著者

Takumi OYAMA Keiji HAGIWARA Hideyuki HORISAWA Kota FUKUDA

出版者

THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES

雑誌

TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN (ISSN:18840485)

巻号頁・発行日

vol.12, no.ists29, pp.Pb_85-Pb_90, 2014 (Released:2014-12-26)

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This paper proposes direct focusing of repetitive high-power laser pulses on an arbitrary surface of a vehicle in the atmosphere to generate a blast wave at each pulse and push the vehicle along an impulse or thrust vector. Fundamental research was conducted on the interaction between a focused high-power laser pulse or blast wave and a surface with arbitrary curvatures. The characteristics of the impulse or thrust vector generation on the surface were numerically simulated. For simplicity, some fundamental shapes of the surface or vehicle were assumed for the simulation (i.e., planar and semicircular bodies) to examine shock–surface interactions. The impulse vector characteristics were also investigated experimentally. The results showed that the composition of the impulse vector (or each component) reached about 90% of the total impulse in the initial 10 μs. In this duration, a significant high-pressure region induced by the shockwave was localized near the laser irradiation spot; it acted on the surface vectors to induce a primary thrust. Based on these results, the directions of impulse vectors are primarily determined by the local surface vectors of the laser irradiation spots.

著者

Kent L. GEE Eric B. WHITING Tracianne B. NEILSEN Michael M. JAMES Alexandria R. SALTON

出版者

THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES

雑誌

TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN (ISSN:18840485)

巻号頁・発行日

vol.14, no.ists30, pp.Po_2_9-Po_2_15, 2016 (Released:2016-07-27)

被引用文献数

5 5

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Near-field characterization of the acoustical environment near rockets has often involved extrapolating far-field measurements. However, because far-field amplitude data reveals only limited information about source characteristics, a vector intensity measurement system and analysis package has been developed to examine source features more directly. This paper describes the development of the measurement and analysis capability and its application to a horizontal firing of a GEM-60 solid propellant rocket motor firing conducted at ATK Space Systems near Promontory, Utah. An analysis of near-field intensity data provides insight both into the spatial extent and principal radiation lobe as a function of frequency. For 50 Hz, the far-field spectral peak frequency in the maximum radiation direction, the dominant source region derived from tracing the near-field intensity vectors spans 17-32 nozzle diameters, with peak radiation at ~68°. At high frequencies, the radiation results from a more contracted region that occurs farther upstream and is directed at about ~85°. These results point to the potential utility of near-field vector intensity measurements, in part because the near-field environments represented do not agree with historical far-field data-based models.

著者

Takashi ZAITSU Toshiko OHTA Hiroshi OHSHIMA Chiaki MUKAI

出版者

THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES

雑誌

TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN (ISSN:18840485)

巻号頁・発行日

vol.12, no.ists29, pp.Tp_7-Tp_9, 2014 (Released:2014-11-27)

被引用文献数

1 1

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Occurrences of dental/oral diseases have been reported in the space environment and pre- or post-spaceflight and the deteriorations of oral defensive functions are evident in the space environment simulated experiments. NASA has identified 6 dental problems (Abscess, Avulsion/Tooth Loss, Caries, Crown Replacement, Exposed Pulp/Pulpitis and Filling Replacement) as the most important dental incidents to be dealt with in the long-term mission. To focus on the dental/oral health management for astronauts, dental examination and dental orthopantomogram are conducted as dental diagnosis. In addition, dental nerve block, dental prosthesis replacement and dental pain control are described in the treatment manual on the International Space Station (ISS). However, the systematic program to evaluate the risk of dental/oral problems in spacecraft and the manual to prevent the dental/oral problems in the space environment are still far from sufficient. To promote the dental/oral health of astronauts, the authors are going to launch “Space Oral Health Promotion (SOHP) project” which will tackle the research tasks and the operational countermeasures in space dentistry.

著者

Sho SASAKI Masaki FUJIMOTO Hajime YANO Takeshi TAKASHIMA Yasumasa KASABA Yukihiro TAKAHASHI Jun KIMURA Yuichi TSUDA Ryu FUNASE Osamu MORI Stefano CAMPAGNOLA Yasuhiro KAWAKATSU

出版者

THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES

雑誌

TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN (ISSN:18840485)

巻号頁・発行日

vol.10, no.ists28, pp.Tk_37-Tk_40, 2012 (Released:2013-06-07)

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EJSM (Europa Jupiter System Mission) is an international Jovian system mission with three spacecraft. Coordinated observation of Jovian magnetosphere is one of the important targets of the mission in addition to icy satellites, atmosphere, and the interior of Jupiter. JAXA will take a role on the magnetosphere spinner JMO (Jupiter Magnetospheric Orbiter), whereas ESA will launch JGO (Jupiter Ganymede Orbiter) and NASA will be responsible for JEO (Jupiter Europa Orbiter). One possibility is to combine JMO with a proposed solar sail mission of JAXA for Jupiter and one of Trojan asteroids. Since Trojan asteroids could be representing raw solid materials of Jupiter or at least outer solar system bodies,involvement of Trojan observation should enlarge the scope and enhance the quality of EJSM.

