O objetivo desse trabalho é o desenvolvimento da parte mecânica de um Telescópio Imageador para observação de raios-x gama emitidos por fontes celestes. Devido à influência da atmosfera, as observações a serem executadas deverão ocorrer a 40 km de altitude em uma gôndola que voará acoplada a um balão estratosférico, capacitada para apontamento e estabilização em alvos celestes através dos eixos de elevação e azimute.Visando o desenvolvimento, foi feita uma ampla revisão bibliográfica levando-se as soluções mecânicas e restrições do projeto. Com base nesse levantamento foi definida a arquitetura do sistema, resultando num mecanismo de elevação do telescópio; um mecanismo de desacoplamento de movimentos rotacionais; uma roda de reação para o controle de movimentos azimutais e a própria gôndola. O projeto do telescópio foi feito com o auxílio de CAD, e na análise estrutural, utilizou-se técnicas de elementos finitos, sendo NASTRAN o software utilizado. Os componentes utilizados foram validados através da simulação do modelo dinâmico desenvolvido. Foi utilizado para essa simulação, um controle bastante simples tipo P-D, através do qual se conclui que a configuração utilizada é satisfatória para que se atenda às restrições do projeto, com um consumo de potência bastante razoável e um bom tempo de resposta.

Discrepancies between the predicted responses of a finite element analysis (FEA) and reference data from test results arise for many reasons. Some are due to measurement errors, such as inaccurate sensors, noise in the acquisition system or environmental effects. Some are due to analyst errors precipitated by a lack of familiarity with the modeling or solver software. Still others are introduced by uncertainty in the governing physical relations (linear versus non-linear behavior), boundary conditions or the element material/geometrical properties. It is the uncertainty effects introduced by this last group that this study seeks to redress. The objective is the obtainment of model improvements that will reduce errors in predicted versus measured responses. This technique, whereby measured structural data is used to correct finite element model (FEM) errors, has become known as “model updating”. Model updating modifies any or all of the mass, stiffness, and damping parameters of a FEM until an improved agreement between the FEA data and test data is achieved. Unlike direct methods, producing a mathematical model representing a given state, the goal of FE model updating is to achieve an improved match between model and test data by making physically meaningful changes. This study replaces measured responses by reference output obtained from a FEA of a small spacecraft. This FEM is referred to as the “Baseline” model. A “Perturbed” model is created from this baseline my making prescribed changes to the various component masses. The degree of mass variation results from the level of confidence existing at a mature stage of the design cycle. Statistical mean levels of confidence are assigned based on the type of mass of which there are three types: • Concentrated masses – nonstructural, lumped mass formulation (uncoupled) • Smeared masses – nonstructural mass over length or area, lumped mass formulation (uncoupled) • Mass density – volumetric mass, lumped mass formulation (uncoupled) A methodology is presented that accurately predicts the forces occurring at the interface between the spacecraft and the launch vehicle. The methodology quantifies the relationships between spacecraft mass variations and the interface accelerations in the form of sensitivity coefficients. These coefficients are obtained by performing design sensitivity /optimization analyses while updating the Perturbed model to correlate with the Baseline model. The interface forces are responses obtained from a frequency response analysis that runs within the optimization analysis. These forces arise due to the imposition of unit white noise applied across a frequency range extending up to 200 hertz, a cut-off frequency encompassing the lift-off energy required to elicit global mass response. The focus is on lift-off as it is characterized by base excitation, which produces the largest interface forces.

Die Mehrkörpersimulation (MKS) kommt in immer mehr Bereichen zum Einsatz. Bis vor einigen Jahren war das Thema fast ausschließlich im Automobilbereich wichtig. Heute wird der Ansatz in fast allen Bereichen der Technik, in dem „Bewegungsabläufe“ eine Rolle spielen, eingesetzt. Im Gegensatz zur Finite Elemente (FE)-Methode, für die eine detaillierte Bauteiltopologie mit einer Vielzahl von Elementen nötig ist, können mit MKS-Systemen selbst komplexe mechanische Systeme mit einer relativ geringen Anzahl an Freiheitsgraden abgebildet werden. Das Programm Adams hat diese Entwicklung maßgeblich mit gestaltet. Neben den Erweiterungen im Bereich der Solver und anderer mathematischer Formulierungen war immer die einfache Benutzerführung, die Integration von weiteren Simulationstechnologien und auch die Entwicklung von Spezialanwendungen ein wichtiges Thema der Entwicklung. Im Rahmen dieses Vortrages wird der Einsatz von Adams an Hand von Beispielen demonstriert. Weiterer Schwerpunkt ist die Erweiterung der Modelle durch Berücksichtigung der elastischen Materialeigenschaften einzelner Bauteile. Die Kopplung zur Lebensdauerberechnung an Hand von Beispielen schließt den Beitrag ab.

