Curriculum Vitaes

Junjiro Onoda

  (小野田 淳次郎)

Profile Information

Affiliation
Professor, Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency
Degree
Ph.D.(The University of Tokyo)

researchmap Member ID
1000144488

Research Interests

 2

Papers

 105
  • Junjiro Onoda, Kenji Minesugi, Seong-Cheol Kwon, Hyun-Ung Oh
    Smart Materials and Structures, 30(6) 065014-065014, Jun 1, 2021  
    Abstract We propose and demonstrate a novel method to enhance vibration harvesting based on surge-induced synchronized switch harvesting on inductor (S3HI). S3HI allows harvesting of a large amount of energy even from low-amplitude vibrations by inducing a surge voltage during the voltage inversion of a synchronized switch harvesting on inductor (SSHI). The surge voltage and the voltage amplification from the conventional voltage inversion improve energy harvesting. S3HI modifies SSHI by both rewiring the circuit without adding components and using a novel switching pattern for voltage inversion, thus maintaining the simplicity of SSHI. We propose a novel switching strategy and circuit topology and analyze six methods that constitute the S3HI family, which includes traditional S3HI and high-frequency S3HI. We demonstrate that the six methods suitably harvest energy even from low-amplitude vibrations. Nevertheless, the harvestable energy per vibration cycle depends on the switching pattern and storage-capacitor voltage. The use of the proposed switching strategy, which allows energy harvesting before energy-dissipative voltage inversion, substantially increases the harvestable energy per vibration cycle. In the typical case considered in this study, the said increase is on the order of 11%–31% and 15%–450% compared to the traditional and existing high-frequency S3HI methods, respectively, depending on the storage-capacitor voltage. Additionally, the proposed circuit can be used as a traditional circuit. It could be considered a promising alternative to S3HI methods owing to its potential auto-reboot capability, which is not found in traditional S3HI circuit.
  • Seong-Cheol Kwon, Junjiro Onoda, Hyun-Ung Oh
    Sensors and Actuators A: Physical, 281 55-66, Oct, 2018  Peer-reviewed
  • Seong-Cheol Kwon, Junjiro Onoda, Hyun-Ung Oh
    Mechanical Systems and Signal Processing, Aug, 2018  Peer-reviewed
  • Junjiro Onoda, Shigeru Shimose, Kenji Minesugi
    JOURNAL OF INTELLIGENT MATERIAL SYSTEMS AND STRUCTURES, 28(7) 888-906, Apr, 2017  Peer-reviewed
    This article describes the optimal configuration and combination of piezoelectric transducers and inductors for the synchronized-switch-damping-on-an-inductor technique. The technique suppresses structural vibrations by inverting the polarity of the electric voltage in a piezoelectric transducer using a switched inductive shunt circuit at each displacement extremum. The energy dissipation rate of synchronized switch damping on an inductor depends on the impedances of the transducer and the inductor in the circuit, especially the resistive component, in this inversion. For this study, mathematical models of the equivalent resistances of transducers and inductors for this inversion phenomenon were formulated based on experiments with various transducers and inductors. Using these models, the optimal ratio of the thickness-area of patch-type piezoelectric transducers and that of the length-cross-sectional area of the lead of the inductors were analytically obtained. The optimization of series-parallel connections of multiple transducers and inductors was also shown to be equivalent to this one. The optimal mass budget allocation for the transducers and inductors was also formulated. Two examples of optimization, involving an increase in energy dissipation rates by a factor of 4, were presented. The examples showed that the time taken to suppress free vibrations in a clamped beam was reduced to half through the optimization.
  • Shigeru Shimose, Kanjuro Makihara, Junjiro Onoda
    Smart Materials Research, 2013(Article No. 736487), Jan, 2013  Peer-reviewed

Misc.

