
The search for life beyond Earth and the possibility of human habitation in space constitute significantly interdisciplinary scientific challenges, especially involving astrobiology and aerospace medicine. Astrobiology investigates the conditions of the emergence of life on Earth and the possible existence of living beings on other worlds, with emphasis on habitability studies for biosignature detection. Aerospace medicine focuses on the physiological and psychological impacts that the space environment, marked by cosmic radiation, microgravity, and confinement, among other aspects, imposes on human beings. This article aims to analyze the contributions of these fields to the contemporary debate on the habitability of extraterrestrial celestial bodies. For these means, an integrative literature review was carried out based on descriptors selected from DeCS, which, when combined, were used for the bibliographic search in PubMed. Twenty-nine articles were selected to compose this current manuscript, whose information was organized into three topics in the Results and Discussion section: (i) "Astrobiology and habitability," (ii) Aerospace medicine and habitability; and (iii) "Syntheses: Life sciences in search of space colonization." The convergence between these disciplines, their integration of knowledge, from identifying potentially habitable exoplanets to ensuring astronaut health, is fundamental to enabling long-duration missions and future space colonization, transforming human activity in the cosmos from a fictional possibility into a sustainable scientific reality, based on collaboration and transdisciplinary innovation.
Conceptual Design and Aerodynamic Analysis of Medium Altitude Long Endurance VTOL Fixed wing UAV
This paper presents the conceptual design and multidisciplinary analysis of a Medium-Altitude Long-Endurance (MALE) Unmanned Aerial Vehicle (UAV) featuring a hybrid Vertical Take-Off and Landing (VTOL) and fixed-wing configuration. The design is driven by demanding mission requirements, including a 650 kg maximum take-off weight, a 100 kg payload capacity, a 200 km operational range, and an endurance of 10 hours at altitudes up to 7000 meters. The proposed twin-boom aircraft integrates an eight-rotor electric VTOL system for vertical flight and a conventional internal combustion engine (Rotax 914 ULF) for efficient forward cruise. The design process followed a systematic approach, beginning with initial sizing and weight estimation using empirical relations from Raymer's methodology, which established a baseline weight distribution. Constraint analysis identified the VTOL-to-cruise transition phase as the most critical, governing the thrust-to-weight ratio and wing loading. Aerodynamic design focused on the high-lift S1223 airfoil, with performance analyzed using XFLR5 and OpenVSP software to optimize the lift-to-drag ratio. Stability and control analysis were conducted to determine the optimal tail arm length of 3.85 meters, ensuring longitudinal and lateral stability, with the vertical stabilizer airfoil selection (NACA 0020) proving crucial for directional stability. Key results demonstrate a feasible design with an empty weight of 352 kg, a fuel weight of 185 kg, and a calculated cruise power requirement of 26 kW. The VTOL system requires a peak power of approximately 233 kW, met by eight 30 kW electric motors. The study concludes that the proposed VTOL fixed-wing UAV successfully balances the competing demands of vertical flight capability and long-endurance cruise performance. The insights and methodologies presented provide a robust foundation for future detailed design, prototyping, and flight testing of advanced hybrid UAVs.
A Low-Cost, Modular Avionics and Thrust Vector Control Architecture for Experimental Rocketry
This paper presents comprehensive results from our prototype demonstration of future rocket avionics and control systems. A thorough literature survey identified key technological gaps, particularly concerning cost-effectiveness and deployment flexibility. Rigorous testing for maneuvering time improvements validated enhanced performance through the implementation of an innovative thrust vector control (TVC) system. The study tackles the long-standing industry issue of high-cost avionics by proposing modular, cost-efficient substitutes that are as reliable but significantly lower in cost barriers to entry. A notable in- novation is the development of portable instrumentation systems capable of being deployed and operated in diverse environments, thereby overcoming traditional location constraints. The thrust vector control system uses solid motor configurations, a significant step away from the traditional approach. In addition, the study explores the scalability and practical feasibility of hybrid propulsion systems, especially under conditions of adequate funding and resource allocation. The main contribution lies in the integrated avionics and control system architecture, which strikes a balance between advanced functionality and operation simplicity. All developmental activities adhered strictly to recognized industrial standards, with particular emphasis on safety protocols. This research pushes the democratization of rocket science by offering robust, low-cost systems that preserve performance integrity while increasing accessibility to a wider variety of applications.
Numerical Investigation of Oblique Shock Attachment, Stand-Off Distance and Shock Thickness over a 25°Wedge
: This work presents a computational study of oblique shock behavior over a fixed 25° wedge for supersonic free-stream Mach numbers M∞=2, 3, 4. Two-dimensional viscous simulations were performed with ANSYS Fluent (density-based solver, SST k −ω turbulence model, energy equation on) on a fine unstructured triangular mesh with prism inflation near the wedge. For M∞=2 the shock detaches producing a bow shock with measured stand-off distance δ≈6.26×10−4 m. For M∞=3 and the oblique shock attaches at the wedge apex. Shock angles were measured from Mach contours and validated against the analytical θ–β–M relation; percent differences are small (≈0.8–0.9%). Shock thicknesses were quantified from density and density-gradient line profiles (reported values from simulation notes: M2 ≈ 0.32 mm, M3 ≈ 0.25 mm, M4 ≈ 0.20 mm), showing a clear decrease with increasing Mach number. Detailed methodology, mesh statistics, theory comparison, and uncertainty estimates are provided. Future work will extend the parametric study to wedge angle variation, Reynolds number effects and experimental validation.
