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北アルプスの上高地に生息するニホンザルの群れを対象に，サルが利用する生息環境の各箇所と，サルの生活している温度について計測して比較を行った。生息環境の温度測定は，サルが繰り返し泊り場として利用したウラジロモミの樹冠内（泊り場），採食場所として利用した落葉広葉樹林（採食場所），森林外の河原のエゾヤナギ（開放地）に温度センサーを設置して生息環境の温度を計測した。また，河原裸地に照度センサーを設置して計測を行い，天気図と合わせて気象条件を特定した。サルの生活している温度は，オトナオス個体にデータロガーを装着して1993年2月19日から22日間の温度を測定した。サルが記録した温度は，日中は採食や移動により大きく変化したが，夜間は高温で大きな変化がなく，サルの行動を忠実に反映していると考えられた。サルの記録した温度は，すべての計測期間中，外気温度より高かった。外気温度は夜間に比べて日中の方が有意に高かったが，サル温度は日中に比べ夜間が有意に高かった。また，冷え込んだ夜ほど，サル温度はより高温を保っていた。この結果から，サルが常緑針葉樹の樹冠内の泊り場内で過ごす夜間は，複数個体が身を寄せ合って過ごすHuddlingの行動により，泊り場内の生息環境を造り上げていることが温度測定によって示された。, Article, 信州大学農学部AFC報告 11（1-2）: 29-36(2013)

東北女子大学・東北女子短期大学紀要, 50, 2012, p.21-31

米苗床用容器に緑色植物を植え,それを校舎の屋根に並べ緑化した。その真下の教室と容器を置いていない下側にある部屋の温度やそれらの真横に位置する2教室の温度を測定した。その結果,天候にも依るが,真下や真横の室内温度は植物容器がある所は置いてない所に比べて2～4℃,外気温度に比べて5℃程低くなる。### その一方で昨年に引き続き校舎南側に曼性植物を植え「グリーン・カーテン」として使用した。そのカーテンの有無による室内温度の違いについて,それぞれの学校や事業所毎に測定が行われている。それによると測定場所にもよるが,グリーン・カーテンがある所はない所に比べて2～3℃,外気温に比べて数℃低くなることが明らかになってきた。### この屋上緑化やグリーン・カーテンのための植栽,その後の管理,温度測定などは理科学習,環境学習,総合学習,食育などに使われ,自然への興味や関心を高めると共に,地域住民と連携した交流に繋がっている。他方,大分県や県教委も今年度から空調に頼らない省エネ思想啓発のために,グリーン・カーテンの普及を県庁舎や県立学校で始めた。### Green plants were grown in seedling containers and they were laid out on the rooftop of a school house. The temperature of a room below the part where the containers were placed and no containers were placed was measured respectively. The temperature of two other classrooms located next to the two rooms was also measured. It was found that depending on the weather, the indoor temperature of the room with containers above it or that of the room next to it was 2 to 4℃ lower than that of the room with no containers above it; and that the indoor temperature was approximately 5℃ lower than atmospheric temperature.

Application of Large scale lithium-ion battery to various satellites and space vehicles has progressed well because of high capacity and high specific energy demands. GS Yuasa Technology (GYT) had developed 100 Ah lithium ion cells in 1999. And we consecutively had developed 50 Ah and 175 Ah cell with the same basic electrode design as the 100 Ah cell. In this study, we investigated the internal cell temperature during charge and discharge operation that is important information to assess the cell life. The temperature measurements were performed on three sizes cells which are the 50 Ah, 100 Ah, and 175 Ah cell. Each cell were opened at the bottom of the cell case and four thermo couple temperature sensors were installed into the cell inside. The detail locations are top (in height)-center (of wound element), middle-center, bottom-center, and bottom-outer (of wound element, but inside of case). The opened cell bottom was sealed by epoxy resin for the charge and discharge test. And additional four thermo couple temperature sensors were attached at cell surface. The charge and discharge conditions are simulated LEO (Low Earth Orbit) and GEO (Geostationary Earth Orbit) satellite operation, as shown below. LEO: Charge: 0.5 CA for 60 minutes, Discharge: 0.8 CA for 30 minutes. GEO: Charge: 0.1 CA for 22 hours 48 minutes, Discharge: 0.58 CA for 72 minutes. These charge and discharge test were repeated six cycles at 0 C, 15 C, and 25 C, respectively. In these test, following results were obtained. Larger cell shows larger temperature difference within the cell. However, even at 175 Ah cell, the largest temperature difference was 3.3 C that is measured between inside and outside of wound element. As for top and bottom direction, the maximum temperature difference was 0.9 C. We think that the reason of this small temperature difference at vertical direction depends on high thermal conductivity of Cupper and Aluminum foil that consist the cell wound element., 資料番号: AA0063965002

