985 research outputs found

    Model-based Design Framework for Shape Memory Alloy Wire Actuation Devices.

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    While Shape Memory Alloys (SMAs) have exceptional actuation characteristics such as high energy density, silent operation, flexible packaging, etc., they have not found widespread use in commercial applications because of the significant learning curve required of engineers before they are capable of designing actuation devices using this unique material. An SMA actuation device design framework consisting of grammar, design methods, and design process enables engineers of different backgrounds to make efficient and appropriate design decisions in different stages of the design process. A reference SMA actuation device structure built on a generalized actuation device hierarchical structure using the actuation device grammar works as a reference structure to identify and populate device design options, and to model and analyze the device actuation performance as well as to enlighten non-expert engineers about the essential elements of SMA actuation devices. Design methods consisting of modular modeling, model aggregation and performance prediction, and visualization approaches support design decisions to serve diverse stakeholders of actuation device design by exposing the effects of individual device elements not only for SMA actuation devices, but also for a wide range of actuation devices. A multi-stage design process is formalized to help engineers create a detailed design including a three-step decoupled equilibrium design procedure which prevents potential iteration by decoupling the force and deflection of actuation output behavior, and hides the complexity of material and SMA architectural models from engineers while still exposing the impact of design parameters. The design framework makes SMA design knowledge more accessible to engineers with different levels of expertise and roles in device development by systematically organizing and presenting the device grammar, design methods, and design process. A design tool software platform based on the framework enables the creation of computer-aided design tools to support a variety of design tasks, which were demonstrated in two use case examples. By having the SMA actuation device design framework, the acceptance of the SMA actuation technology into both research and commercial applications can be increased to utilize promising SMA actuation benefits, and the device development cycle leading to these applications can be streamlined.PhDMechanical EngineeringUniversity of Michigan, Horace H. Rackham School of Graduate Studieshttp://deepblue.lib.umich.edu/bitstream/2027.42/120684/1/wonhekim_1.pd

