Calibración de sensores de fuerza bajo estímulos sinusoidales: contribuciones a su caracterización

El presente trabajo tiene como objetivo el desarrollo de un patrón primario para la calibración de sensores de fuerza bajo excitaciones sinusoidales. Con consecuencia de dicho desarrollo se establecerá un método de calibración de sensores de fuerza en condiciones dinámicas que permitirá la caracterización de estos sensores en dichas condiciones y determinar la incertidumbre asociada. Este patrón se basa en la definición directa de fuerza como masa por aceleración. Para ello se carga el sensor con distintas cargas calibradas y se somete a distintas aceleraciones mediante un excitador de vibraciones. Dichas aceleraciones se generan para frecuencias desde 5 Hz a 2400 Hz. La aceleración se mide mediante un vibrómetro láser con trazabilidad a la unidad de longitud (longitud de onda del láser). Al ser una medición completamente dinámica se necesita un sistema de adquisición de datos multicanal para la toma de datos en tiempo real. Este sistema adquiere las señales eléctricas provenientes del vibrómetro láser, del sensor a caracterizar y del acelerómetro para mediciones auxiliares. Se ha dispuesto de cuatro sensores de fuerza para realizar ensayos, un sensor piezoeléctrico y tres sensores resistivos. En este trabajo se han estudiado los factores de influencia y se ha implementado un método de calibración para minimizar los mismos, así como también se han establecido las correcciones a realizar. Para la caracterización dinámica del sensor se ha partido de un modelo de oscilador armónico amortiguado forzado, se ha establecido la metodología para la determinación de sus parámetros de caracterización y se ha estudiado su validez. También se ha realizado una comparación entre los resultados obtenidos para condiciones estáticas y dinámicas. ABSTRACT The aim in the current work is the development of a primary standard for force sensors calibration under sinusoidal excitations. As consequence of this development a method for force sensors calibration under dynamic conditions will be established that will allow these sensors characterization for such conditions and the determination of their associated uncertainty. This standard is based on the direct definition of force as mass multiplied by acceleration. To do so, the sensor is loaded with different calibrated loads and is maintained under different accelerations by means of a vibration shaker. These accelerations are generated with frequencies from 5 Hz up to 2400 Hz. The acceleration is measured by means of a laser vibrometer with traceability to the unit of length (laser wavelength). As the measurement is totally dynamic a multiple channel data acquisition system is required for data acquisition in real time. This system acquires the electrical signals outputs coming from the laser vibrometer, the sensor to be characterised and two accelerometers for additional measurements. Four force sensors, one piezoelectric sensor and three resistive sensors, have been available to perform the tests. During this work the influence factors have been studied and a calibration method to minimise these factors have been implemented as well as the corrections to be performed have been established. As the starting point for the sensor dynamic characterization, a model for a forced damped harmonic oscillator has been used, a method for the characterizing parameters determination has been established and its validity has been studied. A comparison between results for static and dynamic conditions has been performed as well.

Deviations of cup anemometer rotational speed measurements due to steady state harmonic accelerations of the rotor

The measurement deviations of cup anemometers are studied by analyzing the rotational speed of the rotor at steady state (constant wind speed). The differences of the measured rotational speed with respect to the averaged one based on complete turns of the rotor are produced by the harmonic terms of the rotational speed. Cup anemometer sampling periods include a certain number of complete turns of the rotor, plus one incomplete turn, the residuals from the harmonic terms integration within that incomplete turn (as part of the averaging process) being responsible for the mentioned deviations. The errors on the rotational speed due to the harmonic terms are studied analytically and then experimentally, with data from more than 500 calibrations performed on commercial anemometers.

Provisos for classic linear oscillator design methods. New linear oscillator design based on the NDF/RRT

In this paper, the classic oscillator design methods are reviewed, and their strengths and weaknesses are shown. Provisos for avoiding the misuse of classic methods are also proposed. If the required provisos are satisfied, the solutions provided by the classic methods (oscillator start-up linear approximation) will be correct. The provisos verification needs to use the NDF (Network Determinant Function). The use of the NDF or the most suitable RRT (Return Relation Transponse), which is directly related to the NDF, as a tool to analyze oscillators leads to a new oscillator design method. The RRT is the "true" loop-gain of oscillators. The use of the new method is demonstrated with examples. Finally, a comparison of NDF/RRT results with the HB (Harmonic Balance) simulation and practical implementation measurements prove the universal use of the new methods.

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.

A panel method free-wake code for aeroelastic rotor predictions

A panel method free-wake model to analyse the rotor flapping is presented. The aerodynamic model consists of a panel method, which takes into account the three-dimensional rotor geometry, and a free-wake model, to determine the wake shape. The main features of the model are the wake division into a near-wake sheet and a far wake represented by a single tip vortex, and the modification of the panel method formulation to take into account this particular wake description. The blades are considered rigid with a flap degree of freedom. The problem solution is approached using a relaxation method, which enforces periodic boundary conditions. Finally, several code validations against helicopter and wind turbine experimental data are performed, showing good agreement