資料番号: AA0063719001

Flame spread character along Polyethylene (PE)-insulated wire as a model of electric devices, which is most possible fire source in space, in quiescent closed chamber is examined experimentally. Sub-atmospheric pressure range from 20 kPa to 100 kPa is of interest to simulate the space habitant environment. Throughout the study, ambient gas composition is fixed at 79 volume percent of nitrogen and 21 volume percent of oxygen (same as air), hence the partial pressure of oxygen is decreased as the pressure in the chamber is decreased. Flame spread subsequent forced ignition is observed and the spread rate is determined as a measure of the fire damage. Three types of chamber configuration are demonstrated to investigate the enclosure effect on flame spread; such as (a) with ceiling and side walls (severely confined case), (b) with ceiling but no side wall, (c) open (no obstacle. Least confined case). Results showed that the spread rate is quite sensitive on the imposed enclosure configuration near the extinction condition; the spread rate decreased with ceiling and side walls but no decrement trend is observed in open configuration. It is suspected that the burned gas tends to stagnant near the combustion regime in severely confined case and the oxygen component to be burned is limited. Without any confined effect, faster spread rate is achieved in depressurized environment. It is addressed that the severe regulation for fire safety should be applied in the space habitant., 資料番号: AA0063349034

In this study, we constructed a thermal model of Itokawa considering its shape. And we paid attention to Hayabusa (MUSES-C: Asteroid Sample-return Spacecraft)/XRS (X-Ray Spectrometer) thermometer observations by means of determining the surface conditions of Itokawa. This thermometer was attached to measure the temperature of Hood by which the detectors of XRS were cooled radiatively. Since it was calibrated sufficiently in the thermal vacuum test, we found it is useful to investigate the surface thermal properties of Itokawa. We compared XRS temperature calculated with thermal model with those derived from XRS thermometer observations and made attempt to find the most suitable thermal property of Itokawa., 資料番号: AA0063505021

資料番号: AA0045441083

資料番号: AA0045913020

資料番号: AA0045981044

One dimensional TLZ (Traveling Liquidus-Zone) growth model has been developed and the importance of accurate measurements of temperature gradients in the liquidus-zone has been revealed because sample translation rates for growing homogeneous crystals are directly related to the temperature gradient according to the model. For this purpose, a new method was invented to determine the average temperature gradient in the zone experimentally. In addition, temperature profiles in dummy samples were measured by using thermocouples and these results were utilized for developing numerical analyses of temperature distribution in the sample device. As a result, understanding of the TLZ growth mechanism has been deepened including constitutional supercooling during the crystal growth. Here, experimental results on temperature profile (temperature gradient) measurements and compositional profile analyses based on the TLZ model and measured temperature gradients are summarized together with the TLZ model over view., 資料番号: AA0045402001, レポート番号: NASDA-TMR-020024E

