Design, modelling and analysis of a six component force balance for hypervelocity wind tunnel testing

A combination of modelling and analysis techniques was used to design a six component force balance. The balance was designed specifically for the measurement of impulsive aerodynamic forces and moments characteristic of hypervelocity shock tunnel testing using the stress wave force measurement technique. Aerodynamic modelling was used to estimate the magnitude and distribution of forces and finite element modelling to determine the mechanical response of proposed balance designs. Simulation of balance performance was based on aerodynamic loads and mechanical responses using convolution techniques. Deconvolution was then used to assess balance performance and to guide further design modifications leading to the final balance design. (C) 2001 Elsevier Science Ltd. All rights reserved.

Modelling and aerodynamic simulation of a vehicle and failure analysis of a laminated front fender

Master Thesis in Mechanical Engineering field of Maintenance and Production

Optimization of wind blade design including its energetic characteristics

The goal of the Master’s thesis is to develop and to analyze the optimization method for finding a geometry shape of classical horizontal wind turbine blades based on set of criteria. The thesis develops a technique that allows the designer to determine the weight of such factors as power coefficient, sound pressure level and the cost function in the overall process of blade shape optimization. The optimization technique applies the Desirability function. It was never used before in that kind of technical problems, and in this sense it can claim to originality of research. To do the analysis and the optimization processes more convenient the software application was developed.

Estimation of aircraft aerodynamic derivatives using Extended Kalman Filter

Design of flight control laws, verification of performance predictions, and the implementation of flight simulations are tasks that require a mathematical model of the aircraft dynamics. The dynamical models are characterized by coefficients (aerodynamic derivatives) whose values must be determined from flight tests. This work outlines the use of the Extended Kalman Filter (EKF) in obtaining the aerodynamic derivatives of an aircraft. The EKF shows several advantages over the more traditional least-square method (LS). Among these the most important are: there are no restrictions on linearity or in the form which the parameters appears in the mathematical model describing the system, and it is not required that these parameters be time invariant. The EKF uses the statistical properties of the process and the observation noise, to produce estimates based on the mean square error of the estimates themselves. Differently, the LS minimizes a cost function based on the plant output behavior. Results for the estimation of some longitudinal aerodynamic derivatives from simulated data are presented.

Blade design and forming for fans using finite elements

The necessity of adapting the standardized fan models to conditions of higher temperature has emerged due to the growth of concerning referring to the consequences of the gas expelling after the Mont Blanc tunnel accident in Italy and France, where even though, with 100 fans in operation, 41 people died. However, since then, the defied solutions have pointed to aerodynamic disadvantages or have seemed nonappropriate in these conditions. The objective of this work is to present an alternative to the market standard fans considering a new technology in constructing blades. This new technology introduces the use of the stainless steel AISI 409 due to its good adaptation to temperatures higher than 400°C, particularly exposed to temperatures of gas exhaust from tunnels in fire situation. Furthermore, it presents a very good resistance to corrosion and posterior welding and pressing, due to its alloyed elements. The innovation is centered in the process of a deep drawing of metallic shells and posterior welding, in order to keep the ideal aerodynamic superficies for the fan ideal performance. On the other hand, the finite element method, through the elasto-plastic software COSMOS permitted the verification of the thickness and structural stability of the blade in relation to the aerodynamic efforts established in the project. In addition, it is not advisable the fabrication of blades with variable localized thickness not even, non-uniform ones, due to the verified concentration of tensions and the difficulties observed in the forming. In this way, this study recommends the construction of blades with uniform variations of thickness. © 2007 Springer.

