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Additional file 6:. Supplementary Figure S1. Risk prediction models constructed using clinical information and two hub genes expression. The ROC curves of our risk prediction models in a test set. (a) AUC = 0.878 in AD and CN (b) AUC = 0.683 in MCI and CN (c) AUC = 0.645 in MCI and AD.

Additional file 6:. Supplementary Figure S1. Risk prediction models constructed using clinical information and two hub genes expression. The ROC curves of our risk prediction models in a test set. (a) AUC = 0.878 in AD and CN (b) AUC = 0.683 in MCI and CN (c) AUC = 0.645 in MCI and AD.

Additional file 1: Supplementary Table S1. SNP genotypes included in miR-eQTLs as potential biomarkers.

Additional file 3: Table S3. Genes and the annoatation related to the canonical pathways.

Additional file 1: Table S1. Hyperparameter values in the final GBDT model when using ÎźHEM algorithm.

Additional file 2: Table S2. All features used in the final GBDT risk prediction model.

Additional file 4: Table S4. Genes including in the KEGG pathways.

In Japan, dental charting following a disaster is performed by handwriting the information on a paper-based dental chart before manual input into a computer database. Even if available, radiographic facial or intraoral images, regardless of whether they are analogue or digital, must be stored separately from the dental chart. To create a comprehensive and more permanent database accessible worldwide, we developed a system employing digital pens with image microprocessors. This system digitizes and records characters and drawings as they are being handwritten on a microdotted-paper-based post-mortem dental chart. Data stored in the built-in memory of the digital pen are transferred to a computer or tablet via Bluetooth. Using a cognitive wireless router, the information is relayed to a remote data centre. Radiographic and other images are also transferred into the same folder under a unique ID number. After several practical field tests, the system was employed at a landslide disaster in Hiroshima ...

In order to increase the fuel regression rate, the paraffin fuel was used in the swirlingoxidizer-flow-type hybrid rocket engine. To improve the poor combustion efficiency when using the paraffin fuels, the engine was improved to have a shorter length than the engine using polypropylene fuel and to install an aft combustion chamber. The authors carried out the burning experiments using the engine with three aft combustion chambers with different volume and configuration to determine the optimum volume and configuration of the aft combustion chamber. Appropriate combustion was attained near at the optimum equivalence ratio for the engine performance. The controlling parameter on the fuel regression rate was clarified for the paraffin fuel in the swirling-oxidizer-flow-type hybrid rocket engine. The combustion efficiency was increased with each aft combustion chamber.

In order to increase the fuel regression rate of hybrid rocket engine, the concave-convex surface grain was adopted for the swirling-oxidizer-flow-type hybrid rocket engine. Burning experiments were carried out by changing the convex width from 9 to 18 mm, the concave width from 4.5 to 18 mm and the concave depth from 3 to 9 mm. The fuel regression rate of concave-convex surface grains with and without swirl increased up to about 1.7 and 2.0 times of the rates of cylindrical grains with and without swirl at the same oxygen mass flux conditions, respectively. The upstream side of the convex part increased the fuel regression rate. The local regression rates at the concave part were considerably lower than those at the convex part. Combustion oscillations caused by the Helmholtz resonance occurred.

Activity studies of solar-type stars, especially with reference to the status of our current Sun among them, have exposed the importance of (1) homogeneously selecting the sample stars and (2) reliably evaluating their activities down to a considerably low level. Motivated by these requirements, we conducted an extensive study on the activities of 118 solar-analog stars (of sufficiently similar properties to each other) by measuring the emission strength at the core of Ca II 3933.663 line (K line) on the high-dispersion spectrogram obtained by Subaru/HDS, where special attention was paid to correctly detecting the chromospheric emission by removing the wing-fitted photospheric profile calculated from the classical solar model atmosphere. This enabled us to detect low-level activities down to log R' ~ -5.4 (R' is the ratio of the chromospheric core emission flux to the total bolometric flux), by which we could detect subtle activity differences which were indiscernible in previous studies. Regarding the Sun, we found log R'sun = -5.33 near to the low end of the distribution, which means that it belongs to the distinctly low activity group among solar analogs. This excludes the once-suggested possibility for the high frequency of Maunder-minimum stars showing appreciably lower activities than the minimum-Sun., Comment: 12 pages, 7 figures, 1 table; acccepted for publication in Publ. Astron. Soc. Japan

In order to clarify the overall and local fuel regression rate behavior of hybrid combustion in swirling oxidizer flow, burning tests of the swirling-oxidizer-flow-type hybrid rocket engine were conducted using PP , PMMA and WAX fuel grains. The experiments showed that for all fuels, the relation between the time-averaged overall fuel regression rate, over r& , and the intermediate oxygen mass flux, Goitm, was expressed by a conventional hybrid regression rate formula such as over r& = aGoitm n . The values of a and n differed according to the fuel type. The n values implied that the combustion in the PMMA grains occurred by the diffusion-limited combustion mechanism, and that the gas-phase reaction rate of PP was slower than that of PMMA. For PP grains, the n values at the grain leading edge were smaller than those at the rear grain region. While the local fuel regression rate, loc r& , at the rear region decreased slightly with increasing the burning time tb, loc r& at the leading edge was independent of tb. These results suggested that the combustion mechanisms at the leading edge and the rear region differed.

The axial-direction fuel regression rates of the swirling-oxidizer-flow-type hybrid rocket engine were mesurred using PP fuel grains under the experimental conditions; grain length of 600 mm, intermediate oxygen mass flux Goitm up to about 120 kg/(m 2 ･s), combustion chamber pressure from 1 to 3MPa and burning time up to about 25 s. The experiments showed that the relation between the axial-direction fuel regression rate, l , and Goitm was expressed by a conventional hybrid regression rate formula such as ∝ l G n oitm. Although l was much faster than the timeaveraged local fuel regression rates, the nth power on Goitm for l was almost equal to that for time-averaged local fuel regression rates at the grain leading edge. l was able to be predicted using the time-averaged local fuel regression rate after burn-out and circumferentially averaged wedge angle at the grain leading edge.

A small, hydrogen-fueled pulse detonation combustor with a length of 200 mm and a volume of 120 cm was developed for 1 kW-class micro gas turbines to improve the thermal efficiency. The multi-port fuel injection was proposed to control both spatial and temporal concentration of the premixture. For the parallel and counterflow injection cases, the premixture flow behavior was characterized by the schlieren photography and the concentration measurement were conducted using a hot-wire concentration probe. Detonation was achieved in a short DDT distance of less than 180 mm using initiators.

In order to clarify in detail flame behavior in the combustion chamber of swirlingoxidizer-flow-type hybrid rocket engines, the authors made a new type of small hybrid rocket engine with a large quartz glass window to directly observe the combustion chamber from the front. PP and PMMA fuel grains were burned under the swirling and non-swirling oxygen flow conditions. Swirling flames did not form in the center region of the grain but adhered to the surface. The swirling flame zone of PMMA was approximately twice as width as that of PP. For both PP and PMMA fuels, the swirling flames were found to develop closer to the grain surface than those without swirl, resulting in an increase of the regression rates.

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