Conceptual study of vertical-launch type flyback booster (Rocket plane)

Shigeya Mito, Koichi Yonemoto

Research output: Contribution to conferencePaper

Abstract

Vertical-launch type flyback booster named “Rocket Plane” by National Space Development Agency (NASDA) of Japan has been studied as one of the new concepts for near future Japanese space transportation system that can supplement needs of large earth-to-orbit payload injection post H-II rocket and HOPE (H-II Orbiting Plane). This paper presents the recent results of feasibility study under the contract of NASDA, which focused its feasibility mainly on system sizing and mission flight profile. The primary design requirement is that the flyback booster is reusable to reduce operation cost, and employs the experiences obtained by H-II rocket development as many as possible in order to minimize development cost. This flyback booster transportation system aims at a payload capability of more than 30 Mg into circular orbit of 250 km altitude without using breakthrough technologies. The major design parameters are upper stage configuration (optimized upper stage or H-II rocket stage), cryogenic propellant (LOX/LH2 or LOX/LCH4), auxiliary solid rocket motor and optional cruising engine. It can be concluded that the present conceptual study comes up to a fruitful discussion whether this type of space transportation system can act as a go-between for final aerospace plane of Japan.

Original languageEnglish
Publication statusPublished - 1 Jan 1992
Event4th Symposium on Multidisciplinary Analysis and Optimization, 1992 - Cleveland, United States
Duration: 21 Sep 199223 Sep 1992

Conference

Conference4th Symposium on Multidisciplinary Analysis and Optimization, 1992
CountryUnited States
CityCleveland
Period21/09/9223/09/92

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Mito, S., & Yonemoto, K. (1992). Conceptual study of vertical-launch type flyback booster (Rocket plane). Paper presented at 4th Symposium on Multidisciplinary Analysis and Optimization, 1992, Cleveland, United States.