ESEO satellite thermal model design analysis and validation of thermal solutionsShokry, A.M; Esmat, Ahmed; Elnaggar, W. M.; Elbayoumi, Mohamed
doi: 10.1088/1742-6596/3070/1/012023pmid: N/A
This paper focuses on the analysis and investigating the design of thermal control subsystem for a small satellite operating in low Earth orbit (LEO). The European Student Earth Orbiter (ESEO) satellite was selected as the subject of this study. The primary goal of the thermal control subsystem is to guarantee the proper operation against the hard conditions of environment in space. The goal is to certify that the maximum and minimum temperatures of the panel’s lower sheet remain within the specified design range. Thermal analysis was implemented using commercially available tools. The comparison between the results showed that maximum Hot Case (1) temperature difference is 2.12 ℃ in panel (3), maximum Hot Case (2) temperature difference is 2.61 ℃ AMSAT. maximum cold Case (3) temperature difference is 1.68 ℃ in SOLAR PANEL (+Z). maximum cold Case (4) temperature difference is 2.05 ℃ in SOLAR PANEL (+X).
Peer Review Statementdoi: 10.1088/1742-6596/3070/1/011002pmid: N/A
All papers published in this volume have been reviewed through processes administered by the Editors. Reviews were conducted by expert referees to the professional and scientific standards expected of a proceedings journal published by IOP Publishing.• Type of peer review: Double Anonymous• Conference submission management system: Morressier• Number of submissions received: 36• Number of submissions sent for review: 36• Number of submissions accepted: 31• Acceptance Rate (Submissions Accepted / Submissions Received × 100): 86.1• Average number of reviews per paper: 2• Total number of reviewers involved: 24• Contact person for queries:Name: Mohamed AbdelwahidEmail: [email protected]: Rapporteur
Design & Analysis of a Hot Air-Assisted Flying Wing UAV with Solar Energy Systems for Flight Time EnhancementShahin, Abdelrahman A.; Aboelkasim, Ezzeldeen M.; Awad, Abdelrahman E.; Sakr, Ali A.; Balat, Amr K.; Hassanein, Mahmoud A.; El-Bahloul, Sara A.; Seddik Moustafa, Wael
doi: 10.1088/1742-6596/3070/1/012010pmid: N/A
The growing demand for energy-efficient unmanned aerial vehicles (UAVs) has spurred research into alternative power and lift-enhancing mechanisms to improve flight duration and operational efficiency. Solar film technology has been widely explored, offering lightweight energy solutions that significantly extend UAV endurance. However, integrating active hot air lift mechanisms with solar energy systems remains largely unexplored. This research bridges this gap by proposing and analyzing a hybrid UAV system that incorporates solar film technology and onboard hot air lift-enhancing mechanisms. The proposed system aims to optimize energy utilization and increase flight duration by leveraging the complementary properties of solar and thermal technologies. Using a design of experiments (DOE) approach, the optimal configuration was identified as an ogival delta wing shape, S1223 airfoil, and 150°C hot air system. Results showed a 3.86% reduction in apparent weight due to hot air buoyancy, enhancing flight endurance by approximately 4% compared to a solar-only configuration. These findings demonstrate the viability of integrating solar and thermal systems for energy-efficient and sustainable UAV design.
Development of a Physics-Based Dynamic Model For a Micro Gas Turbine EngineIbrahem, Ibrahem M.A
doi: 10.1088/1742-6596/3070/1/012016pmid: N/A
This paper presents a physics-based, detailed nonlinear dynamic mathematical model (MTCturb) of a micro SR-30 gas turbine engine (GTE) using a component matching method. The model integrates individual component of the gas turbine engine capturing thermodynamic and aerodynamic interactions through nonlinear dynamic equations. MTCturb is designed to predict the engine shaft speed (RPM) response with fuel flow as the primary input, accurately simulating both transient and steady-state performance under varying operating conditions. The model is validated against experimental data and high-fidelity simulation results from GasTurb 10, demonstrating strong agreement and confirming its accuracy and predictive capability. Additionally, a graphical user interface (GUI) is developed in MATLAB to enhance model accessibility, enabling users to interactively visualize simulations, adjust input parameters, and analyze system responses. This work provides a valuable tool for control design, optimization, and further research on gas turbine dynamics.
Enhancing Earth-Mars Transfer Trajectories: A Conic Patch Method Using Evolutionary AlgorithmsAbdelaziz, A.M.; Tealib, S.K.
doi: 10.1088/1742-6596/3070/1/012019pmid: N/A
Given the importance of interplanetary transfers in celestial mechanics, this paper introduces a novel patched-conic method for designing interplanetary orbits, providing an optimized framework for mission planning. The transfer problem is formulated by identifying key parameters such as launch windows, transfer angles, and delta-v requirements, which are optimized using an evolutionary algorithm to minimize fuel consumption and flight duration. The study employs consecutive solutions to Lambert’s problem, focusing on the intersection points of conic sections to calculate the total transfer cost. The proposed method demonstrates rapid convergence, making it highly suitable for computational implementation and practical mission planning. This study presented an optimized interplanetary trajectory for a spacecraft traveling from Earth to Mars using the Particle Swarm Optimization (PSO) algorithm. The results successfully demonstrate the capability of PSO to minimize the total Δv required for the mission while ensuring adherence to mission constraints and achieving efficient flight times.
