0.0 mi
0.0 km altitude
GRAVITY SENSOR
10-mile checkpoint: 0 mi
Natural Earth gravity: 9.820 m/s²
Hypothesis effective gravity: 7.820 m/s²
10-mile checkpoint: 0 mi
Natural Earth gravity: 9.820 m/s²
Hypothesis effective gravity: 7.820 m/s²
CREW GRAVITY — LIVE
Hypothesis crew load: 1.31 g
Crew load reduction: 0.20 g
1.51 g
Baseline crew load:
1.51 gHypothesis crew load: 1.31 g
Crew load reduction: 0.20 g
ENVIRONMENT
Region: LOWER ATMOSPHERE
Density: 1.225 kg/m³
Drag: 0.00 kN
Region: LOWER ATMOSPHERE
Density: 1.225 kg/m³
Drag: 0.00 kN
VEHICLE
45,000 kg
Wet Mass
45,000 kg
Dry Mass
25,000 kg
Propellant
20,000 kg
ASSUMED INPUT
EARTH GRAVITY — LIVE
9.820 m/s²
Surface g₀
9.820 m/s²
Gravity Remaining
100.0%
Checkpoint
0 mi
ESTABLISHED EQUATION
ATMOSPHERE → VACUUM
1.225 kg/m³
Region
LOWER ATMOSPHERE
Drag
0.00 kN
Dynamic Pressure
0.00 kPa
SIMPLIFIED MODEL
CREW GRAVITY — LIVE
1.51 g
Baseline Crew Load
1.51 g
Hypothesis Crew Load
1.31 g
Load Reduction
0.20 g
SIMPLIFIED POWERED-FLIGHT LOAD
BASELINE THRUST — LIVE
666.9 kN
Mass Flow
37.05 kg/s
Velocity
0 m/s
Commanded Net a
5.00 m/s²
CALCULATED
FISSION / THERMAL
1.50 GW
Thermal Exhaust
9 km/s
Final Exhaust
18 km/s
Isp
≈1,835 s
CONCEPT / INPUT
EM PLASMA / MAGNETIC
4.50 GW
Magnetic Field
10 T
Magnetic Pressure
39.79 MPa
Field Energy
397.9 MJ
IDEALIZED EM CALCULATION
SPACETIME HYPOTHESIS
aΦ = 2.00 m/s²
Actual Animated Flight
aΦ = 0
Natural Earth g
9.820
Hypothesis Effective g
7.820
HYPOTHETICAL / UNVERIFIED
GRAVITY-REDUCTION BENEFIT
90.0 kN saved
Normal Thrust
666.9 kN
Hypothesis Thrust
576.9 kN
Fuel Flow Saved
5.00 kg/s
CONDITIONAL COMPARISON
ENERGY
6.00 GW
Thermal KE Rate
1.50 GW
EM KE Increment
4.50 GW
Jet Energy Used
0 GJ
IDEAL EXHAUST KINETIC ENERGY
MODEL / RELATIVITY
1-D CLASSICAL
Trajectory
Vertical Only
Relativistic Dynamics
Not Applied
Current v/c
0
MODEL ASSUMPTION
MISSION READINGS
0.0%
Status
READY
Elapsed Time
0 s
Propellant Used
0 kg
SIMULATION