Application of shape memory alloys in Aerospace industries
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This document discusses the structural design of aircraft. It begins by describing the basic components of an aircraft structure, including wings, fuselage, tail, and control surfaces. It then discusses the functions of different structural elements like skin, spars, ribs, stringers, and frames. It provides details on fuselage types, wing structure, empennage, landing gear, and materials used in aircraft construction. It concludes with an explanation of the V-n diagram used for structural design and load factors specified by airworthiness authorities.
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For comments please contact me at solo.hermelin@gmail.com.
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overview of functionally graded materials
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For Video Lecture of this presentation: https://youtu.be/DqaoNt0LoIE
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Attention! "Gate Aerospace Engineering aspirants", A virtual guide for gate aerospace engineering is provided in "Age of Aerospace" blog for helping you meticulously prepare for gate examination. Respective notes of individual subjects are provided as 'Embedded Google Docs' which are frequently updated. This comprehensive guide is intended to efficiently serve as an extensive collection of online resources for "GATE Aerospace Engineering" which can be accessed free of cost. Use the following link to access the study material
https://ageofaerospace.blogspot.com/p/gate-aerospace.html
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This document discusses the slurry infiltration method for fabricating ceramic matrix composites. It begins with an introduction to ceramic matrix composites, outlining their characteristics and typical materials. It then focuses on the slurry infiltration fabrication method. This involves making a fiber preform, infiltrating it with a slurry of ceramic particles, binders and solvents, drying and consolidating to form a tape, stacking tapes and hot pressing to form a dense composite material. Common ceramic matrices produced via slurry infiltration include alumina, silica, mullite and silicon carbide. Advantages are low porosity and good mechanical properties, while disadvantages include potential fiber damage during hot pressing. Applications include turbine engine components requiring high temperature and thermal
Ablative and Thermal Materials
This document discusses ablative and thermal insulation materials. It provides information on:
1) Ablative materials which protect vehicles during atmospheric reentry by absorbing, dissipating, and blocking heat. They are needed for ballistic missiles, rocket nozzles, and other high heat applications.
2) Thermal insulation materials which prevent or reduce heat transfer to maintain temperatures. They include organic materials like wool and inorganic materials like glass wool.
3) Intumescent ablators which form a foam-like char when heated, decreasing conductivity and insulating the substrate while cutting off oxygen supply. They are common as fire-retardant coatings.
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This document provides an overview of aircraft wings, including their:
- Historical development from ancient kites to the Wright brothers' fixed-wing aircraft.
- Construction, with internal structures like ribs, spars, stringers, and skin covering the framework. Wings also contain fuel tanks, flaps, and other devices.
- Functions, as wings generate lift through Bernoulli's principle and critical angle of attack. Wing design factors like aspect ratio and camber also affect lift.
- Types based on position (fixed or movable) and structure (cantilever or strut-braced). Stability devices like ailerons and flaps are also described.
- Unconventional designs that
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This document discusses smart materials, specifically shape memory alloys. It defines smart materials as materials that can dramatically change properties in response to external stimuli like heat. Shape memory alloys are described as being able to "remember" their original shape when heated above a transition temperature. Examples of applications include orthodontic wires, eyeglass frames, and aircraft components. While smart materials show potential, issues like fatigue and cost need further study.
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aircraft drag reduction methods
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Metal matrix composites (mmc)
This document discusses metal matrix composites (MMCs), which are composite materials with at least two constituent parts including a metal. MMCs can be classified based on their composition and reinforcement materials. Common reinforcement materials include silicon carbide, titanium carbide, and carbon nanotubes. Production methods for MMCs include stir casting and powder metallurgy. MMCs exhibit improved properties over unreinforced metals like high strength and stiffness. Applications of MMCs span aerospace, automotive, and other industries. The document outlines advantages like heat resistance and disadvantages like higher cost compared to unreinforced metals.
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This ppt. is related to the second session of my class about shape memory alloys(SMAs) and their applications.
aircraft drag reduction
This document is a seminar report submitted by Dhanashree Manohar Waghmare on aircraft drag reduction techniques. The report contains an introduction on the importance of reducing aircraft drag. It then provides a literature review on relevant topics like aerodynamics, fluid mechanics, previous studies on drag reduction. The objectives are to study aerodynamic principles, forces on aircraft, types of drag and reduction methods. The body of the report discusses these topics in detail with diagrams. It covers concepts like aerodynamics, aircraft wings, forces, types of drag and techniques to reduce skin friction, lift-induced and wave drag. The report aims to provide a comprehensive overview of aircraft drag and methods to reduce it.
Polymer matrix composites
The document discusses different types of polymer matrix composites, including thermoset and thermoplastic matrices. It covers various processing techniques for composites such as hand layup, filament winding, and injection molding. Key topics include the properties and applications of polymer composites as well as the effects of temperature on thermoplastic polymers.
