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定速移動体の最適軌道計画と軌道追従に関する研究;定速移動体の最適軌道計画と軌道追従に関する研究;Optimal Path Planning and Path Following for a Constant Speed Unicycle 定速移动体的最佳轨道规划和轨道跟随研究;定速移动体的最佳轨道规划和轨道跟随研究;Optimal Path Planning and Path Following for a Constant Speed Unicycle
AEROSPACE TECHNOLOGY JAPAN, THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES Pub Date : 1900-01-01 DOI: 10.2322/ASTJ.13.25
Shunsaku Arita, Seiya Ueno
{"title":"定速移動体の最適軌道計画と軌道追従に関する研究;定速移動体の最適軌道計画と軌道追従に関する研究;Optimal Path Planning and Path Following for a Constant Speed Unicycle","authors":"Shunsaku Arita, Seiya Ueno","doi":"10.2322/ASTJ.13.25","DOIUrl":"https://doi.org/10.2322/ASTJ.13.25","url":null,"abstract":"","PeriodicalId":138366,"journal":{"name":"AEROSPACE TECHNOLOGY JAPAN, THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES","volume":"43 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1900-01-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"114708680","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}
引用次数: 3
Development and Demonstration of a Data Collection System for Sounding Rockets 探空火箭数据采集系统的研制与验证
AEROSPACE TECHNOLOGY JAPAN, THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES Pub Date : 1900-01-01 DOI: 10.2322/astj.21.77
M. Mita
{"title":"Development and Demonstration of a Data Collection System for Sounding Rockets","authors":"M. Mita","doi":"10.2322/astj.21.77","DOIUrl":"https://doi.org/10.2322/astj.21.77","url":null,"abstract":"","PeriodicalId":138366,"journal":{"name":"AEROSPACE TECHNOLOGY JAPAN, THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES","volume":"20 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1900-01-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"126253035","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}
引用次数: 0
Validation of Wall-Modeled LES Based on Lattice Boltzmann Method with Turbulent Channel Flow 基于晶格玻尔兹曼方法的紊流通道壁型LES验证
AEROSPACE TECHNOLOGY JAPAN, THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES Pub Date : 1900-01-01 DOI: 10.2322/astj.jsass-d-20-00021
Hirotaka Maeyama, T. Imamura, J. Osaka, N. Kurimoto
{"title":"Validation of Wall-Modeled LES Based on Lattice Boltzmann Method with Turbulent Channel Flow","authors":"Hirotaka Maeyama, T. Imamura, J. Osaka, N. Kurimoto","doi":"10.2322/astj.jsass-d-20-00021","DOIUrl":"https://doi.org/10.2322/astj.jsass-d-20-00021","url":null,"abstract":"","PeriodicalId":138366,"journal":{"name":"AEROSPACE TECHNOLOGY JAPAN, THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES","volume":"33 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1900-01-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"128107414","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}
引用次数: 0
Evaluation of Ground Experimental Method for Simulating On-orbit Membrane Shape by Gravity Compensation Using Buoyancy of Aqueous Solution 利用水溶液浮力重力补偿法模拟在轨膜形的地面实验方法评价
AEROSPACE TECHNOLOGY JAPAN, THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES Pub Date : 1900-01-01 DOI: 10.2322/astj.21.53
Masanori Matsushita, Hideyuki Takahashi, Y. Satou, T. Iwasa
{"title":"Evaluation of Ground Experimental Method for Simulating On-orbit Membrane Shape by Gravity Compensation Using Buoyancy of Aqueous Solution","authors":"Masanori Matsushita, Hideyuki Takahashi, Y. Satou, T. Iwasa","doi":"10.2322/astj.21.53","DOIUrl":"https://doi.org/10.2322/astj.21.53","url":null,"abstract":"","PeriodicalId":138366,"journal":{"name":"AEROSPACE TECHNOLOGY JAPAN, THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES","volume":"19 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1900-01-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"125596595","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}
引用次数: 0
燃料消費節減に効率的な降下開始地点の予測についての覚書;燃料消費節減に効率的な降下開始地点の予測についての覚書;The Effect of Lower Altitude Wind for Finding Start Descent Point at End of Cruise 关于有效降低燃料消耗的开始地点预测的备忘录;关于有效降低燃料消耗的开始地点预测的备忘录;The Effect of Lower Altitude Wind for Finding Start Descent Point at End of Cruise
