abstract: With the establishment of the emerging adult developmental period and the rise of helicopter parents, attachment theory provides foundation for conceptualizing the continued involvement of helicopter parents in their emerging adults’ emotion regulation processes. This study utilized dyadic data from 66 emerging adult children and their helicopter parents to examine the association of helicopter parent-emerging adult communication in mitigating the associations between experiences of affect and stress. Specifically, the purpose of the present study was to use dyadic data to examine how communication within the helicopter parent-emerging adult relationship associates with emerging adults’ ability to regulate experiences of negative and positive affect. Both associations within the emerging adult and helicopter parent individually (actor effects) and how helicopter parents impact construct associations for emerging adults’ (partner effects) were considered. Two multilevel mediation models using Actor-Partner Interdependence Models were conducted to assess the relations between affect, stress, and helicopter parent-emerging adult communication quality for negative and positive affect separately. The positive direct effect between negative affect and stress was statistically significant for emerging adults, but not for helicopter parents, suggesting that, for emerging adults, higher perceptions of negative affect were associated with higher levels of stress. The direct and indirect effects for the mediation model examining actor and partner effects between negative affect, communication quality, and stress were non-significant for both emerging adults and helicopter parents. The direct effect between positive affect and stress was statistically significant for helicopter parents but not for emerging adults; however, the directionality of the significant association was positive and not as hypothesized. Finally, the direct and indirect effects for the mediation model examining actor and partner effects between positive affect, communication quality, and stress were non-significant for emerging adults and helicopter parents. Considerations for future studies examining aspects of attachment within emotion regulation for the helicopter parent-emerging adult relationship and the importance of considering relationship characteristics, such the relational characteristics of social support and conflict, are discussed. / Dissertation/Thesis / Doctoral Dissertation Counseling Psychology 2017

O uso de materiais inteligentes em problemas de controle de vibração tem sido investigado em diversas pesquisas ao longo dos últimos anos. Apesar de que diferentes materiais inteligentes estão disponíveis, o piezelétrico tem recebido grande atenção devido à facilidade de uso como sensores, atuadores, ou ambos simultaneamente. As principais técnicas de controle usando materiais piezoelétricos são os ativos e passivos. Circuitos piezelétricos passivos são ajustados para uma frequência específica e, portanto, a largura de banda efetiva é pequena. Embora os sistemas ativos possam apresentar um bom desempenho no controle de vibração, a quantidade de energia externa e hardware adicionado são questões importantes. As técnicas SSD (Synchronized Switch Damping) foram desenvolvidas como uma alternativa aos controladores passivos e controladores ativos de vibração. Elas podem ser técnicas semi-ativas ou semi-passivas que introduzem um tratamento não linear na tensão elétrica proveniente do material piezelétrico e induz um aumento na conversão de energia mecânica para energia elétrica e, consequentemente, um aumento no efeito de amortecimento. Neste trabalho, o controle piezoelétrico semi-passivo de uma pá piezelétrica engastada é apresentado e comparado com outros controladores. O modelo não linear electromecânico de uma pá com piezocerâmicas incorporados é determinado com base no método variacional-assintótico (VAM). O sistema rotativo acoplado não linear é resolvido no domínio do tempo, utilizando um método de integração alfa-generalizado afim de garantir a estabilidade numérica. As simulações são realizadas para uma vasta gama de velocidades de rotação. Em primeiro lugar, um conjunto de resistências (variando desde a condição de curto-circuito para a condição de circuito aberto) é considerada. O efeito da resistência ótima (que resulta em máximo amortecimento) sobre o comportamento do sistema é investigado para o aumento da velocidade de rotação. Mais tarde, a técnica SSDS é utilizada para amortecer as oscilações da pá com o aumento da velocidade de rotação. Os resultados mostram que a técnica SSDS pode ser um método útil para o controle de vibrações de vigas rotativas não lineares, tais como pás de helicóptero. / The use of smart materials in vibration control problems has been investigated in several researches over the last years. Although dierent smart materials are available, the piezoelectric one has received great attention due to ease of use as sensors, actuators, or both. The main control techniques using piezoelectric materials are the active and passive ones. Passive piezoelectric networks are adjusted for specic target frequencies and, therefore, the eective bandwidth of such systems is small. Although active systems can achieve good vibration control performance, the amount of external power and added hardware are important issues. The synchronized switch damping (SSD) technique was developed in order to address the issues of passive damping methodologies as well as the issues of active control systems. The SSD can be classied as semi-passive technique or semi-active technique that introduce the nonlinear treatment of the piezoelectric element voltage output and induce an increase in mechanical to electrical energy conversion and, consequently, the shunt damping eect. In this work, the semi-passive piezoelectric control of a rotating cantilever beam response is presented and compared with other controllers. The nonlinear electromechanical model of a rotating beam with embedded piezoceramics is derived based on the variational-asymptotic method (VAM). The coupled non-linear rotary system is solved in the time-domain by using a generalized-alpha integration method in order to guarantee numerical stability. The simulations are performed for a wide range of rotating speeds. First, a set of load resistances (ranging from short circuit condition to open circuit condition) is considered. The eect of optimum load resistance (for maximum damping) on the elastic behavior of the beam is investigated for increasing rotating speed. Later, the synchronized switch damping on short (SSDS) technique is employed to damp the nonlinear oscillations of the rotating beam with increasing rotating speed. Results show that the SSDS technique can be a useful method of control for nonlinear rotating beams such as helicopter blades.

