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Fang, J.

Publications and source records attributed to Fang, J..

44 records · Page 3

Measurement of the branching fraction of the decay J / ψ → p p ¯ η

A high-precision measurement of the branching fraction of the decay J / ψ → p p ¯ η is performed using ( 10 087 ± 44 ) × 10 6 J / ψ events recorded by the BESIII detector at the BEPCII storage ring. The branching fractions of the two decays J / ψ → p p ¯ η ( η → γ γ ) and J / ψ → p p ¯ η ( η → π + π − π 0 ) are measured individually to be B ( J / ψ → p p ¯ η ( η → γ γ ) ) = ( 1.480 ± 0.001 ± 0.024 ) × 10 − 3 and B ( J / ψ → p p ¯ η ( η → π + π − π 0 ) ) = ( 1.557 ± 0.003 ± 0.038 ) × 10 − 3 , where the first uncertainties are statistical and the second systematic. Both results are compatible within their uncorrelated systematic uncertainties. The combined result is B ( J / ψ → p p ¯ η ) = ( 1.495 ± 0.001 ± 0.023 ) × 10 − 3 , where the first uncertainty is the combined statistical uncertainty and the second one the combined systematic uncertainty of both analyses, incorporating correlations between them. In addition, the p p ¯ threshold region is investigated for a potential threshold enhancement, and no evidence for one is observed. Published by the American Physical Society 2024

Ablikim, M.

Measurements of the branching fractions of semileptonic D s + decays via e + e − → D s * + D s * −

We measure the absolute branching fractions of semileptonic D s + decays via the e + e − → D s * + D s * − process using e + e − collision data corresponding to an integrated luminosity of 10.64 fb − 1 collected by the BESIII detector at center-of-mass energies between 4.237 and 4.699 GeV. The branching fractions are B ( D s + → η e + ν e ) = ( 2.35 ± 0.11 stat ± 0.10 syst ) % , B ( D s + → η ′ e + ν e ) = ( 0.82 ± 0.09 stat ± 0.04 syst ) % , B ( D s + → ϕ e + ν e ) = ( 2.21 ± 0.16 stat ± 0.11 syst ) % , B ( D s + → f 0 ( 980 ) e + ν e , f 0 ( 980 ) → π + π − ) = ( 0.15 ± 0.02 stat ± 0.01 syst ) % , B ( D s + → K 0 e + ν e ) = ( 0.24 ± 0.0 4 stat ± 0.0 1 syst ) % , and B ( D s + → K * 0 e + ν e ) = ( 0.19 ± 0.0 3 stat ± 0.0 1 syst ) % . These results are consistent with those measured via the e + e − → D s * ± D s ∓ process by BESIII and CLEO. Using two-parameter series expansion, the hadronic transition form factors of D s + → η e + ν e , D s + → η ′ e + ν e , and D s + → K 0 e + ν e are determined to be f + η ( 0 ) = 0.442 ± 0.02 2 stat ± 0.01 7 syst , f + η ′ ( 0 ) = 0.557 ± 0.06 2 stat ± 0.02 4 syst , and f + K 0 ( 0 ) = 0.677 ± 0.09 8 stat ± 0.02 3 syst . Published by the American Physical Society 2024

Ablikim, M.

Preliminary Design of Ironless Linear Induction Motors for ITER MSE Shutter Actuators

In this article, the shutters need to be closed or opened during the operation and calibration period time for the fusion diagnostic systems, such as the International Thermonuclear Experimental Reactor (ITER) motional stark effect (MSE). Standard electric motors and actuators will not work in a strong magnetic field environment due to the presence of the magnetic field of fusion reactors. The innovative linear induction motor (LIM) with an ironless feature overcomes this kind of challenge and can be used for any application that requires controlled motion with a large stroke in the magnetic field environment. It consists of a high-electrical conductivity plate like copper and three-phase motor windings with nonferrous or stainless-steel stators. The conductor plate attached with the shutter is simply driven by the underneath three-phase linear windings to achieve linear motion. The motor drive can be controlled remotely by a controller using the electrical connection, so no sensitive electronic components are located in the harsh environment where the motor itself is located. The design requirements and test facility have been described. Several 3-D transient Maxwell electromagnetic (EM) models with different locations of three-phase linear motor windings and shutter stators have been analyzed and evolved to meet any applications allowed in the harsh environment inside the vacuum vessel of fusion reactors. The preliminary design results are presented in this article.