The first and clear experimental evidence for the transition from the steady to the oscillatory flow was presented by the non-contact temperature measurement of a molten tin surface and the surface flow visualization. Imaishi et al. confirmed validity of the experimentally determined Ma(sub c2) and frequency of the standing wave in comparison with a numerical result. Some performance tests for radiation thermometer also made this experimental result reliable and accurate. The effect of an aspect ratio (As) on the Ma(sub c2) has been studied. The Ma(sub c2) increases with decreasing of As in the range of As near 1.24. Internal temperature field of liquid bridge at oscillatory flow was speculated by the phase relation analysis of the simultaneous multi-measurement data of surface temperature. The numerical simulation was conducted under the same conditions of the experiment in order to check the onset point and temperature fluctuation data obtained by the experiment. The surface tension of molten tin was measured at various temperatures between 523 and 1023 K under the oxygen partial pressures (P(sub O2)) between 10(exp -19) and 10(exp -6) MPa. It was clarified an appropriate value of the surface tension coefficient for experimental chamber is - 0.9 x 10(exp -4) N/mK. It was also found that the temperature coefficient of surface tension at a constant P(sub O2) raised as P(sub 02) increased, and the sign of the coefficient changed from minus to plus at logP(sub 02) = -9.375 MPa. Visualization technique (3D-UV) of flow field measurements for liquid metals using ultrasonic transducer with high heat resistance has been successively developed for the experiments. Sensitivity of transducer was examined at high temperature condition same as actual thermocapillary experiment. High spatial resolution in the direction of ultrasonic propagation was obtained. Visualization performance of ongoing sensor design was confirmed by numerical simulation. The tracer is also currently under development. Technique for improvement of sphericity and surface roughness was developed. Endurance against molten tin and acoustic characteristics of trial production were experimentally examined., 資料番号: AA0032601006, レポート番号: NASDA-TMR-010015E

As a continuation of the studies performed in the previous fiscal year, the study of feasibility of conducting the dynamic surface deformation measurement on the liquid bridge, to be utilized for the liquid bridge Marangoni convection experiments using the JEM Fluid Physics Experiment Facility (FPEF), was performed. From these studies, the specifications of the experiment cell was established based on the studies of installing the Dynamic Surface Deformation (DSD) measurement device into the experiment cell, and the detailed measurement based on the Microscopic Imaging Displacement Meter (MIDM) method for liquid bridge dynamic surface measurement. This study also included the compatibility with the FPEF and confirmed that all interfaces conform to the requirements. Furthermore, items that require confirmation in order to meet the experiment requirements were extracted and a draft of the development plan that reflect these confirmation items was established., 資料番号: AA0032601009, レポート番号: NASDA-TMR-010015E

航空宇宙技術研究所の大型極超音速風洞では、空力加熱測定を赤外線カメラを用いて行っている。この赤外線カメラによる空力加熱測定法は、従来の離散的なセンサによる測定法に比べ、機体全体にわたる空力加熱を2次元的な面情報として捉えられるため、局所的なピーク加熱も捕捉できる点で優れている。また、これまで定量測定精度の問題が指摘されていたが、誤差量の見積もり、補正方法の確立、3次元マッピングソフトウェアの開発、従来型のセンサとの比較試験などを行い、総合的な測定精度として10％以内の測定が可能であることを確認した。赤外線カメラによる空力加熱測定法は、極超音速風洞における空力加熱測定の実用的なシステムとしてほぼ確立した。ここでは、赤外線カメラによる空力加熱測定法の概要と定量測定精度を高めるために行った誤差の検討と補正法、センサとの比較試験などについて報告する。, 資料番号: AA0032235012, レポート番号: NAL SP-51

宇宙往還機のノーズキャップ取付金具部の熱伝導特性を把握するために、取付金具を模擬した供試体を製作して、加熱試験を行った。供試体は極超音速飛行実験(HYFLEX)機のノーズキャップ取付金具と同じ大きさに同等の素材で製作したものを用いた。供試体の加熱はクセノンランプ加熱装置を用いて行なった。試験は真空中で実施し、熱電対を用いて、供試体の各部位の温度履歴データを取得した。ノーズキャップを模擬したカーボン/カーボン複合材平板の裏面の温度が最大になるときには、機体主構造部材を模擬したアルミニウム合金平板の温度はほとんど上昇しておらず、その温度上昇にタイムラグがあることが観測された。, Heating tests of a model of a nose cap fitting were carried out in order to understand the behavior of thermal conduction of the nose cap fitting of hypersonic re-entry vehicles. The model was constructed of materials equivalent to those used for the nose cap fitting of the Hypersonic Flight Experiment (HYFLEX) vehicle, and was of the same size. The model was heated using a xenon lamp heating system. Tests were carried out in a vacuum, and the temperature history at selected locations on the model were measured with thermocouples. It was observed that the temperature of the main structure of the airframe hardly rose, when the temperature of the back surface of the nose cap reached its peak value., 資料番号: AA0001963000, レポート番号: NAL TM-738

