Initial sizing of fly-back boosters was conducted on the assumption that the booster returns to the launch site, and the following guidelines concerning configuration selection were obtained: (1) when the booster return is a prerequisite, speed increment allocation to the booster is targeted at less than 3,000 m/sec; (2) to reduce the overall rocket size, increasing the upper-stage structural efficiency is more effective than improving the booster structural efficiency in fly-back booster design; and (3) as the result of comparing four systems for return, a system to re-ignite the booster just after separating the upper-stage and return by ballistic flight is deemed to be most prosperous. After studying two types of systems, winged type returning by ballistic flight and flare type (non-winged), both types are feasible by the existing design and materials.
Furai Bakku Busuta No Gainen Kentou (Conceptual Study of Fly-Back Booster)
1992
14 pages
Report
Keine Angabe
Englisch
Space Launch Vehicles & Support Equipment , Reusable launch vehicles , Japanese spacecraft , Spacecraft configurations , Spacecraft design , Booster rocket engines , Flight characteristics , Flight paths , Liquid oxygen , Liquid propellant rocket engines , Methane , Return to earth space flight , Rocket engine design , Spacecraft performance , Spacecraft reentry , Foreign technology