70 PLASMA PHYSICS AND FUSION TECHNOLOGY

Random vibration of nonlinear beams by the new stochastic linearization technique

In this paper, the beam under general time dependent stationary random excitation is investigated, when exact solution is unavailable. Numerical simulations are carried out to compare its results with those yielded by the conventional linearization techniques. It is found that the modified version of the stochastic linearization technique yields considerably more accurate results for the mean square displacement of the beam than the conventional equivalent linearization technique, especially in the case of large nonlinearity.

Fang, J.

Numerical solutions for unsteady subsonic vortical flows around loaded cascades

A frequency domain linearized unsteady aerodynamic analysis is presented for three-dimensional unsteady vortical flows around a cascade of loaded airfoils. The analysis fully accounts for the distortion of the impinging vortical disturbances by the mean flow. The entire unsteady flow field is calculated in response to upstream three-dimensional harmonic disturbances. Numerical results are presented for two standard cascade configurations representing turbine and compressor bladings for a reduced frequency range from 0.1 to 5. Results show that the upstream gust conditions and blade sweep strongly affect the unsteady blade response.

Fang, J.

Aerodynamics of loaded cascades in subsonic flows subject to unsteady three-dimensional vortical disturbances

A highly efficient numerical method is developed for three-dimensional, periodic, vortical flows around a cascade of loaded airfoils. The method linearizes Euler's equations about the mean flow of the cascade and thus fully accounts for the effects of distortion of the vortical disturbances as they propogate and interact with the cascade mean flow. The numerical scheme is based on splitting the unsteady velocity into vortical and potential parts. The latter is governed by a non-constant coefficient inhomogeneous convective wave equation. A new and computationally suitable out-flow conditions are derived and avoid the difficulties associated with the singular velocity downstream. Solutions were obtained in the frequency domain by using a body-fitted coordinate system. Results are presented to demonstrate the effects of the out-flow boundary conditions, cascade spacing, mean blade loading and gust upstream conditions on the aerodynamics response and unsteady pressure field of a cascade.

Fang, J.

LOX/hydrocarbon fuel carbon formation and mixing data analysis

By applying the Priem-Heidmann Generalized-Length vaporization correlation, the computer model developed by the present study predicts the spatial variation of propellant vaporization rate using the injector cold flow results to define the streamtubes. The calculations show that the overall and local propellant vaporization rate and mixture ratio change drastically as the injection element type or the injector operating condition is changed. These results are compared with the regions of carbon formation observed in the photographic combustion testing. The correlation shows that the fuel vaporization rate and the local mixture ratio produced by the injector element have first order effects on the degree of carbon formation.

Fang, J.

An investigation of the open-loop amplification of Reynolds number dependent processes by wave distortion

Analytical and experimental studies were initiated to determine if the response of a constant temperature hot wire anemometer to acoustic oscillations could serve as an analog to the response of the drop vaporization burning rate process to acoustic oscillations, and, perhaps, also as an analog to any Reynolds number dependent process. The motivation behind this study was a recent analytical study which showed that distorted acoustic oscillations could amplify the open-loop response of vaporization limited combustion. This type of amplification may be the cause of unstable combustion in liquid propellant rocket engines. The analytical results obtained for the constant temperature anemometer are similar in nature to those previously obtained for vaporization limited combustion and indicate that the response is dependent on the amount and type of distortion as well as other factors, such as sound pressure level, Mach number and hot wire temperature. Preliminary results indicate qualitative agreement between theory and experiment.

Purdy, K. R.