資料番号: AA0063719010

This report was described the activity of a research working group on Interfacial Phenomena and fluid instability. Primary three themes which would promise to utilize the microgravity condition were discussed. The research plan and organization concerning these themes were established. We start the preparatory study to accomplish each objective., 資料番号: AA0063349026

資料番号: AA0063347001

資料番号: AA0046920035

層流制御翼の研究において環境層遷移点を正確に知ることは、その抵抗特性に対する理解を深めるために必要不可欠である。感温液晶による流れの可視化は遷移点測定法として非常に有効な方法であるが、その実際の応用に際しては、幾つかの困難がある。翼表面の温度と用いた感温塗料の発色温度の不一致は、航技研2次元風洞における2次元ハイブリッド層流制御(HLFC)翼の試験において経験した困難の1つである。本報告ではこのような温度の不一致を避ける有効な方法について検討し、集合胴温度の情報が感温液晶の選択において有意義な情報であることを示すとともに、得られた遷移点位置の結果を、ウェーク抵抗の測定結果と関連づけて論じる。, In the study of laminar-flow-control airfoils, accurate measurement of the boundary layer transition point over the airfoil is quite important to deepen the understanding of its drag characteristics. Flow visualization using temperature-sensing liquid crystals is one of the most useful techniques for detecting the transition point. However, there are some inherent difficulties in its practical applications for wind tunnel testings: mismatching between the airfoil surface temperature and the liquid crystals temperature range is the one encountered in the present blowdown wind tunnel test. With great effort to avoid mismatching, it was used to measure the transition points of a two-dimensional hybrid laminar-flow-control airfoil in high subsonic, high Reynolds number flow at the NAL (National Aerospace Laboratory) 2-D wind tunnel. In the present paper, it is described of the results of the test showing a way to avoid the temperature range mismatching with stagnation temperature in the blowdown wind tunnel test., 資料番号: AA0000001000, レポート番号: NAL TM-679

ケーブル内部に光ファイバを複合する技術として、これまで金属被付CVケーブル内へ光ファイバを複合する技術はあったが、今回、一般的な銅ワイヤーシールドのCVケーブル内に光ファイバを複合するケーブルを開発したので報告する。, There are a number of supply experience of optical fiber composite power cables with metallic sheath, but no experience without metallic sheath. In this paper,Ireport about development of copper wire shield XLPE cable with optical fiber without metallic sheath.

This paper describes an investigation for development of visualization system which aims to observe Marangoni convection in a half-zone liquid bridge of low-Prandtl number fluid of molten tin. Generally, low Prandtl number fluids (eg. molten metal and semiconductor) are opaque. So, the internal flow can not be measured by using a visible light. Therefore we employed the ultrasonic wave to track the particle position. The transducer was made by LiNbO3 single crystal as a piezoelectric element which was attached on titanium shoe. The suitable tracer to mix into the molten tin liquid bridge was examine in several point of view; density match, wettability with mother fluid, acoustic impedance and so on. The hallow Shirasu-balloon coated with Ni and Fe could be made. The feasibility test of this system was performed and the result demonstrates us to be able to visualize the internal flow filed in low Prandtl number liquid column., 資料番号: AA0063889000, レポート番号: JAXA-RM-06-015E

