Development of magnetic suspension and balance system for high-subsonic wind tunnel

Daiki Kai, Hiroki Sugiura, Asei Tezuka

Research output: Chapter in Book/Report/Conference proceedingConference contribution

Abstract

A magnetic suspension and balance system (MSBS) for suspending a model against a high-subsonic flow has been successfully developed at Japan Aerospace Exploration Agency (JAXA). In the transonic regime, it is difficult for an MSBS to support a model because the aerodynamic forces acting on the model increase with increasing flow speed and its fluctuations also increase accordingly. One of JAXA’s MSBSs for a 10 cm low-speed wind tunnel was modified to improve the control system response. A 500 Hz control system with image sensors was developed, and the proportional-integral controller of the system was replaced with a proportional-integral-differential controller. In addition, to cope with a larger aerodynamic force, more powerful amplifiers were installed. To cope with the directional instability of the model, the drag-counterbalancing magnetic field was modified by increasing the output of the front drag coil. These improvements enabled an ogive-cylinder model with a diameter of 10 mm and a length of 156 mm to be suspended in JAXA’s 10 cm MSBS up to a Mach number of 0.6.

Original languageEnglish
Title of host publicationAIAA Aerospace Sciences Meeting
PublisherAmerican Institute of Aeronautics and Astronautics Inc, AIAA
Edition210059
ISBN (Print)9781624105241
DOIs
Publication statusPublished - 2018 Jan 1
EventAIAA Aerospace Sciences Meeting, 2018 - Kissimmee, United States
Duration: 2018 Jan 82018 Jan 12

Other

OtherAIAA Aerospace Sciences Meeting, 2018
CountryUnited States
CityKissimmee
Period18/1/818/1/12

ASJC Scopus subject areas

  • Aerospace Engineering

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  • Cite this

    Kai, D., Sugiura, H., & Tezuka, A. (2018). Development of magnetic suspension and balance system for high-subsonic wind tunnel. In AIAA Aerospace Sciences Meeting (210059 ed.). American Institute of Aeronautics and Astronautics Inc, AIAA. https://doi.org/10.2514/6.2018-0304