1) O documento apresenta uma análise estrutural da asa do avião de transporte militar Lockheed C-130H utilizando o método de elementos finitos.
2) O autor criou um modelo de elementos finitos da asa no programa Ansys para simular diferentes cargas e identificar zonas críticas da estrutura.
3) Os resultados identificaram algumas áreas da asa onde os níveis de esforço são elevados, requerendo atenção para garantir a segurança da aeronave.
Elevated temperature mechanical_characterization_of_isogrid_boomsFranklin Nagao
This document discusses mechanical testing performed on composite tow samples and an isogrid boom structure at various temperatures. Composite tow samples made from ILC's TP283E shape memory polymer resin and carbon fiber reinforcement were tested to determine flexural and tensile modulus as a function of temperature. An isogrid boom structure made from the same materials was also tested in tension, compression, and creep at different temperatures. The test results of the composite tows and isogrid boom were compared to predicted values calculated using a rule of mixtures analysis.
PERSONALITY DEVELOPMENT FROM UTSAV SHIVHAREUtsav Shivhare
This document contains a personality development assignment submitted by Utsav Shivhare. It includes an acknowledgement, various tasks completed under different units and levels (pass/merit), and responses to questions related to defining concepts like personality, SWOT analysis, emotional intelligence. It also discusses time management, leadership qualities observed in the movie "Paan Singh Tomar", ego states, and an experience from a field activity visiting different establishments like hotels and a deaf and dumb school. The assignment demonstrates Utsav's understanding of key personality development concepts and his ability to apply them in real-life examples and case studies.
This document provides information about various aviation topics in 3 sections. It begins by acknowledging the teacher for their guidance and then discusses current affairs in the aviation industry, identifying key leadership changes and issues. The second section identifies and describes the functions of various aircraft parts. The third section discusses emergency equipment used in aviation emergencies such as smoke hoods and oxygen bottles.
Vortex lattice methods are used to estimate aircraft aerodynamics by solving Laplace's equation. They are similar to panel methods in that singularities are placed on a surface and boundary conditions are applied at control points. However, vortex lattice methods are oriented toward lifting surfaces and treat boundary conditions on a mean surface rather than the actual surface. The document outlines the derivation of the thin airfoil boundary condition and pressure relation used in vortex lattice methods through linearization and transfer of the boundary condition to a reference surface. This allows the problem to be treated as a superposition of lift from camber, thickness, and angle of attack.
1. The document outlines the steps needed to model orthotropic materials and composites in ANSYS Workbench versions 14.0 and 14.5.
2. The steps include creating a layered section geometry, defining a coordinate system, associating the layered section with a geometry, and inserting loads and running the analysis.
3. It is important to verify that the element coordinate systems are oriented as intended and that the model progresses as expected.
1) O documento apresenta uma análise estrutural da asa do avião de transporte militar Lockheed C-130H utilizando o método de elementos finitos.
2) O autor criou um modelo de elementos finitos da asa no programa Ansys para simular diferentes cargas e identificar zonas críticas da estrutura.
3) Os resultados identificaram algumas áreas da asa onde os níveis de esforço são elevados, requerendo atenção para garantir a segurança da aeronave.
Elevated temperature mechanical_characterization_of_isogrid_boomsFranklin Nagao
This document discusses mechanical testing performed on composite tow samples and an isogrid boom structure at various temperatures. Composite tow samples made from ILC's TP283E shape memory polymer resin and carbon fiber reinforcement were tested to determine flexural and tensile modulus as a function of temperature. An isogrid boom structure made from the same materials was also tested in tension, compression, and creep at different temperatures. The test results of the composite tows and isogrid boom were compared to predicted values calculated using a rule of mixtures analysis.
PERSONALITY DEVELOPMENT FROM UTSAV SHIVHAREUtsav Shivhare
This document contains a personality development assignment submitted by Utsav Shivhare. It includes an acknowledgement, various tasks completed under different units and levels (pass/merit), and responses to questions related to defining concepts like personality, SWOT analysis, emotional intelligence. It also discusses time management, leadership qualities observed in the movie "Paan Singh Tomar", ego states, and an experience from a field activity visiting different establishments like hotels and a deaf and dumb school. The assignment demonstrates Utsav's understanding of key personality development concepts and his ability to apply them in real-life examples and case studies.
This document provides information about various aviation topics in 3 sections. It begins by acknowledging the teacher for their guidance and then discusses current affairs in the aviation industry, identifying key leadership changes and issues. The second section identifies and describes the functions of various aircraft parts. The third section discusses emergency equipment used in aviation emergencies such as smoke hoods and oxygen bottles.
Vortex lattice methods are used to estimate aircraft aerodynamics by solving Laplace's equation. They are similar to panel methods in that singularities are placed on a surface and boundary conditions are applied at control points. However, vortex lattice methods are oriented toward lifting surfaces and treat boundary conditions on a mean surface rather than the actual surface. The document outlines the derivation of the thin airfoil boundary condition and pressure relation used in vortex lattice methods through linearization and transfer of the boundary condition to a reference surface. This allows the problem to be treated as a superposition of lift from camber, thickness, and angle of attack.
1. The document outlines the steps needed to model orthotropic materials and composites in ANSYS Workbench versions 14.0 and 14.5.
2. The steps include creating a layered section geometry, defining a coordinate system, associating the layered section with a geometry, and inserting loads and running the analysis.
3. It is important to verify that the element coordinate systems are oriented as intended and that the model progresses as expected.