タービン翼の冷却研究目的で、フィルム冷却、インピンジメント冷却の基礎実験、および、それら組み合わせた複合冷却の実験を実施した。実験は673Kの燃焼ガスに対し室温の冷却空気を使用し、試験体表面の温度計測は赤外線カメラによって行った。これら、基礎的な実験データはCFD(Computational Fluid Dynamics)などの解析へ利用することを念頭においており、本報告では、基本的な各冷却構造の試験結果、各冷却構造を組み合わせた複合冷却の基礎試験結果を述べる。さらに、簡単な熱伝導解析を行い、実験結果による冷却性能の予測改善を行った。, Experimental study of film cooling, impingement cooling and integrated cooling were carried out with the aim of applying them to turbine cooling. The experiments were conducted with 673 K hot gas flow and room temperature cooling air. Test plate surface temperature distributions were measured with an infrared camera. This report presents fundamental research data on cooling performance of the test plates for the validation of numerical simulation. Moreover, simplify heat transfer calculations were executed and were evaluated by the experimental measurements., 資料番号: AA0063461000, レポート番号: JAXA-RR-06-027

風洞技術開発センター(WINTEC: Wind Tunnel Technology Center)では、感圧塗料(Pressure-Sensitive Paint: PSP)計測の大型実用風洞群への整備を進めている。従来の静圧孔を用いた電子式センサーによる計測では離散的なデータしか得られなかったが、PSPを用いることで模型上の面情報が得られ、衝撃波位置などの詳細流れ場の情報を可視化することができる。しかしながら、感圧塗料の発光強度は圧力依存性と同時に温度依存性を有しているため、計測精度を向上させるためには何らかの手法を用いて温度補正を施す必要がある。これまで、我々は、模型の左右片側ずつを感圧塗料と感温塗料で塗り分けすることで温度補正を行ってきた。しかし、この手法の場合、流れの左右対称性を仮定しなければならず、さらに片側の圧力場情報しか得られない短所がある。よって、横滑り角をとるような計測や半裁模型など非対称形状模型試験には適用できない。このような背景から、本研究では赤外線カメラ(IRカメラ)を用いて模型上の温度分布を計測し、その温度をPSP温度補正に利用する方法を試みた。温度依存性に起因する計測誤差は、特に圧力変化の小さい低速域で致命的な計測誤差になる。そこで、本PSP計測システムを2m×2m低速風洞試験に適応し、システムの有効性を評価した。その結果、従来の方法(通風直後の無風時画像を用いた計測法)よりも定量的に計測精度を向上させることができ、本システムの温度補正機能が有効であることが実証された。また、低速風洞試験における計測精度は、一様流速50m/sにおいてCp換算で約0.1(0.15kPa)を達成した。, A Pressure-Sensitive Paint (PSP) measurement system has been developed in the large-scale wind tunnels of the Wind Tunnel Technology Center (WINTEC). PSP technique provides a simple and inexpensive way to obtain overall pressure images on an aerodynamic model surface with high spatial resolution. However, the luminescent intensity of PSP depends on both pressure and temperature. Therefore, temperature correction of PSP should be conducted to increase measurement accuracy. For our present PSP system, a PSP/Temperature-Sensitive Paint (TSP) combined system is used for temperature correction. When the PSP/TSP combined system is applied, the flowfield on both right and left wings of a model should be identical. Accordingly, the system cannot acquire pressure images on a model at sideslip angles. A half-model is also inapplicable, because it is not a symmetric configuration. To solve these problems, a PSP system combined with an Infrared (IR) camera was developed. This technique could acquire pressure images without the limitations mentioned above. The PSP/IR combined system was applied to 2 m x 2 m low-speed wind tunnel for verification purposes because measurement accuracy of low-speed PSP is acutely sensitive to error due to the temperature dependence of PSP. It was found that a PSP system with an IR camera could improve measurement accuracy compared with the conventional PSP technique, verifying that this temperature correction method is a useful technique for low-speed testing., 資料番号: AA0063500000, レポート番号: JAXA-RR-06-028

学際領域における分子イメージングフォーラム 宇宙航空研究開発機構 20061116 東京 日本, Interdisciplinary Forum on Molecular Imaging Japan Aerospace Exploration Agency 20061116 Tokyo Japan, 資料番号: AA0063158000, レポート番号: JAXA-SP-06-017

