Catalogue Search | MBRL
Are you sure you want to remove the book from the shelf?
{{itemTitle}}
98
result(s) for
"Airplanes Models Design and construction."
Sort by:
How to build aircraft
\"Take to the skies with How to Build Aircraft. Featuring simple step-by-step instructions, handy templates, vibrant photographs, and easily accessible materials, this title shows readers how to build their very own aircraft that can really fly! Projects include a hot-air balloon, roto-copter, a variety of gliders, and many more.\"-- Provided by publisher.
Book
Model Archiving and Sustainment for Aerospace Design
Model Archiving and Sustainment for Aerospace Design, written by Sean Barker, an industry veteran from the UK, focuses on the techniques developed by the LOTAR (Long Term Archiving and Retrieval) project, a collaboration among the major US and European aerospace companies. Long-term archiving models follows LOTAR by taking the exchange of mechanical CAD fi le as the paradigm for long-term retention and developing general principles for model archiving. These include electrical systems, composite parts, systems engineering and requirementsengineering. The increasing availability of model-based software has made the problems of long-term model sustainment more visible and pressing for a solution. Industries following LOTAR today include aerospace, automotive, nuclear and ship building. In the aerospace sector, the challenges are even bigger. Model Archiving and Sustainment for Aerospace Design makes sense of the immense challenges of rapid software change to ensure that the aircraft can be profitably sustained for the next seventy years.
eBook
Designing and building a miniature aero-engine
Helps you through all the stages of designing and constructing an aero-engine in your workshop at home.
Book
In Situ Experimental Analysis and Performance Evaluation of Airport Precast Concrete Pavement System Subjected to Environmental and Moving Airplane Loads
The behavior of airport precast concrete pavement (APCP) involving new design and construction concepts was experimentally analyzed under environmental and moving airplane loads, and the long-term performance of the APCP was evaluated using fatigue failure analysis. The strain characteristics and curling behavior of the APCP under environmental loads were comprehensively analyzed. The APCP slabs exhibited a pronounced curling phenomenon similar to conventional concrete pavement slabs. The dynamic response of the APCP subjected to impact loads was analyzed by performing heavy weight deflectometer tests. The test results confirmed that the vertical deformation of the APCP was small and within the typical range of vertical deformation of conventional concrete pavement. The dynamic strain response of the APCP under moving airplane loads was then analyzed and the strain variation during day and night times was compared. The strains during the day were found to be significantly larger than those at night under airplane loads because of the curling phenomenon of the APCP slabs. Finally, the long-term performance of the APCP was evaluated using fatigue failure analysis based on the obtained behavior. Even using the most conservative fatigue failure prediction model, the service life of the APCP was ascertained to be more than 30 years. Based on the overall results of this study, it is concluded that the APCP, which is designed to reduce slab thickness by placing reinforcing bars in the slabs via reinforced concrete structural design, exhibits typical behavior of concrete pavements and can be successfully applied to airport pavement rehabilitation.
Journal Article
Impact of the dimple indentation depth and location for passive flow control in Blended Wing Body airframe at low and high subsonic speeds
This research investigates the role of dimples in enhancing the aerodynamic characteristics of a Blended-Wing-Body (BWB) airframe. Numerical simulations, grounded in Computational Fluid Dynamics (CFD), were utilized to model turbulent airflow and assess the aerodynamic forces acting on the wing structure. The k-ω Shear-Stress Transport (SST) turbulence model was applied to effectively solve the governing equations. The impact of four dimple indentation depths ( d/D d = 0.025, 0.05, 0.075, and 0.1) at six specific locations on either the suction or pressure sides of the BWB wing surface was investigated. Simulations were performed at Mach 0.15 and Mach 0.6, treating the flow as incompressible and compressible, respectively, to capture variations in aerodynamic behavior. The evaluation involved analyzing the drag coefficient ( C D ), lift coefficient ( C L ), and lift-to-drag ( L/D ) ratio. The results reveal that, under optimal conditions, a dimpled BWB surface can achieve a reduction in C D by as much as 4.09% relative to a non-modified surface, without negatively impacting lift. This improvement is primarily due to the dimples’ capacity to maintain attached flow and postpone flow separation. Implementing dimples on the BWB wing surface as a passive flow control method has proven effective in enhancing the aerodynamic efficiency of lifting surfaces.