著者

Kazuya IWATA Shinji NAKAYA Mitsuhiro TSUE

出版者

THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES

雑誌

TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN (ISSN:18840485)

巻号頁・発行日

vol.14, no.ists30, pp.Pa_31-Pa_38, 2016 (Released:2016-11-26)

被引用文献数

1 2

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Oblique detonation under incompletely premixed conditions has not been well understood and is of great concern when difficulty of high-speed premixing in Oblique Detonation Wave Engine (ODWE), which is one of the most potential hypersonic aerospace propulsion systems, is taken into account. This study numerically investigated effects of fuel concentration gradients on oblique detonation and shock-induced combustion formed on a 28.20° wedge by solving two-dimensional Navier-Stokes equations with a detailed chemical kinetic mechanism of hydrogen-air combustion. Oblique detonation with smooth-transition formed at a Mach number of 8.00, a static temperature of 300 K, and a static pressure of 8.50 kPa was referred as the completely premixed case. Fuel concentration gradients were described by the Gaussian function. At the maximum equivalence ratio of 2.00, Smooth-transition was replaced by abrupt-transition. When maximum equivalence ratio exceeded 3.00, a V-shaped flame front appeared with its leading edge located away from the wedge, which caused two separate triple-points to be observed. Second triple point appeared at the intersection of the incident shock or the detonation front and a reflected shock generated by compression waves on the lower side of the deflagration front. Increase of the front angle enabled intensive combustion to be maintained downstream of it.

著者

Ryo SUZUMOTO Satoshi IKARI Norihide MIYAMURA Shinichi NAKASUKA

出版者

THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES

雑誌

TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES (ISSN:05493811)

巻号頁・発行日

vol.64, no.2, pp.101-111, 2021 (Released:2021-03-04)

参考文献数

17

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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–1 mm) 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.

著者

Tomohiro YAMAGUCHI Makoto YOSHIKAWA

出版者

THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES

雑誌

TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, SPACE TECHNOLOGY JAPAN (ISSN:13473840)

巻号頁・発行日

vol.7, no.ists26, pp.Pk_11-Pk_15, 2009 (Released:2010-05-08)

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In this paper, the estimation method of impact probability for Near-Earth Objects (NEOs) is investigated. The impact probability of NEOs has been calculated by a linear target plane analysis and a Monte-Carlo method. Since the collisions of NEOs with the Earth are quite sensitive problems, the calculations have to be confirmed by everal methods. A linear target plane analysis cannot be applied if the position uncertainty is too large since the uncertainty ellipsoid is not a good assumption in this case. A Monte-Carlo method can be used for a large position uncertainty, but the computational cost is high. The limitation of using a linear target plane analysis is investigated using the Monte-Carlo method for the close approach of 99942 Apophis (2004 MN4). The relation between impact probability and observation accuracy is investigated by analyzing the close approach of 2007WD5.

著者

寺川 徹

出版者

THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES

雑誌

日本航空学会誌 (ISSN:18835422)

巻号頁・発行日

vol.13, no.136, pp.163-164, 1965

著者

Akira IWAKAWA Tatsuro SHODA Ryosuke MAJIMA Son Hoang PHAM Akihiro SASOH

出版者

THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES

雑誌

TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES (ISSN:05493811)

巻号頁・発行日

vol.60, no.5, pp.303-311, 2017 (Released:2017-09-04)

参考文献数

32

被引用文献数

13

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Supersonic drag reduction performance using repetitive pulse energy depositions over blunt bodies was experimentally studied under two Mach numbers. The normalized drag reduction and energy deposition efficiency of Mach-1.92 over a 10-mm-dia. blunt-cylinder model were 8% and 1.2 at most, respectively. On the other hand, these values at Mach-3.20 over the same model were 22% and 6.2, respectively. The shock-wave deformation period using single-pulse energy deposition at Mach-3.20 was 64 μs. This duration was shorter than that of 80 μs at Mach-1.92, but the deformation magnitude on the model center axis of 40% at Mach-3.20 was larger than that of 15% at Mach-1.92. These experimental characteristics were consistent as solutions of the Riemann problem. Moreover, a drag reduction performance was much improved with a larger model diameter of 20 mm. Therefore, it has been experimentally demonstrated that the drag reduction performance due to energy deposition improves much at a high Mach number and with large model dimensions.

