An ontology-driven approach to applying styles in software engineering is developed in the study. The essence of the approach is to use ontology not only to represent styles but also to control the use of styles when creating and maintaining software. For such purposes, appropriate ontology and developer support tools are provided to represent a style, and tools (reasoners) are created on the ground of the ontological knowledge base to control the application of the style in work products of the software lifecycle phases. Based on descriptive logic, the knowledge base contains two components – terminological (TBox) and factual (ABox). The first component was created in advance by performing a domain analysis. The second component was created when analysing the representation of the corresponding work product. For the purpose of typification in the context of the developed approach, templates for the kernel ontology of the software engineering style were created by analysing the concept of style in different domains. The basic characteristics of style as a domain-independent concept, which are presented in the templates, are formulated in the article. In this case, the Work Product Pattern Application pattern of the Unified Foundational Ontology is used to select the number of templates needed to represent the style. The pattern describes actions that may exist regarding the Work Product style. An example of using the approach is considered by investigating the proposed ontology-driven method for programming style application in software engineering and building the architecture of the tool that implements it. Protege use shows how to build the ontology of a programming style and programmer support. The architecture of the tool for controlling the application of style is developed and implemented in a work product of the design phase – a programme text. The basis of the architecture is the knowledge base of the corresponding style. The terminological component of the knowledge base contains information regarding programming languages and styles, and it is created in advance by the ontology developer. The actual component is created by the reasoner for each representation of the work product – the programme text. The tools developed in the context of the proposed approach automate the processes that take place when applying styles to work products of the software lifecycle phases.

This is a study of five high schools awarded external funding to implement a project, the African American Male Initiative (AAMI). During the first year of implementation, interviews, focus groups, surveys, and student academic transcripts provided sources of data. Survey data showed that AAMI students exhibited high aspirations and anticipations for college. In addition, significant positive correlations were found between the number of people students communicate with about college and financial aid requirement information and their level of college knowledge. Characteristics such as African American male mentoring and advocacy, raised expectations, and forming a “brotherhood” emerged from focus group data.

Architecture's daily impact on its users is the result of neither concentration nor focused attention. Preoccupied with everyday tasks, most people do not stop to observe the architectural object as a work of art. In this paper I investigate the content that may be present when architecture is experienced in the state Walter Benjamin calls 'distraction'. Using a phenomenological model of attention and my applied research, I propose a plausible model for the Lived Experience of the Built Environment (LEBEN). I further consider the possible components of the everyday experience of architecture and the urban surroundings, and suggest an integrative structure for it. Part I explains the need for the research and presents its objectives. Part II discusses the phenomenological model of attention and awareness. Parts III and IV present the LEBEN model, briefly describing its sources in the literature, and applied research, based on a workshop that examined multi-subjective perspectives. I note the research assumptions, methodology and the challenges facing such an investigation, eg, whether it is possible to study a phenomenon that exists beyond the realm of focal attention. Part V introduces the core-themes and categories distilled from my research (edge, depth, change, atmosphere and affordances) and positions them in the LEBEN model.

Airway stenosis represents the commonest airway complication following lung transplantation, affecting between 7% and 18% of patients. Existing treatment options offer limited efficacy and can cause additional patient morbidity. Paclitaxel-coated balloons (PCB) have proved effective in managing postinterventional coronary artery re-stenosis. In a first-in-man study, we evaluated similar PCBs in refractory nonanastomotic airway stenosis in 12 patients. Following a single application, luminal patency was maintained in 50% at 270 days. No significant peri-interventional or early postinterventional complications occurred. Given these encouraging initial findings, further studies appear warranted.

The goal of this research was to evaluate di erent con gurations of morphing wings. The morphing system employed piezoelectric actuators called Macro-Fiber Composites (MFCs) bonded to a thin composite wing. The strain of the MFCs causes deformation and morphing of the entire wing planform. Simulations were performed to evaluate the di erent con gurations. Finite element analysis calculated the de ections, and vortex lattice methods solved for the aerodynamic forces. Di erent wing parameters were varied to quantify their e ect on morphing performance. The performance was measured by the ability to actuate roll and ability to support aerodynamic loading. The parameters compared were: spanwise location of actuators, number and size of actuators, composite wing thickness, and composite material sti ness. Flight testing was then done with a wing built based on the simulation results. In addition to de ection measurements, roll doublets in ight were performed to measure the roll rate induced by the morphing wing. This roll rate was then converted to rolling moment coe cient. A simulation based on the ight test wing geometry was done and compared to the ight results. The simulation overestimated the wingtip de ection. However, the ight testing illustrated some of the variability involved with the manufacture and modeling of MFC-morphing wings. Given the di erent de ections, the rolling moment coe cient from simulation was consistent with that from ight testing.

