This is Part 4 (in work) of work for my Advanced Technology Demonstration Aircraft project, to inspire interest in aerospace engineering for the RAeS and AIAA.
Hands on experience with aircraft major components on aircraft and to identif...
This document provides information on the major components of an aircraft and their locations. It describes the fuselage as the main structural part that carries the maximum load and includes the passenger cabin or cockpit. It also outlines the cockpit location in the front area, wings attached to both sides of the fuselage to generate lift, control surfaces used to control rolling, pitching, and yawing, the power plant such as engines mounted below or attached to the lower fuselage, the empennage or tail section, and the landing gears that support the aircraft when on the ground.
Stringers are longitudinal stiffening members that support aircraft skin and prevent buckling. They transfer loads between the skin and supporting structures like frames and ribs. Stringers are commonly made of aluminum alloy and come in different cross-sectional shapes. Current research is optimizing stringer design and implementing designs in CAD software to minimize weight while ensuring strength and stability. Future work could extend the design methodology to include multiple cracks, fasteners instead of adhesive, drag forces, and design of the full wing box.
The document provides an overview of aircraft structures and their key components. It discusses the fuselage, wings, empennage, landing gear, and powerplants. For each component, it describes the basic design and functions. It also covers important aircraft structural concepts like stressed skin construction, monocoque vs semi-monocoque design, and choices of lightweight metal materials. Overall the document serves as a high-level introduction to aircraft structures and the major structural components of airplanes.
PRELIMINARY DESIGN APPROACH TO WING BOX LAYOUT AND STRUCTURAL CONFIGURATION
This is an assignment that was done to design the basic layout of the aircraft wing and structural configuration. Key aspects of the assignment are to design the structural layout, identify the basic component, identify the structural arrangement
This document discusses aircraft structural design limits and flight envelopes. It explains that flight envelopes graphically show the speed and load factor limits an aircraft can withstand based on factors like stall speed and maneuvering capabilities. The curves account for factors like altitude and critical Mach number. Load factors in the flight envelope are determined based on expected maneuvering loads and gust loads, with statistical analysis used to estimate extreme loads the aircraft may encounter over its operational life. Structural design limits like limit load, proof load, and ultimate load are set to ensure the aircraft can withstand expected loads with safety margins.
This slide is prepared by me for the students studying in 1st Semester of Aircraft Maintenance Engineering. This is only the the introduction of Maintenance Practices involved in Aircraft Maintenance. Reference is taken from various aviation books and websites. Suggestions are welcome. Pls leave a like
PS- after downloading please don't change the name of author as you will be disregarding all the hard work done by me.
This document discusses forming technology applications in aircraft manufacturing. It describes how forming processes are used to produce critical aircraft parts like wings, ribs, spars, stringers, fuselages, engine components, and more. Rolling, stretching, forging, drawing and other forming methods are used to manufacture parts in a way that meets the strength and durability needs for flight while minimizing costs and production challenges. Forming technology plays a key role in the aircraft industry by enabling the mass production of high-quality, complex shapes for various internal and external aircraft structures and systems.
This document summarizes a student aircraft design project to design a cargo plane. The objectives are to design a cargo plane to carry 600,000 kg over 4,000 km with a cruise speed of 850 km/h. The preliminary design was completed and included collecting comparative data, selecting parameters, estimating weights, selecting engines and airfoils, and creating a wing layout. Structural analysis was performed on the wing and fuselage.
This document provides details of an aircraft design project for a new personal jet called "The Flash" being designed by Kent Aerospace. It includes sections on requirements analysis, technical design, manufacturing plan, regulatory compliance, program management, finance, marketing, and socioeconomic impacts. The technical design section provides details on sizing methodology, assumptions, wing and tail geometry, thrust-to-weight ratio, powerplant specifications, wing loading data, and performance results. The design utilizes twin DGEN 380 turbofan engines from Price Induction and is intended to carry 3 passengers up to 800 nautical miles at a cruise speed of 230 knots.
For Video Lecture of this presentation: https://youtu.be/u7bp9IJqRVM
The topics covered in this session are, Slip: Types of slip, Sideslip angle, Sideslip angle sign conventions, restoring yaw moments, physical significance, Calculation of sideslip angle, Measurement of sideslip.
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
This chapter examines human factors and incidents in terms of human error. It discusses Murphy's Law and how even experienced individuals can make errors. Approximately 70% of aircraft accidents are attributable to human performance. The Aloha Flight 243 incident in 1988 involved structural failure due to undetected cracks, highlighting issues with aircraft inspections. The BA 5390 incident in 1990 involved a windscreen blow out due to incorrect replacement bolts, with contributing human factors including poor lighting and failure to wear glasses. Subsequent chapters will discuss human performance limitations and identify areas of vulnerability to help prevent errors.
Airplane (fixed wing aircraft) configuration and various parts | Flight Mecha...
For Video Lecture of this presentation: https://youtu.be/uD_qWvTZEhY
The topics covered in this session are, Airplane (fixed wing aircraft) configurations and various parts of airplane. A detailed list of airplane configuration is discussed with general insight about airplane parts.
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
This document discusses various concepts related to aircraft structural design and airworthiness requirements. It describes how aircraft structure is divided into primary, secondary, and tertiary categories based on their importance. Primary structure, if failed, could cause loss of control or structural collapse. Examples provided stress the importance of withstanding forces like tension, compression, shear, bending, and torsion to ensure structural integrity and safety. Station identification systems are also covered to precisely locate structural components through methods like station numbering and zoning.
For Video Lecture of this presentation: https://youtu.be/NAjezfbWh4Y
The topics covered in this session are, drag, categories of drag, drag polar equation and drag polar graph, drag polar derivation, induced drag coefficient.
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
This document summarizes different types of airplane wings. It describes straight wings, swept-back wings, delta wings, forward-swept wings, variable-sweep wings, flying wings, dihedral wings, tapered wings, and variable geometry wings. For each type, it provides a brief definition and example shape. The document aims to provide an overview of the various wing designs used in aircraft.