AEROSPACE TECHNOLOGY JAPAN, THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES Pub Date : 1900-01-01 DOI: 10.2322/ASTJ.12.107
Tsuneharu Uemura, Shinji Suzuki, Kenji Karasawa
{"title":"燃料消費節減に効率的な降下開始地点の予測についての覚書;燃料消費節減に効率的な降下開始地点の予測についての覚書;The Effect of Lower Altitude Wind for Finding Start Descent Point at End of Cruise","authors":"Tsuneharu Uemura, Shinji Suzuki, Kenji Karasawa","doi":"10.2322/ASTJ.12.107","DOIUrl":"https://doi.org/10.2322/ASTJ.12.107","url":null,"abstract":"The aircraft descent profile has many factors, such as selected airspeed, flight weight, wind, initial altitude, and outside temperature even if fixed idle thrust was assumed. This article tries to prove a rule of thumb that \" Even if the wind changes at lower altitude during descent, the flight path will converge at a lower altitude \". This may be useful information for flight operation, if it is correct. In addition idle thrust descents are a useful method for fuel economy operation. This paper tries to support this rule of thumb by numerical simulations of flight paths with different wind conditions.","PeriodicalId":138366,"journal":{"name":"AEROSPACE TECHNOLOGY JAPAN, THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES","volume":"247 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1900-01-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"115964688","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}
引用次数: 0
Experimental and Analytical Evaluation on the Effects of the Boundary Layer Ingestion (BLI) Using a Simple Engine/Airframe Integration Model 基于简单机/机一体化模型的边界层吸进(BLI)影响的实验与分析
AEROSPACE TECHNOLOGY JAPAN, THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES Pub Date : 1900-01-01 DOI: 10.2322/astj.22.11
M. Kono, K. Okai, Akiyoshi Masaki, Tomoya Kogirima, Tetsuya Sato, J. Kazawa, D. Masaki
{"title":"Experimental and Analytical Evaluation on the Effects of the Boundary Layer Ingestion (BLI) Using a Simple Engine/Airframe Integration Model","authors":"M. Kono, K. Okai, Akiyoshi Masaki, Tomoya Kogirima, Tetsuya Sato, J. Kazawa, D. Masaki","doi":"10.2322/astj.22.11","DOIUrl":"https://doi.org/10.2322/astj.22.11","url":null,"abstract":"","PeriodicalId":138366,"journal":{"name":"AEROSPACE TECHNOLOGY JAPAN, THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES","volume":"87 1 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1900-01-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"131374593","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}
引用次数: 0
Position Estimation Using Crater-based Linear Features for Pinpoint Lunar Landing 基于陨石坑线性特征的精确月球着陆位置估计
AEROSPACE TECHNOLOGY JAPAN, THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES Pub Date : 1900-01-01 DOI: 10.2322/ASTJ.JSASS-D-17-00012
K. Kariya, T. Ishida, S. Sawai, Tomoo Kinoshita, K. Kajihara, Osamu Iwasa, S. Fukuda
{"title":"Position Estimation Using Crater-based Linear Features for Pinpoint Lunar Landing","authors":"K. Kariya, T. Ishida, S. Sawai, Tomoo Kinoshita, K. Kajihara, Osamu Iwasa, S. Fukuda","doi":"10.2322/ASTJ.JSASS-D-17-00012","DOIUrl":"https://doi.org/10.2322/ASTJ.JSASS-D-17-00012","url":null,"abstract":"","PeriodicalId":138366,"journal":{"name":"AEROSPACE TECHNOLOGY JAPAN, THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES","volume":"11 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1900-01-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"134379476","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}
引用次数: 3
Study on Orbital Maneuvers of Electric Sail with On-Off Thrust Control 带开关推力控制的电帆轨道机动研究
AEROSPACE TECHNOLOGY JAPAN, THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES Pub Date : 1900-01-01 DOI: 10.2322/ASTJ.12.79
Kouhei Yamaguchi, H. Yamakawa
