{"title":"Feasibility Analysis of Time-Based Metering Using Cruise-Speed Control and Flight-Level Change for Domestic Flights in Japan","authors":"Yoshinori Matsuno, Adriana Andreeva-Mori","doi":"10.2322/tjsass.65.139","DOIUrl":"https://doi.org/10.2322/tjsass.65.139","url":null,"abstract":"","PeriodicalId":54419,"journal":{"name":"Transactions of the Japan Society for Aeronautical and Space Sciences","volume":null,"pages":null},"PeriodicalIF":1.1,"publicationDate":"2022-01-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"68664307","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":4,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
{"title":"Abstracts of the Papers Published in Journal of the Japan Society for Aeronautical and Space Sciences (Vol. 70, No. 4, Aug. 2022)","authors":"","doi":"10.2322/tjsass.65.230","DOIUrl":"https://doi.org/10.2322/tjsass.65.230","url":null,"abstract":"","PeriodicalId":54419,"journal":{"name":"Transactions of the Japan Society for Aeronautical and Space Sciences","volume":null,"pages":null},"PeriodicalIF":1.1,"publicationDate":"2022-01-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"68664764","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":4,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
H. Tokutake, Soshi Okada, S. Sunada, Y. Tanabe, K. Yonezawa
Drone dynamics are a ff ected by fl ight condition uncertainties, such as the surrounding structure, gust disturbance, and rotor damage, resulting in the deterioration of fl ight performance and safety. Real-time modeling of drone dynamics plays an important role in fl ight safety. In this study, the on-board measurement of downwash speed, which is an important parameter in drone dynamics, was performed using ultrasonic passing-time information. In this method, ultrasonic transmitters and receivers were arranged below the rotor, and the passing time in the downwash was estimated using an extended Kalman fi lter, which was designed for the constructed ultrasonic propagation dynamics model. It was validated that the proposed method is su ffi ciently robust to accurately estimate the downwash speed in a disturbed fl ow under a rotating rotor.
{"title":"On-board Downwash Speed Estimation of Drone Rotor-Based State Observer","authors":"H. Tokutake, Soshi Okada, S. Sunada, Y. Tanabe, K. Yonezawa","doi":"10.2322/tjsass.65.231","DOIUrl":"https://doi.org/10.2322/tjsass.65.231","url":null,"abstract":"Drone dynamics are a ff ected by fl ight condition uncertainties, such as the surrounding structure, gust disturbance, and rotor damage, resulting in the deterioration of fl ight performance and safety. Real-time modeling of drone dynamics plays an important role in fl ight safety. In this study, the on-board measurement of downwash speed, which is an important parameter in drone dynamics, was performed using ultrasonic passing-time information. In this method, ultrasonic transmitters and receivers were arranged below the rotor, and the passing time in the downwash was estimated using an extended Kalman fi lter, which was designed for the constructed ultrasonic propagation dynamics model. It was validated that the proposed method is su ffi ciently robust to accurately estimate the downwash speed in a disturbed fl ow under a rotating rotor.","PeriodicalId":54419,"journal":{"name":"Transactions of the Japan Society for Aeronautical and Space Sciences","volume":null,"pages":null},"PeriodicalIF":1.1,"publicationDate":"2022-01-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"68664790","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":4,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Earth remote sensing from geostationary orbit (GEO) can realize high temporal resolution; however, the spatial resolution is commonly worse than observation from low Earth orbit. In order to achieve high-frequency and high-resolution GEO remote sensing, a “Formation Flying Synthetic Aperture Telescope (FFSAT)”with multiple micro-satellites has been proposed. The FFSAT greatly improves the spatial resolution using a synthetic aperture technique. Therefore the relative positions and attitudes between the optical units of each satellite must be controlled with an accuracy better than 1/10 of the observation wavelength. However, even mm-class accuracy control has not been demonstrated on orbit. As a first practical application of the FFSAT, a forest fire monitoring mission using infrared rays is being considered, in which control accuracy requirement is relaxed as its wavelength is longer than visible light. We proposed a point spread function optimization method for controlling formation flying with an accuracy of approximately 1–1,000 times the wavelength (1 μm–1mm) in the absence of sensors, which can measure absolute distance with μm-accuracy. The effectiveness of the method was demonstrated through simulations in which the satellites’ system and the optical system are coupled. The simulation results show that the method can control the formation within the wavelength order.
