B. H. Iwamoto

ORCID: 0009-0005-9785-9544
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About
Contact & Profiles
Research Areas
  • Particle Accelerators and Free-Electron Lasers
  • Superconducting Materials and Applications
  • Radiative Heat Transfer Studies
  • Rocket and propulsion systems research
  • Real-time simulation and control systems
  • Particle accelerators and beam dynamics
  • Engineering Applied Research
  • Advanced Sensor Technologies Research
  • Geophysics and Sensor Technology
  • Gas Dynamics and Kinetic Theory

Brazilian Center for Research in Energy and Materials
2023-2024

A Superconducting Wavelength Shifter (SWLS) capable of achieving a peak magnetic field 6.6 T is currently being designed for future hard X-ray beamline Sirius, the new Brazilian Light Source. Due to machine requirements, narrow profile in central pole region (FWHM < 30 mm) constraint electromagnetic design. The superconducting racetrack coils, made NbTi wires, are be conduction cooled with an operating margin above 20% at 5 K. Two designs required, lateral coils 180 turns and 1080 turns,...

10.1109/tasc.2024.3357051 article EN IEEE Transactions on Applied Superconductivity 2024-01-23

A cryogen-free 6.6 T Superconducting Wavelength Shifter (SWLS) is currently being designed to produce photons with a critical energy higher than 39 keV for the future hard X-ray beamline of Sirius, new 4th generation Brazilian light source. The magnet based on NbTi coils and holmium poles an operating margin above 20% at 5 K. magnetic gap 7 mm in central pole was required achieve narrow peak field profile (FWHM = 29.8 mm), which did not affect emittance machine. device reuse several parts...

10.1109/tasc.2023.3346851 article EN IEEE Transactions on Applied Superconductivity 2023-12-26

The angle of attack (α) affects the drag, flight path, and stability during rocket ascent. This work proposes an in-flight α measurement system based on pressure measurements at surface nosecone for low apogee rockets. An electronic micro differential transducer was selected to measure difference between points in rocket’s nosecone. Wind tunnel tests were performed correlate with sensor output Mach numbers (Ma ≃ 0.08). experimental results further used as a reference construction CFD models...

10.5380/reterm.v21i4.89676 article EN Revista de Engenharia Térmica 2023-02-06
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