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    • Micro-Lambda – A Micro Satellite Launch Vehicle Concept

    Paper number

    IAC-12,D2,7,9,x14822

    Author

    Mr. Seiji Matsuda, IHI Aerospace Co, Ltd., Japan

    Coauthor

    Mr. Kazuhiro Yagi, IHI Aerospace Co, Ltd., Japan

    Coauthor

    Mr. Yuichi Noguchi, Japan

    Coauthor

    Mr. Takashi Arime, IHI Aerospace Co, Ltd., Japan

    Coauthor

    Mr. Hideki Kanayama, CSP Japan, Inc., Japan

    Coauthor

    Mr. Yoichi Harada, Monohakobi Technology Institute, Japan, Japan

    Coauthor

    Mr. Takayoshi Fuji, Japan Space Systems (J-spacesystems), Japan

    Year

    2012

    Abstract
    Authors have studied a family of launch vehicles suitable for nano/micro/small payloads. “SpaceSpike” series, developed upon flight-proven Japanese sounding rocket SS-520 technology and current solid rocket motor products, are capable of lifting up to 20kg payload to low earth orbit. Authors also develop key technologies under ALSET (Air Launch System Enabling Technology) R\&D project to achieve a commercial air launch system for 150kg-class payload in the future.
These R\&D projects are aiming at providing ideal space access to small satellite users who have to rely on piggyback or share ride on a medium-heavy launch vehicle where they have a limited choice on launch window and orbit selection. Recent vigorous development of small space systems in US and Europe indicates 20-50kg class satellites and sophisticated 3-U and 6-U CubeSat constellations would be used for a wide variety of missions in the middle of 2010s. 
This paper will introduce a concept of $\mu$Lambda rocket capable of lifting 50kg payload to low earth orbit. $\mu$Lambda concept was initially developed in early 1990s as an upgrade of TR-1A microgravity research experiment rocket and $\mu$Lambda modernization study has recently been carried out. Trade studies to develop low-cost $\mu$Lambda launch system and its launch service business in a short period of time will be presented.
    Abstract document

    IAC-12,D2,7,9,x14822.brief.pdf

    Manuscript document

    IAC-12,D2,7,9,x14822.pdf (🔒 authorized access only).

    To get the manuscript, please contact IAF Secretariat.