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This document provides an overview of a presentation on turbofan engines. It introduces the key components of a turbofan engine, including the fan, low and high pressure compressors, combustor, low and high pressure turbines, and exhaust nozzle. It explains the basic functions of each component, such as the fan producing thrust, compressors preparing air for combustion, combustion adding energy through heat, turbines extracting energy to power the compressors and fan, and the nozzle propelling the exhaust. The document also lists some of the major manufacturers of turbofan engines.
advance materials
Smart materials are materials that have one or more properties that can be significantly altered in a controlled fashion by external stimuli, such as stress, temperature, moisture, pH, electric or magnetic fields.
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This document provides an overview of the mechanical properties of engineering materials as presented in a lecture. It defines key terms like elasticity, plasticity, ductility, brittleness, hardness, toughness, stiffness, resilience, endurance, strength, and creep. For each property, examples are given of the types of materials that exhibit that property. The goal of the lecture is to help students understand the behavior and suitability of different materials for engineering applications by learning about their mechanical characteristics.
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The purpose of the intake of an aircraft is to supply the engine with a proper airflow during various flight conditions. A good intake design is characterized by providing high pressure recovery and low distortion. Therefore it is essential to divert as much of the boundary layer as possible since it is a factor which affect the quality of the airflow. On aircrafts with engines installed on wing pylons, which is the most common configuration on transport and passenger aircraft, the inlet is short and leads directly to the engine and the pressure recovery is good. For engines that are integrated with the body, for example on fighter aircrafts, the airflow is travelling along the body of the aircraft before it reaches the air intake. A boundary layer builds up along the body, something which is not desirable, especially in the part of the flow that supplies the engines. The pressure recovery is lower because of this, something that has a negative effect upon engine thrust. There are, however, ways to prevent the boundary layer from entering the inlet, or at least to minimize the amount that does. It is common to use a boundary layer diverter. It affects the aircraft performance in so many ways. So, it needs some other provision or technology to overcome intake problem in fighter crafts. In the present work, a well-designed compression surface is installed in the entry of the engine intake to redirect boundary layer and create shock wave for getting desired flow in the compressor (When a flow crosses a shock wave, its velocity got reduced, which in term increases pressure). The compression surface is placed at the entry of the diffuser to perform the above mentioned operation. The work extents to, a comparative investigation is proposed for with and without compression surface. ANSYS-Fluent is a commercial CFD code which will be used for performing the simulation and the simulation configuration contains two different Mach speeds (0.7 & 2) with three different angles of attacks (0°, 7.5° and 15°). The simulation results are evaluated to find out pressure recovery in the engine intake between with and without compression surface.
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This document discusses research into the effects of adding dimples to the surfaces of horizontal axis wind turbine blades. It aims to investigate how dimples impact the aerodynamic performance of wind turbine blades. The researchers used computational fluid dynamics software to simulate flow over a baseline wind turbine blade design with and without various dimple configurations. The simulations found that blades with dimples experienced delayed flow separation, resulting in enhanced aerodynamic performance and increased power extraction compared to the baseline blade without dimples. Validation with experimental wind tunnel testing of a scaled down model supported the numerical results.
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This document discusses the design optimization of a cam shaft angle monitoring system for industrial improvements. It begins by introducing cam shafts and their importance in properly timing engine valves. It then describes using linear variable differential transformers (LVDTs) to precisely measure cam shaft angle. The document outlines the system components, including an LVDT sensor, servo motor, electromagnetic valves and other sensors. It discusses designing the system to measure cam shaft angle to within 0.5mm precision and control product quality. Finally, it evaluates mounting designs and material choices to optimize the monitoring system.
Performance Analysis of Giromill Vertical Axis Wind Turbine with NACA 63618 A...
This document presents a study on the performance analysis of a vertical axis wind turbine (VAWT) with straight blades (called a Giromill configuration) using computational fluid dynamics (CFD) simulations and experiments.
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This document provides an overview of a knowledge sharing program on generator basics, excitation, protection systems, and overhauling and maintenance. The program is presented by a team of subject matter experts and is mentored by Nimai Mahapatra. The program covers topics such as generator working principles, classification, construction, excitation systems, protection systems, and overhauling testing. It also includes sections on generator basics and design aspects, synchronization, and operation.
Knowledge Based Design of Axial Flow Compressor
In the aerospace industry with highly competitive market the time to design and delivery is shortening every day. Pressure on delivering robust product with cost economy is in demand in each development. Even though technology is older, it is new for each customer requirement and highly non-liner to fit one in another place. Gas turbine is considered one of a complex design in the aircraft system. It involves experts to be grouped with designers of various segments to arrive the best output. The time is crucial to achieve a best design and it needs knowledge automation incorporated with CAD/CAE tools. In the present work an innovative idea in the form of Knowledge Based Engineering for axial compressor is proposed, this includes the fundamental design of axial compressor integrated with artificial intelligence in the form of knowledge capturing and programmed with high level language (Visual Basis.Net) and embedded into CATIA v5. This KBE frame work eases out the design and modeling of axial compressor design and produces 3D modeling for further flow simulation with fluid dynamic in Ansys-Fluent. Most of the aerospace components are developed through simulation driven product development and in this case it is established for axial compressor.
