For astronomical observing missions by formation flying satellites in LEO, satellites require control force to keep the relative position, against Keplerian orbit in an inertia coordinate frame. Since satellites require propulsion systems, i.e. thrusters, but the use of thrusters limits the mission lifetime associated with the finite fuel supply. Thus the authors propose the formation flight using electromagnetic force. In this method, the electromagnetic force between super-conducting magnets are used for the relative position control. This method has the obvious advantage of no-fuel to acquire control force. Since such large magnetic moment in earth magnetism generates large disturbance torque, the magnetic moments should be sinusoidal with shorter period than that of the orbit period. Therefore, this paper proposes the relative position control by changing the phase difference between sinusoidal magnetic moments. The proposed method was evaluated with numerical simulations and the results shows the feasibility of the proposed formation flight.
{"title":"The Relative Position Control in Formation Flying Satellites Using Super-Conducting Magnets","authors":"R. Kaneda, S. Sakai, T. Hashimoto, H. Saito","doi":"10.2322/JJSASS.56.203","DOIUrl":"https://doi.org/10.2322/JJSASS.56.203","url":null,"abstract":"For astronomical observing missions by formation flying satellites in LEO, satellites require control force to keep the relative position, against Keplerian orbit in an inertia coordinate frame. Since satellites require propulsion systems, i.e. thrusters, but the use of thrusters limits the mission lifetime associated with the finite fuel supply. Thus the authors propose the formation flight using electromagnetic force. In this method, the electromagnetic force between super-conducting magnets are used for the relative position control. This method has the obvious advantage of no-fuel to acquire control force. Since such large magnetic moment in earth magnetism generates large disturbance torque, the magnetic moments should be sinusoidal with shorter period than that of the orbit period. Therefore, this paper proposes the relative position control by changing the phase difference between sinusoidal magnetic moments. The proposed method was evaluated with numerical simulations and the results shows the feasibility of the proposed formation flight.","PeriodicalId":144591,"journal":{"name":"Journal of The Japan Society for Aeronautical and Space Sciences","volume":"32 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2008-05-05","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"123077047","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}
Two-stream flow model of ejector including heat and mass transfer was constructed by the comparison of the numerical simulations in the rocket-ramjet combined-cycle engine driven three different rocket gas; cold N2 gas, hot combustion gas and it within excess H2. The analysis of the ejector revealed that the heat and mass transfer from hot rocket plume with supersonic speed to cold airflow induced area change (expansion) of the airflow stream tube and the pressure rise in the constant-area section at the downstream of the rocket base. This pressure rise reduced the pumping performance of the ejector. To absorb the expansion of the airflow, the flowpath was changed from the constant area to the diverging area at the downstream of the rocket base. The numerical simulation in the modified engine demonstrated that the diverging-area section at the downstream of the rocket base improved the pumping performance.
