Flight Time T+ 00:00 PRE-LAUNCH PAD 4E
Altitude 0.0 km Target: 510 km
Velocity 0 m/s Mach 0.00
Dynamic Pressure (q) 0.0 kPa Nominal
Downrange 0.0 km Pitch: 90.0°
Mission Event Sequence
T+00:00Liftoff SLC-4E
T+00:35Pitch Maneuver
T+01:12Max-Q Dynamic Q
T+02:28MECO (Stg 1 Cutoff)
T+02:32Stage Separation
T+03:15Fairing Separation
T+07:45Booster Landing
T+08:35SECO-1 Parking Orbit
T+00:00
Peak Dynamic Pressure 32.8 kPa Occurred at T+72s @ 12.4 km
MECO Staging Velocity 2,145 m/s Mach 6.8 @ 68.2 km alt
Second Stage $\Delta V$ Total 9,340 m/s Gravity loss: ~1,120 m/s
Final Insertion Orbit 512 × 508 km Inclination: 97.4° Polar SSO
Simulation ready. Drag scrubber or click Play to analyze launch profile.

Why Vandenberg Space Force Base (SLC-4E)?

Unlike Cape Canaveral in Florida which launches eastward over the Atlantic to take advantage of Earth's rotational velocity for prograde equatorial orbits, Space Launch Complex 4 East (SLC-4E) at Vandenberg in California opens directly south over the open Pacific Ocean.

This provides a clear launch corridor for Polar and Sun-Synchronous Orbits (SSO), essential for optical reconnaissance, earth observation, and national security missions (such as USSF-385) without overflying populated landmasses during initial staging.

Ascent Physics & Gravity Turn Equations

This flight computer models orbital rocket dynamics through numerical integration:

  • Aerodynamic Drag: $F_{\text{drag}} = \frac{1}{2} \rho(h) v^2 C_d A$, where atmospheric density decays exponentially with scale height $H \approx 7.5\text{ km}$.
  • Max-Q Bucket: Throttling back engines near Mach 1.0–1.4 minimizes peak dynamic pressure $q = \frac{1}{2} \rho v^2$ below structural safety limits.
  • Gravity Turn: After an initial pitch kick at ~1.3 km, the rocket tilts naturally under gravitational torque $\dot{\theta} = -\frac{g(h)}{v}\sin(\theta)$, conserving steering fuel.
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