The Acceleron Aerospace Journal (AAJ) with E-ISSN: 2583-9942 (Online), is the first international and exclusive publishing platform to support innovative and cutting-edge research across sophomores and graduate scholars. The journal publishes a substantial number of articles, categorizing them under student and scholar papers across diverse disciplines, including general sciences, space advancements, aerospace sciences, aeronautics, astronautics, cutting-edge engineering technologies, and various interconnected dimensions related to space exploration. Additionally, the journal has achieved significant Impact Factor of 5.437 [ABCD-Index-FY 2023-2024] and holds an exceptional index in major databases such as Google Scholar, Scilit, NASA Astrophysics Data System, CORE, Semantic Scholar, ResearchGate, Directory of Research Journal Index, Asian Science Citation Index, WorldCat Index, Open Ukrainian Citation Index, and Miscellaneous. Moreover, the journal operates on an Open Access (OA) model, making complete articles publicly available for reading without subscription, thereby enhancing accessibility for global researchers. Furthermore, the editorial team and reviewers, located in India, Germany, and Sweden, ensure the quality of the journal's content. The editorial flow and management are facilitated by the Open Journal Systems (OJS) from PKP/Simon Fraser University. Most Popular Articles Aerospace and Space Sciences [1] Mushrooms to Mars: Harnessing Fungi for Sustainable Human Settlements, Vol 2, Issue 2, 2024. [2] The Common Heritage of Mankind and the Rights of Future Generations in Outer Space Exploration: The Ethical Frontier, Vol 3, Issue 1, 2024. [3] A Short Review on India’s Interplanetary Missions, Vol 2, Issue 1, 2024. [4] Advancements in Lightweight Materials for Aerospace Structures: A Comprehensive Review, Vol 2, Issue 3, 2024 [5] A Comprehensive Review on Nuclear Thermal Propulsion System: Solid Core Design [6] Technical Overview and Prospect of India’s First Solar Mission - Aditya L1 Spacecraft, Vol 1, Issue 3, 2024 Astronomy [1] Review on Photometric Study of Variable Stars [2] Exploring the Role of Gravitational Waves in the Evolution of the Universe: Tracing Origins in Overlapping Gravitational Waves [3] Metamorphosis of Saturn: Unveiling Transformations in Ring Oppositions and Planetary Dynamics [4] The Role of Gravitational Waves in Understanding the Cosmic Evolution and The Underlying Physics of The Universe Journal Metrics, Indexing, and Submission Categories [From 2023 to 2025] Metrics Details Major Indexing Submission Category Authors (From India & Abroad) 260+ Google Scholar Research Article Papers Received 350+ Scilit [MDPI] Review Article Papers Published 180+ NASA ADS Conceptual Paper Journal Acceptance Rate 93% CORE UK Conference Paper Average Review Time 28-45 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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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.
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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.
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.
Probing Exoplanet Atmospheres through Stellar Occultations: A Case Study of WASP-32b
The study of exoplanets provides crucial insights into the nature of planetary atmospheres and orbital dynamics. Transit photometry and secondary eclipse observations have become revolutionary tools in this field. This case study focuses on WASP-32b, a hot Jupiter orbiting an F-type star about 950 light years away in the constellation Pisces. Our objective is to probe the atmospheric and orbital characteristics of WASP-32b through light curve analysis. Data were collected from both ground-based and space-based observatories. SuperWASP-South at the South African Astronomical Observatory first detected WASP-32b using transit photometry. The Swiss Euler Telescope at La Silla Observatory and its CORALIE spectrograph provided radial velocity confirmation, planetary mass, and orbital parameters. Space telescopes contributed complementary data: the Spitzer Space Telescope measured secondary eclipse photometry in the infrared (3.6 µm and 4.5 µm), constraining thermal emission and albedo, while TESS delivered high-precision optical transit data that refined planetary radius and orbital period. Analysis of these datasets reveals signatures of thermal emission, constraints on reflective properties, and preliminary indications of atmospheric circulation. The results underline the importance of multi-wavelength light curves for atmospheric characterization and establish WASP-32b as a significant benchmark for understanding hot Jupiter systems
Rotational Detonation Engines: A Comprehensive Review of Thermodynamic Advantages and Engineering Challenges
Rotational Detonation Engines (RDEs) are considered to be new generation propulsion systems that achieve an increase in thermodynamic efficiency, relative to traditional constant pressure combustion-based engines. Although the theoretical and computational models are extensive and predict significant benefits in terms of specific impulse, engine size, and fuel efficiency, practical use so far has been limited because of a number of as yet unresolved engineering issues. The objective of this paper is therefore to close the gap between theoretical potential and practical application by looking at the underlying physics, design limitations, recent successful experiments, and prospects of RDEs. From the analysis, we identify the main hurdles and the paths for progressing RDEs from laboratory demonstrators to flight propulsion systems.
