Abstract This paper investigates the launch capability of the SS-520 as a CubeSat launch vehicle. The SS-520 was developed by JAXA originally as a two-stage, spin-stabilized, solid-propellant sounding rocket. With less than 2.6 tons in total mass and 10 m in length, the SS-520-5 successfully launched a single 3U-sized CubeSat into orbit on February 3, 2018. The SS-520-5 obtained its capability as a CubeSat launch vehicle by installing a 3 rd stage solid motor in addition to the RCS between the 1 st and 2 nd stages. However, its launch capability was limited due to its rocket system configuration. In order to pursue the SS-520's launch capability, two effective modifications from the SS-520-5 are proposed: thrust enhancement of the 1 st stage motor and installation of an additional RCS between the 2 nd and 3 rd stages. The framework of launch capability analysis is established by a multi-objective genetic algorithm (MOGA), where its two objectives are selected as the altitudes of perigee and apogee. The analysis reveals that the two proposed modifications to the SS-520-5 work effectively but differently. The 10% increase of the 1 st stage enhancement is particularly effective when the target altitude of perigee is low (e.g., 200 km), whereas the installment of the additional RCS with 30 kg increases accessibility to a much higher altitude of perigee, even to circular orbit reaching altitudes of 550 km for a 1U-sized CubeSat and 280 km for a 6U-sized CubeSat. The simultaneous application of both modifications would result in launch capability able to deliver a 10-kg payload. From a more general perspective, the results in this paper suggest that it is possible for a very small launch vehicle (VSLV) of the 3-ton class and 10 m in length to deliver a 10-kg-class payload into low Earth orbit.

    Highlights Two realistic modifications from the SS-520-5 are proposed as a CubeSat launcher. Thrust enhancement of the lower motor and additional RCS installation are effective. Each modification enables carrying a payload nearly twice as heavy. If both are applied simultaneously, it can deliver a 10-kg payload.


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    Titel :

    Sounding rocket SS-520 as a CubeSat launch vehicle


    Beteiligte:
    Ito, T. (Autor:in) / Yamamoto, T. (Autor:in) / Nakamura, T. (Autor:in) / Habu, H. (Autor:in) / Ohtsuka, H. (Autor:in)

    Erschienen in:

    Acta Astronautica ; 170 ; 206-223


    Erscheinungsdatum :

    2019-10-05


    Format / Umfang :

    18 pages




    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Elektronische Ressource


    Sprache :

    Englisch





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