Hands on experience with aircraft major components on aircraft and to identif...Mayank Gupta
This document provides information on the major components of an aircraft and their locations. It describes the fuselage as the main structural part that carries the maximum load and includes the passenger cabin or cockpit. It also outlines the cockpit location in the front area, wings attached to both sides of the fuselage to generate lift, control surfaces used to control rolling, pitching, and yawing, the power plant such as engines mounted below or attached to the lower fuselage, the empennage or tail section, and the landing gears that support the aircraft when on the ground.
Stringers are longitudinal stiffening members that support aircraft skin and prevent buckling. They transfer loads between the skin and supporting structures like frames and ribs. Stringers are commonly made of aluminum alloy and come in different cross-sectional shapes. Current research is optimizing stringer design and implementing designs in CAD software to minimize weight while ensuring strength and stability. Future work could extend the design methodology to include multiple cracks, fasteners instead of adhesive, drag forces, and design of the full wing box.
The document provides an overview of aircraft structures and their key components. It discusses the fuselage, wings, empennage, landing gear, and powerplants. For each component, it describes the basic design and functions. It also covers important aircraft structural concepts like stressed skin construction, monocoque vs semi-monocoque design, and choices of lightweight metal materials. Overall the document serves as a high-level introduction to aircraft structures and the major structural components of airplanes.
PRELIMINARY DESIGN APPROACH TO WING BOX LAYOUT AND STRUCTURAL CONFIGURATIONLahiru Dilshan
This is an assignment that was done to design the basic layout of the aircraft wing and structural configuration. Key aspects of the assignment are to design the structural layout, identify the basic component, identify the structural arrangement
This document discusses aircraft structural design limits and flight envelopes. It explains that flight envelopes graphically show the speed and load factor limits an aircraft can withstand based on factors like stall speed and maneuvering capabilities. The curves account for factors like altitude and critical Mach number. Load factors in the flight envelope are determined based on expected maneuvering loads and gust loads, with statistical analysis used to estimate extreme loads the aircraft may encounter over its operational life. Structural design limits like limit load, proof load, and ultimate load are set to ensure the aircraft can withstand expected loads with safety margins.
This slide is prepared by me for the students studying in 1st Semester of Aircraft Maintenance Engineering. This is only the the introduction of Maintenance Practices involved in Aircraft Maintenance. Reference is taken from various aviation books and websites. Suggestions are welcome. Pls leave a like
PS- after downloading please don't change the name of author as you will be disregarding all the hard work done by me.
This document discusses forming technology applications in aircraft manufacturing. It describes how forming processes are used to produce critical aircraft parts like wings, ribs, spars, stringers, fuselages, engine components, and more. Rolling, stretching, forging, drawing and other forming methods are used to manufacture parts in a way that meets the strength and durability needs for flight while minimizing costs and production challenges. Forming technology plays a key role in the aircraft industry by enabling the mass production of high-quality, complex shapes for various internal and external aircraft structures and systems.
This document summarizes a student aircraft design project to design a cargo plane. The objectives are to design a cargo plane to carry 600,000 kg over 4,000 km with a cruise speed of 850 km/h. The preliminary design was completed and included collecting comparative data, selecting parameters, estimating weights, selecting engines and airfoils, and creating a wing layout. Structural analysis was performed on the wing and fuselage.
This document provides details of an aircraft design project for a new personal jet called "The Flash" being designed by Kent Aerospace. It includes sections on requirements analysis, technical design, manufacturing plan, regulatory compliance, program management, finance, marketing, and socioeconomic impacts. The technical design section provides details on sizing methodology, assumptions, wing and tail geometry, thrust-to-weight ratio, powerplant specifications, wing loading data, and performance results. The design utilizes twin DGEN 380 turbofan engines from Price Induction and is intended to carry 3 passengers up to 800 nautical miles at a cruise speed of 230 knots.
For Video Lecture of this presentation: https://youtu.be/u7bp9IJqRVM
The topics covered in this session are, Slip: Types of slip, Sideslip angle, Sideslip angle sign conventions, restoring yaw moments, physical significance, Calculation of sideslip angle, Measurement of sideslip.
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
Human_Factors_in_Aviation__PowerPoint_.pptx.pptxEndris Mohammed
This chapter examines human factors and incidents in terms of human error. It discusses Murphy's Law and how even experienced individuals can make errors. Approximately 70% of aircraft accidents are attributable to human performance. The Aloha Flight 243 incident in 1988 involved structural failure due to undetected cracks, highlighting issues with aircraft inspections. The BA 5390 incident in 1990 involved a windscreen blow out due to incorrect replacement bolts, with contributing human factors including poor lighting and failure to wear glasses. Subsequent chapters will discuss human performance limitations and identify areas of vulnerability to help prevent errors.
Airplane (fixed wing aircraft) configuration and various parts | Flight Mecha...Age of Aerospace
For Video Lecture of this presentation: https://youtu.be/uD_qWvTZEhY
The topics covered in this session are, Airplane (fixed wing aircraft) configurations and various parts of airplane. A detailed list of airplane configuration is discussed with general insight about airplane parts.
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
Blended Wing Body (BWB) - Future Of AviationAsim Ghatak
What is Blended Wing Body, History, Advantages And Disadvantages, Design and Structure, How airplanes Fly, Conventional airplanes vs. BWB, Future Scope And Challenges.
This document outlines the course details and topics for a 18-week rotorcraft systems, maintenance, and role equipment class at the Malaysian Institute of Aviation Technology. The course will cover 10 topics related to helicopter structure and maintenance, and will evaluate students based on assignments, quizzes, and a final exam. Students who miss more than 10% of classes will be barred from the final exam. The document then provides details on helicopter structural design, including tubular, stressed skin, and bonded construction methods, as well as the stresses and loads placed on helicopter structures.
To determine if a helicopter is within weight limits, a pilot must calculate the basic empty weight and consider the weight of the crew, passengers, cargo, fuel, and helicopter structure. The maximum gross weight and center of gravity range must also be checked to ensure structural integrity and safe handling. Improper loading that shifts the center of gravity outside the allowable range could cause stability and control issues. Accurate weight and balance calculations are important for safety.
Large scale topological optimisation: aircraft engine pylon caseAltair
1) The document discusses using topology optimization to design an improved engine pylon concept for an aircraft. It aims to reduce mass, part count, and assembly time compared to the current design.
2) Topology optimization was performed on the engine pylon and aft pylon fairing using Altair OptiStruct to minimize compliance. This provided optimized structural designs with up to 200kg mass savings per plane.
