This paper proposes a novel passive sun-oriented control using the solar radiation pressure torque. Satellites that solar array panels are allocated as an umbrella is assumed. The top of the umbrella is oriented to the sun direction by the sun pressure and its weathercock stability. In order to dump the oscillation, a reflectance control device is attached on the solar array panels. The method realizes the sun-oriented without any other attitude control devises in the satellite. The availability of the method is evaluated in case of a solar-sail type spacecraft, a 50cm-class LEO satellite, and a 1U CubeSat by numerical simulations. Furthermore, a combination of the proposed control and the other passive attitude control is discussed.
{"title":"Dynamics Analysis of Weathercock like Passive Sun-oriented Control Using Solar Pressure","authors":"H. Nakanishi, Ryuhei Takagi, M. Oda","doi":"10.2322/TASTJ.17.483","DOIUrl":"https://doi.org/10.2322/TASTJ.17.483","url":null,"abstract":"This paper proposes a novel passive sun-oriented control using the solar radiation pressure torque. Satellites that solar array panels are allocated as an umbrella is assumed. The top of the umbrella is oriented to the sun direction by the sun pressure and its weathercock stability. In order to dump the oscillation, a reflectance control device is attached on the solar array panels. The method realizes the sun-oriented without any other attitude control devises in the satellite. The availability of the method is evaluated in case of a solar-sail type spacecraft, a 50cm-class LEO satellite, and a 1U CubeSat by numerical simulations. Furthermore, a combination of the proposed control and the other passive attitude control is discussed.","PeriodicalId":120185,"journal":{"name":"TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN","volume":null,"pages":null},"PeriodicalIF":0.0,"publicationDate":"1900-01-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"124155928","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}
Yukitaka Yamazaki, Kazuhide Mizobata, K. Higashino
A small-scale supersonic flight experiment vehicle (OWASHI) is being developed at Muroran Institute of Technology as a flying testbed for verification of innovative technologies for high speed atmospheric flights which are essential to nextgeneration aerospace transportation systems. The second-generation configuration M2011 of the vehicle with a single Air Turbo Ramjet Gas-generator-cycle (ATR-GG) engine has been proposed. Its transonic thrust margin has been predicted to be insufficient, therefore drag reduction in the transonic regime is quite crucial for attainability of supersonic flights. In this study, we propose configuration modifications for drag reduction on the basis of the so-called area rule, and assess their effects through wave drag analysis, wind tunnel tests, and CFD analysis. As a result, the area-rule-based configurations have less drag than the baseline configuration M2011. However, the effects of the proposed bottleneck on the fuselage below the main wing are smaller than predicted. It would be caused by the drag due to separation and shocks around the bottleneck. It is necessary to redesign the area-rule-based bottleneck to be smoother.
{"title":"Drag Reduction on the Basis of the Area Rule of the Small-Scale Supersonic Flight Experiment Vehicle Being Developed at Muroran Institute of Technology","authors":"Yukitaka Yamazaki, Kazuhide Mizobata, K. Higashino","doi":"10.2322/TASTJ.17.127","DOIUrl":"https://doi.org/10.2322/TASTJ.17.127","url":null,"abstract":"A small-scale supersonic flight experiment vehicle (OWASHI) is being developed at Muroran Institute of Technology as a flying testbed for verification of innovative technologies for high speed atmospheric flights which are essential to nextgeneration aerospace transportation systems. The second-generation configuration M2011 of the vehicle with a single Air Turbo Ramjet Gas-generator-cycle (ATR-GG) engine has been proposed. Its transonic thrust margin has been predicted to be insufficient, therefore drag reduction in the transonic regime is quite crucial for attainability of supersonic flights. In this study, we propose configuration modifications for drag reduction on the basis of the so-called area rule, and assess their effects through wave drag analysis, wind tunnel tests, and CFD analysis. As a result, the area-rule-based configurations have less drag than the baseline configuration M2011. However, the effects of the proposed bottleneck on the fuselage below the main wing are smaller than predicted. It would be caused by the drag due to separation and shocks around the bottleneck. It is necessary to redesign the area-rule-based bottleneck to be smoother.","PeriodicalId":120185,"journal":{"name":"TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN","volume":null,"pages":null},"PeriodicalIF":0.0,"publicationDate":"1900-01-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"122014788","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}