‡‡ A novel morphing control surface design employing piezoelectric Macro Fiber Composite (MFC) actuators is compared to a servo-actuated system. The comprehensive comparison including aerodynamics, size, weight, power, bandwidth, and reliability has been extended to include flight test comparisons. Flight agility and control response of the morphing-actuated and servo-actuated configurations were quantified through state measurement during identical automated maneuvers. The morphing actuation scheme demonstrated superior response times and a fully controllable vehicle, but was unable to match the magnitude of roll and pitch rates attained by the servo-actuated baseline aircraft. The servo-actuated aircraft exhibited velocity deficits during doublet maneuvers, while the morphing actuation negligibly decreased velocity, demonstrating lower drag and more efficient production of control forces and moments. Reliability cycle testing of an MFC bimorph achieved 1 million cycles without failure and minimal degradation in performance.

This paper provides an overview of the development of an aerodynamic analysis tool suitable for use in conceptual and preliminary aircraft design. This tool, AVID APEX, is capable of analyzing subsonic, transonic, and supersonic flows using a zonal approach for lifting surfaces. APEX interfaces directly with parametric geometry modelers, and can provide detailed parasite drag build-ups and estimates of high-lift device effects and static stability and control derivatives. This paper briefly discusses the tools capabilities, the underlying methodologies, and describes the methodology verification approach and program.

The use of piezo-ceramic actuators for UAV ight control has been shown to be e ective both in the wind tunnel and in ight test. Macro ber composite (MFC) actuators are a high strain variant of the lead zirconate titanate (PZT) actuator, and have been employed in a bimorph con guration to cause morphing camber control of aerodynamic surfaces in less than 0.5 m wingspan UAV applications. One of the challenges of operating these conformal actuators is to quantify the voltage input/displacement output relationship given hysteresis and aerodynamic loading e ects. The work presented provides a framework for the practical implementation of these actuators by using both open and closed loop feedback systems for displacement control. Results are presented for thick airfoil designs where only the trailing edge is de ected using smart materials. The two main sources of non-linear behavior include dynamic pressure and actuator hysteresis, and knowledge of these parameters can be used for reasonably good open loop displacement control. Results are presented for 2-D airfoil section testing.

This paper outlines some of the effects of fan angular momentum on ducted fan UAVs. All aircraft will be affected by their propeller’s angular momentum, however, ducted fan vehicles are particularly susceptible due to the relative sizes of the fan and the airframe. During maneuvers, the angular momentum of the fan causes a gyroscopic torque that must be countered by the UAV’s control surfaces. If not accounted for during design, the gyroscopic torque can result in a reduction of the vehicle’s maneuverability. In this paper, the equations of motion for a ducted fan vehicle are provided to visualize the gyroscopic torque. It is also important to understand how the gyroscopic torque scales with fan radius. Through this knowledge, a constraint equation is formulated that ensures that the UAVs control surfaces can counteract the gyroscopic moments acting on the vehicle. It is also shown that, to ensure the control surfaces are adequate, the control surface effectiveness must scale with the square of the fan’s radius if equivalent body angular rates are required. In some cases, however, it may be more beneficial to the vehicle to design a contra-rotating fan system. It is shown how this system eliminates the gyroscopic torque that is present in a conventional single fan UAV. However, contra-rotating fan systems have unique dynamic properties, and modal analysis is used to compare the dynamics of both configurations.

The rigid body equations of motion for ducted fan UAVs are investigated. The nonlinear equations of motion are derived and simplified to linear approximations for different flight conditions and vehicle configurations. It is shown that the ducted fan vehicle dynamics are too coupled to be analyzed without numerical approximation. A numerical technique is then used to perform modal analysis on a representative ducted fan. Dominate vehicle modes are shown. A CG study is presented to investigate the effect of center of gravity placement on vehicle stability.