    Integrated multi-functional morphing aircraft technologies

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    In the past years, the development of morphing wing technologies has received a great deal of interest from the scientific community. These technologies potentially enable an increase in aircraft efficiency by changing the wing shape, thus allowing the aircraft to fly near its optimal performance point at different flight conditions. This thesis explores the development, analysis, building and integration of two new functional Variable-Span Wing (VSW) concepts to be applied in Remotely Piloted Aircraft Systems (RPAS). Additional studies are performed to synthesize the mass of such morphing concepts and to develop mass prediction models. The VSW concept is composed of one fixed rectangular inboard part, inboard fixed wing (IFW), and a moving rectangular outboard part: outboard moving wing (OMW). An aerodynamic shape optimization code is used to solve a drag minimization problem to determine the optimal values of wingspan for various speeds of the vehicle’s flight envelope. It was concluded that, at low speeds, the original wing has slightly better performance than the VSW and for speeds higher than 25 m/s the opposite occurs, due to the reduction in wing area and consequently the total wing drag. A structural Finite Element Model (FEM) of the VSW is developed, where the interface between wing parts is modelled. Deflections and stresses resulting from static aerodynamic loading conditions showed that the wing is suitable for flight. Flutter critical speed is studied. FEM is used to compute the VSW mode shapes and frequencies of free vibration, considering a rigid or the real flexible interface, showing that the effect of rigidity loss in the interface between the IFW and the OMW, has a negative impact on the critical flutter speed. A full-scale prototype is built using composite materials and an electro-mechanical actuation system is developed using a rack and pinion driven by two servomotors. Bench tests, performed to evaluate the wing and its actuation mechanism under load, showed that the system can perform the required extension/retraction cycles and is suitable to be installed on a RPAS airframe, which has been modified and instrumented to serve as test bed for evaluating the prototype in-flight. Two sets of flight tests are performed: aerodynamic and energy characterization. The former aims at determining the lift-to-drag ratio for different airspeeds and the latter to measure the propulsive and manoeuvring energy when performing a prescribed mission. In the aerodynamic testing, in-flight evaluation of the RPAS fitted with the VSW demonstrates full flight capability and shows improvements produced by the VSW over a conventional fixed wing for speeds above 19 m/s. At low speeds, the original wing has slightly better lift-to-drag ratio than the VSW. Contrarily, at 30 m/s, the VSW in minimum span configuration is 35% better than the original fixed wing. In the other performed test, it is concluded that the VSW fitted RPAS has less overall energy consumption despite the increased vehicle weight. The energy reduction occurs only in the high speed condition but it is so marked that it offsets the increase in energy during takeoff, climb and loiter phases. Following the work on the first VSW prototype, a new telescopic wing that allows the integration of other morphing strategies is developed, within the CHANGE EU project. The wing adopted span change, leading and trailing edge camber changes. A modular design philosophy, based on a wing-box like structure, is implemented, such that the individual systems can be separately developed and then integrated. The structure is sized for strength and stiffness using FEM, based on flight loads derived from the mission requirements. A partial span, fullsized cross-section prototype is built to validate the structural performance and the actuation mechanism capability and durability. The wing is built using composite materials and an electromechanical actuation system with an oil filled nylon rack and pinion is developed to actuate it. The structural static testing shows similar trends when compared with numerical predictions. The actuation mechanism is characterized in terms of actuation speed and specific energy consumption and it was concluded that it functioned within its designed specifications. A full-scale prototype is later built by the consortium and the leading and trailing edge concepts from the different partners integrated in a single wing. Wind tunnel tests confirmed that the wing can withstand the aerodynamic loading. Flight tests are performed by TEKEVER, showing that the modular concept works reliably. From the previous works, it is inferred that morphing concepts are promising and feasible methodologies but present an undesired mass increase due to their inherent complexity. On the other hand, mass prediction methods to aid the design of morphing wings at the conceptual design phase are rare. Therefore, a mass model of a VSW with a trailing edge device is proposed. The structural mass prediction is based on a parametric study. A minimum mass optimization problem with stiffness and strength constraints is implemented and solved, being the design variables structural thicknesses and widths, using a parametric FEM of the wing. The study is done for a conventional fixed wing and the VSW, which are then combined to ascertain the VSW mass increment, i.e., the mass penalization of the adopted morphing concept. Polynomials are found to produce good approximations of the wing mass. Additionally, the effects of various VSW design parameters in the structural mass are discussed. On one hand, it was found that the span and chord have the highest impact in the wing mass. On the other hand, the VSW to fixed wing ratio proved that the influence of span variation ratio in the wing mass is not trivial. It is found that the mass increase does not grow proportionally with span variation ratio increase and that for each combination of span and chord, exists a span variation ratio that minimizes the mass penalty. Using the VSW to fixed wing ratio function, the mass model is derived. To ascertain its accuracy, a case study is performed, which demonstrated prediction errors below 10%. Although the mass model results are encouraging, more case studies are necessary to prove its applicability over a wide range of VSWs. The work performed successfully demonstrated that VSW concepts can achieve considerable geometry changes which, in turn, translate into considerable aerodynamic gains, despite the increased weight. They influence all aspects of the wing design, from the structural side to the actuation mechanisms. The parametric study summarizes the mass penalties of such concepts, being successful at demonstrating that the mass penalty is not straightforward and that a careful selection of span, chord and variable-span ratio can minimize the mass increase.Nos últimos anos, o desenvolvimento de asas adaptativas tem sido alvo de um grande interesse por