Vehicle Configuration
STG-1 TANK & ENGINE
Structural Dry Mass
25,000 kg
Tanks, airframe, fairings, and avionics. Less mass saves delta-v but compromises hoop strength.
Propellant Load (LOX/RP-1)
420,000 kg
Governs burn duration and takeoff thrust-to-weight ratio (TWR).
Sea-Level Engine Thrust
7,500 kN
Total engine cluster force. High thrust drives rapid acceleration into thick lower atmosphere.
Specific Impulse (Isp)
311 s
Effective exhaust velocity efficiency (g₀ · Isp).
Structural Safety Margin
1.15x
Design factor above nominal load. Standard aerospace is 1.25x-1.40x. Below 1.20x risks atmospheric dynamic failure.
Engineering Law: Max-Q is the point where aeronaval drag pressure
q = 0.5 · ρ · v² peaks. If vehicle aerodynamic shear exceeds structural skin yield limits, catastrophic structural breakup occurs.
AERO SHEAR STRESS
0%
0 kPa
YIELD THRESHOLD
Awaiting Flight Test Ignition
Select an engineering configuration and fire the engines. Physics will evaluate structural safety margin against peak dynamic pressure (Max-Q).