Open-Starship Mission Control Visualizer

3-DoF State Vector

Time0.00 s

Altitude (z)500.0 m

Downrange (x)0.0 m

Vertical Speed−70.0 m/s

Horizontal Speed0.0 m/s

Pitch Angle90.0°

Pitch Rate0.0 °/s

Propulsion

Active Engines3

Throttle80%

Gimbal (actual)0.0°

TVC Lag0.00°

Prop remaining

25000 kg

Thrust (total)—

TWR—

Aerodynamics & Environment

Dyn. Pressure (q)—

Heat Flux—

Angle of Attack—

Wind Speed—

Discrete GustINACTIVE

Air Density—

Mechazilla Catch Gate

Catch StatusSTANDBY

Lateral Error—

Descent Rate—

Contact Load—

Altitude Profile

Vertical Speed Profile

Nose LOX Header Tank

Pendulum Angle0.0°

Inlet Submergence2.95 m

Gas Ingestion RiskSAFE

Inter-Tank CH₄ Header Tank

Pendulum Angle0.0°

Inlet Submergence2.40 m

Gas Ingestion RiskSAFE

Slosh Dynamics

Net Slosh Torque—

CoM Shift (lat)—

Overall RiskSAFE

BafflesENGAGED

LOX Free-Surface Angle

Orbital Transfer (Artemis III / Mars)

Transfer Target80,000 kg LOX

Flow Rate218.1 kg/s

Duration6.1 min

Bond Number262,559 ✓

Efficiency99.99%

Active Interlock Status

Hold-Down Gate

SAFE

Touchdown Gate

STANDBY

Actuator Alloc

NOMINAL

Engine-Out

NOMINAL

IIP Corridor

CLEAR

AFTS Destruct

NOT ARMED

Hold-Down Clamp Sensor

Vert. Acceleration0.01 m/s²

Vert. Displacement3.0 mm

Clamp Tension5.80 MN

Clamp margin

96%

Multi-Sensor Touchdown Gate

Radar Altimeter—

LiDAR Altimeter—

INS Integrated—

Fused Altitude—

Contact Force—

Plume BackscatterCLEAR

Debris Footprint (IIP)

IIP Downrange0.05 km

3σ Dispersion±1.50 km

Time to Impact—

CorridorSAFE

Incident Reference Library

Tianlong-3 (2024)

Test stand clamp failure → unauthorized liftoff. Mitigated by sub-20ms cutoff gate.

Deep Blue Nebula-1 (2024)

Radar altimeter plume corruption → premature engine cutoff. Mitigated by dual-condition gate.

Hyperbola-1 Y5 (2021)

Grid-fin jam → torque authority lost. Mitigated by pseudo-inverse RCS reallocation.

Zhuque-2 / Engine-Out

Flameout → asymmetric pitch. Mitigated by TVC CoM trim + burn reshaping.

Long March Corridors

Uncontrolled booster impacts on villages. Mitigated by real-time IIP geofencing.

Türksat Fleet Overview

Abort Detector

NOMINAL

Inclined Orbit

DRIFT

EOR Spiral

DAY 30

Wheel Desat

SAFE

XPI Guard

AUPC Boost

+2.9 dB

Upper-Stage Abort — Türksat 1A

Chamber Pressure34.5 / 35.0 bar

Turbopump RPM61,800 / 62,000

LOX Valve99%

GTO Velocity9,800 m/s

Shortfall400 m/s

Abort StatusNOT TRIGGERED

Inclined Orbit — Türksat 1B/1C

Inclination3.08°

N-S Drift Rate0.865°/yr

Pointing Error0.42°

Gain Loss−1.8 dB

Graveyard ΔV7.2 m/s

Disposal SafeYES (15 kg remain)

Electric Orbit Raising — Türksat 5A/5B

Elapsed Days30

Perigee Alt.—

Apogee Alt.—

Solar Array Power11,969 W

Radiation Loss−0.3%

EOR progress

18%

Reaction Wheel Desat — Türksat 6A

SRP Torque3.4 × 10⁻⁵ N·m

Hx momentum

18 N·m·s

Hy momentum

16 N·m·s

Pulse Duration8.3 s

Fuel Consumed0.7 g

Deadband SafeYES ±0.05°

Transponder Guard — Türksat 3A/4A/4B

XPI Isolation33.5 dB > 25 dB ✓

TWTA IBO3.0 dB (linear)

Rain Rate12 mm/hr

Rain Fade2.9 dB

AUPC Command+2.9 dB

IMD3 RiskLOW

Heat Shield Tile Inspection Summary

Total Tiles

600

Intact

569

Missing

Cracked

Chipped

Gap Risk

Intact rate

94.8%

Critical replacements0 (NONE this flight)

Hull Thermal Zone Risk Map

Aerothermal Environment

Peak Heat Flux—

Peak Dyn. Pressure—

Stagnation ZoneNose Cap (25m) ×2.5 risk

Highest Risk Zone—

Flap Hinge Acoustic×2.4 vibration factor

Real-Time Heat Flux