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Rocket Propulsion & Variable Mass Lab

Tsiolkovsky Engine

Variable Mass Dynamics & Altitude Simulation

UDVASH ACADEMIC

Exhaust Velocity (v_e)

With respect to rocket frame

2,500 m/s

500 m/s4,500 m/s

Burn Rate (dm/dt) 120 kg/s

5 kg/s500 kg/s

Fuel Mass (m_fuel) 2,500 kg

100 kg5,000 kg

Dry Mass (m_dry) 300 kg

50 kg1,000 kg

Gravitational Field (g)

Show Thrust & Weight Vectors v-t Graph Overlay Particle Smoke Trails Audio Engine Effects

Speed:

Thrust Force Law F = v_e·(dm/dt)

F_thrust = v_e · (dm/dt)

Calculated Thrust: 300.00 kN

Tsiolkovsky Equation v(t)

v(t) = v_e ln(m₀/m) - gt

Current Velocity: 0.00 m/s

Instantaneous Accel a(t)

a(t) = (F_thrust - mg) / m

Current Accel: 0.00 m/s²

Time (t)

0.00 s

Total Mass (m)

2,800 kg

Altitude (h)

0.00 m

Fuel Level

100%

READY FOR LAUNCH