Naoto Morita, Masaharu Hiruma, T. Tsuchiya, Shuji Ogawa
{"title":"Comparison of Sub-Orbital Plane's Trajectories with Aerodynamic Results from a Panel Method and a CFD analysis","authors":"Naoto Morita, Masaharu Hiruma, T. Tsuchiya, Shuji Ogawa","doi":"10.2322/tastj.19.884","DOIUrl":"https://doi.org/10.2322/tastj.19.884","url":null,"abstract":"","PeriodicalId":120185,"journal":{"name":"TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN","volume":null,"pages":null},"PeriodicalIF":0.0,"publicationDate":"1900-01-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"123956302","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. Nonaka, Tomotaro Muto, Takahiro T. Nakamura, H. Nishida
{"title":"Aerodynamic Characteristics of a Slender-Body Ejecting a Supersonic Jet","authors":"S. Nonaka, Tomotaro Muto, Takahiro T. Nakamura, H. Nishida","doi":"10.2322/tastj.20.59","DOIUrl":"https://doi.org/10.2322/tastj.20.59","url":null,"abstract":"","PeriodicalId":120185,"journal":{"name":"TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN","volume":null,"pages":null},"PeriodicalIF":0.0,"publicationDate":"1900-01-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"125031385","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. Fujino, Kanji Takahashi, Taichi Matsudo, Koji Tanaka
{"title":"Consideration of SPS Test Satellite Receiving Station Arrangement Using Reconstruction by Least Squares Method","authors":"Y. Fujino, Kanji Takahashi, Taichi Matsudo, Koji Tanaka","doi":"10.2322/tastj.19.753","DOIUrl":"https://doi.org/10.2322/tastj.19.753","url":null,"abstract":"","PeriodicalId":120185,"journal":{"name":"TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN","volume":null,"pages":null},"PeriodicalIF":0.0,"publicationDate":"1900-01-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"129390944","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}
Numerical simulation of aerodynamics around the spaceplane was conducted in the equivalent condition to the transonic wind tunnel tests at ISAS/JAXA. Numerical results reproduced experimental results, and they are useful to discuss the experimental results. Two configurations, namely, the experimental model and the original model were investigated. In all Mach numbers, drag coefficient of the experimental model was larger t han that of the original model. Especially the wing and the tail made large drag. The different cross section of the wing and the tail caused the larger drag in the experimental model.
{"title":"Preliminary Numerical Simulation of Flow around Spaceplane for Airframe Engine Integration","authors":"S. Hasegawa, T. Kanda","doi":"10.2322/TASTJ.17.301","DOIUrl":"https://doi.org/10.2322/TASTJ.17.301","url":null,"abstract":"Numerical simulation of aerodynamics around the spaceplane was conducted in the equivalent condition to the transonic wind tunnel tests at ISAS/JAXA. Numerical results reproduced experimental results, and they are useful to discuss the experimental results. Two configurations, namely, the experimental model and the original model were investigated. In all Mach numbers, drag coefficient of the experimental model was larger t han that of the original model. Especially the wing and the tail made large drag. The different cross section of the wing and the tail caused the larger drag in the experimental model.","PeriodicalId":120185,"journal":{"name":"TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN","volume":null,"pages":null},"PeriodicalIF":0.0,"publicationDate":"1900-01-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"132410707","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}
Kohei Kojima, Shigeru Yokota, J. Yamasaki, Moyuru Yonaha, Tatsuya Kimura, Yoshihiro Kawamata, M. Yasui
In recent years, high power electric propulsion systems in the range of several tens to 100 kW are under development for the cargo of the manned missions or the satellite market. The thrusters for these propulsion systems require around 100 A of the discharge current. For these applications, we have been developing a 100 A class hollow cathode. To appropriate the electron emission processes of the LaB6 insert in a 100 A class Hollow Cathode, the characteristics and the diagnostics by single Langmuir probing were investigated. In this paper we report the results and the guidelines for the next step in a 100 A class heaterless hollow cathode.