{"title":"複合エンジンの静止大気中における吸い込み性能 : 第1報 : 数値計算による吸い込み性能予測","authors":"Toshinori Kouchi, Sadatake Tomioka, Takeshi Kanda","doi":"10.2322/JJSASS.56.110","DOIUrl":"https://doi.org/10.2322/JJSASS.56.110","url":null,"abstract":"Two-stream flow model of ejector including heat and mass transfer was constructed by the comparison of the numerical simulations in the rocket-ramjet combined-cycle engine driven three different rocket gas; cold N2 gas, hot combustion gas and it within excess H2. The analysis of the ejector revealed that the heat and mass transfer from hot rocket plume with supersonic speed to cold airflow induced area change (expansion) of the airflow stream tube and the pressure rise in the constant-area section at the downstream of the rocket base. This pressure rise reduced the pumping performance of the ejector. To absorb the expansion of the airflow, the flowpath was changed from the constant area to the diverging area at the downstream of the rocket base. The numerical simulation in the modified engine demonstrated that the diverging-area section at the downstream of the rocket base improved the pumping performance.","PeriodicalId":144591,"journal":{"name":"Journal of The Japan Society for Aeronautical and Space Sciences","volume":"159 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2008-03-05","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"127671052","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":"Perturbed Radius of Geosynchronous-Satellite Orbit","authors":"S. Kawase","doi":"10.2322/JJSASS.56.143","DOIUrl":"https://doi.org/10.2322/JJSASS.56.143","url":null,"abstract":"","PeriodicalId":144591,"journal":{"name":"Journal of The Japan Society for Aeronautical and Space Sciences","volume":"29 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2008-03-05","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"117312518","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":"Unscented Kalman Filterを用いた故障衛星のロバストな姿勢運動推定","authors":"圭吾 吉田, 洋平 白坂, 健久 矢入, 和雄 町田","doi":"10.2322/JJSASS.56.65","DOIUrl":"https://doi.org/10.2322/JJSASS.56.65","url":null,"abstract":"","PeriodicalId":144591,"journal":{"name":"Journal of The Japan Society for Aeronautical and Space Sciences","volume":"13 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2008-02-05","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"134054926","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":"飛行推進統合制御対応航空エンジン制御装置の研究 : 第1報 : FADECシステム及びエンジン制御","authors":"山根 秀公, 松永 易, 草川 剛","doi":"10.2322/JJSASS.56.80","DOIUrl":"https://doi.org/10.2322/JJSASS.56.80","url":null,"abstract":"","PeriodicalId":144591,"journal":{"name":"Journal of The Japan Society for Aeronautical and Space Sciences","volume":"8 5 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2008-02-05","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"124296115","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}
This study concerns a shape optimum design to minimize wrinkle intensity of a membrane under an area constraint. The membrane shape is modeled by non-uniform rational B-spline (NURBS) curves and the curve-passing points are adopted as design variables. The membrane wrinkle intensity is evaluated through the wrinkle-mode deformation energy proposed by one of the authors. Where, the total strain energy in a wrinkled membrane evaluated by the tension field theory is effectively decomposed into elastic strain energy and apparent wrinkle-mode deformation energy by applying a projection matrix. The latter only depends on the deformation caused by wrinkling, and is utilized as an objective function. As a numerical example, the optimization is applied to a typical square membrane design problem to demonstrate the effect of the shape optimization on the wrinkle reduction. The wrinkle-mode deformation energy decreases to 10% of the original design for only 5% reduction of the membrane area. Additionally, a high convergence property is achieved regardless of direct implementation of the nonlinear finite element analysis during the optimization.
{"title":"Shape Optimal Design of Membrane Wrinkling Minimization Using NURBS Curves","authors":"N. Kogiso, Daisuke Hirajo, T. Akita","doi":"10.2322/JJSASS.56.72","DOIUrl":"https://doi.org/10.2322/JJSASS.56.72","url":null,"abstract":"This study concerns a shape optimum design to minimize wrinkle intensity of a membrane under an area constraint. The membrane shape is modeled by non-uniform rational B-spline (NURBS) curves and the curve-passing points are adopted as design variables. The membrane wrinkle intensity is evaluated through the wrinkle-mode deformation energy proposed by one of the authors. Where, the total strain energy in a wrinkled membrane evaluated by the tension field theory is effectively decomposed into elastic strain energy and apparent wrinkle-mode deformation energy by applying a projection matrix. The latter only depends on the deformation caused by wrinkling, and is utilized as an objective function. As a numerical example, the optimization is applied to a typical square membrane design problem to demonstrate the effect of the shape optimization on the wrinkle reduction. The wrinkle-mode deformation energy decreases to 10% of the original design for only 5% reduction of the membrane area. Additionally, a high convergence property is achieved regardless of direct implementation of the nonlinear finite element analysis during the optimization.","PeriodicalId":144591,"journal":{"name":"Journal of The Japan Society for Aeronautical and Space Sciences","volume":"210 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2008-02-05","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"122593761","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 aerodynamic design procedure of a large-scale aircraft noise suppression facility has been developed. Flow quality required for the engine inlet flow has been determined through basic experiment. Aerodynamic design of the facility has been performed by using wind tunnel experiment and CFD. Important relationship between the length of the facility and the inlet flow quality has been found. The operational envelope of the designed facility has been estimated. Then, the aerodynamic characteristics of an actual large-scale aircraft noise suppression facility, constructed based on the new design procedure, have been measured. Obtained flow field showed good agreement with CFD results, and the effectiveness of the design procedure based on CFD and wind tunnel experiment has been confirmed. The engine operations were satisfactory under various wind conditions. Furthermore, the data under commercial operations thereafter have been collected and analyzed. As the result, the aerodynamic design procedure has been validated.