Hybrid Anomaly Detection in Spacecraft Telemetry Data Using Sparse Feature-Based Methods and Spatial-Temporal Generative Adversarial NetworksAkl, Amr; Elattar, Hatem
doi: 10.1088/1742-6596/3070/1/012021pmid: N/A
Anomaly detection in spacecraft telemetry data is critical for ensuring mission success and operational reliability. However, the high dimensionality, complex temporal dynamics, and multivariate nature of telemetry data pose significant challenges for traditional anomaly detection methods. This paper proposes a hybrid anomaly detection system that combines Sparse Feature-Based Anomaly Detection (SFAD) and Spatial-Temporal Generative Adversarial Networks (ST-GAN) to address these challenges. The SFAD module reduces dimensionality and extracts sparse features from telemetry data, while the ST-GAN module captures temporal dependencies and spatial correlations between parameters. Additionally, an adaptive thresholding mechanism is introduced to dynamically adjust the anomaly detection threshold, reducing false positives and improving robustness. The proposed system is evaluated on the SMAP and MSL datasets, demonstrating superior performance in terms of Precision, Recall, and F1-Score compared to state-of-the-art methods such as LSTM-GAN, GRU-VAE, and Isolation Forest. The results show that the hybrid approach is particularly effective at detecting multivariate and contextual anomalies, which are often missed by traditional methods. The system’s ability to perform near real-time anomaly detection makes it suitable for practical spacecraft monitoring applications. This work contributes to the field of telemetry analysis by providing a robust, scalable, and accurate solution for anomaly detection, with potential applications in other domains such as industrial monitoring and autonomous vehicles.
Aeroelastic Coupled Mode Behavior of Swept Composite WingElshazly, E.; Kassem, Mohammed; Elshafei, M. A.
doi: 10.1088/1742-6596/3070/1/012001pmid: N/A
The aeroelastic behavior of swept composite wings is predominantly governed by the coupling between bending and torsion modes due to the anisotropic characteristics of composite materials. This study analytically investigates the aeroelastic response of swept rectangular wings, modeled as carbon fiber/epoxy plates, to determine flutter and divergence speeds. The analytical approach integrates classical plate theory, Rayleigh-Ritz energy formulation, potential and kinetic energy equations, and unsteady incompressible two-dimensional aerodynamic theory within the Lagrange framework for free vibration and aeroelastic analyses. Numerical free vibration analysis is conducted using NASTRAN to validate the proposed analytical model. V-g curves are employed to extract flutter and divergence speeds, and the results exhibit excellent agreement with published findings. The study reveals that negative bending-torsion coupling stiffness significantly increases the likelihood of divergence occurring before flutter. Positive bending-torsion coupling significantly increases the divergence speed, effectively shifting the critical divergence speed beyond the typical flight envelope. Moreover, increasing the sweepback angle generally increases divergence speed. The effect on flutter speed is complex and depends on various factors, such as fiber orientation, stacking sequence, and bending-torsion coupling. These findings provide critical insights into aeroelastic behavior and offer a foundation for optimizing the performance and structural design of swept composite wings.
Influence of Winglets Design Parameters on Aerodynamic and Stability of a Blended Wing-Body AircraftSheneshen, Ahmed M; kamal, Ashraf M
doi: 10.1088/1742-6596/3070/1/012004pmid: N/A
The Blended Wing Body (BWB) aircraft is a non-conventional aerodynamic configuration that merges the fuselage and wings into a seamless structure, offering significant advantages in fuel efficiency, payload capacity, and aerodynamic efficiency. However, the absence of conventional tail units introduces aerodynamic and stability challenges that require careful design optimization. This study investigates the aerodynamic and static stability characteristics of a baseline BWB design from the European Distributed Multi-Disciplinary Design and Optimization (EU MOB) project. The analysis is performed using a mid-fidelity numerical tool based on the vortex lattice method, incorporating geometric and mass properties from previous studies. Aerodynamic curves and static stability derivatives are evaluated across a specific flight regime and compared with existing literature verifying the suitability of the used tool for preliminary aerodynamic and stability assessments. Subsequently, a parametric study is conducted to assess the effects of varying winglet design parameters, including height, sweep, cant, and toe angles, on aerodynamic efficiency and static stability characteristics. The results demonstrate that optimized winglet configurations can enhance lift-to-drag ratio and improve static stability characteristics without significantly increasing drag. These findings provide valuable insights into the role of winglets in improving BWB aircraft performance and contribute to the optimization of next-generation aerodynamic designs.
Parametric Investigation of Wing Geometric Characteristics for Enhancing UAV EnduranceHassouna, Shehab; Mohamed Kamal, Ashraf
doi: 10.1088/1742-6596/3070/1/012008pmid: N/A
Improving endurance in airplane design is important for specific types such as in medium altitude long endurance (MALE) unmanned aerial vehicle (UAV). Achieving this objective requires obtaining the best wing geometric characteristics that maximize the relevant aerodynamic parameters without compromising the overall performance. In this study, a parametric investigation is performed using the USAF DATCOM mid-fidelity aerodynamic tool to examine the effect of varying taper ratio, aspect ratio, and sweep angle on a baseline wing configuration of a case study MALE UAV. The analysis begins with evaluating the aerodynamic characteristics of the selected wing, followed by a systematic variation of the geometric parameters, while maintaining the original airfoil and wing area. First, thirty different wing configurations are generated by varying the taper and aspect ratios, from which the most aerodynamically efficient configuration is selected for further evaluation by varying the sweep angle. The results indicate that increasing aspect ratio has the most significant effect on improving endurance, followed by taper ratio, whereas increasing sweep angle reduces endurance.