O whirl flutter é um fenômeno aeroelástico característico de aeronaves com motores a hélice. Trata-se da instabilidade do movimento de precessão da hélice devido ao acoplamento dos deslocamentos de arfagem e guinada em conjunto com a atuação das forças aerodinâmicas, que alimentam as oscilações do sistema. Inicialmente, o presente trabalho busca entender este mecanismo de flutter através de uma revisão bibliográfica e da obtenção das equações de movimento para um sistema simples com dois graus de liberdade. A seguir, apresenta-se uma metodologia para os cálculos de whirl flutter com o uso do software comercial MSC/NASTRAN. O processo é aplicado ao estudo de caso de uma aeronave bimotora de pequeno porte, utilizando um modelo de elementos finitos para a estrutura de fixação do motor. A introdução dos efeitos giroscópicos e aerodinâmicos da hélice é proporcionada por um pré-processador externo, que também tem o seu funcionamento apresentado. As respostas do NASTRAN para o estudo de caso são então comparadas aos resultados de um programa específico para o cálculo de whirl flutter.

This work describes the creation of detailed FEM models of the selected area. Primarily is focused on the process of creating a detailed FEM model of the part of airplane using the static condensation. This work also contains a description of the process stress analysis of part of the fuselage of the airplane EV-55 Outback.

No description available.

Die Mehrkörpersimulation (MKS) kommt in immer mehr Bereichen zum Einsatz. Bis vor einigen Jahren war das Thema fast ausschließlich im Automobilbereich wichtig. Heute wird der Ansatz in fast allen Bereichen der Technik, in dem „Bewegungsabläufe“ eine Rolle spielen, eingesetzt. Im Gegensatz zur Finite Elemente (FE)-Methode, für die eine detaillierte Bauteiltopologie mit einer Vielzahl von Elementen nötig ist, können mit MKS-Systemen selbst komplexe mechanische Systeme mit einer relativ geringen Anzahl an Freiheitsgraden abgebildet werden. Das Programm Adams hat diese Entwicklung maßgeblich mit gestaltet. Neben den Erweiterungen im Bereich der Solver und anderer mathematischer Formulierungen war immer die einfache Benutzerführung, die Integration von weiteren Simulationstechnologien und auch die Entwicklung von Spezialanwendungen ein wichtiges Thema der Entwicklung. Im Rahmen dieses Vortrages wird der Einsatz von Adams an Hand von Beispielen demonstriert. Weiterer Schwerpunkt ist die Erweiterung der Modelle durch Berücksichtigung der elastischen Materialeigenschaften einzelner Bauteile. Die Kopplung zur Lebensdauerberechnung an Hand von Beispielen schließt den Beitrag ab.

The AHRLAC aircraft is a high performance light aircraft that is developed and manufactured in South Africa by Aerosud ITC in partnership with Paramount. This aircraft is the first of its kind to originate from South Africa. The aircraft has a twin boom, tandem pilot seating configuration, with a Pratt and Whitney turbine-propeller engine in a pusher configuration. The main structure of the aircraft is a conventional metallic structure, while the fairings and some secondary structures are composite. This study will focus on the design and development of the composite ventral fin of the first prototype aircraft, the experimental demonstrator model (XDM). It is crucial to ensure that the ventral fin can function safely within the design requirements of the aircraft under the loads which the fin is likely to encounter. Preceding the design process, a critical overview of composite materials used in aircraft applications is provided. This will include the materials, manufacturing methods, analysis and similar work done in this field of study. The literature will be used in the study for decision-making and validation of proven concepts and methodologies. The first part of this study entailed choosing a suitable composite material and manufacturing method for this specific application. The manufacturing method and materials used had to suit the aircraft prototype application. The limitations of using composite materials were researched as to recognize bad practice and limit design flaws on the ventral fin. Once the material and manufacturing methods were chosen, ventral fin concepts were evaluated using computer aided finite element analysis (FEA) with mass, stiffness and strength being the main parameters of concern. The load cases used in this evaluation were given by the lead structural engineer and aerodynamicist. The calculations of these loads are not covered in detail in this study. The FEA input material properties used, were determined by material testing by the relevant test methods. The ventral fin concept started as the minimal design with the lowest mass. The deflections, composite failure and fastener failure were then evaluated against the required values. The concept was modified by adding stiffening elements, such as ribs and spars, until satisfactory results were obtained. In this way a minimal mass component is designed and verified that it can adequately perform its designed tasks under the expected load conditions. Each part used in the ventral fin assembly was not individually optimized for mass, but rather the assembly as a whole. The final concept was modelled using the computer aided design software, CATIA. This model used in combination with a ply book made it possible to manufacture the ventral fin in a repeatable manner. A test ventral fin was manufactured using the selected materials and manufacturing methods to validate the design methodology. In the next step the selected load cases were used in static testing to validate the FEM through comparison. The result of the study is a composite ventral fin of which the mass, stiffness and strength are suitable to perform its function safely on the first prototype AHRLAC aircraft. The study concludes on the process followed from material selection to FEA and detail design, in order for this same method to be used on other AHRLAC XDM composite parts. / M (Mechanical Engineering), North-West University, Potchefstroom Campus, 2015