Design of wireless sensor networks for fluid dynamic applications

In fluid dynamics research, pressure measurements are of great importance to define the flow field acting on aerodynamic surfaces. In fact the experimental approach is fundamental to avoid the complexity of the mathematical models for predicting the fluid phenomena. It’s important to note that, using in-situ sensor to monitor pressure on large domains with highly unsteady flows, several problems are encountered working with the classical techniques due to the transducer cost, the intrusiveness, the time response and the operating range. An interesting approach for satisfying the previously reported sensor requirements is to implement a sensor network capable of acquiring pressure data on aerodynamic surface using a wireless communication system able to collect the pressure data with the lowest environmental–invasion level possible. In this thesis a wireless sensor network for fluid fields pressure has been designed, built and tested. To develop the system, a capacitive pressure sensor, based on polymeric membrane, and read out circuitry, based on microcontroller, have been designed, built and tested. The wireless communication has been performed using the Zensys Z-WAVE platform, and network and data management have been implemented. Finally, the full embedded system with antenna has been created. As a proof of concept, the monitoring of pressure on the top of the mainsail in a sailboat has been chosen as working example.

Dynamic modeling, simulation and control design of a parafoil-payload system for ship launched aerial delivery system (SLADS)

The objective of this research was to develop a high-fidelity dynamic model of a parafoilpayload system with respect to its application for the Ship Launched Aerial Delivery System (SLADS). SLADS is a concept in which cargo can be transfered from ship to shore using a parafoil-payload system. It is accomplished in two phases: An initial towing phase when the glider follows the towing vessel in a passive lift mode and an autonomous gliding phase when the system is guided to the desired point. While many previous researchers have analyzed the parafoil-payload system when it is released from another airborne vehicle, limited work has been done in the area of towing up the system from ground or sea. One of the main contributions of this research was the development of a nonlinear dynamic model of a towed parafoil-payload system. After performing an extensive literature review of the existing methods of modeling a parafoil-payload system, a five degree-of-freedom model was developed. The inertial and geometric properties of the system were investigated to predict accurate results in the simulation environment. Since extensive research has been done in determining the aerodynamic characteristics of a paraglider, an existing aerodynamic model was chosen to incorporate the effects of air flow around the flexible paraglider wing. During the towing phase, it is essential that the parafoil-payload system follow the line of the towing vessel path to prevent an unstable flight condition called ‘lockout’. A detailed study of the causes of lockout, its mathematical representation and the flight conditions and the parameters related to lockout, constitute another contribution of this work. A linearized model of the parafoil-payload system was developed and used to analyze the stability of the system about equilibrium conditions. The relationship between the control surface inputs and the stability was investigated. In addition to stability of flight, one more important objective of SLADS is to tow up the parafoil-payload system as fast as possible. The tension in the tow cable is directly proportional to the rate of ascent of the parafoil-payload system. Lockout instability is more favorable when tow tensions are large. Thus there is a tradeoff between susceptibility to lockout and rapid deployment. Control strategies were also developed for optimal tow up and to maintain stability in the event of disturbances.

Aerodynamic Optimization of High-Speed Trains Nose using a Genetic Algorithm and Artificial Neural Network

An aerodynamic optimization of the train aerodynamic characteristics in term of front wind action sensitivity is carried out in this paper. In particular, a genetic algorithm (GA) is used to perform a shape optimization study of a high-speed train nose. The nose is parametrically defined via Bézier Curves, including a wider range of geometries in the design space as possible optimal solutions. Using a GA, the main disadvantage to deal with is the large number of evaluations need before finding such optimal. Here it is proposed the use of metamodels to replace Navier-Stokes solver. Among all the posibilities, Rsponse Surface Models and Artificial Neural Networks (ANN) are considered. Best results of prediction and generalization are obtained with ANN and those are applied in GA code. The paper shows the feasibility of using GA in combination with ANN for this problem, and solutions achieved are included.

Aerodynamic optimization of the ICE2 high-speed train nose using a genetic algorithm and metamodels

An aerodynamic optimization of the ICE 2 high-speed train nose in term of front wind action sensitivity is carried out in this paper. The nose is parametrically defined by Be?zier Curves, and a three-dimensional representation of the nose is obtained using thirty one design variables. This implies a more complete parametrization, allowing the representation of a real model. In order to perform this study a genetic algorithm (GA) is used. Using a GA involves a large number of evaluations before finding such optimal. Hence it is proposed the use of metamodels or surrogate models to replace Navier-Stokes solver and speed up the optimization process. Adaptive sampling is considered to optimize surrogate model fitting and minimize computational cost when dealing with a very large number of design parameters. The paper introduces the feasi- bility of using GA in combination with metamodels for real high-speed train geometry optimization.