{"title":"Plasma Diagnostics in High Current Hollow Cathode","authors":"Kohei Kojima, Shigeru Yokota, J. Yamasaki, Moyuru Yonaha, Tatsuya Kimura, Yoshihiro Kawamata, M. Yasui","doi":"10.2322/TASTJ.17.90","DOIUrl":"https://doi.org/10.2322/TASTJ.17.90","url":null,"abstract":"In recent years, high power electric propulsion systems in the range of several tens to 100 kW are under development for the cargo of the manned missions or the satellite market. The thrusters for these propulsion systems require around 100 A of the discharge current. For these applications, we have been developing a 100 A class hollow cathode. To appropriate the electron emission processes of the LaB6 insert in a 100 A class Hollow Cathode, the characteristics and the diagnostics by single Langmuir probing were investigated. In this paper we report the results and the guidelines for the next step in a 100 A class heaterless hollow cathode.","PeriodicalId":120185,"journal":{"name":"TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN","volume":null,"pages":null},"PeriodicalIF":0.0,"publicationDate":"1900-01-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"131980288","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 feasibility study was conducted to investigate the potential performance advantages of Supersonic Retro-Propulsion in support of future high-mass Mars robotic landing missions. A notional reference architecture for a potential future Mars Sample Return formed the basis for assuming a 4.7 m diameter SRP entry vehicle containing the Mars Ascent Vehicle element. Configuration analysis was conducted to ensure that the payload and required SRP components (including engines and propellant) fit within in the capsule volume. Optimized trajectory analysis highlighted several key performance sensitivities of SRP for ballistic coefficients of 150, 300, and 450 kg/m 2 . These results indicated a broad SRP ignition envelope (1-4 km altitude, 300-750 m/s velocity), as well as relatively small propellant mass fraction sensitivities to SRP thrust/weight, landing site elevation, and the application of a 4-g entry deceleration constraint (relevant for future crewed mission trajectories). Finally, mass-sizing was performed to assess sensitivities to ballistic coefficient and entry velocity, and showcased the ability of the SRP system to land payload masses on the order of twice that of MSL.
{"title":"Supersonic Retro-Propulsion for Future High-Mass Robotic Mars Lander Missions","authors":"M. Lobbia, A. Wolf, C. Whetsel","doi":"10.2322/TASTJ.17.19","DOIUrl":"https://doi.org/10.2322/TASTJ.17.19","url":null,"abstract":"A feasibility study was conducted to investigate the potential performance advantages of Supersonic Retro-Propulsion in support of future high-mass Mars robotic landing missions. A notional reference architecture for a potential future Mars Sample Return formed the basis for assuming a 4.7 m diameter SRP entry vehicle containing the Mars Ascent Vehicle element. Configuration analysis was conducted to ensure that the payload and required SRP components (including engines and propellant) fit within in the capsule volume. Optimized trajectory analysis highlighted several key performance sensitivities of SRP for ballistic coefficients of 150, 300, and 450 kg/m 2 . These results indicated a broad SRP ignition envelope (1-4 km altitude, 300-750 m/s velocity), as well as relatively small propellant mass fraction sensitivities to SRP thrust/weight, landing site elevation, and the application of a 4-g entry deceleration constraint (relevant for future crewed mission trajectories). Finally, mass-sizing was performed to assess sensitivities to ballistic coefficient and entry velocity, and showcased the ability of the SRP system to land payload masses on the order of twice that of MSL.","PeriodicalId":120185,"journal":{"name":"TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN","volume":null,"pages":null},"PeriodicalIF":0.0,"publicationDate":"1900-01-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"125515714","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. Nunome, S. Ozaki, Youhei Kino, S. Tomioka, T. Tomita
Flow visualization within rocket combustion chambers remains to be a challenge, especially under high pressure and high heat flux. In the present study, glass tubes chamber was proposed to observe the flame in conditions equivalent to those in past test with occurrence of combustion instability. No cooling gas injection was adopted to reproduce the test conditions. Inner / outer glass tube configuration was adopted to separate thermal load and mechanical (pressure) load. This non-cooling configuration survived for more than 5 seconds under chamber pressure of 7.5 MPa. Design and test procedure are herein described.
{"title":"Flame Visualization within a Rocket Combustion Chamber without Film Cooling System","authors":"Y. Nunome, S. Ozaki, Youhei Kino, S. Tomioka, T. Tomita","doi":"10.2322/TASTJ.17.7","DOIUrl":"https://doi.org/10.2322/TASTJ.17.7","url":null,"abstract":"Flow visualization within rocket combustion chambers remains to be a challenge, especially under high pressure and high heat flux. In the present study, glass tubes chamber was proposed to observe the flame in conditions equivalent to those in past test with occurrence of combustion instability. No cooling gas injection was adopted to reproduce the test conditions. Inner / outer glass tube configuration was adopted to separate thermal load and mechanical (pressure) load. This non-cooling configuration survived for more than 5 seconds under chamber pressure of 7.5 MPa. Design and test procedure are herein described.","PeriodicalId":120185,"journal":{"name":"TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN","volume":null,"pages":null},"PeriodicalIF":0.0,"publicationDate":"1900-01-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"125531845","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":"Propellantless Close-Range Guidance for Small Satellite Docking Using Simple Electromagnetic Devices","authors":"Yuki Yamada, T. Inamori","doi":"10.2322/tastj.19.500","DOIUrl":"https://doi.org/10.2322/tastj.19.500","url":null,"abstract":"","PeriodicalId":120185,"journal":{"name":"TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN","volume":null,"pages":null},"PeriodicalIF":0.0,"publicationDate":"1900-01-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"126519774","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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