The results of the study on a future space transportation system, a flyback booster, is presented. The initial sizing of the rocket was conducted, and the following guidelines concerning the selection of its configurations are presented: (1) the speed increment allotment for the booster is aimed at less than 3,000 m/s in an ideal velocity when the rocket is on the premise that the booster returning to the launch site; (2) to minimize the rocket size, upgrading the upper stage structural efficiency is effective in designing the flyback booster; and (3) assuming and comparing four kinds of returning systems, it is deemed most prosperous to return in ballistic flight by re-igniting the booster immediately after upper stage separation. A study was conducted on winged and flare type (non-winged) bodies as examples based on the initial sizing data, and it was concluded that both types are feasible within the category of the existing design and materials.
Shouraigata Roketto No Kenkyuu: Furaibakku Basuta No Gainen Kentou (Conceptual Study on Future Space Transportation Systems. Part A: Conceptual Study of Flyback Booster)
1993
25 pages
Report
Keine Angabe
Englisch
Manned Spacecraft , Rocket Engines & Motors , Booster rocket engines , Japanese spacecraft , Reusable rocket engines , Rocket engine design , Flight paths , Hydrogen oxygen engines , Propulsion system performance , Recoverable launch vehicles , Reusable spacecraft , Spacecraft configurations , Spacecraft performance , Specifications , Foreign technology