Niezwykle jasno wyłożyłeś tę myśl
!
A swoją drogę cytuję jednak tabelkę z osiągami obu wersji CZ-9, ale nie chce mi się tłumaczyć na polski:
Configurations Studies: Concept-A* / Concept-BLaunch thrust metric ton’s: 5,200 / 5,000
Payload capacity - metric tons mass: 130 / 133
Maximum overall booster diameter meters: 15.70 / 15.70
Maximum design height for study meters: 98 / 101-108
Launch mass metric tons: 4,100 / 4,150
Strap-on boosters: 4 – liquid Kerosene, Lox boosters / 4 five segment solid propellant motors
Strap-on boosters diameter meters: 3.35 / 3.35
Strap-on booster thrust metric tons: 1 x 650 x 4 = 2,600, engine YF-650 / 1 x 1,000, x 4 = 4,000 Solid Motor
Strap-on propellant mass metric tons: 1 x 320 x 4= 1,280 / 1 x 575 4 =2,300
Core Stages diameter meters: 8-9 / 8-9
Core first stage metric tons thrust, propellants and engines: 4 x 650 = 2,600, YF-650 engines, Kerosene, Lox propellants / 5 x 200 = 1,000 YF-220 engines, Lox, Hydrogen propellants
Core first stage propellant mass metric tons: 1,756 / 1,000
Core second stage maximum diameters meters: 8-9 / 8-9
Core second stage thrust metric tons and propellants: 2 x 200 = 400, Lox, Hydrogen propellants / 1 x 200 = 200, YF-220 engine, Lox, Hydrogen
Core second stage propellant mass metric tons: 500 / 200
Źródło:
http://www.americaspace.org/?p=22881