Modélisation du comportement dynamique des rotors d'hélicoptèresL'objectif de la thèse est l'étude et la modélisation du comportement dynamique et aérodynamique du rotor de l'hélicoptère en considérant à la fois les forces d'inertie et les forces aérodynamiques et en tenant compte des déformations élastiques des pales. L'algorithme de couplage proposé permet d'effectuer le calcul transitoire avec échange de données entre les solveurs fluide et structure à chaque pas de temps.La particularité de cette étude est l'utilisation du modèle aérodynamique de la ligne active, qui représente les forces de pale appliquées au fluide par des termes sources. Ces termes sources sont répartis dans les cellules de maillage à l'emplacement de la pale. Ainsi, la rotation, la torsion et le battement de la pale peuvent être représentés sans aucune déformation du maillage. Un avantage de la ligne active est que la simulation utilise un nombre réduit de nœuds, car des conditions aux limites «lois des parois» ne doivent pas être modélisées.Le cas d'un petit rotor expérimental d'hélicoptère est étudié en vol d'avancement. Les solveurs de fluide et de structure sont couplés pour calculer le comportement aérodynamique et dynamique du rotor. Pour ce faire, un algorithme de couplage faible en série décalé est appliqué. Les calculs itératifs sont contrôlés par un code spécialement conçu. Au début de chaque itération, le code calcule et répartit les termes sources dans le domaine fluide. A la fin du pas de temps, le code exécute le solveur de calcul de structure pour calculer un seul pas de temps. Ce solveur calcule le déplacement de la pale sous l'effet des forces aérodynamiques, élastiques et d'inertie et renvoi les résultats au solveur fluide. Les déplacements de la pale calculés servent de référence pour le solveur fluide au pas de temps suivant, pour distribuer les termes sources. Le calcul s'arrête lorsque le critère de convergence est vérifié.Afin de valider le cas simulé, des expérimentations sont réalisées en soufflerie. La puissance et la poussée aérodynamique du rotor sont mesurées. La Vélocimétrie par images de particules (PIV) est utilisée pour obtenir le champ de vitesse autour du rotor. Les mesures PIV à phase bloqué dans des plans azimutaux ont permis de reconstituer le champ d'écoulement 3D. La comparaison entre les résultats numériques et les expériences montre un bon accord et permet de valider la méthode de couplage proposée. / MODELING THE DYNAMIC BEHAVIOR OF HELICOPTER ROTORThe aim of the thesis is the investigation and modeling of dynamic and aerodynamic behavior of helicopter rotor considering both inertial and aerodynamic forces and taking into account the elastic deformation of the blades. The proposed coupling algorithm allows the transient calculations with data exchange between the fluid and structure solvers at each time step.The particularity of this research is the use of an actuator line aerodynamic model, which represents the blade forces applied to the fluid as source terms. These source terms are distributed in the grid cells where the blade is located. Thus the rotation, flapping and torsion of the blade can be represented without any grid deformation. An advantage of the actuator line is that the simulation uses a reduced number of nodes, because the “wall” boundary conditions do not need to be modeled.The case of small experimental helicopter rotor is studied in forward flight. The fluid and structure solvers are coupled to calculate aerodynamic and dynamic behavior of the rotor. For this purpose, a loosely coupling serial staggered algorithm is applied. The iterative calculations are controlled by specially developed code. At the beginning of each iteration, this code calculates and distributes the source terms in the fluid domain. At the end of the time step, the code runs the structural solver to execute a single time step. This solver calculates the blade displacement under aerodynamic, elastic and inertial forces, and the results are returned to the fluid solver. The calculated blade displacements serve as reference in the next fluid step to distribute the source terms. The calculation stops when the convergence criteria are met.In order to validate the simulated case, measurements are carried on in the wind tunnel. The power and aerodynamic thrust of the rotor are measured. Particle Image Velocimetry (PIV) is used to obtain the velocity field around the rotor. Phase locked measurement in azimuth planes enabled to reconstruct 3D flow field. The comparison between numerical results and experiments shows good agreement and permits to validate the proposed coupling method.