parte da comunidade científica. Nesta tese explora-se o desenvolvimento, análise, construção e integração de dois novos conceitos de Asas de Envergadura Variável (VSWs) funcionais a serem aplicados em Sistemas de Aeronaves Pilotadas Remotamente (RPASs). Estudos adicionais são levados a cabo para sintetizar a massa desses conceitos e desenvolver modelos de previsão de massa. O conceito da VSW é constituído por uma parte interna retangular fixa, Asa Fixa Interna (IFW), e por uma parte externa retangular móvel, Asa Móvel Externa (OMW). Um código de otimização aerodinâmica é utilizado para minimizar a resistência ao avanço, determinando os valores ótimos de envergadura para várias velocidades de voo do veículo. Concluiu-se que, a baixas velocidades, a asa original apresenta um desempenho ligeiramente melhor que a VSW, enquanto que a velocidades superiores a 25 m/s, a VSW apresenta um desempenho melhor devido à redução da área das asas e, consequentemente, à redução da resistência total das asas. Para levar a cabo um estudo estrutural, foi desenvolvido um Modelo de Elementos Finitos (FEM) estrutural da VSW, no qual se modelou a interface entre a IFW/OMW. As deflexões e tensões resultantes dos carregamentos aerodinâmicos estáticos mostraram que a asa é capaz de suportar as cargas em voo. A velocidade de flutter é também investigada, sendo o FEM utilizado para calcular as formas dos modos de vibração da VSW e respetivas frequências de vibração livre. Considerou-se uma interface colada ou flexível, confirmando-se que o efeito da perda de rigidez na interface IFW/OMW, tem um impacto negativo sobre a velocidade de flutter. Um protótipo da VSW é construído, utilizando materiais compósitos, e um sistema de atuação eletromecânico é desenvolvido usando um sistema de pinhão e cremalheira movido por dois servomotores. Os testes de bancada, realizados para avaliar a asa e o mecanismo de atuação, mostraram que o sistema é capaz de realizar a extensão/retração da asa, sendo adequado para ser instalado num RPAS. Este RPAS foi modificado e instrumentado para servir de banco de ensaio para avaliação do protótipo em voo. São realizados dois conjuntos de testes de voo: caracterização aerodinâmica e energética. O primeiro incide na determinação da razão de planeio para diferentes velocidades e o segundo é levado a cabo para determinar a energia propulsiva e de manobra ao executar uma missão típica. Nos testes aerodinâmicos ficou comprovado que o RPAS equipado com a VSW é capaz de uma normal operação e ainda que mostra melhorias sobre uma asa fixa convencional para velocidades acima de 19 m/s. A velocidades mais reduzidas, a asa original tem um desempenho ligeiramente melhor do que a VSW. Por outro lado, a 30 m/s, a VSW na configuração de envergadura mínima é 35% melhor do que a asa fixa original. No outro ensaio realizado, conclui-se que o RPAS de envergadura variável tem menos consumo de energia global, apesar do aumento de peso do veículo. A redução de energia ocorre apenas na fase de cruzeiro de alta velocidade, mas foi tão acentuada que compensou o aumento da energia durante as fases de descolagem, subida e espera. Na sequência do trabalho anterior e no âmbito do projeto europeu CHANGE, é desenvolvida uma nova VSW que permite a integração de outras estratégias adaptativas. A nova asa adotou a mudança de envergadura, e a mudança de curvatura nos bordos de ataque e de fuga. Esta adotou uma filosofia de projeto modular, baseada numa caixa de torção, permitindo o desenvolvimento das diferentes tecnologias adaptativas separadamente. A estrutura é divmensionada para resistência e rigidez usando FEM, com base em cargas de voo derivadas dos requisitos da missão. Um primeiro protótipo é construído para validar o desempenho estrutural e a funcionalidade do mecanismo de atuação. A asa é construída usando materiais compósitos e utiliza um sistema de pinhão e cremalheira e um servomotor, para variar a envergadura. Testes estruturais estáticos mostram que as deflexões corroboram as previsões numéricas. O mecanismo de atuação é caracterizado em termos de velocidade de atuação e consumo de energia específica, concluindo-se que funciona dentro do previsto. O segundo protótipo é construído pelo consórcio e os conceitos de bordo de ataque e de fuga são integrados. Testes em túnel de vento confirmaram que a asa suporta o carregamento aerodinâmico. Os testes de voo, realizados pela TEKEVER, mostram que o conceito modular funciona de forma fiável. Baseado nos trabalhos anteriores, conclui-se que os conceitos adaptativos são promissores e viáveis, mas apresentam um aumento de massa indesejável devido à sua inerente complexidade. Por outro lado, os métodos de previsão de massa para auxiliar o projeto de asas adaptativas na fase de projeto conceitual são raros. Deste modo, um modelo de massa da VSW com um dispositivo de borda de fuga é proposto. A previsão de massa estrutural é baseada num estudo paramétrico. Um problema de minimização de massa com constrangimentos de rigidez e resistência é implementado e resolvido, sendo as variáveis de projeto espessuras e larguras estruturais. Para o levar a cabo, um FEM paramétrico da VSW é desenvolvido. O estudo é feito para uma asa fixa convencional e para a VSW, os quais são combinados para determinar o incremento de massa da VSW. Aproximações polinomiais das massas da asa são produzidas, mostrando serem capazes de produzir uma adequada representação. Adicionalmente, são discutidos os efeitos dos vários parâmetros de design da VSW na massa estrutural. Por um lado, verificou-se que a envergadura e a corda têm o maior impacto na massa da asa. Por outro lado, a razão de massas da VSW e da asa fixa provou que a influência da razão de variação de envergadura na massa das asas não é trivial. Verifica-se que o aumento de massa não cresce proporcionalmente com o aumento da razão de variação de envergadura e que para um dado conjunto de envergadura e corda existe uma razão de variação de envergadura que minimiza o aumento de massa. O modelo de massa é derivado usando a aproximação polinomial da razão da VSW com a asa fixa. Para verificar a precisão do modelo, é realizado um caso de estudo que demonstrou erros de previsão abaixo dos 10%. Embora os resultados do modelo de massa sejam encorajadores, mais casos de estudo são necessários para provar a sua aplicabilidade a uma ampla gama de VSW. O trabalho realizado demonstrou com sucesso que os conceitos de VSW podem alcançar consideráveis mudanças de geometria, que se traduzem em ganhos aerodinâmicos consideráveis, apesar do aumento de peso. Estes influenciam todos os aspetos do projeto da asa, desde a parte estrutural até aos mecanismos de atuação. O estudo paramétrico tentou resumir a penalização de massa de tais conceitos, sendo bem sucedido em demonstrar que esta penalização não é simples e que uma seleção cuidadosa de envergadura, corda e razão de variação de envergadura pode minimizar o aumento de peso.This thesis and the associated research was partially funded by the European Community’s Seventh Framework Programme (FP7) under the Grant Agreement 314139