An Optimized Hybrid CDN-P2P Framework for Efficient Live Streaming: Design, Implementation, and Evaluation
The rapid growth of live video streaming has highlighted critical limitations in traditional Content Delivery Networks (CDNs), particularly their high costs and scalability constraints during traffic surges. While Peer-to-Peer (P2P) networks offer a more scalable and cost-efficient alternative, their reliability remains inconsistent due to variable peer performance. This study introduces an optimized hybrid CDN-P2P framework designed to balance stability and scalability for efficient live streaming. At its core is a dynamic scheduling algorithm, HQACS (Hybrid QoS-Aware Chunk Scheduler), which intelligently prioritizes P2P transmission when peers meet predefined quality thresholds, such as an upload speed exceeding 3 Mbps and uptime above 85%, while seamlessly switching to CDN support for critical data segments or unstable conditions. The framework was implemented using open-source tools, including Python, Node.js, and Web Torrent, and evaluated through realistic simulations. Results demonstrated a peak P2P throughput of 16.5 MB/s, an average latency of 148 MS, and 88% of video chunks delivered via P2P, reducing CDN reliance to just 12%. These findings underscore the system’s adaptability through intelligent peer selection and robust fallback mechanisms. This research contributes a cost-effective, scalable, and low-latency solution for modern streaming platforms by merging CDN reliability with P2P flexibility. Future work should explore reinforcement learning for adaptive decision-making and large-scale deployments to further refine performance under diverse network conditions. The proposed framework holds significant promise for both academic research and industry applications, offering a practical approach to enhancing live streaming efficiency.
An Overlay Management Strategy to Enhance Peer Stability in P2P Live Streaming Systems
Peer-to-Peer (P2P) live streaming systems face persistent challenges due to dynamic peer participation, unpredictable churn, and fluctuating network conditions. This study introduces SPOM (Stable Peer Overlay Manager), a novel overlay management strategy based on preferential attachment, designed to enhance peer stability and network resilience. The approach prioritizes high-degree nodes to strengthen connectivity, minimize service disruptions from peer turnover, and optimize resource utilization for continuous streaming. The proposed method was evaluated using the Gnutella P2P dataset within a Python-based simulation environment, leveraging the Network framework. Key performance metrics including node degree distribution, clustering coefficient, and churn resilience demonstrated significant improvements. Results showed a network expansion of 10,000 additional edges, a 23.9% increase in average node degree (from 7.35 to 9.11), and enhanced local clustering, indicating a more robust overlay structure. Comparative analysis against random and cluster-based strategies revealed superior performance in reducing latency and maintaining fault tolerance during streaming sessions. These findings highlight the efficacy of structured, preference-driven overlay management in real-world P2P systems. The study contributes actionable insights for decentralized media delivery, offering scalable solutions to improve Quality of Service (QoS) in dynamic environments. Future research directions include adaptive enhancements via machine learning and deployment in heterogeneous and mobile networks to further strengthen resilience under high churn.
Navigation through Extended Phase Manifolds: A Falsifiable Framework for Faster-than-Light Translation
We present a framework for navigation through an extended phase manifold (M, g, Φ) in which conventional Lorentzian trajectories admit embeddings into oscillatory domains. Within this formulation, faster-than-light (FTL) travel is not interpreted as exceeding the invariant speed ccc, but as realignment of geodesics through laminar corridors defined by bounded phase curvature. Astrophysical systems provide natural anchors: black hole quasi-normal mode spectra function as central reference combs; pulsar timing drifts supply intermediate invariants; and stellar oscillations offer regional stabilization. Together these form hierarchical anchor constellations analogous to terrestrial navigation grids. Translation operators embed Einstein tensors, twistor null lines, and causal fermion operator invariants into oscillatory form, ensuring compatibility across established frameworks. A stepwise, falsifiable developmental pathway is outlined: (i) laboratory analogues (optical Möbius fibers, analogue horizons) demonstrating comb invariants and jitter scaling; (ii) twin-cavity locks enforcing Zero-Error Lock (ZEL) criteria; (iii) astrophysical HAC triangulation; (iv) solar-system probe fold-lock tests; (v) volumetric corridor trials with adiabatic boundaries; and (vi) cross-framework consistency with twistor and CFS formulations. Safety protocols include invariant-based ZEL gating, crest-hold stabilization, return-lock recovery, and no- signalling compliance. The framework is therefore calculable, falsifiable, and experimentally approachable, reframing FTL not as propulsion but as navigation through an extended manifold structure.
The Harmonic Lifecycle of Black Holes: The Spiral Collapse into White Space
We present a harmonic framework for the anatomy and lifecycle of black holes, weaving conventional astrophysics with our pre-existing works on the PETAL-native architecture of primes, residuals, and White Space. Black holes, in this view, are not dead ends but recursive return pathways: spiral collapse vectors that retrace the same prime-sequence scaffold which first carried the universe outward from the primordial asymmetry. The anatomy of the black hole horizon, singularity, accretion disk, curvature tension, and Hawking whispers can be written both as equations and as harmonic organs, each with falsifiable predictions. Ringdown data already hints at prime-aligned combs, while Hawking radiation emerges as the irreducible residual squeezed from collapse. We outline a full harmonic lifecycle: birth in accretion, spiral descent along the prime ladder, residual exhalation, evaporation, and reconciliation into White Space, leaving fossil fireballs inscribed as voids and background scars. Each stage carries testable signatures. To study black holes, we argue, is to study the recursive structure of being itself, expansion and collapse, noise and silence, form and signal, each reconciled in the return to origin.