{"title":"Study of Aerodynamic Design Procedure of a Large-Scale Aircraft Noise Suppression Facility","authors":"M. Kawai, K. Nagai, S. Aso","doi":"10.2322/JJSASS.56.88","DOIUrl":"https://doi.org/10.2322/JJSASS.56.88","url":null,"abstract":"The aerodynamic design procedure of a large-scale aircraft noise suppression facility has been developed. Flow quality required for the engine inlet flow has been determined through basic experiment. Aerodynamic design of the facility has been performed by using wind tunnel experiment and CFD. Important relationship between the length of the facility and the inlet flow quality has been found. The operational envelope of the designed facility has been estimated. Then, the aerodynamic characteristics of an actual large-scale aircraft noise suppression facility, constructed based on the new design procedure, have been measured. Obtained flow field showed good agreement with CFD results, and the effectiveness of the design procedure based on CFD and wind tunnel experiment has been confirmed. The engine operations were satisfactory under various wind conditions. Furthermore, the data under commercial operations thereafter have been collected and analyzed. As the result, the aerodynamic design procedure has been validated.","PeriodicalId":144591,"journal":{"name":"Journal of The Japan Society for Aeronautical and Space Sciences","volume":"144 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2008-01-07","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"133349906","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":"積極的COTSを導入した超小型推進系の開発とS-310-36号機による宇宙実証","authors":"H. Sahara, S. Nakasuka","doi":"10.2322/JJSASS.55.579","DOIUrl":"https://doi.org/10.2322/JJSASS.55.579","url":null,"abstract":"","PeriodicalId":144591,"journal":{"name":"Journal of The Japan Society for Aeronautical and Space Sciences","volume":"21 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2007-12-05","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"126543958","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}
A series of lab-scale firing tests was conducted to investigate the fuel regression characteristics of Cascaded Multistage Impinging-jet (CAMUI) type hybrid rocket. The alternative fuel grain used in this rocket consists of a number of cylindrical fuel blocks with two ports, which were aligned along the axis of the combustion chamber with a small gap. The ports are aligned staggered with respect to ones of neighboring blocks so that the combustion gas flow impinges on the forward-end surface of each block. In this fuel grain, forward-end surfaces, back-end surfaces and ports of fuel blocks contribute as burning surfaces. Polyethylene and LOX were used as a propellant, and the tests were conducted at the chamber pressure of 0.5–2MPa and the mass flux of 50–200kg/m2s. Main results obtained in this study are in the followings: The regression rate of each surface was obtained as a function of the propellant mass flux and local equivalent ratio of the combustion gas. At back-end surfaces the regression rate has a high sensitivity on the gap height of neighboring fuel blocks. These fuel regression characteristics will contribute as fundamental data to improve the optimum design of the fuel grain.