The AHRLAC aircraft is a high performance light aircraft that is developed and manufactured in South Africa by Aerosud ITC in partnership with Paramount. This aircraft is the first of its kind to originate from South Africa. The aircraft has a twin boom, tandem pilot seating configuration, with a Pratt and Whitney turbine-propeller engine in a pusher configuration. The main structure of the aircraft is a conventional metallic structure, while the fairings and some secondary structures are composite. This study will focus on the design and development of the composite ventral fin of the first prototype aircraft, the experimental demonstrator model (XDM). It is crucial to ensure that the ventral fin can function safely within the design requirements of the aircraft under the loads which the fin is likely to encounter. Preceding the design process, a critical overview of composite materials used in aircraft applications is provided. This will include the materials, manufacturing methods, analysis and similar work done in this field of study. The literature will be used in the study for decision-making and validation of proven concepts and methodologies. The first part of this study entailed choosing a suitable composite material and manufacturing method for this specific application. The manufacturing method and materials used had to suit the aircraft prototype application. The limitations of using composite materials were researched as to recognize bad practice and limit design flaws on the ventral fin. Once the material and manufacturing methods were chosen, ventral fin concepts were evaluated using computer aided finite element analysis (FEA) with mass, stiffness and strength being the main parameters of concern. The load cases used in this evaluation were given by the lead structural engineer and aerodynamicist. The calculations of these loads are not covered in detail in this study. The FEA input material properties used, were determined by material testing by the relevant test methods. The ventral fin concept started as the minimal design with the lowest mass. The deflections, composite failure and fastener failure were then evaluated against the required values. The concept was modified by adding stiffening elements, such as ribs and spars, until satisfactory results were obtained. In this way a minimal mass component is designed and verified that it can adequately perform its designed tasks under the expected load conditions. Each part used in the ventral fin assembly was not individually optimized for mass, but rather the assembly as a whole. The final concept was modelled using the computer aided design software, CATIA. This model used in combination with a ply book made it possible to manufacture the ventral fin in a repeatable manner. A test ventral fin was manufactured using the selected materials and manufacturing methods to validate the design methodology. In the next step the selected load cases were used in static testing to validate the FEM through comparison. The result of the study is a composite ventral fin of which the mass, stiffness and strength are suitable to perform its function safely on the first prototype AHRLAC aircraft. The study concludes on the process followed from material selection to FEA and detail design, in order for this same method to be used on other AHRLAC XDM composite parts. / M (Mechanical Engineering), North-West University, Potchefstroom Campus, 2015

This thesis presents a research project and results of design and optimization of a composite wing structure for a large aircraft in flying wing configuration. The design process started from conceptual design and preliminary design, which includes initial sizing and stressing followed by numerical modelling and analysis of the wing structure. The research was then focused on the minimum weight optimization of the /composite wing structure /subject to multiple design /constraints. The modelling, analysis and optimization process has been performed by using the NASTRAN code. The methodology and technique not only make the modelling in high accuracy, but also keep the whole process within one commercial package for practical application. The example aircraft, called FW-11, is a 250-seat commercial airliner of flying wing configuration designed through our MSc students Group Design Project (GDP) in Cranfield University. Started from conceptual design in the GDP, a high-aspect-ratio and large sweepback angle flying wing configuration has been adopted. During the GDP, the author was responsible for the structural layout design and material selection. Composite material has been chosen as the preferable material for both the inner and outer wing components. Based on the derivation of structural design data in the conceptual phase, the author continued with the preliminary design of the outer wing airframe and then focused on the optimization of the composite wing structure. Cont/d.