{"title":"Study on Orbital Maneuvers of Electric Sail with On-Off Thrust Control","authors":"Kouhei Yamaguchi, H. Yamakawa","doi":"10.2322/ASTJ.12.79","DOIUrl":"https://doi.org/10.2322/ASTJ.12.79","url":null,"abstract":"An electric sail is a new propulsion system uses the solar wind dynamic pressure as a thrust force. We analyzed the probability of the orbital control not changing sail plane angle but switching an electron gun connected with tethers. First, locally optimal switching laws are derived from Lagrange variational equations analytically. By theoretical calculations and numerical simulations, these switching laws are effective for changing some orbital elements. Moreover, mission applicability is studied. Assuming minimum time transfer problem between circular and coplanar orbits, optimal control laws are studied with direct approach. We conclude that the switching orbital control method is effective for exploration of other planets. 1. は じ め に 帯電セイル (第 1図)は,2004年に Janhunen氏によっ て考案された次世代の推進システムである.システムの概 要としては,まず宇宙機本体をスピンさせることで,長さ 数十 kmの導電性テザーを 100本程度展開する.導電性テ ザーと接続された電子銃を作動させることにより,テザー は十数 kVの高電位に保たれ,高速のプラズマ流である太 陽風中の陽子と相互作用することで推力を得る.電子銃に 用いる電力は,テザーの一部に取り付けられた太陽電池か ら供給される.太陽風中の陽子の運動量を推力に変換する ことで、推進剤を用いない高効率な推進が可能とされてい る.高電位の導電性テザーと太陽風の相互作用は,1次元 及び 2次元の粒子シミュレーションによって研究されてお り,テザーが単位長さあたりに太陽風から得る推力値がテ ザー電位とテザーを構成するワイヤの半径,及び太陽風パ ラメータの関数として求められている.また,得られた推 力モデルを元に,実際の宇宙機を想定した場合に得られる 加速度や電位と推力の関係,及び 2次元における円軌道間 移行への適用可能性などの検討も行われている.更に,太 陽系外深宇宙探査を主な目的とし,帯電セイルを推進シス テムとした場合の太陽系脱出軌道の達成条件や最適制御則 などが検討され,その有用性が示されている.しかし,こ れらの先行研究の多くが帯電セイルの姿勢変更を用いた推 力方向制御を前提としているにも関わらず,燃料消費など を考慮した具体的な姿勢制御方法は提案されていない.帯 ∗1 C ⃝ 2013 日本航空宇宙学会 平成 25 年 3 月 25 日原稿受付 ∗2 京都大学 生存圏研究所 電セイルは,展開した数十 km級のテザーを安定させるた めに,回転しながら運用を行う非常に規模の大きな推進シ ステムであることから,その姿勢変更のためには更なる検 討が必要な状況である.そこで本論文では,帯電セイルの 姿勢変更を行わず,そのスピン軸方向が慣性座標系に対し て常に一定である状況を仮定する.推力方向が宇宙機の運 動によって変化するこのような状況で,テザー電位の調整 による推力の増減やスイッチングのみを用いた軌道制御の 可能性について検討する.","PeriodicalId":138366,"journal":{"name":"AEROSPACE TECHNOLOGY JAPAN, THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES","volume":"1 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1900-01-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"130695403","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}
引用次数: 24
Development of Separation Mechanism Using Non-Explosive Separation Nuts 非爆炸分离螺母分离机构的研制
AEROSPACE TECHNOLOGY JAPAN, THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES Pub Date : 1900-01-01 DOI: 10.2322/astj.jsass-d-20-00024
A. Takano, Sayaka Nishino
{"title":"Development of Separation Mechanism Using Non-Explosive Separation Nuts","authors":"A. Takano, Sayaka Nishino","doi":"10.2322/astj.jsass-d-20-00024","DOIUrl":"https://doi.org/10.2322/astj.jsass-d-20-00024","url":null,"abstract":"","PeriodicalId":138366,"journal":{"name":"AEROSPACE TECHNOLOGY JAPAN, THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES","volume":"9 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1900-01-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"132437520","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}
引用次数: 0
Development of Bus-Support-Structure for the Further GEO Satellite 进一步地球同步轨道卫星总线支撑结构的研制
AEROSPACE TECHNOLOGY JAPAN, THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES Pub Date : 1900-01-01 DOI: 10.2322/ASTJ.10.75
A. Takano, C. Takano, Kozo Hayata, Y. Ishijima, M. Utsunomiya, R. Shimizu
{"title":"Development of Bus-Support-Structure for the Further GEO Satellite","authors":"A. Takano, C. Takano, Kozo Hayata, Y. Ishijima, M. Utsunomiya, R. Shimizu","doi":"10.2322/ASTJ.10.75","DOIUrl":"https://doi.org/10.2322/ASTJ.10.75","url":null,"abstract":"The development of bus-structure for the further GEO satellite is described. The target of the further GEO satellite is to be the satellite with 8 kW solar generation, 3650 kg launch weight, and sufficiently global competitiveness on the next decade. The target weight of the bus-structure is lower than 215 kg (lower than 5.9 % of launch weight). The design and mechanical tests of the bus structure have been successfully completed.","PeriodicalId":138366,"journal":{"name":"AEROSPACE TECHNOLOGY JAPAN, THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES","volume":"32 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1900-01-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"115493020","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}
引用次数: 2
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