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Nagai, H., Anyoji, M., Nonomura, T., Oyama, A., Okamoto, M., et al. (2015) Aerodynamic Challenge to Realize Mars Airplane. Proceedings of the 30th International Symposium on Space Technology and Science, Kobe, July 2015.

has been cited by the following article:

  • TITLE: Wind Tunnel Test for Videogrammetric Deformation Measurement of UAV for Mars Airplane Balloon Experiment-1 (MABE-1)

    AUTHORS: Koji Fujita, Akira Oyama, Daisuke Kubo, Masahiro Kanazaki, Hiroki Nagai

    KEYWORDS: Wind Tunnel, UAV, Deformation, Video Grammetry, Mars Exploration

    JOURNAL NAME: Journal of Flow Control, Measurement & Visualization, Vol.7 No.2, April 4, 2019

    ABSTRACT: This paper reports the results of the aerodynamic deformation measurements of the meter-scale, entire shape, actual UAV in the wind tunnel using a video grammetry technique. The measured airplane was the airplane for Mars exploration being developed by Japan Aerospace Exploration Agency (JAXA) and Japanese universities. Its main wing span length was 2.4 m. The video grammetry measurement was performed using VICON’s system. Retroactive markers and stickers were put on the airplane. JAXA’s 6.5 m × 5.5 m Low-Speed Wind Tunnel was used. The airplane was mounted on the strut support with pitch-free or pitch-locked conditions. The deformations of the main wing bending, the main wing twisting, the tail boom bending, and the elevator deflection angle change were revealed quantitatively. The bending stiffness of a main wing spar that was designed as a safety factor of 2.8 at load factor of 5 was sufficient. The main wing spar was located around a center of pressure of an airfoil and it showed enough stiffness for twisting at nominal condition. The effects of the main wing bending and twisting, and the tail boom bending on the aerodynamic performance were estimated but they were in an acceptable range from the standpoint of the controllability of the aerodynamic performance using control surfaces. Even though the servo motor was located near the elevator and the linkage between the servo motor and the elevator was short, the measured elevator deflection angle was at most 4% smaller than the angle at no-wind condition. The obtained results and presented method are useful for control, flight data analysis, and design of lightweight airplanes.