本稿は、現在宇宙航空研究開発機構において開発が行われており、地上から飛行マッハ数6条件に至るまでの試験が計画されている小型極超音速ターボエンジンに搭載される、小型水素燃料逆流アニュラ燃焼器の開発および試験結果について述べたものである。小型試験模型としてのサイズの制約から、ガスタービン燃焼器として逆流アニュラ燃焼器方式を選定した。混合と燃焼を規定の流路・条件で満足させるために、動径方向噴射予混合器を採用した。本燃焼器の製作における設計の過程を略述し、試験を行った結果について広範に説明した。燃焼試験は、地上静止条件から、飛行マッハ数マッハ6に至るまでの条件で行った。試験の結果、燃焼器出口温度、圧力損失などの基本的な特性が、全ての試験条件で仕様の範囲内であることが確認された。今回導入した、動径方向噴射予混合器によって、気体水素を燃料とする条件の下で小型の燃焼器においても規定の性能を満足することが確認された。, This paper describes the development and test results of a small hydrogen-fueled reverse-flow annular combustor for a scaled pre-cooled turbojet engine. The Japan Aerospace Exploration Agency is encouraging the development of this turbojet engine, and a practical demonstration will be made under both ground and in-flight conditions up to Mach 6. Due to the limited size of the entire engine, a small reverse-flow annular combustor has been adopted for this demonstration. The particular type of pre-mixer that we use is important for achieving favorable degree of mixing and combustion. In the paper, the procedure used to arrive at the present design is briefly described, and the results of the combustion test are reported in detail. The combustion test was performed under a wide range of conditions: from sea level static conditions to in-flight conditions up to Mach 6. The test result shows that the overall combustion characteristics, such as exit temperature profile and pressure loss, are within the allowable limits under all test conditions. It was shown that the restrictions arising from the geometry in a flyable small gas-turbine engine were overcome in the composition of gaseous fuels with the introduction of the radial-injection pre-mixer configuration., 資料番号: AA0049796000, レポート番号: JAXA-RM-05-011

SiC/SiC材などの先進耐熱複合材は軽量で耐熱強度に優れていることからガスタービンの回転部材に適した材料として注目されている。これら先進材料を回転部材に適応するためには室温はもとより高温での回転強度特性を把握する必要がある。金属材料(導体)であれば、その試験片の周りにコイルを巻いて高周波誘導加熱により加熱し、高温回転破壊試験が行われる。しかし、セラミックスなどの絶縁体では誘導加熱により直接加熱することは困難なので、高温雰囲気中で回転確認試験のみが行われている。本報告は回転部材の候補材料が導体、絶縁体の区別無く加熱が可能で、破壊試験を行った場合でも2次破壊を出来るだけ生じさせない回転試験用高温加熱装置を試作した結果について述べる。, SiC/SiC composites can not be heated with induction heating equipments. Therefore, the high-temperature rotating tests for ceramics are usually performed at high temperature gas environments. In this paper, the heating equipment for high-temperature rotating test was made in order to understand the high temperature rotation strength property of advanced materials. This induction heating equipment enabled high-temperature rotating tests of metals or ceramics disks. The high-temperature rotating tests of CMC disks at 1,200 K were successfully demonstrated., 資料番号: AA0063151000, レポート番号: JAXA-RM-05-008

Experimental study on thermocapillary convection of low Prandtl number fluid was carried out to estimate the mode structure after the onset of oscillatory flow. The half-zone liquid bridge of molten tin was used as a experimental configuration. In order to detect very slight temperature changes, the temperature measurement system was improved. Temperature oscillations at the interface between liquid and cold rod were obtained by several thermocouples. The first transition could be detected and the transition processes have been clarified. The mode structure appeared in a low frequency oscillation region after the onset was presumed from the phase differences among them. The mode structure was supposed to be 2 and rotation with a frequency of 0.008 Hz. Furthermore, the rotation of the temperature field was elucidated through the multipoint measurements. In addition to above experiment, the preliminary test to visualize the flow field by using ultrasonic wave was performed. The result demonstrates us to be able to visualize the internal flow filed in low Prandtl number liquid column., 資料番号: AA0049790000, レポート番号: JAXA-RR-05-023E

