CASE STUDY
2022 Orbital Mechanics
PROPAGATING SPACECRAFT TRAJECTORY BY ΔT
Orbital Mechanics MATLAB Numerical Methods Astrodynamics
Challenge
Accurately predicting spacecraft position and velocity over time requires robust numerical integration and perturbation modeling.
Approach
Implemented and compared multiple numerical integration schemes (RK4, etc.) for the two-body problem, adding perturbation models incrementally.
Outcome
Validated propagator achieving sub-kilometer accuracy over multi-orbit timeframes, with clear comparison of integration method performance.
Duration
3 months
Tools
MATLAB Numerical Methods Orbital Mechanics
Overview
This project explored spacecraft trajectory propagation using various numerical integration methods. The goal was to accurately predict spacecraft position and velocity over time intervals (Δt).
Technical Approach
- Implementation of numerical integration schemes (RK4, etc.)
- Two-body problem analysis
- Perturbation modeling
- MATLAB simulation development
Key Learnings
Understanding trajectory propagation is fundamental to:
- Mission planning and design
- Orbit determination
- Rendezvous maneuver calculations
- Satellite constellation management