3) Preliminary analysis shows the optimized design could reduce the part count from over 650 parts to just 14 parts, and assembly time from over 2600 fixes to around 350 fixes.
The document discusses the different types and functions of aircraft fuselages. It describes how fuselages form the main body of an aircraft and house key components. There are three main types of fuselage structures: frame, monocoque, and semi-monocoque. Frame structures use a series of pipes but are heavier, while monocoque structures rely on the skin to take all loads but are fragile. Semi-monocoque fuselages provide a balance by sharing loads between the skin and internal structures. The document also outlines features like windows, doors, engines mounts and shapes that fuselages can take.
This is the statement of work for my Advanced Technology Demonstration Aircraft project, to inspire interest in aerospace engineering for the RAeS and AIAA.
IRJET- Static and Fracture Analysis for Aircraft Fuselage and Wing Joint with...IRJET Journal
This document discusses static and fracture analysis of aircraft fuselage and wing joints using composite materials. Finite element analysis software ANSYS and a post-processing program called 3MBSIF are used to determine stress intensity factors for cracks in longitudinal and circumferential fuselage joints under internal pressure loading. Residual strength is predicted using strain energy density theory of fracture. Fatigue life is represented using the Goodman curve. The structural component is designed and analyzed in CREO and ANSYS to calculate stresses and determine fatigue life for different loading conditions.
Design and Finite Element Analysis of Aircraft Wing using Ribs and SparsIRJET Journal
This document describes the design and finite element analysis of an aircraft wing structure using ribs and spars. The wing structure was modeled in PRO-ENGINEER and then analyzed in ANSYS. Static, fatigue, and modal analyses were performed to determine stresses, life, damage, and deformation under different loads and speeds. The analyses showed that a carbon epoxy composite material performed better than aluminum or glass materials, with lower stresses and higher safety factors. In conclusion, the carbon epoxy material was determined to be better suited for aircraft wings.
Static and Dynamic Analysis of Floor Beam (Cross beam) of AircraftIRJET Journal
This document summarizes a study analyzing the static and dynamic behavior of floor beams used in aircraft. Floor beams experience bending stresses and support the weight of the aircraft. The researchers modeled a floor beam in CATIA and analyzed it in ANSYS to study stresses under different loads. They also analyzed a carbon fiber reinforced plastic floor beam. Modal analysis determined the beam's natural frequencies under vibration to ensure it can withstand operating conditions. The study aims to optimize floor beam design and materials to reduce weight while maintaining strength.
This document is a project report that analyzes and redesigns the landing gear of two light aircraft - the Piper PA28 and Grob G115. The report investigated landing gear failures using data from the Civil Aviation Authority. Finite element analysis was conducted on CAD models of the landing gears under different loading conditions. The results showed that three of the four original landing gears failed to meet safety standards. The report then redesigns the failing landing gears by changing materials and designs, and conducts new FEA to analyze if the redesigns meet standards.
The document outlines the methodology for a project that will design four plausible future commercial aircraft configurations and produce 3D printed models of each that can be tested in a wind tunnel. The methodology includes initial research on aircraft design, sketching initial designs, learning CAD software to model the designs, consulting with lab technicians on wind tunnel requirements, obtaining permissions for 3D printing, printing the models individually, and evaluating the models' surface quality for wind tunnel testing. The goal is to efficiently produce high quality models to analyze different wing and fuselage designs while making the most effective use of time and minimizing financial risks.
Structural Analysis and Optimization for Spar Beam of an AircraftIRJET Journal
This document summarizes a study analyzing and optimizing the structural design of a tapered spar beam for an aircraft wing. The study involved creating a geometric model of the spar beam, applying loads and boundary conditions representative of flight loading, conducting a finite element analysis to determine stresses and displacements, and performing topological optimization to reduce weight. Key results were stresses of up to 38 MPa at the fixed end of the beam, displacements of up to 3.1 mm at the free end, and a 40% reduction in web weight achieved through topological optimization while maintaining structural integrity. The optimized design demonstrated potential to strengthen the spar beam structure while reducing material usage and weight.
The document describes the design and fabrication of a V-tail unmanned aerial vehicle (UAV). It aims to study the stability, design parameters, and operation of a V-tail configuration. The project involves designing all parts of the RC aircraft using CATIA software, performing calculations to determine dimensions, and assembling the final prototype. The design process considers various factors like material selection, component orientation, weight estimation, and control surface sizing. The report outlines the various stages of completing the project, from initial conceptualization to fabrication and testing of the final V-tail UAV model.
Structural Weight Optimization of Aircraft Wing Component Using FEM Approach.IJERA Editor
One of the main challenges for the civil aviation industry is the reduction of its environmental impact by better fuel efficiency by virtue of Structural optimization. Over the past years, improvements in performance and fuel efficiency have been achieved by simplifying the design of the structural components and usage of composite materials to reduce the overall weight of the structure. This paper deals with the weight optimization of transport aircraft with low wing configuration. The Linear static and Normal Mode analysis were carried out using MSc Nastran & Msc Patran under different pressure conditions and the results were verified with the help of classical approach. The Stress and displacement results were found and verified and hence arrived to the conclusion about the optimization of the wing structure.
Aviq Design Sdn Bhd is an engineering services company formed in 2004 comprising experienced aerospace engineers. Their vision is to be a center of excellence for engineering services, and their mission is to be competitive in engineering through developing capabilities, people, and products. They offer services including CAD/CAM/CAE, engineering design, structural and mechanical design, engineering analysis, and project management. They have experience with projects for companies such as BAE Systems, Airbus, and Bombardier.
Avinash has over 4.5 years of experience in aircraft stress analysis. He has expertise in finite element modeling and analysis using Nastran/Patran. Some of his projects include static and dynamic analysis of the A350 composite and metallic components. He is skilled in CAD tools like CATIA and analysis tools like ISAMI. He has a Master's degree in Mechanical Engineering.
This document discusses the structural idealization of aircraft wings for stress analysis purposes. It begins by describing the various structural components of a wing, including spars, ribs, skins, and stringers. It then explains that real wing structures are complex, so they must be simplified for analysis by idealizing them as direct stress-carrying booms and shear stress-carrying panels. The document provides examples of constructing idealized wing box sections and calculating the areas of stress-carrying booms based on equilibrium of bending stresses. It also discusses modeling idealized wing structures in a global finite element model using bar and shell elements.