    Development and testing of a variable-spam morphing wing

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    The present work focuses on the development and validation of a variable-span morphing wing (VSW) to be fitted to a mini UAV. An electro-mechanical actuation mechanism is developed using a simple rack and pinion system. The wing model is designed with the help of graphical CAD/CAE tools and then a full scale model is built for bench testing the strength, power consumption, deployment time and efficiency. The concepts used on the morphing wing for both fixed and moving wing parts are considered simple and effective. Construction methods and materials were evaluated in order to obtain a system as reliable as possible. Still, in future work the VSW structure can be improved by changing some interface components to achieve a smoother deployment. Also, some work is planned on the design optimization code: implementation of a coupled aero-structural analysis model for simultaneous aerodynamic and structural design optimization problems. Main results: deployment times; efficiency.O presente trabalho apresenta o desenvolvimento e ensaio de uma asa de envergadura variável actuada por um sistema electromecânico simples para aplicação no UAV “Olharapo”. Um mecanismo de accionamento electromecânico é desenvolvido com base num sistema de cremalheira e pinhão. O modelo da asa é projectado com a ajuda de ferramentas gráficas CAD / CAE e, em posteriormente, é construído um modelo em escala para ensaios quanto a resistência, consumo de energia, tempo de extensão/retracção e eficiência. Os conceitos utilizados na asa morphing para ambas as partes, fixas e móveis, da asa são consideradas simples e eficazes. Foram avaliados métodos e materiais de construção no intuito de obter um sistema mais fiável e eficaz. Ainda assim, em trabalhos futuros a estrutura VSW pode ser melhorada alterando alguns componentes de interface para conseguir uma actuação mais suave e eficaz. Além disso, é previsto no código de optimização de envergadura capaz de controlar esta em função da velocidade