Multi-objective Aerodynamic Optimization of High-speed Trains in Tunnels

A genetic algorithm (GA) is employed for the multi-objective shape optimization of the nose of a high-speed train. Aerodynamic problems observed at high speeds become still more relevant when traveling along a tunnel. The objective is to minimize both the aerodynamic drag and the amplitude of the pressure gradient of the compression wave when a train enters a tunnel. The main drawback of GA is the large number of evaluations need in the optimization process. Metamodels-based optimization is considered to overcome such problem. As a result, an explicit relationship between pressure gradient and geometrical parameters is obtained.

Aerodynamic Analysis of Cup Anemometers Performance: The Stationary Harmonic Response

The effect of cup anemometer shape parameters, such as the cups’ shape, their size, and their center rotation radius, was experimentally analyzed.This analysis was based on both the calibration constants of the transfer function and the most important harmonic termof the rotor’smovement,which due to the cup anemometer design is the third one.This harmonic analysis represents a new approach to study cup anemometer performances. The results clearly showed a good correlation between the average rotational speed of the anemometer’s rotor and the mentioned third harmonic term of its movement.

Probabilistic approach for longitudinal ventilation system design in fire situations

The main objective of ventilation systems in tunnels is to reach the highest possible safety level both in service and fire situation; being the fire one, the most relevant when designing the system. When designing a longitudinal ventilation system, the methodology to evaluate the capacity of the system is similar both in service and fire situation, with the exception of the chimney effect and the phenomena of thermal transfer which is responsible or the changes in the density of the air. When facing the dimensioning task for longitudinal ventilated tunnels, although similar methodologies are used in different countries, specific hypothesis (aerodynamic, thermal properties, traffic) even if discussed in the literature or current practice, are not usually detailed in the regulations or recommendations. The aim of this paper is to propose a probabilistic approach to the problem which would allow the designer, and the tunnel owner, to understand the uncertainty and sensibility adopted in the results and, eventually, identify possible ways of optimizing the ventilation solution to be adopted.