{"title":"縦列多段衝突噴流(CAMUI)方式を用いたハイブリッドロケットの燃料後退特性","authors":"光紀 伊藤, 剛典 前田, 彰仁 柿倉, 雄大 金子, 一大 森, 卓巳 中島, 督司 脇田, 努 植松, 剛 戸谷, 伸行 大島, 晴紀 永田","doi":"10.2322/JJSASS.55.516","DOIUrl":"https://doi.org/10.2322/JJSASS.55.516","url":null,"abstract":"A series of lab-scale firing tests was conducted to investigate the fuel regression characteristics of Cascaded Multistage Impinging-jet (CAMUI) type hybrid rocket. The alternative fuel grain used in this rocket consists of a number of cylindrical fuel blocks with two ports, which were aligned along the axis of the combustion chamber with a small gap. The ports are aligned staggered with respect to ones of neighboring blocks so that the combustion gas flow impinges on the forward-end surface of each block. In this fuel grain, forward-end surfaces, back-end surfaces and ports of fuel blocks contribute as burning surfaces. Polyethylene and LOX were used as a propellant, and the tests were conducted at the chamber pressure of 0.5–2MPa and the mass flux of 50–200kg/m2s. Main results obtained in this study are in the followings: The regression rate of each surface was obtained as a function of the propellant mass flux and local equivalent ratio of the combustion gas. At back-end surfaces the regression rate has a high sensitivity on the gap height of neighboring fuel blocks. These fuel regression characteristics will contribute as fundamental data to improve the optimum design of the fuel grain.","PeriodicalId":144591,"journal":{"name":"Journal of The Japan Society for Aeronautical and Space Sciences","volume":"254 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2007-11-05","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"132823597","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}
K. Kitamura, K. Mori, K. Hanai, Tsutomu Yabashi, H. Ozawa, Yoshiaki Nakamura
Supersonic flow fields around Two-Stage-To-Orbit (TSTO) models with different configurations have been experimentally examined in this paper. Four configurations for the orbiter have been considered: A) a hemisphere-cylinder, B) a hemisphere-cylinder with a flat bottom, C) an obliquely truncated circular cylinder, and D) a cone-cylinder. All the flow fields around these models showed complicated shock/shock and shock/boundary-layer interactions, which can be categorized into three patterns, depending on the extent to which the separation shock wave contributes to these interactions. The models B, C and D were proposed to suppress the pressure rise due to the interactions observed in the model A. As a result, the model B showed almost the same interactions as the model A, while in the model C they did not present. In the model D, a large pressure rise was seen in the case with no clearance, whereas the model undergoes the least aerodynamic interaction at a rather large clearance. It is concluded from these results that the model C is less affected by aerodynamic interactions due to the clearance than the other models.
{"title":"Effects of TSTO Orbiter Configuration on Supersonic Flow Field with Aerodynamic Interactions","authors":"K. Kitamura, K. Mori, K. Hanai, Tsutomu Yabashi, H. Ozawa, Yoshiaki Nakamura","doi":"10.2322/JJSASS.55.509","DOIUrl":"https://doi.org/10.2322/JJSASS.55.509","url":null,"abstract":"Supersonic flow fields around Two-Stage-To-Orbit (TSTO) models with different configurations have been experimentally examined in this paper. Four configurations for the orbiter have been considered: A) a hemisphere-cylinder, B) a hemisphere-cylinder with a flat bottom, C) an obliquely truncated circular cylinder, and D) a cone-cylinder. All the flow fields around these models showed complicated shock/shock and shock/boundary-layer interactions, which can be categorized into three patterns, depending on the extent to which the separation shock wave contributes to these interactions. The models B, C and D were proposed to suppress the pressure rise due to the interactions observed in the model A. As a result, the model B showed almost the same interactions as the model A, while in the model C they did not present. In the model D, a large pressure rise was seen in the case with no clearance, whereas the model undergoes the least aerodynamic interaction at a rather large clearance. It is concluded from these results that the model C is less affected by aerodynamic interactions due to the clearance than the other models.","PeriodicalId":144591,"journal":{"name":"Journal of The Japan Society for Aeronautical and Space Sciences","volume":"17 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2007-11-05","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"124424193","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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