Journal Article
Investigating the Effects of Leading- and Trailing-Edge Shapes of a Flapping Wing on Power Extraction Performance
Flapping wings present a promising approach to harnessing energy from fluid flow by leveraging a synchronized pitching and heaving motion of the airfoil. The impact of modifying the leading and trailing edge shapes of a flapping wing on energy harvesting performance is investigated using sinusoidal pitching motion. The pitch angle varies between 80° and 90°. The wing thickness (T1) varies from 8% to 48% of the chord length, with a flat plate chord length of c = 1.0. A promising airfoil profile is achieved by increasing only the leading-edge thickness to 32% of the chord, significantly enhancing energy capture by improving the generation of pushing forces and power. The results show that a wing configuration with a semicircular leading edge and a rectangular trailing edge outperforms the baseline case (a rectangular flat plate) and all other configurations under the same conditions. This configuration shows a notable improvement in power output and efficiency at a pitch angle of 85° and a leading-edge thickness of 32% of the chord. The maximum power output (Cpt) represents a 16.73% increase over the baseline, while the maximum efficiency (η) reflects a 12.77% improvement. These findings highlight the superior energy extraction performance of the new configuration, emphasizing the dominant role of the leading edge in enhancing energy harvesters compared to the trailing edge.
Journal Article
Aerostructural Optimization of a Composite Low Reynolds Wing Using Surrogate Modeling Techniques
This study presents an aerostructural optimization framework for the preliminary design of a low-Reynolds-number composite UAV wing, aiming to simultaneously enhance aerodynamic efficiency and structural performance. While previous work has primarily addressed aerodynamic optimization in isolation, the present approach integrates Computational Fluid Dynamics (CFD) and Finite Element Method (FEM) analyses within a surrogate-based optimization (SBO) framework. The design space includes both aerodynamic parameters—aspect ratio, taper ratio, sweep angle, and twist—and structural variables related to the internal wing layout and component thicknesses. To reduce the computational cost associated with high-fidelity simulations, Kriging surrogate models are employed in conjunction with an Expected Improvement (EI) infill strategy, enabling efficient exploration of the coupled design space. The framework is evaluated through multiple independent optimization runs using different initial sampling strategies, demonstrating consistent convergence toward feasible high-performance designs. The surrogate models exhibit strong predictive capability, as confirmed by Root Mean Square Error (RMSE) and Leave-One-Out (LOO) cross-validation metrics. The results indicate that aerodynamic variables, particularly aspect ratio and twist, are the primary drivers of range performance. However, structural variables—most notably skin thickness—strongly influence constraint satisfaction, especially with respect to buckling and strength requirements, and therefore play a key role in defining the feasible design space. The optimal configuration achieves a maximum range of approximately 203 km while satisfying all strength, stiffness, and aerodynamic constraints. Overall, the proposed methodology provides an efficient and robust tool for the early-stage aerostructural design of low-Reynolds-number UAV wings.
Journal Article
Design of Glider Airborne Wind Turbine
Producing clean and renewable energy is the aim of many countries worldwide. Wind is one of the most vast renewable energy sources. High‐quality wind is available at high altitudes. To harvest such energy, wind turbines should reach such high altitudes. An airborne wind turbine system is conceptually designed to harvest wind energy at relatively high altitudes regardless of location. A glider is designed to carry a small wind turbine mounted at its nose. The glider is connected to the ground through a tether and electric wires to transmit power from the flying generator to the ground station. The resulting model airplane has a square wing with a Selig high‐lift, low‐Reynolds‐number airfoil section (S1223‐il) and a wingspan of 2 m. Tail airfoil sections are NASA airfoil 0012. The total mass of the glider is 3.35 kg. The aerodynamic design analysis is performed through CFD simulation. The forces and loads obtained from the CFD analysis are transferred to finite element software to perform structural analysis. Overshooting in lift and drag forces occurs in both cruise and nose‐up flights. Such overshoot behavior is eliminated by the wind turbine rotation effect. The developed model meets the design objectives successfully, since both structural and CFD analyses show the aircraft′s capability to carry the load. The CFD results prove that the glider is stable when the center of gravity is forward, and stability is achieved within 0.2 s. When the wind turbine is installed, there is slight oscillation in the lift force, but stability is reached within the design target of 0.2 s.
Journal Article
Numerical Investigation on the Influence of Turbine Rotor Parameters on the Eddy Current Sensor for the Dynamic Blade Tip Clearance Measurement
Eddy current sensors are increasingly being used to measure the dynamic blade tip clearance in turbines due to their robust anti-interference capabilities and non-contact measurement advantages. However, the current research primarily focuses on enhancing the performance of eddy current sensors themselves, with few studies investigating the influence of turbine rotor parameters on the measurements taken by these sensors for dynamic blade tip clearance. Hence, this paper addresses this gap by using COMSOL Multiphysics 6.2 software to establish a finite model with circuit interfaces. Additionally, the model’s validity was verified through experiments. This model is used to simulate the voltage output of the sensor and the measurement of dynamic blade tip clearance under various rotor parameters. The results indicate that the length and number of blades, as well as the hub radius, significantly affect the sensor voltage output in comparison to rotation speed. Furthermore, we show that traditional static calibration methods are inadequate for measuring dynamic blade tip clearance using eddy current sensors. Instead, it is demonstrated that incorporating rotor parameters into the calibration of eddy current sensors can enhance the accuracy of dynamic blade tip clearance measurements.
Journal Article