This paper describes a falling detection system by using two thermal array sensors. In the system, the sensors are attached to the ceiling and wall in a room, and acquire temperature distributions by each 16 × 16 pixels. The temperature distributions represent a state of temperature in the room, and they are analyzed to detect human falling. The falling is detected by time-series posture transition diagram and the sum of temperature. In our experiment, we measured the temperature distributions in a room modeled as private room in a nursing home. As the results, the system successfully detected the falling.
The method of bioelectrical impedance-based visceral fat estimation is in advance of other methods such as X-ray CT or MRI from the point views of cost and safety. However, it requires complex and diversity signal analysis and modeling to realize its high estimation accuracy. In response to this requirement, complication of feature attributes and simplification in selection of them to model the estimation has been proposed and evaluated in this paper. The complication of feature attributes is realized by applying priori knowledge and by employing the idea of cardinality as quantitative evaluation index. The simplification of the estimation model is realized by employing Akaike information criteria. The experiments were conducted to evaluate the proposed method and the results prove high estimation accuracy and stability of the proposed method.2007 IEEE International Conference on Granular Computing 0-7695-3032-X/07 $25.00
This paper describes the calculation of transonic stall flutter of a fan. A new CFD code has been developed and validated. The code is an unsteady 3D multi-block flow solver. The Reynolds-Averaged Navier-Stokes equations are solved using a finite volume method with Spallart-Allmaras 1 equation turbulence model. A grid deforming system is applied, so the new code is capable of simulating an oscillating blade row. This grid deforming system produces less grid distortion and the code has robustness for a blade oscillating calculation. The code has validated on an IHI’s research transonic fan rig test, and the result was in good agreement with the test data in the prediction of the flutter boundary. In the rig test at part-speed condition, stall-side flutter was experienced. In that condition, the inlet relative Mach number in the tip region is about unity. The aerodynamic work by the CFD at the near flutter condition is positive, which means that the flutter characteristic is unstable, while at other conditions the aerodynamic work is negative. The aerodynamic work increases rapidly just before the zero damping point with the increase of the blade loading. From the detailed CFD result, the shock wave on the suction surface contributes to the excitement of the blade oscillation, and the aerodynamic work of the shock wave has large value at the flutter condition.
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