Alternativa a la fabricación de costillas con otros materiales compuestos

La investigación tiene como objetivo establecer los valores organizacionales que afectan la productividad. El trabajo empírico se desarrolló en una muestra intencional de 142 PYMES del sector metalmecánico de Venezuela. Se consultó a un panel de expertos a fin de determinar la importancia relativa de estos valores en la productividad. Fueron sometidos a evaluación 22 valores. Los valores que resultaron más importantes son: Recurso Humano, Calidad, Trabajo en equipo, Responsabilidad y Seguridad. Se recomienda a la PYME metalmecánica Venezolana, orientar esfuerzos hacia la promoción y puesta en práctica de este Sistema de Valores, pues tan sólo Recurso Humano y Calidad son los valores que tienen una mayor presencia en sus filosofías de gestión. The research aims to establish the organizational values that affect productivity. The empirical work was conducted in a purposive sample of 142 SMEs in the engineering sector in Venezuela. We consulted a panel of experts to determine the relative importance of these values on productivity. Were evaluated at 22 values. The values that were most important are: Human Resources, Quality, Teamwork, Responsibility and Safety. SMEs are encouraged to Venezuelan metalworking, focusing efforts towards the promotion and implementation of this system of values, as only Human Resources and Quality are the values that are more active in their management philosophies.

Development of a tanks line for waxing landing gear parts

The aim of this article is to define the technical specifications and to design the implementation of a line of tanks that would be used in the process of waxing and de-waxing large pieces. As it is based in a real case, it is also analyzed the process of dismantling the former installation that supported these functions. The origin of this project is due to a new rating for the maintenance of landing gears which makes the previous waxing line that was prepared to work on smaller aircraft?s pieces, no longer adequate to the current workflow and processes.

Spline-based hyperelasticity for transversely isotropic incompressible materials

In this paper we present a spline-based hyperelastic model for incompressible transversely isotropic solids. The formulation is based on the Sussman-Bathe model for isotropic hyperelastic materials. We extend this model to transversely isotropic materials following a similar procedure. Our formulation is able to exactly represent the prescribed behavior for isotropic hyperelastic solids, recovering the Sussman-Bathe model, and to exactly or closely approximate the prescribed behavior for transversely isotropic solids. We have employed our formulation to predict, very accurately, the experimental results of Diani et al. for a transversely isotropic hyperelastic nonlinear material.

WYPIWYG Hyperelasticity

In this paper we describe a new promising procedure to model hyperelastic materials from given stress-strain data. The main advantage of the proposed method is that the user does not need to have a relevant knowledge of hyperelasticity, large strains or hyperelastic constitutive modelling. The engineer simply has to prescribe some stress strain experimental data (whether isotropic or anisotropic) in also user prescribed stress and strain measures and the model almost exactly replicates the experimental data. The procedure is based on the piece-wise splines model by Sussman and Bathe and may be easily generalized to transversely isotropic and orthotropic materials. The model is also amenable of efficient finite element implementation. In this paper we briefly describe the general procedure, addressing the advantages and limitations. We give predictions for arbitrary ?experimental data? and also give predictions for actual experiments of the behaviour of living soft tissues. The model may be also implemented in a general purpose finite element program. Since the obtained strain energy functions are analytic piece-wise functions, the constitutive tangent may be readily derived in order to be used for implicit static problems, where the equilibrium iterations must be performed and the material tangent is needed in order to preserve the quadratic rate of convergence of Newton procedures.

Effect of the Wake of the Transducer Supports on the Ultrasonic Anemometer Measurements

The wake produced by the structural supports of the ultrasonic anemometers (UAs)causes distortions in the velocity field in the vicinity of the sonic path. These distortions are measured by the UA, inducing errors in the determination of the mean velocity, turbulence intensity, spectrum, etc.; basic parameters to determine the effect of wind on structures. Additionally, these distortions can lead to indefinition in the calibration function of the sensors (Cuerva et al., 2004). Several wind tunnel tests have been dedicated to obtaining experimental data, from which have been developed fit models to describe and to correct these distortions (Kaimal, 1978 and Wyngaard, 1985). This work explores the effect of a vortex wake generated by the supports of an UA, on the measurement of wind speed done by this instrument. To do this, the Von Karman¿s vortex street potential model is combined with the mathematical model of the measuring process carried out by UAs developed by Franchini et al. (2007). The obtained results are the correction functions of the measured wind velocity, which depends on the geometry of the sonic anemometer and aerodynamic conditions. These results have been validated with the ones obtained in a wind tunnel test done on a single path UA, especially developed for research. The supports of this UA have been modified in order to reproduce the conditions of the theoretical model. Good agreements between experimental and theoretical results have been found.

