Small-Lift Launch Vehicle Design
This launch vehicle was the culmination of several iterative design projects for AE 498: Space Launch Vehicle Systems. Through my work, I developed a two-stage small-lift launch vehicle for 1000 kg LEO payload with RP-1/Keralox propulsion. This page highlights the systems-level analysis and trajectory optimization that I conducted.
All constraints and considerations came from the Don Edberg book.
Trajectory Optimization Calculations
load calculations
I conducted systems-level analysis for vehicle sizing, propellant requirements, flight loads, structural stress, and trajectory optimization, and the project provided end-to-end experience in launch vehicle design—from propellant choice and stage sizing to trajectory and structural margins—reflecting my interest in complex, multi-domain engineering systems.