{"title":"µm-class Control of Relative Position and Attitude for a Formation Flying Synthetic Aperture Telescope with Micro-satellites","authors":"Ryo Suzumoto, S. Ikari, N. Miyamura, S. Nakasuka","doi":"10.2322/TJSASS.64.101","DOIUrl":"https://doi.org/10.2322/TJSASS.64.101","url":null,"abstract":"Earth remote sensing from geostationary orbit (GEO) can realize high temporal resolution; however, the spatial resolution is commonly worse than observation from low Earth orbit. In order to achieve high-frequency and high-resolution GEO remote sensing, a “Formation Flying Synthetic Aperture Telescope (FFSAT)”with multiple micro-satellites has been proposed. The FFSAT greatly improves the spatial resolution using a synthetic aperture technique. Therefore the relative positions and attitudes between the optical units of each satellite must be controlled with an accuracy better than 1/10 of the observation wavelength. However, even mm-class accuracy control has not been demonstrated on orbit. As a first practical application of the FFSAT, a forest fire monitoring mission using infrared rays is being considered, in which control accuracy requirement is relaxed as its wavelength is longer than visible light. We proposed a point spread function optimization method for controlling formation flying with an accuracy of approximately 1–1,000 times the wavelength (1 μm–1mm) in the absence of sensors, which can measure absolute distance with μm-accuracy. The effectiveness of the method was demonstrated through simulations in which the satellites’ system and the optical system are coupled. The simulation results show that the method can control the formation within the wavelength order.","PeriodicalId":54419,"journal":{"name":"Transactions of the Japan Society for Aeronautical and Space Sciences","volume":null,"pages":null},"PeriodicalIF":1.1,"publicationDate":"2021-01-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"68662531","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":4,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
F. Cheng, Jing-zhou Zhang, Jingyang Zhang, Yuyan Zhang
1)College of Mechanical and Electronic Engineering, Nanjing Forestry University, Nanjing 210037, China 2)AVIC Nanjing Engineering Institute of Aircraft Systems, Nanjing 211106, China 3)Jiangsu Province Key Laboratory of Aerospace Power System, College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China 4)Aviation Key Laboratory of Science and Technology on Aero Electromechanical System Integration, Nanjing 211106, China 5)College of Astronautics, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China
{"title":"Effect of Cutbacks on Tip Leakage Flow and Film-Cooling Effectiveness of a Turbine Blade Tip under Relative Moving Condition","authors":"F. Cheng, Jing-zhou Zhang, Jingyang Zhang, Yuyan Zhang","doi":"10.2322/tjsass.64.293","DOIUrl":"https://doi.org/10.2322/tjsass.64.293","url":null,"abstract":"1)College of Mechanical and Electronic Engineering, Nanjing Forestry University, Nanjing 210037, China 2)AVIC Nanjing Engineering Institute of Aircraft Systems, Nanjing 211106, China 3)Jiangsu Province Key Laboratory of Aerospace Power System, College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China 4)Aviation Key Laboratory of Science and Technology on Aero Electromechanical System Integration, Nanjing 211106, China 5)College of Astronautics, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China","PeriodicalId":54419,"journal":{"name":"Transactions of the Japan Society for Aeronautical and Space Sciences","volume":null,"pages":null},"PeriodicalIF":1.1,"publicationDate":"2021-01-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"68663419","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":4,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
This paper presents a method to obtain a robust optimal path in an environment with time-varying safety features, such as in the lunar polar region. In designing the path for planetary exploration rovers, we must consider various safety conditions, such as terrain hazards, illumination, and communication visibility to the Earth. Some of the safety features are time-varying, and the optimal path should be searched for both the spatial direction and the temporal direction. In addition, there is no guarantee that all of the sequences will be successfully executed on time due to misoperation, failures, or trou-ble. Therefore, a path that is robust against the delay must be planned so as to guarantee safety even when behind schedule. The authors propose an algorithm called “ Robust Spatio-Temporal Path Planner for the Planetary Rover (R OBUST -STP3R) ” to obtain a path that is robust against schedule delay in a time-varying environment. This method de fi nes a cost function that consists of the distance as well as the region type cost. To add robustness against schedule delays, the authors consider a weighted summation of the time-varying region type cost with regard to the temporal direction. The e ff ectiveness of the proposed method is demonstrated through use in a simulated lunar polar exploration exercise.
