This paper addresses simultaneous optimal design of adaptive truss structures, in which we compromise structural and control systems while taking into account structural layout, shape and control systems. The problem becomes nonconvex discrete optimization problem in terms of continuous and discrete design variables. Noticing that the nonconvex problem can be approximated by a convex one by adding a semidefinite positive function, so-called a convexifying function, to make the constraint convex, first, we solve this nonconvex problem using successive LMI optimization in cross-sectional area of truss members and state feedback gains. Second, we solve this discrete problem using genetic algorithm for simultaneous optimization of layout of truss structures. In this way, a hybrid method combining successive LMI optimization and genetic algorithm is used in this study. A numerical example of a simple structure is provided to demonstrate the effectiveness of the proposed method.
{"title":"Simultaneous Optimal Design of Structural Layout, Shape and Control Systems for Truss Structure","authors":"Shinsuke Sakamoto, T. Shimomura, H. Okubo","doi":"10.2322/JJSASS.57.267","DOIUrl":"https://doi.org/10.2322/JJSASS.57.267","url":null,"abstract":"This paper addresses simultaneous optimal design of adaptive truss structures, in which we compromise structural and control systems while taking into account structural layout, shape and control systems. The problem becomes nonconvex discrete optimization problem in terms of continuous and discrete design variables. Noticing that the nonconvex problem can be approximated by a convex one by adding a semidefinite positive function, so-called a convexifying function, to make the constraint convex, first, we solve this nonconvex problem using successive LMI optimization in cross-sectional area of truss members and state feedback gains. Second, we solve this discrete problem using genetic algorithm for simultaneous optimization of layout of truss structures. In this way, a hybrid method combining successive LMI optimization and genetic algorithm is used in this study. A numerical example of a simple structure is provided to demonstrate the effectiveness of the proposed method.","PeriodicalId":144591,"journal":{"name":"Journal of The Japan Society for Aeronautical and Space Sciences","volume":"98 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2009-07-05","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"124222655","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
S. Takeuchi, E. Sato, J. Onoda, K. Higuchi, Y. Arakawa
Adhesive bonding structure around a metalic mouthpiece of a cryogenic composite tank was analyzed based on fracture mechanics. Energy release rate was analytically formulated considering difference in strain energies in tension and bending between before and after the crack growth based on a simplified mathematical model. The analytical results were compared with the calculated results by finite element method for five example tanks; they revealed fairly good match. This analysis gives a guideline of the initial optimal design of a cryogenic composite tank based on fracture mechanics.
{"title":"Evaluation of Adhesive Bonding Structure in Cryogenic Composite Tank Based on Fracture Mechanics","authors":"S. Takeuchi, E. Sato, J. Onoda, K. Higuchi, Y. Arakawa","doi":"10.2322/JJSASS.56.169","DOIUrl":"https://doi.org/10.2322/JJSASS.56.169","url":null,"abstract":"Adhesive bonding structure around a metalic mouthpiece of a cryogenic composite tank was analyzed based on fracture mechanics. Energy release rate was analytically formulated considering difference in strain energies in tension and bending between before and after the crack growth based on a simplified mathematical model. The analytical results were compared with the calculated results by finite element method for five example tanks; they revealed fairly good match. This analysis gives a guideline of the initial optimal design of a cryogenic composite tank based on fracture mechanics.","PeriodicalId":144591,"journal":{"name":"Journal of The Japan Society for Aeronautical and Space Sciences","volume":"2 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2009-05-04","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"128131045","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
{"title":"Development of the Explosion Breakup Model for Space Debris","authors":"H. Hata, T. Hiroe, K. Fujiwara","doi":"10.2322/JJSASS.57.135","DOIUrl":"https://doi.org/10.2322/JJSASS.57.135","url":null,"abstract":"","PeriodicalId":144591,"journal":{"name":"Journal of The Japan Society for Aeronautical and Space Sciences","volume":"90 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2009-04-05","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"122096514","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Mixing and spreading characteristics of an orifice free jet are investigated changing the orifice plate thickness t/do, where do is the nozzle exit diameter, ranged from 0.01 to 1.5. Schlieren images show high mixing and spreading performances at t/do = 0.5 and Reynolds number Re = 1.5×104 because at the t/do = 0.5 the jet fluctuates by the separated flow from the inner edge of orifice alternates attachment and detachment to the outer edge. Hot-wire anemometry measurements are also performed to investigate the mean and fluctuating velocity profiles. It is found that the jet potential core length is insensitive to Re at Re > 7.0 × 103, but significantly influenced by the orifice plate thickness. The potential core length for t/do = 0.5 is the shortest reflecting the fluctuation at the nozzle exit.