    DESIGN OF A SEMI-ACTIVE STEERING SYSTEM FOR A PASSENGER CAR

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    This thesis presents research into an improved active steering system technology for a passenger car road vehicle, based on the concept of steer-by-wire (SBW) but possessing additional safety features and advanced control algorithms to enable active steering intervention. An innovative active steering system has been developed as 'Semi-Active Steering' (SAS) in which the rigid steering shaft is replaced with a low stiffness resilient shaft (LSRS). This allows active steer to be performed by producing more or less steer angle to the front steered road wheels relative to the steering wheel input angle. The system could switch to either being 'active' or 'conventional' depending on the running conditions of the vehicle; e.g. during normal driving conditions, the steering system behaves similarly to a power-assisted steering system, but under extreme conditions the control system may intervene in the vehicle driving control. The driver control input at the steering wheel is transmitted to the steered wheels via a controlled steering motor and in the event of motor failure, the LSRS provides a basic steering function. During operation of the SAS, a reaction motor applies counter torque to the steering wheel which simulates the steering 'feel' experienced in a conventional steering system and also applies equal and opposite counter torque to eliminate disturbance force from being felt at the steering wheel during active control operation. The thesis starts with the development of a mathematical model for a cornering road vehicle fitted with hydraulic power-assisted steering, in order to understand the relationships between steering characteristics such as steering feel, steering wheel torque and power boost characteristic. The mathematical model is then used to predict the behaviour of a vehicle fitted with the LSRS to represent the SAS system in the event of system failure. The theoretical minimum range of stiffness values of the flexible shaft to maintain safe driving was predicted. Experiments on a real vehicle fitted with an LSRS steering shaft simulator have been conducted in order to validate the mathematical model. It was found that a vehicle fitted with a suitable range of steering shaft stiffness was stable and safe to be driven. The mathematical model was also used to predict vehicle characteristics under different driving conditions which were impossible to conduct safely as experiments. Novel control algorithms for the SAS system were developed to include two main criteria, viz. power-assistance and active steer. An ideal power boost characteristic curve for a hydraulic power-assisted steering was selected and modified and a control strategy similar to Steer-by-Wire (SBW) was implemented on the SAS system. A full-vehicle computer model of a selected passenger car was generated using ADAMS/car software in order to demonstrate the implementation of the proposed SAS system. The power-assistance characteristics were optimized and parameters were determined by using an iteration technique inside the ADAMS/car software. An example of an open-loop control system was selected to demonstrate how the vehicle could display either under-steer or over-steer depending on the vehicle motion. The simulation results showed that a vehicle fitted with the SAS system could have a much better performance in terms of safety and vehicle control as compared to a conventional vehicle. The characteristics of the SAS system met all the requirements of a robust steering system. It is concluded that the SAS has advantages which could lead to its being safely fitted to passenger cars in the future. Keywords: steer-by-wire, active steering, innovative, power-assisted steering, steering control, flexible shaft, steering intervention, system failure, safety features

    Hydraulically-actuated compliant revolute joint for medical robotic systems based on multimaterial additive manufacturing