L'augmentation de la vitesse de croisière des hélicoptères à architecture conventionnelle (rotor principal et rotor anticouple) atteint aujourd'hui une asymptote. Le concept X3, associant 2 hélices et une aile pour alléger la charge du rotor principal, propose une solution viable économiquement, qui s'appuie sur l'utilisation de technologies éprouvées telles que le rotor Spheriflex® du Dauphin. Les essais en vol menés sur le démonstrateur X3 ont montré un bon comportement en performances et en qualités de vol de ce type de rotor, mais un niveau de charges très importants dans les commandes de vol. Pour limiter la masse à vide, la solution de surdimensionner toutes les pièces mécaniques n'est pas envisageable. Ce travail de thèse propose d'étudier les opportunités de réduction des efforts de commandes.Afin de pouvoir réduire ces efforts, il a été nécessaire de comprendre leur origine et de proposer une modélisation qui permette de les prédire. Des mesures expérimentales réalisées sur le démonstrateur X3 ont permis d'identifier les excitations aérodynamiques et le comportement dynamique des pales en torsion. Les phénomènes responsables de l'augmentation des efforts de commande ont été identifiés, ce qui a permis de corriger le modèle de calcul des efforts de commande HOST actuellement utilisé par Airbus Helicopters.A partir du logiciel HOST corrigé et de la compréhension des phénomènes physiques, des solutions technologiques pour réduire les efforts de commandes ont été étudiées. Deux familles de solutions sont alors considérées : l'optimisation du système de commandes de vol et la réduction des efforts dans les bielles de pas. L'optimisation du système de commandes de vol permet d'obtenir une réduction significative des efforts de commandes grâce à un algorithme d'optimisation de l'architecture de placement des servocommandes. L'étude de la réduction des efforts dans les bielles de pas montre que le choix de l'équilibre appareil conduit à des opportunités de réduction des efforts de commandes, alors que la modification du design de pale n'apporte pas de réduction notable et engendre une diminution des performances en stationnaire. / Nowadays, the increase of cruise speed for conventional helicopters (main rotor and anti-torque rear rotor) reaches an asymptote. The X3 concept proposed by Airbus Helicopters is a hybrid helicopter combining 2 propellers at the tip of small wings in order to unload the main rotor. This solution is economically viable because it reuses well-proven technologies such as the Spheriflex rotor, already used on the Dolphin family for many years. X3 flight tests have shown a good behavior of the rotor concerning performances as well as handling qualities, but control loads in the rotor system were significantly higher in cruise conditions than for conventional helicopters. In order to save the payload, over-sizing of the mechanical parts in order to withstand these loads can't be an appropriate solution. The work presented in this thesis deals with the problematic of control loads reduction.In order to reduce the control loads, the first step is to highlight the roots of these loads and to get a predictive tool over the whole flight domain. Experimental measurements from X3 flight tests give the aerodynamic loads on the blade sections, leading to understand the blades torsional dynamic behavior in several flight test cases (cruise, turns and high speed flight). Phenomena responsible for the increase of control loads are then identified, and the rotor computation tool HOST used at Airbus Helicopters is corrected to predict accurately control loads over the conventional as well as the high speed helicopter flight domain.The corrected rotor computation tool HOST, associated with the physical comprehension of the blade torsional dynamics, is used to quantify the possible solutions proposed for control loads reduction. Two main ways are studied: the optimization of the control system architecture and the reduction of pitch link loads. The optimization of control system architecture shows a dramatic reduction of control loads in the servo actuators and in the non-rotating scissors, thanks to an optimization algorithm developed during this thesis. The reduction of pitch link loads study shows that the optimization of the helicopter equilibrium leads to drastic reduction, whereas the modification of blade design does not show any significant reduction even at high speed.

