著者

Kenjiro Kamijo Hitoshi Yamada Norio Sakazume Shogo WARASHINA

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.44, no.145, pp.155-163, 2001 (Released:2005-07-09)

参考文献数

9

被引用文献数

9 14

---

The first stage of the H-2 rocket used a 110-ton thrust liquid oxygen, liquid hydrogen, pump-fed engine, the LE-7. This engine required high-pressure and high-power liquid oxygen and liquid hydrogen turbopumps to achieve the two-stage combustion cycle in which the combustion pressure is around 13 MPa. Furthermore, it was very important to operate both turbopumps at higher rotational speeds to obtain a smaller, lighter-weight engine because the LE-7 had not low-speed, low-pressure pumps ahead of both the main pumps. The present paper shows the design, test results, and modifications that had been performed until a flight-type liquid oxygen turbopump for the LE-7 engine was completed. The liquid oxygen turbopump had been developed by the use of three models, that is, research, prototype, and flight models.

著者

Shin-ichiro SASAHARA Yuichi OI Shotaro DOKI Daisuke HORI Yuh OHTAKI Christina-Sylvia ANDREA Tsukasa TAKAHASHI Nagisa SHIRAKI Yu IKEDA Tomohiko IKEDA Ryutaro IZUMI Tamaki SAITO Ichiyo MATSUZAKI

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.18, no.5, pp.180-185, 2020 (Released:2020-09-04)

参考文献数

32

被引用文献数

1

---

Over the past few years, the number of Japanese astronauts recruited for a long-term stay in the International Space Station (ISS) has increased. Being on a prolonged mission with the same people, in the same room, should impose psychosocial stress on the astronauts, possibly causing feelings of “psychological suffocation”. Several confinement studies have been conducted to simulate the conditions of the ISS, the Mir space station, and potential habitats on Mars, and to survey psychological interpersonal communication between the crew in a confined environment, including the Isolation Study for European Manned Space Infrastructure, Experimental Campaign for the European Manned Space Infrastructure, Simulation of Flight of International Crew on Space Station, Human Behavior in Extended Spaceflight, Mars-500, and Hawaii Space Exploration Analog and Simulation. Here, the findings from these studies were integrated into a structured review according to an evidence-based set of items for reporting in systematic reviews and meta-analyses. The results indicated that metaanalyses would not always be appropriate because it is difficult to design a research protocol with a high level of evidence in this field. Therefore, future research in this field should be focused on the following three points: 1) developing more accurate parameters for monitoring stress levels in long-term confinement environments; 2) analyzing stress levels in such situations with higher precision; and 3) accumulating and assembling existing and future data from long-term confinement environments.

著者

Nobuyuki YATSUYANAGI

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.52, no.177, pp.180-187, 2009 (Released:2009-11-02)

参考文献数

11

被引用文献数

4 6

---

A comprehensive design method for a LOX/Liquid-Methane (L-CH4) rocket engine combustor with a coaxial injector and the preliminary design of the regenerative cooling combustor with 100-kN thrust in vacuum at a combustion pressure of a 3.43 MPa are presented. Reasonable dimensions for the combustor that satisfy the targeted C* efficiency of more than 98% and combustion stability are obtained.

著者

Qin XU Peter HOLLINGSWORTH Katharine SMITH

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.62, no.4, pp.175-183, 2019 (Released:2019-07-04)

参考文献数

24

被引用文献数

3

---

The rapid developments in micro-technologies and the introduction of modularity and standardization into system designs, present significant opportunities for cost reduction in the design and development of satellite systems. However, the high cost of space launch has become a major hindrance to capitalizing on these opportunities. Therefore, seeking appropriate launch opportunities and reducing launch costs might contribute to further growth of the space market. This paper focuses on the analysis of dedicated launch costs factoring in the effect of launch reliability, which in return, can enable the optimization of system designs. Applying a value-centric architecture, system characteristic space is introduced as the design space to define the characteristics of different systems. Based on our launch vehicle database, the launch cost and reliability of different families of launch vehicles are investigated, where the reliability is calculated using a modified two-level Bayesian analysis. The factors of launch cost and reliability are subsequently integrated into the expected launch cost, acting as the objective function for the analysis and optimization process associated with the manufacturing cost of satellites. Through reviewing and redesigning a few classical launch cases, the effectiveness and applicability of the design architecture proposed are validated.