Autonomous Orbit Changing and Out-of-the Orbit to Interstellar Point Maneuvering: A Novel Concept
A satellite, throughout its operational lifetime, typically follows a pre-defined orbit, which restricts its ability to observe only specific regions on Earth. This paper explores methods by which a satellite can modify its current orbit and transition to a newly defined trajectory to expand its coverage and increase the number of observable locations on Earth’s surface. Furthermore, the paper describes how a satellite can temporarily depart from its orbital regime and travel into deep space for the purpose of observing astronomical events before returning to its designated orbit. To support these advanced maneuvers, a conceptual framework for trajectory planning is presented, detailing the sequence of operations required for seamless orbital changes and deep-space excursions. The entire process including transitioning to a new orbit, conducting interstellar observations, and autonomously returning to the original orbits designed to be executed automatically once an appropriate trigger or mission command is received. Additionally, the paper discusses the potential advantages, limitations, and technical challenges associated with such autonomous orbital and deep-space operations.
AI-Based Predictive Laser Beam Control for UAV Interception in Directed Energy Weapon Systems Using Velocity-Based Trajectory Prediction
The rapid proliferation of unmanned aerial vehicles (UAVs) in defence and surveillance zones presents an escalating challenge to national security, demanding the deployment of agile, real-time interception systems. While high-energy laser-based directed energy weapons (DEWs) provide a non-kinetic alternative to missile defence, their performance is hampered by actuator latency, beam jitter, and inability to track erratically manoeuvring drones. To overcome these challenges, this study proposes a novel AI-augmented predictive beam control framework that anticipates UAV trajectories by estimating future positions using velocity-informed regression modelling. The system, developed in MATLAB, simulates and predicts evasive UAV motions sinusoidal, zigzag, and spiral through a shallow neural network trained on synthetic trajectory data. It incorporates beam delay modelling and sinusoidal jitter to replicate real-world laser transmission imperfections. The predictive model achieves a tracking accuracy of 94.12% and a mean squared error (MSE) of 0.1834, validated across diverse UAV paths. Key simulation outcomes include six comparative trajectory plots, error histograms, and cumulative accuracy profiles that highlight the system’s robustness. This research contributes (i) an integrated beam latency compensation module for predictive DEWs, (ii) a simulation dataset curated from recent UAV motion and targeting literature, and (iii) a control framework extendable to reinforcement learning (RL) and Kalman filtering approaches for adaptive targeting. The proposed framework advances the design of autonomous DEW systems by enhancing hit accuracy, energy efficiency, and responsiveness in contested aerial environments. The framework’s modular design enables extensions to real-world testing and broader applications in high-speed target tracking beyond defence systems.
Computational Investigation of Combustion Efficiency in LOX-HTPB Hybrid Rocket Motors
Hybrid rocket engines that use hydroxyl-terminated polybutadiene (HTPB) fuel and liquid oxygen (LOX) oxidiser are appealing because they are safe, work well, and are good for the environment. Nevertheless, combustion efficiency is still low because the oxidiser and fuel are not mixed well enough. This study offers a computational and experimental analysis of the internal ballistics of LOX–HTPB hybrid motors, focusing on injector design and chamber flow dynamics. CFD simulations validated with experimental data were used to compare swirl and pintle injectors to baseline injectors. The results show that pintle and tangential swirl injectors make combustion more efficient by improving the distribution of oxygen, turbulence, and pressure uniformity. The results show how to make the design of injectors and chambers better in hybrid propulsion systems.