 51
  • 小野田淳次郎, 峯杉賢治, KWON Seong-Cheol, OH Hyun-Ung
    構造強度に関する講演会講演集, 62nd, 2020  
  • 小野田淳次郎, 峯杉賢治, KWON Seong-Cheol, OH Hyun-Ung
    構造強度に関する講演会講演集, 61st, 2019  
  • 小野田淳次郎, 峯杉賢治, 下瀬滋
    構造強度に関する講演会講演集, 60th, 2018  
  • 小野田淳次郎
    日本法科学技術学会誌, 20(Supplement) 1-2, Oct 26, 2015  
  • ONODA Junjiro
    22(1) 1-1, Apr 30, 2012  
  • MAKIHARA Kanjuro, SHIMOSE S., TAKEUCHI S., ONODA J.
    Dynamics and Design Conference : D & D, 2011 18-18, Sep 4, 2011  
  • MAKIHARA Kanjuro, ONODA Junjiro, YABU Takuya
    Dynamics & Design Conference, 2006 "621-1"-"621-6", Aug 6, 2006  
    This paper presents a self-sensing method for semi-active vibration suppression that measures only the value of piezoelectric voltage. The method separates electrical status into two cases concerning electrical current, and characterize each of these to establish a self-sensing system. Experiments revealed that the self-sensing system suppressed vibrations by combining the state-switching control or the synchronized-switching control. We confirmed that the self-sensing method is robust against model errors through the vibration suppression experiment subject to model errors caused by intentional frequency shift.
  • 槙原幹十朗, 小野田淳次郎, 峯杉賢治
    自動制御連合講演会(CD-ROM), 49th ROMBUNNO.SU2-3-3, 2006  
  • 槙原幹十朗, 小野田淳次郎, 峯杉賢治
    自動制御連合講演会(CD-ROM), 48th H1-26, Nov 25, 2005  
  • MAKIHARA Kanjuro, ONODA Junjiro, MINESUGI Kenji
    Dynamics and Design Conference, 2005(9) 271-276, Aug 22, 2005  
    A novel self-sensing method using piezoelectric actuators for semi-active vibration suppression is proposed. By using extended system equations, this self-sensing method can be implemented with a Kalman filter instead of the conventional bridge circuit technique. This method is so advanced that it can be applied to multiple-degree-of-freedom (MDOF) structures with multiple piezoelectric actuators. A numerical simulation demonstrated that the self-sensing method works well on a truss structure and has significant robustness against parameter variations. Experimental results also confirmed that the self-sensing method suppresses not only single-mode vibrations but also complicated multiple-mode vibrations.
  • MAKIHARA Kanjuro, ONODA Junjiro, MINESUGI Kenji
    Dynamics & Design Conference, 2005 "713-1"-"713-6", Aug 22, 2005  
    A novel method of hybrid vibration suppression using piezoelectric materials is proposed. It combines bangbang active control and energy-recycling semi-active control. The hybrid method saves actively supplied energy and is thus a low energy-consumption vibration control. Its effectiveness in suppressing vibrations was proven in numerical simulations and experiments using a 10-bay truss structure. Moreover, an innovative method to prevent undesired control chattering is proposed to further save energy supplied from the external source.
  • 金田英宏, 中川貴雄, 村上浩, 小野田淳次郎, 佐藤英一, 名取通弘, 八田博志, 峯杉賢治, 奥泉信克, 塩谷圭吾, 尾中敬, 山城亮治
    日本天文学会年会講演予稿集, 2004, 2004  
  • 小野田淳次郎
    ミノル記念講演会講演録, 10th 29P, Dec 16, 2003  
  • 小野田淳次郎
    宇宙科学研究所報告 特集, (47) 5-11, Mar, 2003  
  • 小野田淳次郎, 峯杉賢治
    宇宙科学研究所報告 特集, (47) 25-84, Mar, 2003  
  • 安野拓也, 栗林一彦, 峯杉賢治, 小野田淳次郎
    いわき明星大学理工学部研究紀要, (13) 55-64, Mar 20, 2000  
  • 小野田淳次郎
    日本航空宇宙学会誌, 46(538) 585-593, Nov, 1998  
  • 竹内伸介, 小野田淳次郎, 峯杉賢治, 橋元保雄, 富沢利夫, 下瀬滋
    宇宙科学研究所報告, 100(100) 36P-34, Mar, 1998  
    In this paper, the trajectory dispersion of the Viper rocket caused by the elastic vibration of the vehicle and rocket launcher is investigated. In order to estimate the trajectory dispersion, a three dimensional numerical simulation of the launch was carried out considering the elastical effect of the vehicle and rocket launcher. The accuracy of the numerical simulation was validated first by the comparison with the vibration data measured on actual launch, and after that the trajectory dispersion was estimated by the simulation. As the result, it is confirmed that the trajectory dispersion caused by th elastic vibration is no matter on actual launch mission.
  • ONODA Junjiro, NAGASHIMA Ryuichi
    45(517) 77-78, Feb, 1997  
  • 森昌彦, 西田稔夫, 久利修平, 名山理介, 小野田淳次郎, 栗林一彦