著者

Frank JANSEN Waldemar BAUER Frédéric MASSON Jean-Marc RUAULT Jean-Claude WORM Emmanouil DETSIS Francois LASSOUDIERE Richard GRANJON Enrico GAIA Maria Cristina TOSI Simona FERRARIS Anatoly S. KOROTEEV Alexander V. SEMENKIN Alexander SOLODUKHIN Tim TINSLEY Zara HODGSON Christoph KOPPEL Lamartine Nogueira Frutuoso GUIMARÃES

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.Pb_225-Pb_233, 2016 (Released:2017-02-08)

被引用文献数

5

---

The European Commission Horizon 2020 funded DEMOCRITOS project (2015-2017, see under democritos.esf.org) will be primary focused to prepare preliminary design of the ground, core and space demonstrators and their test benches for the mega-watt class nuclear electric space propulsion INPPS flagship (International Nuclear Power and Propulsion System). In addition programmatic, organizational and funding aspects for international cooperation related to INPPS realization are sketched. The new project includes partners from Europe, Russia and the Brazilian guest observer IEAv and is the follow-up of the mega-watt class nuclear electric propulsion European-Russian MEGAHIT project (www.megahit-eu.org). Europe already established the high power nuclear MEGAHIT and the low power nuclear (20 to 200 kW NEP) DiPoP (www.DiPoP.eu) roadmaps. Because Europe has started the implementations for INPPS flagship in the 2030-2040 timeframe, both roadmaps will be also described – from MEGAHIT the INPPS technology options, the launcher, assembly and system architecture, space mission requirements, communications and public support. In case of DiPoP it will be explained the survey of European capabilities, technical options, potential space missions and the public acceptance as well.

著者

Yudai YUGUCHI Warley F. R. RIBEIRO Kenji NAGAOKA Kazuya YOSHIDA

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.Pk_125-Pk_130, 2016 (Released:2017-02-08)

被引用文献数

1 5

---

The surface of an asteroid features an irregular terrain and microgravity. Therefore, robotic exploration in an asteroid requires the adoption of an appropriate locomotion strategy. Moreover, an exploration robot is expected to be capable of moving to an area of scientific interest. In response to this, we have proposed a ground grip robot that moves by gripping the surface like a rock climber. By gripping the surface, the robot can prevent unintended flotation and rotation while propelling itself across the surface. When the idling arm is moved while the supporting arm's gripper is attached to the surface, all of the reaction forces act on the gripper. If the gripping force is to be exceeded, however, the robot could come adrift from the surface. In this paper, therefore, we propose a motion control method that does not act the reaction force on the gripper by utilizing the reaction null-space. Additionally, the tip position trajectory is generated as an ellipse to enable smooth movement and eliminate any frictional force. This control law was validated by a planar dynamic simulation. The simulation model assumes a dual-armed robot with three degrees of freedom (DOF) in each arm, while the uneven surface is simulated under certain conditions. As a result, the robot was able to move continuously with reactionless motion and the propriety of the control law was confirmed.

著者

Hikaru AONO Katsutoshi KONDO Taku NONOMURA Masayuki ANYOJI Akira OYAMA Kozo FUJII Makoto YAMAMOTO

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.63, no.1, pp.8-17, 2020 (Released:2020-01-04)

参考文献数

63

被引用文献数

7

---

Aerodynamics of an owl-like wing model at low Reynolds numbers (Re = O(104–5)) are investigated using large-eddy simulations with high-resolution computational schemes. The airfoil shape of the owl-like wing model is constructed based on a cross-sectional geometry of the owl wing at 40% wingspan from the root. The chord-based Re ranges from 1.0 × 104 to 5.0 × 104 and the angle of attack (α) varies from 0 to 14 deg. The time-averaged lift (Cl) and drag coefficients computed are in reasonable agreement with the results of force measurement. The results computed clarify a nonlinear change in the Cl curve slope, which is due to an increase in the suction peaks in conjunction with the change in type of separation, the formation of a laminar separation bubble (LSB), and pressure recovery on the pressure side. The generation of the LSB on the suction and/or pressure sides at the Re of 2.3 × 104 and 4.6 × 104 are seen, while reattachments are observed only on the pressure side at the Re of 1.0 × 104 due to the camber of the wing. Furthermore, the owl-like wing model demonstrates favorable aerodynamic performance in terms of a maximum lift-to-drag ratio in comparison with several airfoils at the Re range considered. This is due to the strong suction peaks and distribution of surface pressure on the pressure side. It is emphasized that the concave lower surface enhances the time-averaged aerodynamic performance at all of the α even though the LSB is generated and fluctuation in lift history is induced at low α.