Automatic Navigation Map Decomposition for Efficient Reinforcement Learning
Safe navigation in an environment with obstacles is a challenging problem. Reinforcement learning (RL) is a promising approach to solve the problem. However, RL often suffers lengthy training time with large maps. This paper presents an algorithm to decompose a map into smaller regions to enable efficient RL. The approach is based on the use of generalized Voronoi Diagrams. The idea is to decompose a large map into a set of regions that are free of crossroads, which greatly reduces the state complexity. In the experiments, the method is applied to decompose six maps. The results show that the approach is effective and efficient.
Bio-Inspired Flapping Wing Micro Aerial Vehicle: Blade Element Modeling and Experimental Flight Validation
Flapping wing micro aerial vehicles (MAVs), inspired by biological flight, offer advantages in acoustic stealth, aerodynamic efficiency, and mechanical resilience over rotary-wing platforms. This study presents the design, aerodynamic modeling, and fabrication of a bird-sized flapping-wing UAV. Employing empirical formulations from classical flight dynamics, structural and mechanical configurations were created with advanced design tools. Aerodynamic performance was predicted using quasi-steady blade element theory and advanced computational methods. Simulations confirmed that lift and thrust exceeded vehicle weight and drag, indicating viable sustained flight. The prototype was constructed using lightweight composite materials, carbon fiber for the fuselage and carbon rods with parachute fabric for wings and tail. A three-bar linkage mechanism converted motor input into oscillatory wing motion, with passive spanwise rotation optimizing the angle-of-attack throughout flapping cycles. Ground tests validated the aerodynamic predictions by demonstrating sufficient lift generation. This work provides a foundational platform for future research in bio-inspired MAVs, specifically targeting autonomous surveillance, lightweight propulsion, and low-speed maneuverability. Flutter analysis also identified a critical flutter velocity of approximately 415 m/s.
Laser-Based Thorium Processing and Utilization for In-Situ Nuclear Power Generation in Space Exploration: A Comprehensive Review
The growing need for long-duration, high-density energy systems in space has revitalized interest in nuclear fission for extraterrestrial missions. Thorium (Th-232), with its favourable nuclear characteristics, long half-life, and planetary abundance, offers a promising alternative to uranium for compact, low-maintenance power systems on the Moon and Mars. Simultaneously, laser-based materials processing has emerged as a key enabler for precision manufacturing, in-situ resource utilization (ISRU), and real-time elemental analysis in space-like conditions. This review explores the integration of laser-based techniques in the extraction, fabrication, and application of thorium-bearing materials for space nuclear systems. It covers laser ablation and laser-induced breakdown spectroscopy (LIBS) for thorium detection in regolith, laser sintering and melting for fuel preparation, and additive manufacturing approaches for producing radiation-tolerant components. Advances in simulation and thermal modelling of laser–material interactions are reviewed, alongside key challenges such as radioactive handling, microgravity effects, and material degradation. Current experimental gaps and technology readiness limitations are identified, and a development roadmap is proposed. The findings highlight the potential of laser-assisted thorium processing as a critical enabler of sustainable, deployable space nuclear power systems.
Unsupervised Classification of Binary SMBH Candidates in Gaia DR3: A Machine Learning Approach to Astrometric Jitter and Cluster-Based Candidate Identification
We present an unsupervised machine learning analysis of astrometric variability in Gaia DR3 quasars, aimed at identifying indirect signatures of unresolved binary supermassive black holes (SMBHBs). Using a filtered sample of ∼10,000 high-quality quasars, we extract key features including RUWE, astrometric excess noise, parallax, color index, and G-band magnitude. These features are normalized and reduced using Principal Component Analysis (PCA) and t-distributed Stochastic Neighbor Embedding (t-SNE) to uncover low-dimensional structure. We apply both K-Means and DBSCAN clustering algorithms to the projected feature space. The K-Means algorithm identifies three distinct populations, with one cluster exhibiting statistically higher excess noise and intermediate RUWE values, suggestive of potential centroid jitter induced by binary SMBH orbital motion. The clustering results are further validated using silhouette scores and consistent spatial separability in t-SNE projections. A catalog of candidate high-jitter quasars is compiled from the most deviant cluster, comprising over 3500 sources. These candidates are promising targets for future multi-wavelength follow-up using VLBI, variability surveys, and higher-precision Gaia astrometry. Our work demonstrates that unsupervised learning techniques offer a powerful, scalable alternative to classical threshold-based methods for probing the hidden binary SMBH population at cosmological distances. This study represents one of the first applications of machine learning to stochastic astrometric variability in extragalactic sources and provides a reproducible framework for future discovery in Gaia DR4 and LSST-era datasets.