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    IEEE International Conference on Robotics and Automation (ICRA), Montréal, Canada, janvier 2019 Research team : AV

    Design of a variable-span morphing wing

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    The present work focuses on the study, design and validation of a variable-span morphing wing to be tted to the UAV \Olharapo". Using an optimization code, which uses a viscous two-dimensional panel method formulation coupled with a non-linear liftingline algorithm and a sequential quadratic programming optimization routine, na aerodynamic analysis is performed to estimate the optimal values of wing span which ensure minimum drag across the ight speed envelope. The UAV ies in a relatively short speed range - from about 12 m/s to 30 m/s. Near its maximum speed it is possible to obtain a 20% drag reduction with the variable-span wing in comparison with the original xed wing. A stability analysis is also performed to estimate the roll rate available with asymmetric span control. The variable-span wing matches the aileron in terms of roll power and maximum roll rate. It is concluded that roll control is possible with asymmetric span control. A new electro-mechanical actuation mechanism is developed using a simple and cheap rack and pinion system. The wing model is designed with graphical CAD/CAM tools and then a full scale model is built for bench testing the wing/actuator system. The concepts used on the morphing wing for both xed and movable part are considered simple and e ective. The actuation concept is also feasible but needs improvements in the attenuator. A powerful servo is also needed to more easily deploy the wing. Some future modi cations at structural level and ideas for an in-flight automatic span controller are also presented.O presente trabalho centra-se no estudo, concepcão e validação de uma asa de envergadura variável para aplicação no UAV \Olharapo". Usando um código de optimização, que usa uma formulação de painéis viscoso bidimensional acoplado a um algoritmo de linha sustentadora não-linear e uma rotina de optimização de programação sequencial quadrática, é realizada uma análise aerodinâmica para estimar os valores óptimos de envergadura de forma a garantir um arrasto mínimo para todas as velocidades do envelope de voo. O UAV opera numa gama de velocidades relativamente pequena - de 12 m/s a 30 m/s, sensivelmente. Próximo da velocidade máxima é possível obter uma redução de 20% no arrasto com a asa de envergadura variável em comparação com a asa fixa original. É realizada uma análise de estabilidade com o objectivo de estimar a taxa de rolamento disponível com controlo assimétrico de envergadura. O desempenho da asa de envergadura variável é idêntico ao da asa original com ailerons em termos de poder de rolamento e de taxa de rolamento. Conclui-se que o controlo de rolamento pode ser efectuado com controlo assimétrico da envergadura. É feita a concepcão de um novo sistema actuador eletro-mecânico recorrendo a um sistema simples de pinhão e cremalheira. O modelo da asa é projectado recorrendo a ferramentas CAD/CAM e posteriormente construído para que o sistema asa/actuador seja testado em bancada. Os conceitos usados na asa morphing para a parte fixa e móvel são considerados simples e efectivos. O sistema de actuação é funcional mas necessita de melhoramentos ao nível do atenuador e requer um servo mais potente para uma actuação da asa mais fácil. Algumas modicações futuras a nível estrutural e algumas ideias para o desenvolvimento de um controlador para regulação automática da envergadura são também apresentadas

    The 29th Aerospace Mechanisms Symposium

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    The proceedings of the 29th Aerospace Mechanisms Symposium, which was hosted by NASA Johnson Space Center and held at the South Shore Harbour Conference Facility on May 17-19, 1995, are reported. Technological areas covered include actuators, aerospace mechanism applications for ground support equipment, lubricants, pointing mechanisms joints, bearings, release devices, booms, robotic mechanisms, and other mechanisms for spacecraft

    The 31st Aerospace Mechanisms Symposium

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    The proceedings of the 31st Aerospace Mechanisms Symposium are reported. Topics covered include: robotics, deployment mechanisms, bearings, actuators, scanners, boom and antenna release, and test equipment. A major focus is the reporting of problems and solutions associated with the development and flight certification of new mechanisms
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