The document provides details of a project to design a composite winglet attachment system for an aircraft fleet operated by SpeedAir. The system is being designed by Team TKJ for Sharp Aero Structures (SAS) to attach winglets to 248 aircraft to improve fuel efficiency. The document outlines the project objectives, customer requirements, and aircraft specifications. It includes figures illustrating the aircraft, wing, and winglet geometry. Tables list the initial customer requirements and constraints provided by SAS. The design must meet all regulatory requirements while withstanding flight loads, being removable for maintenance, and not negatively impacting fuel efficiency through excessive weight.
This is an overview presentation of my current composite design for manufacture and manufacturing engineering capabilities research. Based on my career and two MSc degrees: - MSc in Advanced Manufacturing Technology University of Portsmouth graduating 1st May 1998, and MSc in Aircraft Engineering Cranfield University 8th June 2007.
Bend twist coupling effect on the Performance of the Wing of an Unmanned Aeri...IRJET Journal
This document discusses the design and analysis of a composite wing for an unmanned aerial vehicle (UAV) to minimize weight while maintaining stiffness and strength. Two wing models are created - one with all isotropic materials and one with composite materials. The composite wing is designed with glass-epoxy ribs and carbon-epoxy spars to take advantage of intrinsic bend-twist coupling effects. The wing models are analyzed in ANSYS to compare the performance of composite and isotropic materials. The results show that a composite wing can achieve lower weight without compromising structural performance.
The International Journal of Engineering & Science is aimed at providing a platform for researchers, engineers, scientists, or educators to publish their original research results, to exchange new ideas, to disseminate information in innovative designs, engineering experiences and technological skills. It is also the Journal's objective to promote engineering and technology education. All papers submitted to the Journal will be blind peer-reviewed. Only original articles will be published.
The papers for publication in The International Journal of Engineering& Science are selected through rigorous peer reviews to ensure originality, timeliness, relevance, and readability.
The document describes a conceptual design for a take-off and landing system (TLS) for the Insitu Integrator unmanned aircraft system. It provides background details on the aircraft configuration, structural scheme, and current TLS. Five concepts for a new TLS were generated and two were selected for further analysis based on a trade study. The feasibility of integrating the selected concepts with the aircraft was then evaluated through analytical calculations and simulations. A failure modes and effects analysis was also conducted to assess the safety of the proposed design. The results were discussed to evaluate the feasibility and suitability of the new TLS concept for the Integrator.
This is Stage one of my Future Deep Strike Aircraft project to develop a replacement for the FB-111 / F-111F / F-15E and B-1B. This stage covers requirements and threats. Stage 2 will cover Design Studies, and the CCA Wingman.
This is an overview presentation of my current Finite Element Analysis engineering capabilities research. Based on my career and two MSc degrees: - MSc in Advanced Manufacturing Technology University of Portsmouth graduating 1st May 1998, and MSc in Aircraft Engineering Cranfield University 8th June 2007.
This is an overview of my current metallic design and engineering knowledge base built up over my professional career and two MSc degrees : - MSc in Advanced Manufacturing Technology University of Portsmouth graduated 1st May 1998, and MSc in Aircraft Engineering Cranfield University graduated 8th June 2007.
This is an overview of my career in Aircraft Design and Structures, which I am still trying to post on LinkedIn. Includes my BAE Systems Structural Test roles/ my BAE Systems key design roles and my current work on academic projects.
Conservation of Taksar through Economic RegenerationPriyankaKarn3
This was our 9th Sem Design Studio Project, introduced as Conservation of Taksar Bazar, Bhojpur, an ancient city famous for Taksar- Making Coins. Taksar Bazaar has a civilization of Newars shifted from Patan, with huge socio-economic and cultural significance having a settlement of about 300 years. But in the present scenario, Taksar Bazar has lost its charm and importance, due to various reasons like, migration, unemployment, shift of economic activities to Bhojpur and many more. The scenario was so pityful that when we went to make inventories, take survey and study the site, the people and the context, we barely found any youth of our age! Many houses were vacant, the earthquake devasted and ruined heritages.
Conservation of those heritages, ancient marvels,a nd history was in dire need, so we proposed the Conservation of Taksar through economic regeneration because the lack of economy was the main reason for the people to leave the settlement and the reason for the overall declination.
Unblocking The Main Thread - Solving ANRs and Frozen FramesSinan KOZAK
In the realm of Android development, the main thread is our stage, but too often, it becomes a battleground where performance issues arise, leading to ANRS, frozen frames, and sluggish Uls. As we strive for excellence in user experience, understanding and optimizing the main thread becomes essential to prevent these common perforrmance bottlenecks. We have strategies and best practices for keeping the main thread uncluttered. We'll examine the root causes of performance issues and techniques for monitoring and improving main thread health as wel as app performance. In this talk, participants will walk away with practical knowledge on enhancing app performance by mastering the main thread. We'll share proven approaches to eliminate real-life ANRS and frozen frames to build apps that deliver butter smooth experience.
A brief introduction to quadcopter (drone) working. It provides an overview of flight stability, dynamics, general control system block diagram, and the electronic hardware.
Online music portal management system project report.pdfKamal Acharya
The iMMS is a unique application that is synchronizing both user
experience and copyrights while providing services like online music
management, legal downloads, artists’ management. There are several
other applications available in the market that either provides some
specific services or large scale integrated solutions. Our product differs
from the rest in a way that we give more power to the users remaining
within the copyrights circle.
A brand new catalog for the 2024 edition of IWISS. We have enriched our product range and have more innovations in electrician tools, plumbing tools, wire rope tools and banding tools. Let's explore together!