著者

Yutaka WADA Yo KAWABATA Kenji OGIMOTO Hiroaki AKIYAMA Takao YANAGI Seiichi SAKAMOTO

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.6, pp.506-510, 2018 (Released:2018-09-04)

参考文献数

11

---

In this study, a reusable educational motor that can burn different types of materials in the chamber was developed. Specifically, five candidate sweets were selected as fuel and burnt. The combustion performances of these sweets were compared, and the soft candy was selected as the solid fuel to be used in the motor, because it had the highest total impulse. The SOUKI Systems Co. Ltd. designed a small candy hybrid rocket based on these results. The candy rocket was launched successfully using soft candy at the Kada Cosmo Park. The motor carried the candy rocket to 319 m altitude and was fully functional under the high-acceleration environment.

著者

Junichi HARUYAMA Shujiro SAWAI Takahide MIZUNO Tetsuo YOSHIMITSU Seisuke FUKUDA Ichiro 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.10, no.ists28, pp.Pk_7-Pk_10, 2012 (Released:2013-02-20)

被引用文献数

4 16

---

The Japanese lunar orbiter SELENE discovered three giant holes, Marius Hills Hole, Mare Tranquillitatis Hole, and Mare Ingenii Hole, that exceed tens of meters in diameter and depth, and that are possible lava tube skylights. These lunar-hole structures and possibly underlying lava tubes have great significance for lunar science and potential utilization, and thus should be priority targets of future lunar exploration. It is essential to acquire detailed information on terrain around the holes, multi-layered outcrops on the inner walls of the holes, debris and thermal conditions on the floor of the holes, and entrances of predicted lava tubes extending from the bottoms of the holes. The Smart Lander for Investigating the Moon (SLIM) mission, a future Japanese lunar lander mission being considered, is planned to land in an area within 100m around the Marius Hills Hole. Rovers will be dispatched from SLIM and approach the hole. SLIM and its rovers are small but the mission return could be huge.

著者

Kenji SHIBUSAWA Masato FUNATSU

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.62, no.2, pp.86-92, 2019 (Released:2019-03-04)

参考文献数

20

被引用文献数

4

---

The spectroscopic measurement of low-pressure microwave-discharged nitrogen plasma was conducted in the wavelength region of 550 to 1070 nm. Radiation from the N2 first positive band of the Δv=0 to Δv=+4 band series and nitrogen atomic lines were observed. The experimental spectrum was compared with the theoretical spectrum, showing the effect of the predissociation of N2 B 3Πg state through N2 A′5Σg+ state and triplet splitting for the transition of 3Π to the 3Σ state. They agreed very well with each other for the Δv=0 to Δv=+2 band series, which consisted of the lower vibrational levels of Δv′=0 to 7, but did not agree well for the higher vibrational levels of Δv′=8 to 12 in the Δv=+3 and +4 band series. By comparing the band head intensity of the experimental and theoretical spectra, the experimental vibrational population on each vibrational level for the B 3Πg state was estimated to be a non-Boltzmann distribution at the higher vibrational levels. In addition, the theoretical vibrational population distribution in the B 3Πg state was calculated using a master equation, and then agreement between the experimental spectrum and the theoretical spectrum with the non-Boltzmann distribution obtained from the master equation was improved.

著者

Junichi HARUYAMA Isao KAWANO Takashi KUBOTA Masatsugu OTSUKI Hiroki KATO Toshihiko NISHIBORI Takahiro IWATA Yukio YAMAMOTO Yoshiaki ISHIHARA Aiko NAGAMATSU Kazuhito SHIMADA Toshiaki HASENAKA Tomokatsu MOROTA Masaki N. NISHINO Ko HASHIZUME Kazuto SAIKI Motomaro SHIRA Goro KOMATSU Nobuyuki HASEBE Hisayoshi SHIMIZU Hideaki MIYAMOTO Kensei KOBAYASHI Shinichi YOKOBORI Tatsuhiro MICHIKAMI Satoru YAMAMOTO Yasuhiro YOKOTA Hitoshi ARISUMI Genya ISHIGAMI Katsushi FURUTANI Yuichi MICHIKAWA

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.Pk_147-Pk_150, 2016 (Released:2017-02-14)

被引用文献数

1 5

---

We are planning to explore the caverns through the skylight holes on the Moon and Mars. The holes and their associated subsurface caverns are among the most important future exploration targets. The importance of the lunar and Martian holes and their associated caverns is categorized from two aspects: (1) fresh materials are easily observed and sampled there, and (2) the subsurface caverns provide a safe, quiet environment. The expectation of lunar and Martian hole and cavern exploration is increasing in Japan. We name the project as UZUME (Unprecedented Zipangu (Japan) Underworld of the Moon Exploration) whose name is after a Japanese mythology. The ultimate purpose of the UZUME project is to investigate how to expand human activity and survival in space and on extraterrestrial bodies.