CFD-Based Analysis of Divergent Section Deflection for Thrust Vector Control in 2D Nozzles
This study presents a computational fluid dynamics (CFD) analysis of thrust vector control (TVC) through mechanical deflection of the divergent section in a 2D convergent-divergent nozzle. Using CATIA, three nozzle configurations with deflection angles of 15°, 20°, and 25° were designed and simulated in ANSYS Fluent under identical boundary conditions. Air was modeled as an ideal gas with temperature-dependent viscosity, and the simulations employed a density-based, steady-state solver with the SST k-ω turbulence model. High-resolution unstructured meshing with wall inflation layers ensured accurate capture of near-wall effects, flow separation, and shock formations. The results reveal how variations in divergent geometry influence internal flow characteristics, including Mach number, pressure distribution, temperature gradients, and mass flow rate. Particular attention was given to the generation and interaction of oblique shock waves at higher deflection angles. The findings provide insight into nozzle performance, thrust deviation, and shock-induced flow asymmetries, contributing to more effective TVC system design in aerospace applications.
Theoretical Modeling and Design of a Coaxial-Swirl Injector and Thruster Components for MMH/NTO-Based Upper Stage Thrusters
Coaxial swirl injectors solve the major problem when it comes to liquid propulsion, which is the mixing of the fuel and oxidizer. It helps by mixing the fuel at an atomic level and making sure that the mixture is even. This paper focuses on the design of an engine with coaxial swirl injector faceplate using hypergolic propellant. The major problem with the hypergolic propellant is that it ignites on contact, but with the help of a coaxial swirl injector we can take it as an advantage by modifying the spray cone angle so that the contact point is at an optimal distance. The work entails the design of a modified coaxial swirl injector for hypergolic propellants which is then integrated into a faceplate with multiple injectors. Then, with the help of the dimensions of the faceplate, the combustion chamber is designed to withstand the simultaneous instant combustion from the multiple injectors, which is then focused onto the custom-designed nozzle to maximize the output thrust.
Integrating Artificial Intelligence with Space-Based ADS-B for Next-Generation Space Traffic Management
This paper explores into the concept of space traffic management using current aircraft navigation and surveillance systems such as ADS-B technologies, along with artificial intelligence (AI). This paper conducts a feasibility study on the use of present ADS-B systems that are modified for space flight and satellite surveillance. The scope of the paper focuses on mainly the surveillance of commercial space flights, as well as sub-orbital space vehicles (such as reusable launch vehicles, satellites in low earth orbit (LEO), etc.), and the potential safety hazards that can be posed. The objective of this study is to build a model to manage space traffic along with commercial air traffic simultaneously, while also focusing on tracking and guiding space traffic, to ensure safe operations. A conceptual view of the model, along with the introduction of ADS-B, how it works and the integration of it, with AI, potential limitations and hazards that can occur and possible solutions to these are explained, and recommendations for future studies is also mentioned. The proposed idea could use the help of the current trends of AI and Machine Learning that will be instrumental in the future for making such models more efficient, reliable and safer. Hence, this paper explores the idea of AI-enhanced ADS-B Systems for Space Traffic. By using AI and Machine Learning to optimize the efficiency of ADS-B, it was found that anomalies could be easily detected quicker [1], safety could be improved, analysis of flight path regions could be automated, etc.