超高温材料研究センターの酸化揮散試験機を用いて高純度CVD-SiCの静的加熱試験を実施する際に、装置各部で大きな温度分布が生じることが考えられる。装置各部で生じる現象を予測し、結果の評価などに活用可能なデータを得るために濃度分布測定を行なったので報告する。, 資料番号: AA0046965000, レポート番号: JAXA-RM-03-012

本資料では、当所において1985年頃から実施された太陽熱スラスタの試作研究について述べる。当初はステンレス鋼を材料とした習作スラスタであり、加熱・噴射試験結果も平凡で、比推力500〜600秒級であった。次段階では物質・材料研究機構が日本および米国の特許を有する単結晶モリブデン材を採用して、超小型(外径約6mm)から大型(外径65mm)までの各種サイズのスラスタの試作・太陽集光加熱・推進剤噴射試験を実施した。この材料では推進剤温度2,300K、比推力800秒が期待できる。これが本資料の主要部である。さらに究極の材料として単結晶タングステンを採用して、比推力1,000秒級に対応可能なスラスタを試作して予備実験を実施した。このスラスタはアポジおよびペリジでの噴射が可能な対向型で、この型の試作・実験結果の発表は世界初と思われる。, This paper presents an investigation of solar thermal propulsion (STP) thruster activities including design, fabrication and the results of experiments involving 4 mm, 10 mm, 20 mm and 50 mm cavity diameter windowless axisymmetric thrusters made of single crystal molybdenum or tungsten (SC-Mo, SC-W) with Ru/Mo brazing and/or a W-CVD coating. The nitrogen or helium propellant in the thrusters was heated to a maximum of around 2,300 K (800 s of Isp for hydrogen propellant) by concentrated solar energy, using the 0.6 and 1.6 solar concentrators of NAL, and a very precise concentrator of 10 m in diameter, made from 181 locally paraboloidal segmented mirrors by Tohoku University. Unfortunately, these axisymmetric thrusters usually only work at perigee or apogee, meaning inconvenience for the orbit transfer from LEO to GEO. The next step is therefore an opposed-cavity STP thruster heated with a pair of cavities aligned in a back-to-back position. The opposed-concentrator, which consists of a pair of face-to-face concentrators, heated the opposed-cavity thrusters successfully, allowing NAL to establish a basis for STP thruster technology., 資料番号: AA0045945000, レポート番号: NAL TM-769

資料番号: AA0045402000, レポート番号: NASDA-TMR-020024E

航空宇宙技術研究所構造材料総合研究グループ熱構造研究グループにおいて、我々は新たに赤外線ランプを用いた真空加熱試験装置を製作し、その基本性能の確認のための予備加熱試験、および再突入機高温結合部分を模擬した供試体に対する真空下の加熱試験を行った。その結果、加熱試験装置の性能は最大約260kw/sq m と推算された。また、赤外線ランプの速い応答性によりシステム同定に有用なステップ状入力が容易に行える事を確かめる事ができた。本報告では今回の試験装置開発の経緯と、各加熱試験結果について報告、考察する。, In the Structural and Material Research Center of National Aerospace Laboratory, the vacuum heating test equipment using the infrared lamp was newly developed, and the heating test of water-cooled specimen and C/C composite plate with thermal protection attachment were carried out. The test results showed that the performance of the heating test equipment was around 260 kw/sq m. Also it was confirmed this test equipment could perform a step input into the infrared quartz lamp that was useful for system identification. In this paper, the outlines of the development of an infrared quartz lamp heating system and results of its heating tests are shown., 資料番号: AA0032233000, レポート番号: NAL TM-758

資料番号: AA0063158018, レポート番号: JAXA-SP-06-017