研究了改变孔板厚度 t/do（do 为喷嘴出口直径，范围为 0.01 至 1.5）时无孔喷流的混合和扩散特性。Schlieren 图像显示，在 t/do = 0.5 和雷诺数 Re = 1.5×104 时，混合和扩散性能较高，因为在 t/do = 0.5 时，射流通过孔板内缘的分离流交替附着和脱离外缘而波动。此外，还进行了热丝风速测量，以研究平均速度和波动速度曲线。研究发现，当 Re > 7.0 × 103 时，射流势核长度对 Re 不敏感，但受孔板厚度的影响很大。t/do = 0.5 时的潜在核心长度最短，反映了喷嘴出口处的波动。
{"title":"オリフィス自由噴流の混合・拡散特性の改善・制御","authors":"敏彦 社河内, 鬼頭 みずき, 佐藤 光太郎, 公一 辻本, 俊剛 安藤","doi":"10.2322/JJSASS.57.160","DOIUrl":"https://doi.org/10.2322/JJSASS.57.160","url":null,"abstract":"Mixing and spreading characteristics of an orifice free jet are investigated changing the orifice plate thickness t/do, where do is the nozzle exit diameter, ranged from 0.01 to 1.5. Schlieren images show high mixing and spreading performances at t/do = 0.5 and Reynolds number Re = 1.5×104 because at the t/do = 0.5 the jet fluctuates by the separated flow from the inner edge of orifice alternates attachment and detachment to the outer edge. Hot-wire anemometry measurements are also performed to investigate the mean and fluctuating velocity profiles. It is found that the jet potential core length is insensitive to Re at Re > 7.0 × 103, but significantly influenced by the orifice plate thickness. The potential core length for t/do = 0.5 is the shortest reflecting the fluctuation at the nozzle exit.","PeriodicalId":144591,"journal":{"name":"Journal of The Japan Society for Aeronautical and Space Sciences","volume":"19 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2009-04-05","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"132644609","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Automatic differentiation through source code transformation is a very powerful strategy for gradient-based optimization studies. However, memory allocation is a significant challenge if the transformed code is used without any modifications because automatic differentiation requires huge memory space. A general strategy to calculate derivatives of CFD solutions analytically through automatic differentiation without the memory problem is proposed in this paper. The problem of memory allocation is avoided by wisely modifying the code generated by automatic differentiation, and by feeding a set of converged solutions to the modified code. This strategy is validated by comparing derivatives computed through automatic differentiation and finite differentiation. The proof of concept application is the optimization of airfoil shape in transonic speed regime using a general CFD software available on line.
{"title":"Aerodynamic Optimization through Automatic Differentiation and CFD","authors":"Tetsushi Takemiya, D. Mavris","doi":"10.2322/JJSASS.57.89","DOIUrl":"https://doi.org/10.2322/JJSASS.57.89","url":null,"abstract":"Automatic differentiation through source code transformation is a very powerful strategy for gradient-based optimization studies. However, memory allocation is a significant challenge if the transformed code is used without any modifications because automatic differentiation requires huge memory space. A general strategy to calculate derivatives of CFD solutions analytically through automatic differentiation without the memory problem is proposed in this paper. The problem of memory allocation is avoided by wisely modifying the code generated by automatic differentiation, and by feeding a set of converged solutions to the modified code. This strategy is validated by comparing derivatives computed through automatic differentiation and finite differentiation. The proof of concept application is the optimization of airfoil shape in transonic speed regime using a general CFD software available on line.","PeriodicalId":144591,"journal":{"name":"Journal of The Japan Society for Aeronautical and Space Sciences","volume":"109 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2009-03-05","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"131815663","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Hidemi Takahashi, M. Hirota, Hiroki Oso, G. Masuya
Structure of flow field formed by normal sonic injection into a Mach 1.8 air stream was investigated with acetone planar laser induced fluorescence (acetone PLIF). Parametric calculation of fluorescence intensity indicates that it represent molar concentration within ±2.5% error for the present experimental condition. For the special situation of isentropic flow without any mixing, Mach number can be deduced from the fluorescence intensity. Mach number distribution from PLIF data was compared with one obtained from PIV measurement, and showed good agreement. The jet trajectories obtained from images visualized by acetone PLIF and Mie scattering are compared. We find that the acetone PLIF gives reasonable trajectory while the Mie scattering over estimate the jet penetration.