{"title":"Spatio-Temporal Path Planning for Lunar Polar Exploration with Robustness against Schedule Delay","authors":"H. Inoue, S. Adachi","doi":"10.2322/tjsass.64.304","DOIUrl":"https://doi.org/10.2322/tjsass.64.304","url":null,"abstract":"This paper presents a method to obtain a robust optimal path in an environment with time-varying safety features, such as in the lunar polar region. In designing the path for planetary exploration rovers, we must consider various safety conditions, such as terrain hazards, illumination, and communication visibility to the Earth. Some of the safety features are time-varying, and the optimal path should be searched for both the spatial direction and the temporal direction. In addition, there is no guarantee that all of the sequences will be successfully executed on time due to misoperation, failures, or trou-ble. Therefore, a path that is robust against the delay must be planned so as to guarantee safety even when behind schedule. The authors propose an algorithm called “ Robust Spatio-Temporal Path Planner for the Planetary Rover (R OBUST -STP3R) ” to obtain a path that is robust against schedule delay in a time-varying environment. This method de fi nes a cost function that consists of the distance as well as the region type cost. To add robustness against schedule delays, the authors consider a weighted summation of the time-varying region type cost with regard to the temporal direction. The e ff ectiveness of the proposed method is demonstrated through use in a simulated lunar polar exploration exercise.","PeriodicalId":54419,"journal":{"name":"Transactions of the Japan Society for Aeronautical and Space Sciences","volume":null,"pages":null},"PeriodicalIF":1.1,"publicationDate":"2021-01-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"68663503","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":4,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
This paper conducts a safety assessment for reduced route spacing for RNP 2 aircraft under a radar environment. Although the criteria for 15 NM separation standards exist, past safety assessment did not consider the surveillance environment. This consideration may reduce the possible route spacing. Here, to account for the surveillance environment, the recently developed ASEPS model is applied. Since this model was intended for deployment on oceanic route systems, the model parameters are modified appropriately while keeping the consistency of the past safety analysis and data analysis. In particular, the parameter of occupancy is set based on one-year flight data in Japanese airspace, and the calculation of action time to resolve the conflict is modified to estimate the collision probability more accurately. The results show that 8 NM route spacing satisfies the safety criteria.
{"title":"Safety Analysis of Reduced Route Spacing for RNP 2 under Radar Environment","authors":"Ryota Mori","doi":"10.2322/TJSASS.64.165","DOIUrl":"https://doi.org/10.2322/TJSASS.64.165","url":null,"abstract":"This paper conducts a safety assessment for reduced route spacing for RNP 2 aircraft under a radar environment. Although the criteria for 15 NM separation standards exist, past safety assessment did not consider the surveillance environment. This consideration may reduce the possible route spacing. Here, to account for the surveillance environment, the recently developed ASEPS model is applied. Since this model was intended for deployment on oceanic route systems, the model parameters are modified appropriately while keeping the consistency of the past safety analysis and data analysis. In particular, the parameter of occupancy is set based on one-year flight data in Japanese airspace, and the calculation of action time to resolve the conflict is modified to estimate the collision probability more accurately. The results show that 8 NM route spacing satisfies the safety criteria.","PeriodicalId":54419,"journal":{"name":"Transactions of the Japan Society for Aeronautical and Space Sciences","volume":null,"pages":null},"PeriodicalIF":1.1,"publicationDate":"2021-01-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"68662273","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":4,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Qiang Zhang, Fumiya Takahashi, Kotaro Sato, W. Tsuru, K. Yokota
We propose a tangential blowing cylinder, a type of circulation control wing, to control the direction of a jet replacing a blade or a cascade. Flow characteristics including de fl ection are experimentally investigated. Speci fi cally, visualization observations, velocity distribution measurements, and the e ff ects of momentum ratio, injection angle, and location of the cylinder on the de fl ection angle of the jet are analyzed. The stalling at an angle-of-attack above 20° with a single blade impedes direction control for such large angles. However, the jet may be bent to approximately 90° by using the proposed tangential blowing cylinder. The optimal injection angle for controlling the jet direction and the unsteady characteristics downstream of the tangential blowing cylinder are also determined.