Aerodynamic loads on bluff bodies under wind gusts

Esta tesis doctoral se ha centrado en el estudio de las cargas aerodinámicas no estacionario en romos cuerpos o no aerodinámicos (bluff bodies). Con este objetivo se han identificado y analizado los siguientes puntos: -Caracterización del flujo medido con diferentes tipos de tubos de Pitot y anemómetro de hilo caliente en condiciones de flujo no estacionario inestable generado por un túnel aerodinamico de ráfagas. -Diseño e integración de los montajes experimentales requeridos para medir las cargas de viento internas y externas que actúan sobre los cuerpos romos en condiciones de flujo de viento con ráfagas. -Implementación de modelos matemáticos semi-empíricos basados en flujo potencial y las teorías fenomenológicas pertinentes para simular los resultados experimentales. -En diversan condiciones de flujo con ráfagas, la identificación y el análisis de la influencia de los parámetros obtenida a partir de los modelos teóricos desarrollados. -Se proponen estimaciones empíricas para averiguar los valores adecuados de los parámetros que influyente, mediante el ajuste de los resultados experimentales y los predichos teóricamente. Los montajes experimentales se has reakizado en un tunel aerodinamico de circuito abierto, provisto de baja velocidad, cámara de ensayes cerrada, un nuevo concepto de mecanismo generador de ráfaga sinusoidal, diseñado y construido en el Instituto de Microgravedad "Ignacio Da Riva" de la Universidad Politécnica de Madrid, (IDR / UPM). La principal característica de este túnel aerodynamico es la capacidad de generar un flujo con un perfil de velocidad uniforme y una fluctuación sinusoidal en el tiempo. Se han realizado pruebas experimentales para estudiar el efecto de los flujos no estacionarios en cuerpos romos situados en el suelo. Se han propuesto dos modelos teóricos para diterminar las cargas de presión externas e internas respectivamente. Con el fin de satisfacer la necesidad de la crea ráfagas de viento sinusoidales para comprobar las predicciones de los modelos teóricos, se han obtenido velocidades de hasta 30 m/s y frecuencias ráfaga de hasta 10 Hz. La sección de la cámara de ensayos es de 0,39 m x 0,54 m, dimensiónes adecuadas para llevar a cabo experimentos con modelos de ensayos. Se muestra que en la gama de parámetros explorados los resultados experimentales están en buen acuerdo con las predicciones de los modelos teóricos. Se han realizado pruebas experimentales para estudiar los efectos del flujo no estacionario, las cuales pueden ayudar a aclarar el fenómeno de las cargas de presión externa sobre los cuerpos romos sometidos a ráfagas de viento: y tambien para determinan las cargas de presión interna, que dependen del tamaño de los orificios de ventilación de la construcción. Por último, se ha analizado la contribución de los términos provenientes del flujo no estacionario, y se han caracterizado o los saltos de presión debido a la pérdida no estacionario de presión a través de los orificios de ventilación. ABSTRACT This Doctoral dissertation has been focused to study the unsteady aerodynamic loads on bluff bodies. To this aim the following points have been identified and analyzed: -Characterization of the flow measured with different types of Pitot tubes and hot wire anemometer at unsteady flow conditions generated by a gust wind tunnel. -Design and integrating of the experimental setups required to measure the internal and external wind loads acting on bluff bodies at gusty wind flow conditions. -Implementation of semi-empirical mathematical models based on potential flow and relevant phenomenological theories to simulate the experimental results.-At various gusty flow conditions, extracting and analyzing the influence of parameters obtained from the developed theoretical models. -Empirical estimations are proposed to find out suitable values of the influencing parameters, by fitting the experimental and theoretically predicted results. The experimental setups are performed in an open circuit, closed test section, low speed wind tunnel, with a new sinusoidal gust generator mechanism concept, designed and built at the Instituto de Microgravedad “Ignacio Da Riva” of the Universidad Politécnica de Madrid, (IDR/UPM). The main characteristic of this wind tunnel is the ability to generate a flow with a uniform velocity profile and a sinusoidal time fluctuation of the speed. Experimental tests have been devoted to study the effect of unsteady flows on bluff bodies lying on the ground. Two theoretical models have been proposed to measure the external and internal pressure loads respectively. In order to meet the need of creating sinusoidal wind gusts to check the theoretical model predictions, the gust wind tunnel maximum flow speed and, gust frequency in the test section have been limited to 30 m/s and 10 Hz, respectively have been obtained. The test section is 0.39 m × 0.54 m, which is suitable to perform experiments with testing models. It is shown that, in the range of parameters explored, the experimental results are in good agreement with the theoretical model predictions. Experimental tests have been performed to study the unsteady flow effects, which can help in clarifying the phenomenon of the external pressure loads on bluff bodies under gusty winds: and also to study internal pressure loads, which depend on the size of the venting holes of the building. Finally, the contribution of the unsteady flow terms in the theoretical model has been analyzed, and the pressure jumps due to the unsteady pressure losses through the venting holes have been characterized.

Genetically aerodynamic optimization of the nose shape of a high-speed train entering a tunnel

The optimization of the nose shape of a high-speed train entering a tunnel has been performed using genetic algorithms(GA).This optimization method requires the parameterization of each optimal candidate as a design vector.The geometrical parameterization of the nose has been defined using three design variables that include the most characteristic geometrical factors affecting the compression wave generated at the entry of the train and the aerodynamic drag of the train.

Aerodynamic shape optimization of the nose of a high-speed train subjected to crosswind conditions

When dealing with the design of a high-speed train, a multiobjective shape optimization problem is formulated, as these vehicles are object of many aerodynamic problems which are known to be in conflict. More mobility involves an increase in both the cruise speed and lightness, and these requirements directly influence the stability and the ride comfort of the passengers when the train is subjected to a side wind. Thus, crosswind stability plays a more relevant role among the aerodynamic objectives to be optimized. An extensive research activity is observed on aerodynamic response in crosswind conditions.