{"title":"Measurement of Supersonic Injection Flowfield Using Acetone PLIF","authors":"Hidemi Takahashi, M. Hirota, Hiroki Oso, G. Masuya","doi":"10.2322/JJSASS.55.318","DOIUrl":"https://doi.org/10.2322/JJSASS.55.318","url":null,"abstract":"Structure of flow field formed by normal sonic injection into a Mach 1.8 air stream was investigated with acetone planar laser induced fluorescence (acetone PLIF). Parametric calculation of fluorescence intensity indicates that it represent molar concentration within ±2.5% error for the present experimental condition. For the special situation of isentropic flow without any mixing, Mach number can be deduced from the fluorescence intensity. Mach number distribution from PLIF data was compared with one obtained from PIV measurement, and showed good agreement. The jet trajectories obtained from images visualized by acetone PLIF and Mie scattering are compared. We find that the acetone PLIF gives reasonable trajectory while the Mie scattering over estimate the jet penetration.","PeriodicalId":144591,"journal":{"name":"Journal of The Japan Society for Aeronautical and Space Sciences","volume":"101 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2009-02-04","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"133635785","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
REIMEI/INDEX (INnovative-technology Demonstration EXperiment) is a 70kg class small satellite which the Institute of Space and Astronautical Science, Japan Exploration Agency, ISAS/JAXA, has developed for observation of auroral small-scale dynamics as well as demonstration of advanced satellite technologies. An important engineering mission of REIMEI is integrated satellite control using commercial RISC CPUs with a triple voting system in order to ensure fault-tolerance against radiation hazards. Software modules concerning every satellite function, such as attitude control, data handling, and mission applications, work cooperatively so that highly sophisticated satellite control can be performed. In this paper, after a concept of the integrated satellite control is introduced, the Integrated Controller Unit (ICU) is described in detail. Also unique topics in developing the integrated control system are shown.
REIMEI/INDEX(创新技术示范实验)是一颗70公斤级的小卫星，由日本研究开发机构(ISAS/JAXA)空间和宇航科学研究所开发，用于观测极光小尺度动力学以及先进卫星技术的示范。REIMEI的一项重要工程任务是利用商用RISC cpu和三重投票系统集成卫星控制，以确保对辐射危害的容错性。涉及每个卫星功能的软件模块，如姿态控制、数据处理和任务应用，协同工作，以便执行高度复杂的卫星控制。本文在介绍卫星综合控制概念的基础上，详细介绍了卫星综合控制单元(integrated Controller Unit, ICU)。并指出了开发综合控制系统的独特课题。
{"title":"れいめい（INDEX）衛星における統合化衛星制御","authors":"盛介 福田, 貴秀 水野, 坂井 真一郎, 洋介 福島, 宏文 齋藤","doi":"10.2322/JJSASS.57.25","DOIUrl":"https://doi.org/10.2322/JJSASS.57.25","url":null,"abstract":"REIMEI/INDEX (INnovative-technology Demonstration EXperiment) is a 70kg class small satellite which the Institute of Space and Astronautical Science, Japan Exploration Agency, ISAS/JAXA, has developed for observation of auroral small-scale dynamics as well as demonstration of advanced satellite technologies. An important engineering mission of REIMEI is integrated satellite control using commercial RISC CPUs with a triple voting system in order to ensure fault-tolerance against radiation hazards. Software modules concerning every satellite function, such as attitude control, data handling, and mission applications, work cooperatively so that highly sophisticated satellite control can be performed. In this paper, after a concept of the integrated satellite control is introduced, the Integrated Controller Unit (ICU) is described in detail. Also unique topics in developing the integrated control system are shown.","PeriodicalId":144591,"journal":{"name":"Journal of The Japan Society for Aeronautical and Space Sciences","volume":"11 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2009-01-05","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"126855266","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
The supersonic biplane is well known as the airfoil that has zero wave drag at the supersonic speed. This paper investigates aerodynamic characteristics of the supersonic biplane with the finite span length and effects of the aspect and taper ratios by comparing with the two-dimensional supersonic biplane which has the infinite span length using the computational fluid dynamics. The rectangular wing was employed to examine the effect of the aspect ratio and tapered wing was employed to inspect the effect of the taper ratio. Both the rectangular wing and the two-dimensional supersonic biplane choke at the high angle of attack. The drag of the three-dimensional wing becomes smaller when it has a higher aspect ratio. The drag polar curve of the three-dimensional wing approaches asymptotically to the drag polar curve of the two-dimensional supersonic biplane when it has a higher taper ratio. The drag of the tapered wing becomes smaller when it has an adequate taper ratio.