    三菱重工技報, 33(3) 186-189, May, 1996  
  • ONODA Junjiro
    44(507) 212-213, Apr 5, 1996  
  • Junjiro Onoda, Hyun Ung Oh, Kenji Minesugi
    37th AIAA/ASME/ASCE/AHS/ASC Structure, Structural Dynamics and Materials Conference, 1569-1577, Jan 1, 1996  
    © 1996, American Institute of Aeronautics and Astronautics, Inc. To semiactively suppress the vibration of space truss structures, a variable damper using Electro- Rheological (ER) fluid is designed and fabricated. The characteristics of the damper are measured, and a simple mathematical model of the damper is proposed. Based on this mathematical model, several semiactive control laws are proposed for vibration suppression of multiple degree- of-freedom (MDOF) structures with multiple dampers. To investigate the performances of the scheme, numerical simulations of semiactive vibration suppression of a ten-bay truss beam with ER fluid dampers are performed. Simulation results indicate that the most of the proposed semiactive control laws result in much higher performances than that of the optimally tuned passive system. A semiactive vibration suppression experiment of the ten-bay truss beam with the ER fluid damper is also performed. The experiment results also demonstrate the effectiveness of the scheme for the actual MDOF structure.
  • 小野田淳次郎
    システム/制御/情報, 39(3) 136-141, Mar, 1995  
  • 横田俊昭, 佐々木進, 田中真, 遠山文雄, 太田正広, 小野田淳次郎, 戸田勧, 鈴木良昭, 八坂哲雄
    宇宙基地利用基礎実験費研究成果報告書 平成6年度 国際宇宙観測共同事業費(IML-2計画参加), 22-45, 1995  
  • Kenji Minesugi, Junjiro Onoda, Yoji Hanawa
    Collection of Technical Papers - AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference, 1 200-206, Jan 1, 1995  
    Vibration environment at lift-off of satellite launchers is one of critical conditions for electrical devices or systems on board. Countermeasure against the vibration is sometimes required, however, it is difficult to find an effective and practical one under the restrictions of weight increase and space. In this paper, a polyimid tape with viscous lamina is noted on the application to the passive vibration suppression, since it has shown a remarkable effect for vibration suppression in the practical application to a satellite. In order to investigate its damping mechanism, several kinds of experiments have been performed and their results are reported in this paper.
  • Junjiro Onoda, Dan Ying Fu, Kenji Minesugi
    Collection of Technical Papers - AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference, 2 1060-1067, Jan 1, 1995  
    A two-dimensionally deployable truss structure is newly proposed for space application, whose most significant feature is its small number of mechanisms to be locked when it is deployed. Its packaging efficiency is shown to be better than many known deployable trusses. Several versions of the truss are also proposed. To confirm that the new deployable truss has enough design flexibility, a paraboloidal truss platform is designed for trial. Furthermore, a numerical investigation shows that the platform is actually deployable/foldable from the practical point of view.
  • Junjiro Onoda, Tetsuji Sano, Kenji Minesugi
    Collection of Technical Papers - AIAA/ASME Structures, Structural Dynamics and Materials Conference, 2095-2100, Jan 1, 1993  
    A new approach to the passive vibration suppression of truss structures has been proposed and investigated. The approach is to take advantage of the preloaded backlashes introduced at the joints of truss structures. Because of the preload, the structure keeps its high stiffness and high static shape accuracy when the external load and the vibration level are low enough. When the response of the structure exceeds a certain level, e.g. allowable level, the backlashes at the joints start slipping, introducing the frictional damping and a nonlinearity. This nonlinearity transfers energy from a vibration mode to another. Because the vibration of higher modes usually damp sooner, this nonlinearity transfers energy from the lower modes to the higher modes, resulting in a quick damping of entire vibration. Numerical simulations show that the energy transfer between the modes drastically enhances the inherent damping capability of the structure. Resulting damping can be as large as that due to the frictional force at the backlashes even when the inherent damping ratio of each mode is as low as 0.1-0.2%. The simulation results demonstrate that both the frictional force and the enhanced inherent damping, especially the combination of them, suppress the vibration nicely.