{"title":"Jet Direction Control Using Circular Cylinder with Tangential Blowing","authors":"Qiang Zhang, Fumiya Takahashi, Kotaro Sato, W. Tsuru, K. Yokota","doi":"10.2322/TJSASS.64.181","DOIUrl":"https://doi.org/10.2322/TJSASS.64.181","url":null,"abstract":"We propose a tangential blowing cylinder, a type of circulation control wing, to control the direction of a jet replacing a blade or a cascade. Flow characteristics including de fl ection are experimentally investigated. Speci fi cally, visualization observations, velocity distribution measurements, and the e ff ects of momentum ratio, injection angle, and location of the cylinder on the de fl ection angle of the jet are analyzed. The stalling at an angle-of-attack above 20° with a single blade impedes direction control for such large angles. However, the jet may be bent to approximately 90° by using the proposed tangential blowing cylinder. The optimal injection angle for controlling the jet direction and the unsteady characteristics downstream of the tangential blowing cylinder are also determined.","PeriodicalId":54419,"journal":{"name":"Transactions of the Japan Society for Aeronautical and Space Sciences","volume":null,"pages":null},"PeriodicalIF":1.1,"publicationDate":"2021-01-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"68662761","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":4,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Masatoshi Chono, N. Yamamoto, R. Tsukizaki, Takato Morishita, K. Kubota, Shinatra Cho, K. Kinefuchi, Toru Takahashi
1)Department of Advanced Energy Engineering Science, Kyushu University, Kasuga, Fukuoka 816–8580, Japan 2)Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency, Sagamihara, Kanagawa 252–5210, Japan 3)Department of Aeronautics and Astronautics, The University of Tokyo, Tokyo 113–8656, Japan 4)Japan Aerospace Exploration Agency, Chofu, Tokyo 182–8522, Japan 5)Japan Aerospace Exploration Agency, Sagamihara, Kanagawa 252–5210, Japan 6)Department of Aerospace Engineering, Nagoya University, Nagoya, Aichi 464–8603, Japan 7)Takahashi Denki Seisakusyo, Iwaki, Fukushima 972–8326, Japan
{"title":"Performance of a Miniature Hall Thruster and an In-house PPU","authors":"Masatoshi Chono, N. Yamamoto, R. Tsukizaki, Takato Morishita, K. Kubota, Shinatra Cho, K. Kinefuchi, Toru Takahashi","doi":"10.2322/TJSASS.64.189","DOIUrl":"https://doi.org/10.2322/TJSASS.64.189","url":null,"abstract":"1)Department of Advanced Energy Engineering Science, Kyushu University, Kasuga, Fukuoka 816–8580, Japan 2)Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency, Sagamihara, Kanagawa 252–5210, Japan 3)Department of Aeronautics and Astronautics, The University of Tokyo, Tokyo 113–8656, Japan 4)Japan Aerospace Exploration Agency, Chofu, Tokyo 182–8522, Japan 5)Japan Aerospace Exploration Agency, Sagamihara, Kanagawa 252–5210, Japan 6)Department of Aerospace Engineering, Nagoya University, Nagoya, Aichi 464–8603, Japan 7)Takahashi Denki Seisakusyo, Iwaki, Fukushima 972–8326, Japan","PeriodicalId":54419,"journal":{"name":"Transactions of the Japan Society for Aeronautical and Space Sciences","volume":null,"pages":null},"PeriodicalIF":1.1,"publicationDate":"2021-01-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"68662819","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":4,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
M. Matsui, R. Kobayashi, Takashi Okamoto, Kazuhiko Yamada, H. Tanno
An expansion tube is a promising facility to simulate atmospheric entry conditions, although its fl ow conditions have not been completely characterized mainly owing to its short operation time. In this study, laser absorption spectroscopy was applied to diagnose HEK-X expansion tube fl ow in the Kakuda Space Center. The target is an absorption line of an oxygen molecule at 763nm. To increase the sensitivity, optical path length was extended by fi ve times using mirrors. Con-sequently, an absorption pro fi le with a fractional absorption of 2.4 « 0.3% was detected at a shock velocity of 7.65 « 0.05km / s. The estimated translational temperature from the Voigt fi tting was 2750 « 450K.
{"title":"Temperature Measurement of HEK-X Expansion Tube Flow by Laser Absorption Spectroscopy","authors":"M. Matsui, R. Kobayashi, Takashi Okamoto, Kazuhiko Yamada, H. Tanno","doi":"10.2322/TJSASS.64.193","DOIUrl":"https://doi.org/10.2322/TJSASS.64.193","url":null,"abstract":"An expansion tube is a promising facility to simulate atmospheric entry conditions, although its fl ow conditions have not been completely characterized mainly owing to its short operation time. In this study, laser absorption spectroscopy was applied to diagnose HEK-X expansion tube fl ow in the Kakuda Space Center. The target is an absorption line of an oxygen molecule at 763nm. To increase the sensitivity, optical path length was extended by fi ve times using mirrors. Con-sequently, an absorption pro fi le with a fractional absorption of 2.4 « 0.3% was detected at a shock velocity of 7.65 « 0.05km / s. The estimated translational temperature from the Voigt fi tting was 2750 « 450K.","PeriodicalId":54419,"journal":{"name":"Transactions of the Japan Society for Aeronautical and Space Sciences","volume":null,"pages":null},"PeriodicalIF":1.1,"publicationDate":"2021-01-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"68662875","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":4,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
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