Best Practices of Clothing Businesses in Talavera, Nueva Ecija, A Foundation ...IJAEMSJORNAL
This study primarily aimed to determine the best practices of clothing businesses to use it as a foundation of strategic business advancements. Moreover, the frequency with which the business's best practices are tracked, which best practices are the most targeted of the apparel firms to be retained, and how does best practices can be used as strategic business advancement. The respondents of the study is the owners of clothing businesses in Talavera, Nueva Ecija. Data were collected and analyzed using a quantitative approach and utilizing a descriptive research design. Unveiling best practices of clothing businesses as a foundation for strategic business advancement through statistical analysis: frequency and percentage, and weighted means analyzing the data in terms of identifying the most to the least important performance indicators of the businesses among all of the variables. Based on the survey conducted on clothing businesses in Talavera, Nueva Ecija, several best practices emerge across different areas of business operations. These practices are categorized into three main sections, section one being the Business Profile and Legal Requirements, followed by the tracking of indicators in terms of Product, Place, Promotion, and Price, and Key Performance Indicators (KPIs) covering finance, marketing, production, technical, and distribution aspects. The research study delved into identifying the core best practices of clothing businesses, serving as a strategic guide for their advancement. Through meticulous analysis, several key findings emerged. Firstly, prioritizing product factors, such as maintaining optimal stock levels and maximizing customer satisfaction, was deemed essential for driving sales and fostering loyalty. Additionally, selecting the right store location was crucial for visibility and accessibility, directly impacting footfall and sales. Vigilance towards competitors and demographic shifts was highlighted as essential for maintaining relevance. Understanding the relationship between marketing spend and customer acquisition proved pivotal for optimizing budgets and achieving a higher ROI. Strategic analysis of profit margins across clothing items emerged as crucial for maximizing profitability and revenue. Creating a positive customer experience, investing in employee training, and implementing effective inventory management practices were also identified as critical success factors. In essence, these findings underscored the holistic approach needed for sustainable growth in the clothing business, emphasizing the importance of product management, marketing strategies, customer experience, and operational efficiency.
A vernier caliper is a precision instrument used to measure dimensions with high accuracy. It can measure internal and external dimensions, as well as depths.
Here is a detailed description of its parts and how to use it.
In May 2024, globally renowned natural diamond crafting company Shree Ramkrishna Exports Pvt. Ltd. (SRK) became the first company in the world to achieve GNFZ’s final net zero certification for existing buildings, for its two two flagship crafting facilities SRK House and SRK Empire. Initially targeting 2030 to reach net zero, SRK joined forces with the Global Network for Zero (GNFZ) to accelerate its target to 2024 — a trailblazing achievement toward emissions elimination.
Natural Is The Best: Model-Agnostic Code Simplification for Pre-trained Large...YanKing2
Pre-trained Large Language Models (LLM) have achieved remarkable successes in several domains. However, code-oriented LLMs are often heavy in computational complexity, and quadratically with the length of the input code sequence. Toward simplifying the input program of an LLM, the state-of-the-art approach has the strategies to filter the input code tokens based on the attention scores given by the LLM. The decision to simplify the input program should not rely on the attention patterns of an LLM, as these patterns are influenced by both the model architecture and the pre-training dataset. Since the model and dataset are part of the solution domain, not the problem domain where the input program belongs, the outcome may differ when the model is trained on a different dataset. We propose SlimCode, a model-agnostic code simplification solution for LLMs that depends on the nature of input code tokens. As an empirical study on the LLMs including CodeBERT, CodeT5, and GPT-4 for two main tasks: code search and summarization. We reported that 1) the reduction ratio of code has a linear-like relation with the saving ratio on training time, 2) the impact of categorized tokens on code simplification can vary significantly, 3) the impact of categorized tokens on code simplification is task-specific but model-agnostic, and 4) the above findings hold for the paradigm–prompt engineering and interactive in-context learning and this study can save reduce the cost of invoking GPT-4 by 24%per API query. Importantly, SlimCode simplifies the input code with its greedy strategy and can obtain at most 133 times faster than the state-of-the-art technique with a significant improvement. This paper calls for a new direction on code-based, model-agnostic code simplification solutions to further empower LLMs.
Response & Safe AI at Summer School of AI at IIITHIIIT Hyderabad
Talk covering Guardrails , Jailbreak, What is an alignment problem? RLHF, EU AI Act, Machine & Graph unlearning, Bias, Inconsistency, Probing, Interpretability, Bias
Development of Chatbot Using AI/ML Technologiesmaisnampibarel
The rapid advancements in artificial intelligence and natural language processing have significantly transformed human-computer interactions. This thesis presents the design, development, and evaluation of an intelligent chatbot capable of engaging in natural and meaningful conversations with users. The chatbot leverages state-of-the-art deep learning techniques, including transformer-based architectures, to understand and generate human-like responses.
Key contributions of this research include the implementation of a context- aware conversational model that can maintain coherent dialogue over extended interactions. The chatbot's performance is evaluated through both automated metrics and user studies, demonstrating its effectiveness in various applications such as customer service, mental health support, and educational assistance. Additionally, ethical considerations and potential biases in chatbot responses are examined to ensure the responsible deployment of this technology.
The findings of this thesis highlight the potential of intelligent chatbots to enhance user experience and provide valuable insights for future developments in conversational AI.
20CDE09- INFORMATION DESIGN
UNIT I INCEPTION OF INFORMATION DESIGN
Introduction and Definition
History of Information Design
Need of Information Design
Types of Information Design
Identifying audience
Defining the audience and their needs
Inclusivity and Visual impairment
Case study.
1. Mr. Geoffrey Allen Wardle. MSc. MSc. ATDA Airframe Design Study 2012-2020
ATDA STUDY PRESENTATION PART: - 4 (ATDA EMPENNAGE DESIGN,
STRUCTURAL LAYOUT, MANUFACTURING ASSEMBLY).
By Mr. GEOFFREY ALLEN WARDLE. MSc. MSc. MRAeS. CEng. Snr MAIAA.
ATDA HT internal structural layout.
ATDA VT internal key datum layout.
2. Mr. Geoffrey Allen Wardle. MSc. MSc. ATDA Airframe Design Study 2012-2020
This presentation has been created, for the sole purpose of private study and is not the work of a
company or government organisation it entirely the work of the author using resources in the public
domain. The final paper will be submitted for peer - review to the American Institute of Aeronautics
and Astronautics, Design Engineering Technical Committee, and the RAeS Structures and
Materials Group, for pre submission assessment. Readers must be aware that the work contained
may not be necessarily 100% correct, and caution should be exercised if this project or the data it
contains is being used for future work. If in doubt, please refer to the AIAA, Design Engineering
Technical Committee and the author.