Three decades of Space Activities at the Instituto Universitario de Microgravedad "Ignacio Da Riva" / Universidad Politécnica de Madrid (IDR/UPM) en History of Rocketry and Astronautics

Strictly speaking, space related activities at the Escuela Técnica Superior de Ingenieros Aeronáuticos (ETSIA) begun in 1973, when Prof. Ignacio Da Riva got a contract from the European Space Agency (ESA) to compile a handbook on spacecraft thermal control. By the same time, ESA issued an announcement of opportunities offering to the European scientific community the possibility of perform microgravity relevant experiments on board space platform like the European orbital laboratory Spacelab. Prof. Da Riva proposed one of the few selected experiments dealing with fluid physics under microgravity conditions, later flown on Spacelab-1 mission in 1983. These two events were the starting point where Prof. Da Riva, full professor of Aerodynamics at ETSIA, nucleated a small group of young professors and students located at the Laboratorio de Aerodinámica y Mecánica de Fluidos (LAMF) of ETSIA. Such group was leaded by Prof. Da Riva since its creation till 1991, when Prof. Da Riva died, and it was the seed of the more recently created research institute for aerospace science and technology named "Ignacio Da Riva" (IDR) in his honour. In this communication space related activities performed either at LAMF or IDR during the last three decades are briefly described.

Choked flow in water/CO2 solutions on air-independent propulsion systems

We develop a simplified model of choked flow in pipes for CO2-water solutions as an important step in the modelling of a whole hydraulic system with the intention of eliminating the carbon dioxide generated in air-independent submarine propulsion. The model is based on an approximate fitting of the homogeneous isentropic solution upstream of a valve (or any other area restriction), for given fluid conditions at the entrance. The relative maximum choking back-pressure is computed as a function of area restriction ratio. Although the procedure is generic for gas solutions, numeric values for the non-dimensional parameters in the analysis are developed only for choking in the case of carbon dioxide solutions up to the pure-water limit.

Effect of the Reference Line on Main Roughness Parameters

In the present paper the influence of the reference system with regard to the characterization of the surface finishing is analyzed. The effect of the reference system’s choice on the most representative surface finishing parameters (e.g. roughness average Ra and root mean square values Rq) is studied. The study can also be applied to their equivalent parameters in waviness and primary profiles. Based on ISO and ASME standards, three different types of regression lines (center, mean and orthogonal) are theoretically and experimentally analyzed, identifying the validity and applicability fields of each one depending on profile’s geometry.

A non-perturbative Kolmogorov turbulence approach to the cosmic web structure

The Kolmogorov approach to turbulence is applied to the Burgers turbulence in the stochastic adhesion model of large-scale structure formation. As the perturbative approach to this model is unreliable, here a new, non-perturbative approach, based on a suitable formulation of Kolmogorov's scaling laws, is proposed. This approach suggests that the power-law exponent of the matter density two-point correlation function is in the range 1–1.33, but it also suggests that the adhesion model neglects important aspects of the gravitational dynamics.

Linear Approach to the Orbiting Spacecraft Thermal Problem

A linear method is developed for solving the nonlinear differential equations of a lumped-parameter thermal model of a spacecraft moving in a closed orbit. This method, based on perturbation theory, is compared with heuristic linearizations of the same equations. The essential feature of the linear approach is that it provides a decomposition in thermal modes, like the decomposition of mechanical vibrations in normal modes. The stationary periodic solution of the linear equations can be alternately expressed as an explicit integral or as a Fourier series. This method is applied to a minimal thermal model of a satellite with ten isothermal parts (nodes), and the method is compared with direct numerical integration of the nonlinear equations. The computational complexity of this method is briefly studied for general thermal models of orbiting spacecraft, and it is concluded that it is certainly useful for reduced models and conceptual design but it can also be more efficient than the direct integration of the equations for large models. The results of the Fourier series computations for the ten-node satellite model show that the periodic solution at the second perturbative order is sufficiently accurate.