  • 小野田淳次郎, 渡辺直行, 市田和夫, 橋元保雄, 中田篤
    宇宙科学研究所報告 特集, 29(29) 87-113, Jun, 1991  
  • 小野田淳次郎, 渡辺直行
    CAS研究報告, (31) 129-132, Mar, 1988  
  • 小野田淳次郎, HAFTKA R T
    CAS研究報告, (30) 9-12, Mar, 1987  
  • 森大吉郎, 小野田淳次郎, 橋本保雄, 中田篤, 名取通弘, 市田和夫
    宇宙科学研究所報告 特集, 16(16) 161-168, Oct, 1986  
  • 小野田淳次郎, 富沢利夫, 中田篤, 橋元保雄, 今沢茂夫, 市田和夫, 森大吉郎
    宇宙科学研究所報告, 40(40) 22P-21, Oct, 1986  
    This report presents the outline of the rocket structural testing facility constructed in Sagamihara campus of ISAS in 1984. The facility is composed of a) a 12m long, 8m tall, 6m wide testing stand, b) a 2-channel 70 MPa hydropressure loading device with a control unit, c) a 600-channel strain/displacement measureling system, and d) a data acquisition, processing and display system. Although the planning of the facility was motivated by the structural testings required in the process of development of Mu-3SII launch vehicle, it was designed so as to carry out the various structural testing of various kinds of structures as flexibly and efficiently as possible.
  • 小野田淳次郎
    CAS研究報告, (28) 125-134, Mar, 1985  
  • 小野田淳次郎
    CAS研究報告, (27(A)) 35-46, Mar, 1984  
  • 小野田淳次郎, 名島憲治, 岡崎洋
    宇宙科学研究所報告 特集, (6) 155-166, Mar, 1983  
  • 三浦公亮, 酒巻正守, 小野田淳次郎, 名取通弘
    CAS研究報告, (26) 61-66, Mar, 1983  
  • 森大吉郎, 小野田淳次郎, 細村建夫, 白銀博
    CAS研究報告, (26) 67-71, Mar, 1983  
  • 小野田淳次郎, 森大吉郎
    CAS研究報告, (25) 33-44, Mar, 1982  
  • Daikichiro Mori, Junjiro Onoda
    宇宙科学研究所報告, 3(3) 1-18, Mar, 1982  
    Development of spherical cases for the solid propellant rocket motors is presented. These motor cases, made of titanium alloy, have been designed for upper stages of satellite launchers for scientific satellites. In past twenty years, many type of motor cases have been developed corresponding to the ever increasing mission requirement of the Japanese scientific satellites, thereby, overcoming the shortage of budget. In this report, research work carried out to produce more efficient and more large motor cases are outlined, emphasizing the improvement both in material property and manufacturing process.
  • Daikichiro Mori, Junjiro Onoda, Toshiro Imamasa, Toshikazu Shimoyama, Kazuo Saito, Hiroshi Okazaki
    宇宙科学研究所報告, 1(1) 1-24, Sep, 1981  
    This paper presents the development of the motor case of the newly developed single stage sounding rocket"S-520". This rocket being a single stage rocket, in compariosn with the previously developed K-9M and K-10 versions which are two stage, has the advantage of simplicity in operation and handling, and also of better range safety. In the development of this sounding rocket of high performance, extreme weight saving, precise alignment and high reliability of the motor case were required. Using the improved material, design technique using FEM structural analysis and new fabrication techniques such as EBW, the motor case which satisfies all the requirements has been developed and the burst test by hydropressure showed its high reliability.
  • 小野田淳次郎, 森大吉郎
    CAS研究報告, (24) 77-84, Mar, 1981  
  • 森大吉郎, 小野田淳次郎, 橋元保雄, 村上卓司, 白銀博, 小野島昇
    東京大学宇宙航空研究所報告, 16(4A) 1207-1221, Nov, 1980  
  • 森大吉郎, 小野田淳次郎, 今政惇郎, 下山仁一, 斉藤一雄, 岡崎洋
    三菱重工技報, 17(5) 120-129, Sep, 1980  
  • 小野田淳次郎, 森大吉郎
    CAS研究報告, (23) 121-126, Mar, 1980  
  • 今沢茂夫, 小野田淳次郎, 中田篤, 富沢利夫
    東京大学宇宙航空研究所報告, 16(1 (B)) 355-367, Feb, 1980  
  • 森大吉郎, 小野田淳次郎, 橋元保雄, 細村健夫
    東京大学宇宙航空研究所報告, 16(1 (B)) 215-231, Feb, 1980  
  • 小野田淳次郎, 今沢茂夫, 森大吉郎, 砂川恵, 秋葉鐐二郎, 棚次亘弘
    東京大学宇宙航空研究所報告, 15(1 (B)) 177-185, Mar, 1979  
  • 今沢茂夫, 小野田淳次郎, 中田篤
    東京大学宇宙航空研究所報告, 14(1 (B)) 311-321, Mar, 1978  
  • 橋元保雄, 八坂哲雄, 小野田淳次郎
    東京大学宇宙航空研究所報告, 14(1B) 53-76, Mar, 1978  

Presentations

 241

Research Projects

 12