Un cadre d'optimisation multi-Objectif pour les pales d'hélicoptère est développé en utilisant des modèles de simulation de haute fidélité. Des fonctions objectives caractérisant la performance de l'hélicoptère en vol stationnaire et d'avancement sont retenues. Deux solveurs sont utilisés afin de prédire la performance du rotor: le code général HOST et le solveur CFD elsA. Le premier axe de recherche porte sur la caractérisation de la précision des méthodes de prédiction. L'influence de la prise en compte de la souplesse de la pale, du trim rotor et/ou de l'utilisation de modélisations aérodynamiques simplifiées est caractérisée pour chaque cas de vol en utilisant des mesures en soufflerie. Un cadre numérique adapté à l'optimisation est développé. Le deuxième axe de recherche porte sur des techniques d'optimisation multi-Objectif de pales en vol stationnaire et d'avancement. Deux algorithmes novateurs basés sur la compétition (Jeux de Nash) et la coopération (Descente à Gradients Multiples) sont présentés comme des alternatives aux approches traditionnelles pour traiter le problème multi-Objectif. Afin de réduire le coût des simulations, un cadre de simulation basé sur des métamodèles est développé y compris une stratégie multi-Fidélité pour prédire la performance du rotor en vol d'avancement. Ces techniques sont appliquées à un cas réaliste de rotor, en utilisant des simulations CFD trimmées avec pale souple pour le cas du vol d'avancement et des simulations CFD avec pale rigide en vol stationnaire. Les résultats sont ensuite analysés, démontrant le potentiel de ces techniques pour l'obtention de conceptions réalistes représentant des bons compromis entre les objectifs. / This work addresses the development of a multi-Objective optimization framework for helicopter rotor blades using high-Fidelity simulation models. In particular, objective functions corresponding to hover and forward flight are considered. Two solvers are used to predict the rotor performance: the comprehensive rotor code HOST and the Computational Fluid Dynamics (CFD) solver elsA. The first research axis of this work is the characterization of the accuracy of each available prediction method. The influence of considering the blade elasticity, the rotor trim and/or simplified aerodynamics is characterized for each flight case using wind-Tunnel data. As a result, a numerical framework adapted to the optimization is developed. The second part of this work concerns the formulation and development of techniques adapted to the multi-Objective optimization of rotor blades in hover and in forward flight. Innovative algorithms based on competition (Nash Games) and cooperation (Multi-Gradient Descent) are presented as alternatives to traditional multi-Objective approaches. In order to reduce the simulation costs, a surrogate-Based framework is developed, including a multi-Fidelity strategy to predict the rotor performance in forward flight. These techniques are finally applied to a realistic rotor, considering trimmed elastic CFD computations in the forward flight case and rigid blade CFD computations in the hover case. The results are subsequently analyzed, demonstrating the potential of these techniques to obtain realistic designs realizing interesting trade-Offs.

No description available.

The main objective of the thesis is to design and construct a taxiway and a lifting device for moving a BELL helicopter with slides. Handling equipment is used for transporting helicopters between the airfield and hangars. The thesis is divided into several parts. The first part includes the design of taxiway and lifting equipment. Other parts contain strength calculation of selected parts and design documentation, which includes assembly drawings and important groups drawings.

The main goal this thesis is presenting solution for manipulation with chopper BELL between of hangar and landing zone. The main task is design useful construction solution by required task, also perform a strenght calculations each part of mechanism and drawing documentation. Also included is a 3D visualization of the entire mechanism.

KRIŠTŮFEK, T. The Concept of Training for a Qualification CPL(H): Master´s Thesis. Brno: VUT Brno – Brno University of Technology, Faculty of Mechanical Engineering, Institute of Aerospace Engineering, 2013, 58 p. Supervisor: Mgr. Hammer, J. This master´s thesis deals with flight training to obtain the qualification CPL(H). In the introduction part of this thesis are specified the requirements for obtaining this qualification and there is a description of the type of modular flight training. Other chapters are focused on the type rating for helicopters, the use of helicopter simulators and the choice of an appropriate flight training school. There is also a list of helicopter flight schools, including an overview of helicopters which are used in the Czech Republic. The final chapter is consisted of the financial analysis of the flight modular training at flight schools and evaluation of this analysis, the possibility of providing loans and credits. There is an overview of the total costs for the qualification of the commercial helicopter pilot.

This thesis solves design of rescue helicopters. It is a machine designed especially for rescuing injured people. It does not exclude the possibility of other uses. The aim is to design an extraordinary and timeless construction machine compliance with all technical and technological requirements. Emphasis is placed on innovative design and functionality. Design is designed after a detailed analysis and using the experience and information gained during their studies at the college.