All of the views and material contained within this document are the sole research of the author and
are not meant to directly imply the intentions of the Boeing Company, Airbus Group, GKN
Aerospace, or any contractor thereof, or any third party at this date. Although the USAF and NASA
have awarded contracts for studies into stitched composite transport aircraft structures, this work is
not the product of their results or any part of their body of research, and should not be considered
as such.
This document contains no material what so ever generated or conceived by myself or others
during my employment with BAE SYSTEMS (PLC), or that is governed by ITAR restrictions. This
work is solely my own creation and is based on my own academic studies and literature research
and the distribution of all information contained within this document is unlimited public release and
has been approved through the AIAA. This document and any part thereof cannot be reproduced
by any means in any format or used for any other research project without consultation with AIAA
Design Engineering Technical Committee or the author.
2
Presentation “Health” Warning.
.
3. Mr. Geoffrey Allen Wardle. MSc. MSc. ATDA Airframe Design Study 2012-2020
3
This is an overview covering my current private design trade studies into the incorporation of new
structural technologies and manufacturing processes into a future transport airframe design, and
the incorporation of mission adaptive wing (MAW) technology for per review through the AIAA
This study has been undertaken after my 13 years at BAE SYSTEMS MA&I, in airframe design
development as a Senior Design Engineer, and my Cranfield University MSc in Aircraft Engineering
completed in 2007(part-time), and was commenced in 2012 and I aim to complete it at the end of
2020. This utilises knowledge and skills bases developed throughout my career in aerospace,
academic studies and new research material I have studied, to produce a report and paper
exploring the limits to which an airframe research project can be perused using a virtual tool set,
and how the results can be presented for future research and manufacturing. The toolsets used are
Catia V5.R20 for design / analysis / kinematics / manufacturing simulation: PATRAN / NASTRAN for
analysis of composite structures: AeroDYNAMIC™ for analysis of aircraft OML / Structural Loads /
performance. This work will also form the basis for a PhD study, it is the product of my own
research, and has not in any part been produced or conceptualised during my employment with
BAE SYSTEMS or any company which is any part thereof.
About this presentation:-
This presentation is Part 4 of a series of 5 presentation Parts which cover the airframe major
structural component development and engine and landing gear integration, and assembly
manufacturing technologies. The contents of this presentation are given in the following slide.
Overview of my current research activities in aircraft design for the ATDA paper.
4. Mr. Geoffrey Allen Wardle. MSc. MSc. ATDA Airframe Design Study 2012-2020
Section 1:- The general design, structural layout of the ATDA Empennage:
Section 2:- The design, structural layout and detail part material selection and manufacturing requirements of
the ATDA Horizontal Tail:
Section 2:- Manufacture / Assembly of PRSUES aircraft Horizontal Tail Torsion Box skin structure:
Section 3:- Manufacture / Assembly of PRSUES aircraft Horizontal Tail Torsion Box internal sub-structure:
Section 4:- Manufacture / Assembly of PRSUES aircraft Horizontal Tail Carry Through Box skins:
Section 5:- Manufacture / Assembly of PRSUES aircraft Horizontal Tail Carry Through Box internal sub-
structure:
Section 6:- Robotic assembly in the development of the Baseline Horizontal Tail (also Robotic Kinematic for
ATDA airframe Study LinkedIn presentation) (in work):
Section 7:- Horizontal tail systems and elevator integration, and integration with aft Fuselage Sections 19 and
19.1 (in work):
Section 8:- The design, structural layout and detail part material selection and manufacturing requirements of
the ATDA Vertical Tail:
Section 9:- Manufacture / Assembly of PRSUES aircraft Vertical Tail Torsion Box skin structure:
Section 10:- Manufacture / Assembly of PRSUES aircraft Vertical Tail Torsion Box internal sub-structure:
Section 11:- Robotic assembly in the development of the Baseline Horizontal Tail (also Robotic Kinematic for
ATDA airframe Study LinkedIn presentation) (in work):
Section 12:- Vertical tail systems and rudder integration, and integration with Fuselage Sections 19 and 19.1
(in work):
ONLY WORK FROM REFERENCED STUDIES MAY BE REPRODUCED WITHOUT EXPRESS PERMISSION
OF MYSELF AND THE AIAA. 4
Contents of this ATDA study overview presentation.
5. Mr. Geoffrey Allen Wardle. MSc. MSc. ATDA Airframe Design Study 2012-2020
ATDA Baseline Vertical tail design.
The vertical tail presents a set of design issues which are different from those of the wing, or
horizontal tail and these are be itemised below:-
a) It is not unusual for the vertical tail of a large transport to be integrally attached to (but still
removable from) the rear fuselage, the leading and trailing edge spars of the vertical tail being
attached to dedicated fuselage frames. A root integration plate is built into the vertical tail to
coincide with the upper surface of the fuselage and is used to transmit the vertical tail root skin
shear loads directly into the fuselage skin, this is the case with the Boeing 787 and 777 CFC
vertical tails which use a tension fitting plate to interface with the fuselage with attachment to
this plate at the VT torsion box leading and trailing edge spars. Vertical tail span-wise bending
results in a fuselage torsion. In some cases it is logical to incline the rear spar bulkhead to
continue the line of the rear spar of the vertical tail torsion box, as this is usually at the end of
the fuselage well aft of the rear pressure bulkhead, although no current airliner produced by
either Airbus or Boeing has adopted this layout. All of the current large Airbus and Boeing
passenger aircraft, based on published data from literature surveys and examination of aircraft
cutaways attaching the rear spar to perpendicular frames. The front spar and any intermediate
attachments to frames are also made to perpendicular frame stations within the aft fuselage,
with the transition being made at the Vertical Tail root rib or integration plate in the case of the
B-777 , and B-787, shown in figure 1(a)ii The structural layout is generally the same format as
the wing with front and rear spars and ribs forming the vertical tail torsion box, with additional
rudder hinge ribs and auxiliary front spar to support de-icing equipment and other systems in
the vertical tail leading edge fairing. 5
Section 1:- The general design and structural layout of ATDA empennage.