著者

佐藤 博

出版者

THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES

雑誌

日本航空学会誌 (ISSN:18835422)

巻号頁・発行日

vol.9, no.89, pp.184-190, 1961

著者

落合 一夫

出版者

THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES

雑誌

日本航空学会誌 (ISSN:18835422)

巻号頁・発行日

vol.9, no.89, pp.201-202, 1961

著者

KITAGAWA Yosuke KITAGAWA Koki NAKAMIYA Masaki KANAZAKI Masahiro SHIMADA Toru

出版者

THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES

雑誌

Transactions of the Japan Society for Aeronautical and Space Sciences (ISSN:05493811)

巻号頁・発行日

vol.55, no.4, pp.229-236, 2012-07-04

被引用文献数

1 13

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The multi-objective genetic algorithm (MOGA) is applied to the multi-disciplinary conceptual design problem for a three-stage launch vehicle (LV) with a hybrid rocket engine (HRE). MOGA is an optimization tool used for multi-objective problems. The parallel coordinate plot (PCP), which is a data mining method, is employed in the post-process in MOGA for design knowledge discovery. A rocket that can deliver observing micro-satellites to the sun-synchronous orbit (SSO) is designed. It consists of an oxidizer tank containing liquid oxidizer, a combustion chamber containing solid fuel, a pressurizing tank and a nozzle. The objective functions considered in this study are to minimize the total mass of the rocket and to maximize the ratio of the payload mass to the total mass. To calculate the thrust and the engine size, the regression rate is estimated based on an empirical model for a paraffin (FT-0070) propellant. Several non-dominated solutions are obtained using MOGA, and design knowledge is discovered for the present hybrid rocket design problem using a PCP analysis. As a result, substantial knowledge on the design of an LV with an HRE is obtained for use in space transportation.

著者

能見 公博 大井 克己 詫間 哲 苧側 正明

出版者

THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES

雑誌

航空宇宙技術 (ISSN:18840477)

巻号頁・発行日

vol.9, pp.37-42, 2010

被引用文献数

1 1

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This paper describes solar paddle antenna proposed in the development of Kagawa Satellite "KUKAI." KUKAI is a mother-daughter pico-satellite for technical verification of a tethered space robot. The mother and the daughter satellites communicate respectively with the ground station by amateur radio frequencies. For the purpose of simple deployment system on orbit and antenna directivity suitable for KUKAI, solar paddle antenna mounted at the edge of a solar paddle is employed. After sufficient antenna adjustment on the ground, KUKAI was launched on 23 January 2009 by the H-IIA rocket from Tanegashima Space Center. The solar paddles were successfully deployed, and communication by the solar paddle antenna was successful.

出版者

THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES

雑誌

日本航空宇宙学会誌 (ISSN:00214663)

巻号頁・発行日

vol.19, no.210, pp.323-330, 1971 (Released:2009-05-25)

著者

Marco GOMEZ-JENKINS Julio CALVO-ALVARADO Adolfo CHAVES-JIMÉNEZ Johan CARVAJAL-GODÍNEZ Esteban MARTINEZ Yeiner ARIAS Ana Julieta CALVO-OBANDO Vladimir JIMENEZ Juan José ROJAS Alfredo VALVERDE-SALAZAR Julio RAMIREZ-MOLINA

出版者

THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES

雑誌

TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES (ISSN:05493811)

巻号頁・発行日

vol.66, no.6, pp.217-225, 2023 (Released:2023-11-04)

参考文献数

19

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Project Irazú was an innovative space mission that aimed to propel the advancement of the aerospace sector in Costa Rica, by developing a ground to space communication solution for daily monitoring of carbon fixation in forests and tree plantations. Irazú is Central America’s first satellite mission and is a joint endeavor between the Central American Association of Aeronautics and Space and the Costa Rica Institute of Technology, along with national and international partners. The 1U CubeSat developed in this project was deployed from the International Space Station on May 2018, commencing straightaway operations. The scientific mission demonstrated a practical novel solution to monitor daily tree growth by using wireless electronic sensors and a store and forward satellite link. This article presents an overview of the project, along with the mission architecture, summary of the Assembly, Integration and Testing (AI&T) and operations phases, and results from the scientific mission, including the sensor’s performance and measurements of the daily estimated tree diameter during six months. The impacts that the project had on an emerging space nation such as Costa Rica is included as well.

