Simulate rocket staging, gravity turn pitch profiles, delta-V budgets, and ground-track constellation deployments for low-Earth orbit missions.
Launches from California (Vandenberg Space Force Base) utilize southern launch azimuths over the Pacific Ocean to achieve polar and high-inclination orbits safely without overland overflight hazards. The vehicle initiates a pitch maneuver shortly after clearing the launch tower, allowing aerodynamic flow and gravity to pull the velocity vector down toward the horizontal.
Reaching Low Earth Orbit (LEO) demands ~9.1 to 9.4 km/s of equivalent delta-V. This accounts for orbital kinetic energy (~7.8 km/s), potential energy climb (~0.5 km/s), gravity losses (~1.0 km/s), and atmospheric drag (~0.15 km/s). Stage 1 accelerates the payload to hypersonic speeds before separation, after which the vacuum-optimized Stage 2 inserts the satellites into an elliptical parking orbit.
Flat-pack satellite stacks (such as 27 Starlink units) are released in Low Earth Orbit using mechanical retention bands. Natural orbital dynamics and slight differential drag cause the satellites to slowly drift apart into a characteristic "train" before individual onboard ion propulsion thrusters raise each spacecraft into its designated operational orbital plane.