F2010C207
Development of Measuring System of Gravity Center in Unbalanced Models
There are many unbalanced models such as hard-disk's actuator, high-speed small-sized spindle, small-sized precision motor and helicopter's rotor blades in industrial applications. In the real products, their center of gravity usually does not accord with the desired center of gravity. If the deviation is large between them, it can be a major cause of generating vibration and noise as rotate the part of model. Therefore the center of gravity in the rotational parts should be controlled properly because of static and dynamic balancing of the parts. In this research, especially, measurement system of gravity center for the static balance of the rotor blade of unmanned helicopter has been considered. The system is primarily useful to manufacturing process of rotor blade and to calibrating process of the used blades. In the real manufacturing process of rotor blade by using aluminum alloys and composite materials, it is not easy to assure the precision location of gravity center of the parts. In the calibrating process of gravity center for repairing of used blades, proper mass may be added locally according to the weighing and analyzing of the blades by using the measuring system. Multiple-point Weighing Method, that is static method, has been used to control the center of gravity in the rotor blade. In the construction of the measuring system, major components are rotation platform that is machined V-slots under the surface for reducing measurement error, load cell that is used for weighing, balls, rigid frame, and lab-view program that is correlated to the numerical data acquisition and data calculation during the measurement. The length and the maximum width of the manufactured rotor blade for unmanned helicopter are 1000mm, and 7mm, respectively. It has been measured over 10 phases in order to find out the real center of gravity. The developed system can be finally contributed to improve the dynamic balancing of unmanned helicopter, and enhance the flight performance by using static balancing of blades.
This abstract is supplemented by a PDF, which can be viewed here.