著者

Seiichiro MORIZAWA Taku NONOMURA Akira OYAMA Kozo FUJII Shigeru OBAYASHI

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.61, no.6, pp.258-267, 2018 (Released:2018-11-04)

参考文献数

27

被引用文献数

8

---

The effects of Mach number at Re = 3,000 for different airfoils (NACA0012, NACA0002, NACA4412, NACA4402) with thickness and camber geometries are investigated for the propeller blade design of a Mars airplane. The present study shows that thin and cambered airfoils have larger variations in Cl than symmetric airfoils. As for thin airfoils, Cl at higher α has rapid increases when the M∞ is low. This is because the flow separation occurs at the leading edge, and the flow is reattached on the airfoil surface. However, the rapid increase in Cl disappear as M∞ increases because the flow reattachment does not occurs. As for cambered airfoils, the decrease in Cl becomes larger than that on the symmetric airfoils when M∞ is higher. This is because Cp near the leading edge on the lower surface is smaller than that on the upper surface and the high-speed region on the lower side of the leading edge is enlarged as M∞ increases. Then, the Mcr at Re = 3,000 tends to be larger than that predicted by linear theory.

著者

Jun MATSUMOTO Chisato OKAMOTO Yusuke OKI Takuma NAKAMURA Jun AOKI

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.7, pp.698-705, 2018 (Released:2018-11-04)

参考文献数

18

被引用文献数

1

---

The Japan Aerospace Exploration Agency is now planning a Jupiter Trojan asteroid exploration mission using a 40 m-wide solar power sail spacecraft. In this mission, a 100 kg lander is soft-landed on an asteroid in order to perform in-situ analysis of asteroid samples by a mass spectrometer. In this mission, not only surface sampling, but also sub-surface sampling up to a depth of 1 m, will be performed. In the present paper, a sampling scenario including sub-surface sampling is proposed that does not require an anchoring system and that omits contamination from the analyzed sample. In this scenario, newly developed sampling instruments are implemented. In addition, ground experiments have been performed using these sampling instruments, surface sampling instruments, and sub-surface sampling instruments. The results of these experiments indicate that the sample mass required for in-situ analysis can be collected and that the proposed scenario is realistic and practical.

著者

Paul ACQUATELLA B.

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.61, no.2, pp.79-86, 2018 (Released:2018-03-04)

参考文献数

34

被引用文献数

4

---

The satellite platform BIROS is the second technology demonstrator of DLR’s ‘FireBIRD’ space mission aiming to provide infrared remote sensing for early fire detection. Among several mission goals and scientific experiments, to demonstrate a high-agility attitude control system, the platform is actuated with an extra array of three orthogonal ‘High-Torque-Wheels.’ However, to enable agile reorientation, a challenge arises from the fact that time-optimal slew maneuvers are, in general, not of the Euler-axis rotation type; especially whenever the actuators are constrained independently. Moreover, BIROS’ on-board computer can only accommodate rotational acceleration commands twice per second. The objective is therefore to find a methodology to design fast slew maneuvers while considering a highly dynamic plant commanded by piecewise-constant sampled-time control inputs. This is achieved by considering a comprehensive analytical nonlinear model for spacecraft equipped with reaction wheels and transcribing a time-optimal control problem formulation into a multi-criteria optimization problem. Solutions are found with a direct approach using the trajectory optimization package ‘trajOpt’ of DLR-SR’s optimization tool, Multi-Objective Parameter Synthesis (MOPS). Results based on numerical simulations are presented to illustrate this method.

著者

KOMATSU Mitsuhito NAKASUKA Shinichi

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.26, pp.Tf_19-Tf_24, 2009

被引用文献数

2 5

---

ISSL is now developing a new super small satellites for Earth remote sensing, "PRISM". This satellite has a unique optics system with flexible extensible boom, aiming at 30m ground resolution. Super small remote sensing satellite can be used for the low-cost global Earth observation missions. To achieve such high ground resolution with flexible telescope, it has some compensation strategies against structural errors or dynamic movement. This satellite will be launched with GOSAT by H-IIA rocket in 2008, and we have finished FM development phase. This paper describes its key concepts and features of PRISM, as well as the problems we encountered and the methodologies for project management by university students.

