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 stage solid motor in addition to the RCS between the and 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 stage motor and installation of an additional RCS between the and 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 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.
Sounding rocket SS-520 as a CubeSat launch vehicle
Acta Astronautica ; 170 ; 206-223
2019-10-05
18 pages
Aufsatz (Zeitschrift)
Elektronische Ressource
Englisch
Effect of launch angle on sounding rocket trajectories.
AIAA | 1968
|The Facilities at Chinese Hainan Sounding Rocket Launch Site
British Library Conference Proceedings | 2013
|Recent CubeSat Launch Experiences on U.S. Launch Vehicles
British Library Conference Proceedings | 2011
|