{"title":"CFD Analysis Based Evaluation of Aerodynamic Characteristics for Supersonic Biplane with Finite Span Length","authors":"M. Yonezawa, S. Obayashi","doi":"10.2322/JJSASS.57.32","DOIUrl":"https://doi.org/10.2322/JJSASS.57.32","url":null,"abstract":"The supersonic biplane is well known as the airfoil that has zero wave drag at the supersonic speed. This paper investigates aerodynamic characteristics of the supersonic biplane with the finite span length and effects of the aspect and taper ratios by comparing with the two-dimensional supersonic biplane which has the infinite span length using the computational fluid dynamics. The rectangular wing was employed to examine the effect of the aspect ratio and tapered wing was employed to inspect the effect of the taper ratio. Both the rectangular wing and the two-dimensional supersonic biplane choke at the high angle of attack. The drag of the three-dimensional wing becomes smaller when it has a higher aspect ratio. The drag polar curve of the three-dimensional wing approaches asymptotically to the drag polar curve of the two-dimensional supersonic biplane when it has a higher taper ratio. The drag of the tapered wing becomes smaller when it has an adequate taper ratio.","PeriodicalId":144591,"journal":{"name":"Journal of The Japan Society for Aeronautical and Space Sciences","volume":"243 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2009-01-05","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"114600853","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Y. Aoyanagi, Toshiki Kato, Toshihiko Yasunaka, T. Uematsu, S. Satori
A laser communication system has an advantage of realizing the high speed transmission under the conditions of small size and low electrical power. The laser communication system requires a high accuracy of pointing control because of the directional characteristics of laser beam. Due to the attitude control accuracy of micro-satellites, the pointing device carried in micro-satellite is required to have mitigated pointing accuracy, wide range pointing, small size, mass and low electrical power. We have developed a new pointing device characterized by two-axis pointing control mechanism. Breadboard model of pointing control mechanism consists of steering mirror, angular sensor and electrical unit. The steering mirror mechanism is accomplished using rod-end-bearings. The pointing accuracy and the performance of tracking system of the laser communication device were evaluated in simulator of between satellite and ground station. This paper describes development of the breadboard model of pointing control mechanism and the performance evaluation.
{"title":"Miniaturization and Evaluation of Laser Communication System for Satellite by 2-Axis Steering Mirror Mechanism","authors":"Y. Aoyanagi, Toshiki Kato, Toshihiko Yasunaka, T. Uematsu, S. Satori","doi":"10.2322/JJSASS.56.573","DOIUrl":"https://doi.org/10.2322/JJSASS.56.573","url":null,"abstract":"A laser communication system has an advantage of realizing the high speed transmission under the conditions of small size and low electrical power. The laser communication system requires a high accuracy of pointing control because of the directional characteristics of laser beam. Due to the attitude control accuracy of micro-satellites, the pointing device carried in micro-satellite is required to have mitigated pointing accuracy, wide range pointing, small size, mass and low electrical power. We have developed a new pointing device characterized by two-axis pointing control mechanism. Breadboard model of pointing control mechanism consists of steering mirror, angular sensor and electrical unit. The steering mirror mechanism is accomplished using rod-end-bearings. The pointing accuracy and the performance of tracking system of the laser communication device were evaluated in simulator of between satellite and ground station. This paper describes development of the breadboard model of pointing control mechanism and the performance evaluation.","PeriodicalId":144591,"journal":{"name":"Journal of The Japan Society for Aeronautical and Space Sciences","volume":"138 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2008-12-05","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"114414329","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
: The operational stress data is quite useful in managing the structural integrity and airworthiness of an aircraft. Since the aerodynamic load (pressure) distributes continuously on the structure surface, identifying the load from finite number of measured strain data is not easy. Although this is an inverse problem, usually used is an empir-ical correlation between load and strain obtained through expensive ground tests. Some analytical studies have been conducted but simple mathematical expressions were assumed to approximate the pressure distribution. In the present study a more flexible approximation of continuous load distribution is proposed. The pressure distribution is identified based on finite number of strain data with using the conventional finite element method and pseudo-inverse matrix. Also an extension is made by coupling an aerodynamical restriction with the elastic equation. Numerical examples show that this extension improves the precision of the inverse analysis with very small number of strain data.
{"title":"Inverse Analysis of Distributed Load Using Strain Data","authors":"Toshiya Nakamura, H. Igawa","doi":"10.2322/JJSASS.56.566","DOIUrl":"https://doi.org/10.2322/JJSASS.56.566","url":null,"abstract":": The operational stress data is quite useful in managing the structural integrity and airworthiness of an aircraft. Since the aerodynamic load (pressure) distributes continuously on the structure surface, identifying the load from finite number of measured strain data is not easy. Although this is an inverse problem, usually used is an empir-ical correlation between load and strain obtained through expensive ground tests. Some analytical studies have been conducted but simple mathematical expressions were assumed to approximate the pressure distribution. In the present study a more flexible approximation of continuous load distribution is proposed. The pressure distribution is identified based on finite number of strain data with using the conventional finite element method and pseudo-inverse matrix. Also an extension is made by coupling an aerodynamical restriction with the elastic equation. Numerical examples show that this extension improves the precision of the inverse analysis with very small number of strain data.","PeriodicalId":144591,"journal":{"name":"Journal of The Japan Society for Aeronautical and Space Sciences","volume":"61 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2008-12-05","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"127042567","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
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