Considerations on vehicle design criteria for space tourism

• Published in: Acta astronautica 1995, Vol.37, p.223-237
• Main Authors: Isozaki, Kohki, Taniuchi, Akira, Yonemoto, Koichi, Kikukawa, Hiroshige, Maruyama, Tomoko
• Format: Article
• Language: English
• ISSN: 0094-5765; 1879-2030
• DOI: 10.1016/0094-5765(95)00088-H

The transportation research committee of JRS (Japanese Rocket Society) has begun conceptual design of vertical takeoff and landing fully reusable SSTO (Single Stage to Orbit) rocket type vehicle as a standard vehicle model for space tourism. The design criteria of the vehicle have paid most attention to the requirements of service to meet space tour amusement. The standard vehicle, which has 22m body length and weighs about 550 tons at takeoff, can provide attractive tours of 24 hours maximum for 50 passengers into the low earth orbit with a variety of space flight pleasures such as experience of weightlessness and earth sightseeing. Within the reach of our near future rocket technology, the design utilizes MMC, CF Epy and Ti Mw advanced materials. The twelve LOX/LH2 engines consist of two nozzle types, which can be throttled and gimbaled during the whole mission time, perform vertical launch and tail-first reentry to final landing associated with aerodynamic control of body flaps within tolerable acceleration acting on passengers.