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2010 Vol.43 No.1

IHI ENGINEERING REVIEW

2010 Vol.43 No.1

1. JEM Exposed Facility System and Operation

TAKATA Masaharu

International Space Station (ISS) is currently constructing. For Japanese Experiment Module (JEM) “Kibo,” ELM-PS (Experiment Logistics Module - Pressurized Section) and PM (Pressurized Module) were launched in 2008, and JEM Exposed Facility (EF) and ELM-ES (Experiment Logistics Module - Exposed Section) were launched in 2009. This paper describes the system summary, features, and operation of JEM-EF.

2. Development of Experiment Equipment and Racks of the JEM-PM (Japanese Experiment Module-Pressurized Module)

ONISHI Mitsuo, SAKAI Yumiko, TOMOBE Toshiyuki, NAGASHIMA Takao, TAKADA Tetsuya

Japanese Experiment Module-Pressurized Module (JEM-PM) was launched to the International Space Station (ISS) on the STS-124 (1J) in June 2008. The experiment equipment (FPEF, SPCF, FPEF experiment cells, ICE cell, Facet cell, and JAXA PCG Cell) and experiment racks (RYUTAI rack, SAIBO rack) developed by IHI Aerospace (IA) under the contract with JAXA (Japan Aerospace Exploration Agency) were installed on JEM-PM. With these experimental cells, Japan performed experiments including Marangoni convection, ice crystal, and facet cell experiments from August 2008 to September 2009. This report describes experiment equipment and racks together with the results of experiments. The racks under development for launching in the future is outlined.

3. HTV Exposed Pallet and its Mechanisms

YOSHIE Yuki, SUGIMURA Fumitaka

The first HTV (H-II transfer vehicle) was launched by the H-IIB rocket from the Tanegashima Space Center to transport various cargoes to ISS (International Space Station) on Sept. 11, 2009. Two exposed payloads were carried to ISS by the Exposed Pallet. All mechanisms manufactured by IA were successfully operated, and the experiments on orbit started. The Exposed Pallet is a module mounted on HTV to carry various exposed payload. This paper describes the mission operation and the system outline of Exposed Pallet, two unique mechanisms, HCSM (HTV connector separation mechanism), and HCAM (HTV cargo attachment mechanism). HCSM is the mechanism to keep electrical connector mated to provide heater power to the payload during launch and separate the connector on orbit. HCAM is the structural latch mechanism. A payload is supported by four HCAMs during launch and is disengaged from Exposed Pallet on orbit.

4. HAN/HN-Based Monopropellant Thrusters

FUKUCHI B Apollo, NAGASE Sakae, MARUIZUMI Haruki, AYABE Muneo

HAN-based monopropellant has been anticipated to be an alternative to hydrazine currently used for space propulsion application. They are very favorable in potentially higher performance, significantly less toxic, and environmentally harmless compared with hydrazine. The practical use of HAN-based monopropellant has not been achieved so far due to the lack of reliable ignition technology with Ir catalysts and because of its complicated combustion mechanism and its high detonability. This paper presents the development and hot firing test results of a mixture of HAN/HN/TEAN/H2O. The HN addition realized a reliable catalytic ignition and combustion characteristics with 1N-20N class thrusters and safety characteristics without detonability.

5. Research on Advanced Solid Rocket Launcher

OHTSUKA Hirohito, YAGI Kazuhiro, KISHI Kohichi, NOHARA Masaru, SANO Naruhisa

JAXA has started the research on the Advanced Solid fuel Rocket Launcher (ASRL). IHI Aerospace has been selected as the system integration company of the ASRL development. The ASRL is a successor to the M-V rocket, which has the top performance of the solid rocket launcher in the world. Moreover, the operational performance and cost reduction are targeted mainly in the ASRL development. Small satellites for space science or worldwatch technology demonstration are planned by JAXA and USEF. The ASRL is designed to be best for the small satellite users who have various special demands. The paper describes the summary of general ideas and the development plan of ASRL.

6. Development of the GX Launch Vehicle, New Medium Class Launch Vehicle of Japan

IZUMIYAMA Taku, SHISA Akira, KOBAYASHI Kenji

The GX launch vehicle is a medium class launch vehicle, objectives of which are to support launching demand for medium-size satellite flexibly, to be back-up for the national main space transportation system, and to establish LNG propulsion system technology. This paper describes outline of the GX program such as its configuration, program merits including establishment of the LNG propulsion system, the main characteristics and its performance, etc. The future development concept of the GX is also described.

7. Development of Turbopump for LE-X Engine

MIZUNO Tsutomu, KOBAYASHI Satoshi, OGUCHI Hideo

The LE-X is a new cryogenic booster engine with high performance, high reliability, and low cost, which is designed for the next generation Japanese launch vehicle. It will be the first booster engine in the world with an expander cycle. In the designing process, the characteristics of a turbopump and other components can simultaneously be evaluated in engine system calculation with response surface models that have the characteristics of information of turbopump of various shapes. This paper reports the characteristics of LE-X engine, and baseline specifications of turbopump.

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