6. Mr. Geoffrey Allen Wardle. MSc. MSc. ATDA Airframe Design Study 2012-2020
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Figure 1(a):- ATDA Vertical tail showing fuselage attachment design philosophy.
Figure 1(a)i:- Airbus A350 XWB Vertical tail to
fuselage attachment philosophy i.e. leading edge,
trailing edge spar, and intermediate attachment lugs
into fuselage clevis fittings (Flight International and
Airbus gallery). Rudder is CFC and Nomex
honeycomb skins with aluminium ribs.
Figure 1(a)ii:- Boeing 777 and 787 Vertical tail to fuselage
attachment philosophy i.e. Tension fixtures and integration
plate (Flight International and Boeing gallery). Rubber is CFC
and Nomex honeycomb skins with aluminium ribs.
7. Mr. Geoffrey Allen Wardle. MSc. MSc. ATDA Airframe Design Study 2012-2020
b) Alternatively the vertical tail is designed to be readily detached as in the case of fighter aircraft
and modern large transports, in this case attachment is through a system of lugs attached to
the leading edge and trailing edge spars and intermediate lugs as shown for the Airbus A350 in
figure 1(a)i. The vertical attachment lugs are arranged in both lateral and fore and aft directions
so that in addition to vertical loads they react side and drag loads. The normal layout being that
the lugs attached to the leading edge spar arranged laterally and react the vertical and drag
loads, and the lugs attached to the trailing edge spar are arranged in the fore and aft direction
and react the vertical and side loads. This lug attachment philosophy was selected for the
ATDA vertical tail which is attached at the leading edge and trailing edge spars with lateral and
fore and aft lugs to perpendicular fuselage frames.
c) The rudder attachment to the vertical tail is invariably supported by a number of discrete hinges
and number and location of these hinges depends on the length and weight of the rudder, and
the other major points to consider in rudder attachment design are as follows:-
i. The bending distortion of the control surface relative to the fixed vertical tail must be limited
so that the nose of the control does not foul the fixed shroud:
ii. The control hinge loads and the resulting shear forces and bending moments should be
equalized as far as possible:
iii. Structural failure of a single hinge should be tolerated unless each hinge is of fail-safe
design and can tolerate cracking in one load path.
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The design and structural layout of ATDA empennage (continued).
8. Mr. Geoffrey Allen Wardle. MSc. MSc. ATDA Airframe Design Study 2012-2020
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Figure 1(b):- ATDA Vertical tail showing internal structural layout key datum positions.
Fwd Attachment Frame interface:- two
lateral lugs the Leading Edge spar root.
Aft Fuselage
barrel section.
Mid Attachment Frame interface:- two Fore
and Aft lugs on the Mid spar root.
Aft Attachment Frame interface:- two Fore
and Aft lugs on the Trailing Edge spar root.
Triplex rudder
EHA actuators.
CFC Stringers.
CFC Leading Edge Spar.
CFC Vertical Tail Leading
Edge box with Al/Li Ribs.
CFC Mid (Intermediate) Spar.
CFC Trailing Edge Spar.
Al/Li alloy all Ribs.
Rudder CFC Honeycomb
skins with Al/Li ribs .
Figure 1(b)i:- VT / Frame interface.
FWD
Figure 1(b)ii:- VT internal layout Port
skin and stringers removed.
UP
CFC Skins.
Vertical Tail Pf Area = 35.36m²
Rudder Pf Area = 15.00m²
9. Mr. Geoffrey Allen Wardle. MSc. MSc. ATDA Airframe Design Study 2012-2020
These points suggest the use of a relatively large number of discrete hinges but there are
issues associated with this solution. There is the obvious issues of high assembly complexity
and maintenance, and hinge alignment difficulties. Additionally the loads likely to be induced in
the rudder by the distortion under load of the vertical tail to which it is attached may be
significant. These problems do not arise if only two hinge points are used as any span-wise
distortion or misalignment can be accommodated by designing one of the hinges so that it can
rotate about a vertical axis a so called „floating‟ hinge. When more than two hinges are used
this „floating‟ hinge concept cannot fully overcome the problems. However it is possible to
design the control surface so that it is flexible in bending and indeed the more hinges there are
the easier this is to accomplish. One hinge must always be capable of reacting side loads in the
plane of the control surface, the hinges being supported near to the aft extremities of the
vertical tail ribs. For the initial internal structural layout concept the ATDA Baseline Vertical Tail
the rudder attachment layout of the Airbus A330 was used as a starting point for analysis using
AeroDYNAMIC™ of loads and detailed structural analysis.
ATDA Baseline Horizontal tail design.
When the horizontal tail is constructed as a single component across the centreline of the aircraft
the basic structural requirements are the very similar to the wing see above. Therefore to address
this the concept structure was designed as two spar multi rib torsion box, with two actuator
positions for the elevator on the Port and Stbd Horizontal Tail Planes figure 2(b), this is similar to
the Airbus A350 WXB, and A330. The Boeing 787 takes a different approach with the horizontal tail
torsion box being multi spar construction. The all moving ATDA horizontal tail is attached to the
fuselage by the fwd Screw Jack actuator fitting and aft pivot lugs figure 2(a). 9
The design and structural layout of ATDA empennage (continued).
10. Mr. Geoffrey Allen Wardle. MSc. MSc. ATDA Airframe Design Study 2012-2020
10
Figure 2(a):- ATDA Horizontal tail showing internal and interface design philosophy.
Figure 2(a):- Airbus A350 XWB Horizontal tail to fuselage attachment philosophy i.e. stiffened centre box is attached to
the screw jack actuator at the front, and at trailing edge is attachment with two pivot outer lugs. The same basic layout is
used by Boeing (Flight International and Airbus gallery). Elevators are constructed of CFC skinned Nomex honeycomb
skin panels with aluminium ribs, and mesh instead of electrical bonding straps.
Port Lug
Stbd Lug
HT Composite leading edge spars.
11. Mr. Geoffrey Allen Wardle. MSc. MSc. ATDA Airframe Design Study 2012-2020
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Figure 2(b):- ATDA Horizontal tail showing internal structure layout.
