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将来の人工衛星に求められる高度な観測性能を実現するためには、熱的な寸法安定性に優れた構造体が必要不可欠である。その構造体は予測される軌道上での熱環境の変動に対して高い安定性を有するように設計されており、その安定性は打ち上げ前の地上試験において徹底的に検証される必要がある。そのため、初期の設計解析段階における材料物性の正確性の向上に加えてシステムレベルの実構造体の安定性を検証する技術の向上が必要である。実構造体を用いてシステムレベルでの熱構造特性の実測による正確な評価を実施するために、JAXAでは試験検証技術の開発を進めておりその最初の段階として中型規模の評価設備を試験的に構築した。本稿では、その設備の重要な要素である恒温恒湿・防音防振クリーンルームとゼロ膨張セラミックスを用いた低熱膨張除振台とレーザ干渉変位計による高精度変位測定系の開発について記載する。性能確認試験の結果、試験室内の温湿度の安定度が0.14 度C、1.0 %RH以下、低熱膨張定盤の熱膨張係数が0 ± 0.02 ppm/K、測定系の変位測定精度が0.04 μm以下であることを確認した。, Thermally stable structures are essential components to realize advanced quality of observation for future satellite missions. Their structures should be designed to be stable against the predicted thermal disturbances on orbit and their stabilities should be verified completely through ground tests before launch. Previous research and development activities have highlighted the importance of system level verification technologies in addition to accurate evaluation of material properties used as the design parameters. The development of a test facility is currently in progress at JAXA with the aim of verification of the mechanical design accuracy by measuring actual amount of thermal deformation of satellite structures precisely under highly stable environments. A middle-sized test facility has been developed as a first step to overcoming a range of technical challenges. This report summarizes the development of the key equipment for the test facility, i.e. a highly stable temperature and humidity controlled environmental room, a low thermal expansion optical breadboard with pneumatic isolators and a highly precise displacement measuring system using the next generation laser interferometers. As a result, we obtained core testing technologies such as the stable measurement environment (fluctuation less than 0.14 C and 1.0 %RH in air condition), the thermally stable fixture base with vibration isolation mechanisms (CTE = 0 +/- 0.02 ppm/K at room temperature) and the precise displacement measurement system (accuracy less than 0.04 μm)., 形態: カラー図版あり, Physical characteristics: Original contains color illustrations, 資料番号: AA1630040000, レポート番号: JAXA-RM-16-004

資料番号: AA0063716003

資料番号: AA0049122103

高温高圧燃焼試験設備の拡充整備が完了した。これにより、圧力5MPa、温度1,000K、流量4kg/sの燃焼用空気を燃焼器に供給することができ、実圧実温での性能評価が可能となった。, JAXA AP-7 High-Temperature & High-Pressure Combustion Test Facility is a unique facility that can supply air at temperatures up to 1,000 K and pressures up to 5 MPa. In order to make this facility more attractive and useful in developing combustors of aero-engines, every effort has been made to increase flow rates of air up to 4.0 kg/s, which is the triple of the previous performance. A traversing measurement system and a direct monitoring system for combustion are also equipped in this facility. By virtue of the augmentation of airflow rate, we can meet the requirement, up to about 2 MPa, for conducting combustion tests of sector combustors, to be installed in the ECO engine, being aimed for production in the 'Research and Development for an Environment-Friendly, Small Aircraft Engine' project, supervised by the Ministry of Economy, Trade and Industry. Furthermore, this augmentation gives us an opportunity for developing a low-NOx fuel-injector for the single combustor of the next generation civil aero-engines, operating under high-pressure ratios. Having finished competitive combustion tests for examining performance of sector combustions for ECO engines, it is strongly anticipated for this facility to be used in refining the combustor, to be selected in the competition., 資料番号: AA0063150000, レポート番号: JAXA-RM-05-007

The Cryogenic Inducer Test Facility (CITF) was constructed in the JAXA Kakuda Space Center and has been in operation since 2003. Liquid nitrogen and liquid hydrogen are used as working fluids for experiments on rocket engine turbopump inducers, enabling the thermodynamic effects on cavitation to be examined. The performance of CITF was verified from the elemental tests and inducer running tests. In this article, the verification test results and future programs are presented., 資料番号: AA0049203000, レポート番号: JAXA-RR-05-042

わが国においては現在大型ロケットH-IIの開発が進んでいる。このロケットには同じく開発中の大型液酸・液水エンジンLE-7が使用される。LE-7エンジンには高圧・大流量の液体酸素を燃焼器に供給する液酸ターボポンプが必要になる。航空宇宙技術研究所は同ターボポンプの研究開発を担当している。1985年角田支所に高圧液酸ターボポンプ試験設備を整備した。本報告は,同設備のタービン駆動系について記述したものであり,特に高圧水素ガス/液体酸素ガス発生器の作動シーケンスや高圧・大流量のタービン排ガス処理装置について詳しく記述した。, A large launch vehicle, called the H-II, has been developed in Japan, and will use the LE-7 liquid oxygen/liquid hydrogen engine which is also under development. The engine requires a liquid oxygen (LOX) turbopump which supplies the main combustion chamber with a large quantity of high pressure liquid oxygen. The National Aerospace Laboratory (NAL) has been in charge of the research and development of this turbopump, with a test facility having been constructed at the Kakuda Research Center in 1985. The facility's turbine drive system is discussed, with emphasis on the control sequence of the high presssure gaseous hydrogen/liquid oxygen gas generator, and also on the turbine exhaust gas disposal equipment which designed to handle high pressures and large flows., 資料番号: NALTM0631000, レポート番号: NAL TM-631