The first system review on rocket systems composed of fly-back booster and expendable upper-stage rockets which are capable of launching a payload of 30 tons into low earth orbit is conducted. Three types of winged reusable fly-back booster systems are reviewed on the following premises: (1) payload launch capability of 30 tons; (2) start of operation in the years 2000 to 2010; (3) two-staged vertically launched vehicles; and (4) the core will be a LH2/LOX two-stage launch vehicle with LE-7A rocket engines. 2nd-stage fundamental features, booster stage aerodynamic design, aerodynamic performance estimates, booster stage sizing, orbit analysis, and system trade-off of the fly-back boosters are reviewed. Fly-back booster launch vehicle flight sequence, 2nd-stage features, configuration and characteristics of three types of rocket system, and fly-back booster orbit condition histories are outlined.
Furai Bakku Busuta (Fly-Back Boosters)
1991
13 pages
Report
No indication
English
Manned Spacecraft , Rocket Engines & Motors , Booster rocket engines , Propulsion system configurations , Reusable launch vehicles , Reusable rocket engines , Rocket engine design , Space transportation , Spacecraft design , Aerodynamic characteristics , Hydrogen oxygen engines , Multistage rocket vehicles , Orbital mechanics , Reusable spacecraft , Weight analysis , Foreign technology
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