Jack Screw actuator
attachment fitting
Elevators CFC Honeycomb
skins with Al/Li ribs
HT pivot lugs
Fixed CFC LE /TE spars
CFC Torsion Box Skins
CFC Ribs attached to Stitched Skin Cleats
Al/Li Topologically
Stiffened AM Ribs
Al/Li Topologically
Stiffened AM Ribs
PRSEUS Skin Stringers
Al/Li Machined Ribs
Ti Ribs to Spar Cleats
Ti Machined
Removable LE Spar
Ti Machined
Removable Ribs
Ti Machined Tip Rib
Ti Machined Root Ribs
FWD
UP
PORT
Top cover skins, splices and
stringers removed for clarity.
12. Mr. Geoffrey Allen Wardle. MSc. MSc. ATDA Airframe Design Study 2012-2020
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Figure 3:- ATDA HT Port / Stbd Top Cover Skin With PRSEUS Stringers.
Top Port cover skin, laid up on female tool in dry state,
preform stringers are mounted in position using soft
tooling. The stringers are then stitched by robot arm to
the cover skin. This is followed by covering the internal
surface with permeable membrane, and vacuum
bagging of the assembly.
This assembly is then positioned in a walk in oven and the inlet and exit feed
tubes are connected being positioned with main feed tubes at the root and
main vacuum tubes at the tip. The oven is heated to 60ºC, during injection the
permeable material results in a combination of in-plane and through thickness
flow reducing infusion times. Following injection cured at 93ºC, for 5 hours,
and finally with vacuum bag removed post cured at 176ºC for two hours. This
is followed by CNC machining to remove excess material.
13. Mr. Geoffrey Allen Wardle. MSc. MSc. ATDA Airframe Design Study 2012-2020
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Figure 4:- ATDA HT Port / Stbd Bottom Cover Skin With PRSEUS Stringers and Cleats.
Bottom Port cover skin, laid up on female tool in dry state, preform
stringers are mounted in position using soft tooling. The stringers
are then stitched by robot arm to the cover skin. The CFC Rib
cleats are then mounted over the stringers and stitched in place
using the stringers as determinate assembly aids. This is followed
by covering the internal surface with permeable membrane, and
vacuum bagging of the assembly.
This assembly is then positioned in a walk in oven and the inlet and exit feed
tubes are connected being positioned with main feed tubes at the root and
main vacuum tubes at the tip. The oven is heated to 60ºC, during injection the
permeable material results in a combination of in-plane and through thickness
flow reducing infusion times. Following injection cured at 93ºC, for 5 hours,
and finally with vacuum bag removed post cured at 176ºC for two hours. This
is followed by CNC machining to remove excess material.
14. Mr. Geoffrey Allen Wardle. MSc. MSc. ATDA Airframe Design Study 2012-2020
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Figure 5:- ATDA HT Port / Stbd Internal Structural Layout.
CFC Resin Infused Rib
with integral fwd cleats.
CFC Resin Infused Rib
with integral fwd cleats.
CFC Resin Infused Rib.
CFC Resin Infused Rib.
Al/Li Single Sided Topologically
Stiffened EB wire AM formed Ribs
Al/Li Standard Single
Sided Machined Ribs
Ti Standard Double Sided
Machined Tip Rib
CFC Fibre Placed TE Spar.
CFC Resin Infused TE Spar
with tip integral cleat.
CFC Resin
Infused Stub
Ribs Integral
stiffeners.
Ti Machined Cleats.
Ti Standard Single Sided Machined
removable spar and ribs.
15. Mr. Geoffrey Allen Wardle. MSc. MSc. ATDA Airframe Design Study 2012-2020
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Figure 6:- ATDA HT Carry Through Box Top Cover Skin With PRSEUS Stringers.
Top HT Carry Through Box Top cover skin, laid up on
female tool in dry state, preform stringers are mounted
in position using soft tooling. The stringers are then
stitched by robot arm to the cover skin. This is followed
by covering the internal surface with permeable
membrane, and vacuum bagging of the assembly.
This assembly is then positioned in a walk in oven and the inlet and exit feed
tubes are connected being positioned with main feed tubes at the root and
main vacuum tubes at the tip. The oven is heated to 60ºC, during injection the
permeable material results in a combination of in-plane and through thickness
flow reducing infusion times. Following injection cured at 93ºC, for 5 hours,
and finally with vacuum bag removed post cured at 176ºC for two hours. This
is followed by CNC machining to remove excess material.
16. Mr. Geoffrey Allen Wardle. MSc. MSc. ATDA Airframe Design Study 2012-2020
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Figure 7:- ATDA HT Carry Through Box Bottom Cover Skin With PRSEUS Stringers.
Top HT Carry Through Box Bottom cover skin, laid up
on female tool in dry state, preform stringers are
mounted in position using soft tooling. The stringers are
then stitched by robot arm to the cover skin. This is
followed by covering the internal surface with
permeable membrane, and vacuum bagging of the
assembly.
This assembly is then positioned in a walk in oven and the inlet and exit feed
tubes are connected being positioned with main feed tubes at the root and
main vacuum tubes at the tip. The oven is heated to 60ºC, during injection the
permeable material results in a combination of in-plane and through thickness
flow reducing infusion times. Following injection cured at 93ºC, for 5 hours,
and finally with vacuum bag removed post cured at 176ºC for two hours. This
is followed by CNC machining to remove excess material.
17. Mr. Geoffrey Allen Wardle. MSc. MSc. ATDA Airframe Design Study 2012-2020
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Figure 8:- ATDA HT Carry Through Box Internal Structural Layout.
Ti Standard Double Sided
Machined Root Rib
Ti Standard Double Sided
Machined Root Rib
Ti Spar to Root Rib
Fwd Splice Plates
Ti Spar to Root Rib
Fwd Splice Plates
Ti Spar to Root Rib
Aft Splice Plates
Ti Spar to Root Rib
Aft Splice Plates
Al/Li Double Sided Topologically
Stiffened EB wire AM formed Ribs
CFC Fibre Placed TE Spar.
CFC Fibre Placed LE Spar.
Jack Screw actuator
attachment fitting
Jack Screw over
run Stop Rod lug.
Jack Screw over run
Stop Rod lug.
HT pivot lugs.
18. Mr. Geoffrey Allen Wardle. MSc. MSc. ATDA Airframe Design Study 2012-2020
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WORK IN PROGRESS DRAFT NOT FOR ISSUE
AIAA.