Asymptotic Description of Flutter Amplitude Saturation by Nonlinear Friction Forces

The computation of the non-linear vibration dynamics of an aerodynamically unstable bladed-disk is a formidable numerical task, even for the simplified case of aerodynamic forces assumed to be linear. The nonlinear friction forces effectively couple dif- ferent travelling waves modes and, in order to properly elucidate the dynamics of the system, large time simulations are typically required to reach a final, saturated state. Despite of all the above complications, the output of the system (in the friction microslip regime) is basically a superposition of the linear aeroelastic un- stable travelling waves, which exhibit a slow time modulation that is much longer than the elastic oscillation period. This slow time modulation is due to both, the small aerodynamic effects and the small nonlinear friction forces, and it is crucial to deter- mine the final amplitude of the flutter vibration. In this presenta- tion we apply asymptotic techniques to obtain a new simplified model that captures the slow time dynamics of the amplitudes of the travelling waves. The resulting asymptotic model is very re- duced and extremely cheap to simulate, and it has the advantage that it gives precise information about the characteristics of the nonlinear friction models that actually play a role in the satura- tion of the vibration amplitude.

Campus of Excellence: The Power of Diversity in Engineering Education

This paper presents the results of a strategy to modernise the Spanish University system through the establishment of an International Campus of Excellence (CEI). The current, ambitious but realistic, project is a joint initiative of a number of institutions located in the Moncloa Campus, amongst them the Complutense and the Technical Universities, as well as CIEMAT, CSIC and INIA. The aim of the project is to transform the Moncloa Campus into an international point of reference with regard to research, education and innovation. This paper describes the project and presents the qualitative and quantitative results.

Understanding time-drift for different aircraft descent guidance strategies

In this paper the effect of different aircraft automated descent guidance strategies on fuel burn and the temporal predictability of the executed trajectory is investigated. The paper aims to provide an understanding of how airborne automation can be permitted by Air Traffic Control to remain in control of the descent in the presence of disturbances while providing sufficient predictability. Simulations have been performed investigating different guidance strategies. While each strategy has its advantages and disadvantages, results indicate that improved temporal predictability comes at the cost of additional fuel burn and loss of predictability in other dimensions of the trajectory.

El impacto ambiental del transporte aéreo y las medidas para mitigarlo

La preocupación medioambiental guía en la actualidad muchas de las estrategias globales y nacionales de aplicación al sector del transporte. En transporte aéreo, el impacto ambiental es importante, pero los beneficios socioeconómicos también lo son. El crecimiento del transporte aéreo es el mayor de los desafíos del sector. Por el momento, está limitado por el mantenimiento de la seguridad y por la disponibilidad de infraestructuras, pero el impacto ambiental puede convertirse en el principal factor limitador. El transporte aéreo presenta actualmente el mayor crecimiento de todos los modos de transporte. La aviación comercial se enfrenta al reto de tomar un papel activo en la búsqueda e impulso de soluciones para alcanzar la sostenibilidad del sector, por lo tanto es necesario realizar un diagnóstico de situación a través de unos indicadores y modelos adecuados que midan el impacto ambiental del transporte aéreo. Los tipos de impacto ambiental del transporte aéreo se pueden clasificar como de efecto local (ruido, contaminación de aire local, uso de espacio), o de efecto global (consumo de materiales no renovables, aportación al cambio climático). La gestión del impacto ambiental comprende, además de medidas de reducción técnicas, diversas posibilidades económicas, que utilizan mecanismos de mercado (acuerdos voluntarios entre administración, operadores y consumidores, o cualquier combinación de ellos, impuestos y tasas, comercio de emisiones). En este trabajo se pasa revista a las diferentes medidas de gestión del impacto ambiental que se están implantando, tanto de carácter técnico como de contenido económico. Algunas de estas medidas están ya en vigor, otras en estudio. El análisis se centra fundamentalmente en el seno de la Unión Europea, que ha adoptado un papel de liderazgo mundial en la adopción de regulaciones ambientales, y el objetivo final es sacar conclusiones sobre la repercusión de estas medidas en general, y sobre el transporte aéreo en particular.

Cuerpos de forma óptima en vuelo hipersónico

Se estudia la obtencion de la forma del fuselaje optimo de un vehiculo hipersonico, tipo planeador,de gran radio de accion, para el que es fundamental conseguir un valor alto de ( L / D ) inAx.Se utiliza la teoria de NEWTON-BUSEMANN para el cálculo de las caracteristicas aerodinámicas. Para la solucion del problema variacional, se consideran fijos ciertos parámetros (por ejemplo, el radio de curvatura en el morro) que afectan directamente al calor recibido por el cuerpo y a las caracteristicas en vuelo subsónico. Como ejemplo, se considera la solucion de un caso particular.