Knowledge Based Design of Axial Flow Compressor
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Cfd analysis of flow charateristics in a gas turbine a viable approach
This document summarizes a computational fluid dynamics (CFD) analysis of flow characteristics in a gas turbine. It describes the design of a simulated combustor test section to match conditions of a real gas turbine engine. This includes scaling engine parameters, designing liner panels with film cooling holes and dilution holes, and matching mass flow distributions. It also details the meshing of the combustor and downstream vane geometry using GAMBIT for the CFD analysis in Fluent. The goal is to predict the effect of the combustor flow field on turbulence in the turbine.
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This project work is to investigate the compression efficiency of different configuration of Turbo-Prop Co-Rotor Blade System of Subsonic Axial Flow Compressor. By this method the highly compressed air can be passed over the intake of the engine to the compressor with high mass flow rate in change of low velocity and high pressure ratio. The length of the small rotor is varied in terms of large rotor length by 25,50 & 75% . Each will have three space configuration in terms of diameter of rotor and in the percentage of 5,10,15%. A total of 12 configurations will be simulated to arrive optimum blade configuration. The blades are made in the shape of an airfoil like wing of an aircraft. The engine rotates the propeller blades, which produce lift. This lift is called thrust and moves the aircraft forward. Blades are usually made of high lift airfoil which allows more rotation to generate high pressure for engine. ANSYS- Fluent is commercial software which is robust for most of the fluid dynamic problems and it is used in this project work to evaluate the different configurations of co-rotor propeller system to arrive the best.
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1:该专业认证可证明留学生真实身份
2:同时对留学生所学专业登记给予评定
3:国家专业人才认证中心颁发入库证书
4:这个认证书并且可以归档倒地方
5:凡事获得留信网入网的信息将会逐步更新到个人身份内，将在公安局网内查询个人身份证信息后，同步读取人才网入库信息
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Climate change's impact on the planet forced the United Nations and governments to promote green energies and electric transportation. The deployments of photovoltaic (PV) and electric vehicle (EV) systems gained stronger momentum due to their numerous advantages over fossil fuel types. The advantages go beyond sustainability to reach financial support and stability. The work in this paper introduces the hybrid system between PV and EV to support industrial and commercial plants. This paper covers the theoretical framework of the proposed hybrid system including the required equation to complete the cost analysis when PV and EV are present. In addition, the proposed design diagram which sets the priorities and requirements of the system is presented. The proposed approach allows setup to advance their power stability, especially during power outages. The presented information supports researchers and plant owners to complete the necessary analysis while promoting the deployment of clean energy. The result of a case study that represents a dairy milk farmer supports the theoretical works and highlights its advanced benefits to existing plants. The short return on investment of the proposed approach supports the paper's novelty approach for the sustainable electrical system. In addition, the proposed system allows for an isolated power setup without the need for a transmission line which enhances the safety of the electrical network
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- 1. Mohammad Tanhaei Sahand University of Technology (SUT) Iran - Tabriz
- 2. VGC (Variable Geometry Chevron) VAFN (Variable Area Fan Nozzles) Actuators : Telescopic wing system Servo valve Retractable landing gear Reconfigurable Rotor Blade (RRB)
- 3. VAFN ( Variable Area Fan Nozzle ) Significant reduction in noise and improved fuel consumption The nozzle : is the exhaust duct of the engine. This is the engine part which actually produces the thrust for the plane.
- 4. VAFN ( Variable Area Fan Nozzle ) Larger diameterat take off can reduce jet velocity reducing noise Adjusting the diameter in cruise reduce fuel consumption Boeing tested VAFN capable of 20% area change SMA actuators were used to position 12 panels at the nozzle exit
- 5. Cruise
- 6. Thrust
- 7. Nozzle Design SMA actuators designed to expand the nozzle when heated, are attached to half of the panels. A support is attached to a nozzle Panels is attached to a support ring by a small piece of thin steel Actuator base is attached to support ring
- 8. Nozzle Design A small resistive heater is bonded on the surface of each actuator SMA 60%Ni 40%Ti Transition Temp: -55 to 70 Recoverable strain : up to 2.5 % 1000s of actuator cycles
- 9. VGC (Variable Geometry Chevron) What is chevrons ? that are used for noise reduction. Their principle of operation is that, as hot air from the engine core mixes with cooler air blowing through the engine fan, the shaped edges serve to smooth the mixing, which reduces noise creating turbulence .
- 10. VGC (Variable Geometry Chevron)
- 11. VGC (Variable Geometry Chevron)
- 12. VGC (Variable Geometry Chevron) Static and Flight engine test 6 flights over 5 days with 3 engine configurations 3 days of testing June 2006
- 13. Telescopic wing system A B Structure Outer wing segment Slot Inner wing segment
- 14. Telescopic wing system Coiled SMA actuator Flexible tube fluid Outer wing segment
- 15. Thanks for your Attention SahandUniversity of Technology (SUT) Iran -Tabriz
- 16. Jet engine (Turbo jet)