Evaluation of frictional drag increase in M-34 extensible nozzle
- Paper number
IAC-06-C4.P.1.02
- Author
Dr. Shinsuke Takeuchi, Japan Aerospace Exploration Agency (JAXA)/ISAS, Japan
- Coauthor
Prof. Toru Shimada, Japan Aerospace Exploration Agency (JAXA)/ISAS, Japan
- Coauthor
Mr. Masatoshi Nakamura, IHI Aerospace Co, Ltd., Japan
- Coauthor
Ms. Kyoko Nagayama, IHI Aerospace Co, Ltd., Japan
- Coauthor
Mr. Katsunori Chinen, IHI Aerospace Co, Ltd., Japan
- Year
2006
- Abstract
The third stage propulsion system, M-34, of Mu-V launch vehicle of Japan Aerospace Exploration Agency (JAXA) is a high performance solid rocket motor which has composite filament winding case and extensible nozzle. In a pre-flight (assembling) operation of Mu-V-6, which was launched in July 2005, we found the increase of drag in extension of the nozzle during the function test and made many basic examinations which evaluate the increase and investigate the reason. In the result we determined to exchange the nozzle with the one prepared for next Mu-V-8 in order to make product assurance doubly sure and continued examinations and evaluation. At last we found that the clearance and compression of the gasket, which prevents the leak of high temperature combustion gas through the slit between fixed and extended part of the nozzle, have large effect on the drag force in nozzle extension and modified the nozzle to reuse in the next Mu-V-8 instead of exchanging the nozzle. After modification we attached the nozzle to Mu-V-8 and launched it successfully in February 2006. This paper shows the process and result of examinations, the method to modify the nozzle, and availability for the reuse of the nozzle. This paper also includes the basic description and development and operational history of the extensible nozzle of M-34.
- Abstract document
- Manuscript document
IAC-06-C4.P.1.02.pdf (🔒 authorized access only).
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