著者

SAKAMOTO Yuji TANABE Yuta YAGISAWA Hitoshi SUGIMURA Nobuo YOSHIDA Kazuya NISHIO Masanori NAKAJO Tomoyuki AKIYAMA Hiroaki

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.29, pp.Tf_7-Tf_12, 2014

被引用文献数

2

---

The 2-unit size cubesat RAIKO is a nanosatellite developed by Tohoku University and Wakayama University. This paper shows the mission and system specifications. The satellite was released to space on October 4, 2012 from International Space Station, which was the 419-km alt. circular orbit. The techniques for 50-kg microsatellites by Tohoku University are transferred to this satellite, so a lot of functions are included although the power and mass budgets are strongly restricted. The primary missions are the photo storage by different 3 optical sensors, the de-orbit mechanism experiment by expandable thin films, and Ku-band downlink communication experiment. The satellite operation was finished by orbital decay on August 6, 2013. The telemetry data were successful received in total 123 passes, in which total 63 photo images were obtained and maximum 100 kbps (200 ksps) downlink was successful. Using color CMOS camera, gradually separating ISS could be confirmed. From analysis of house-keeping data, the solar generation power in sunshine was 3.38 W (no paddles) to 5.77 W (with paddles) in average, the temperature of onboard computer was in the range of 20.8 to 28.7 deg C, and the battery temperature was 4.2 deg C in average. The real flight data from the 10-month operation will be precious information for future nanosatellite projects.

著者

ZAITSU Takashi OHTA Toshiko OHSHIMA Hiroshi MUKAI Chiaki

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.29, pp.Tp_7-Tp_9, 2014

被引用文献数

1

---

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

葛山 浩 小紫 公也 桃沢 愛 荒川 義博

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.1, pp.9-16, 2003

被引用文献数

5 14

---

エンジンサイクル解析を用いて,パルスレーザーラムジェット機のSSTO打ち上げの検討が行われた. 高々度では,多くのレーザーエネルギーが化学反応凍結流によって失われるが,重量100kg,断面積 1m²程度の機体にたいして,100MW程度のレーザーパワーでレーザーラムジェット機をSSTO打ち上げ 可能であることがわかった. また,エンジンサイクル解析により得られた運動量結合係数Cmを, CFDを用いて得られたCmと比較することでその妥当性を検討した. 結果として,エンジンサイクル解析はCmを過小評価していることがわかった. この理由は,実際の加熱過程における強い非定常なエネルギー入力と機体のafterbody上での 空間的にローカライズされた圧力上昇のためであると考えられる.

著者

羽生 宏人 和田 英一 丹羽 崇博 近藤 靖雄 川村 尚史 丸山 信也 岡村 彩乃 山科 早英良 永井 康仁 中道 達也 上道 茜 田中 成明 小林 直樹 笠原 次郎 森田 泰弘

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.15-21, 2010

被引用文献数

1

---

The educational hybrid-rocket was successfully launched and it also landed within the predicted area. Aerodynamic characteristics of the rocket designed by students of Tsukuba University were evaluated by the wind tunnel testing with the support of Tokai University. The flight path affected by the environmental condition, especially wind direction and velocity, was simulated with the original calculation program. The altitude of the rocket was measured with the optical equipment and the apex was 123 m although the calculation indicated 198 m. We expected that the insufficient filling or the volatilization of Nitrous oxide as an oxidizer led to this result. And then, the apex was verified with a function of the oxidizer filling ratio. The results showed that 81.2 % of the oxidizer volume in comparison with the firing test condition was accumulated in the tank at the launch.

著者

武田 和也 河島 信樹 矢部 恭一

出版者

THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES

雑誌

宇宙技術 (ISSN:13473832)

巻号頁・発行日

vol.7, pp.27-32, 2008

被引用文献数

1 5

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我々は半導体レーザーを用いた飛翔体へのエネルギー伝送システムを構築した.これはレーザーでエネルギーを受けている間飛行し続けることができるシステムである.これを用いた飛行実験を大阪ドームにおいて行った.その結果,高度50mを旋回飛行する無人飛翔体へ,自動追尾によってエネルギー伝送を行い,長時間飛行に成功した.