著者

Kojiro SUZUKI

出版者

THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES

雑誌

TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN (ISSN:18840485)

巻号頁・発行日

vol.16, no.5, pp.412-419, 2018 (Released:2018-07-04)

参考文献数

15

被引用文献数

1 1

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A Mars orbiter/lander mission using a micro-satellite (less than 100 kg at Mars arrival) with a deployable membrane aeroshell for the orbit insertion by the aerocapture and the electric propulsion for the trajectory maneuver was considered. The aerodynamic heating environment during the atmospheric flight was investigated solving the thermo-chemical nonequilibrium axi-symmetric Navier-Stokes equations around the spacecraft with the flare-shaped aeroshell. To obtain the appropriate amount of deceleration at the atmospheric pass, the drag modulation technique, in which the aeroshell is timely jettisoned from the spacecraft, was assumed. The hypersonic wind tunnel experiment successfully demonstrated that the backward jettison works well without significant time delay and attitude disturbance. Finally the corridor width for the entry path angle was estimated considering the ability of the orbit insertion, the peak aerodynamic heating, and the capability of the electric propulsion to raise the periapsis altitude. The combination of a low ballistic coefficient flight with the membrane aeroshell and an electric propulsion works well to acquire a finite width of the entry corridor for the aerocapture.

著者

Hiroshi SASAKI Takane IMADA Shinichi TAKATA

出版者

THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES

雑誌

TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, SPACE TECHNOLOGY JAPAN (ISSN:13473840)

巻号頁・発行日

vol.7, no.ists26, pp.Tk_77-Tk_82, 2009 (Released:2010-08-06)

被引用文献数

1

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The H-II Transfer Vehicle (HTV) is an unmanned transfer vehicle that will rendezvous with manned facilities and deliver up to six tons of cargo. HTV is a key space transportation system technology in Japan together with the H-IIA/H-IIB launch vehicle and is designed to fully satisfy the manned safety requirements of the International Space Station (ISS) program. Therefore, the technology and its system acquired through HTV development and operation will be widely utilized in future manned transportation and lunar and planetary exploration missions.

著者

Hironori SAHARA Satoshi HOSODA Yoshiki SUGAWARA Masakatsu NAKANO Shinichi NAKASUKA

出版者

THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES

雑誌

TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN (ISSN:18840485)

巻号頁・発行日

vol.8, no.ists27, pp.Tu_1-Tu_4, 2010 (Released:2011-06-14)

参考文献数

1

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This paper proposes to hold “Ig Satellite Design Contest,” in order to expand our space utilization by means of content-based satellites in the stream of recent microsatellite development. Going back to the history of the recent microsatellite, such a content-based satellite is positioned as the third-generation one. Ig Satellite Design Contest stands on the position of the two policies, that is, the satellite is chip in porridge for practical effect, but is to bring pleasure or happiness to people, or to stimulate access to the space and our future space activities.

著者

Hironori SAHARA Satoshi HOSODA Yoshiki SUGAWARA Masakatsu NAKANO Shinichi NAKASUKA

出版者

THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES

雑誌

TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN (ISSN:18840485)

巻号頁・発行日

vol.10, no.ists28, pp.Tf_1-Tf_4, 2012 (Released:2012-03-29)

参考文献数

1

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We organize Ig Satellite Design Contest to collect the NEEDS and to establishment of NEEDS database for microsatellite. It will be polestar for the satellite developers. This paper shows an example of NEEDS collection and derivation of the key technologies from the NEEDS, which should offer a strategic direction to the SEEDS, the satellite developers for example.

著者

Naoyuki NISHIO Shin-Ichiro NISHIDA Shintaro NAKATANI

出版者

THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES

雑誌

TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN (ISSN:18840485)

巻号頁・発行日

vol.19, no.4, pp.469-476, 2021 (Released:2021-07-04)

参考文献数

16

被引用文献数

1

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The rover for future Mars exploration will be expected to have higher rough terrain traveling performance compared with conventional rovers. In this paper, we propose a rover with a weight of about 30 kg that can be transported to Mars by a Japanese rocket. The purpose of this study is to propose and develop a hinge-type movable center-of-gravity mechanism wherein the bending of the rover's body with a motor shows high rough terrain-driving performance with minimum degrees of freedom. The proposed mechanism's performance is evaluated by conducting travel experiments on a assumed terrain, that is, a hard rock with a grade inclination of 45 deg and a height of 0.15 m above the sand. The effectiveness of the proposed mechanism in getting over a step was confirmed by conducting experiments using a prototype model.