v0.8.0 - Orbital Dynamics & Interplanetary Mission Design Engine

Overview

Initial milestone release of the NewtonianPropagator orbital mechanics and trajectory design suite. This release provides numerical propagation tools ranging from perturbed low-Earth orbits to multi-leg interplanetary flyby trajectories.

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Key Features & Scenarios

• High-Fidelity LEO Propagation: RK4 numerical integrator supporting Earth $J_2$ oblateness, atmospheric drag (exponential density model), and solar radiation pressure (SRP).
• Low-Thrust Trajectory Dynamics: Edelbaum analytical velocity estimators and continuous tangent low-thrust spiral propagators.
• Formation Flying & Swarm Dynamics: Clohessy-Wiltshire (HCW) linearized equations of motion for multi-agent spacecraft relative motion.
• Cislunar Dynamics (CR3BP): Circular Restricted Three-Body Problem equations of motion, Jacobi constant conservation tracking, analytical $L_1$ - $L_5$ Lagrange point solvers, and Apollo-style free-return trajectory modeling.
• Interplanetary Trajectory Design:
  • Lambert boundary-value problem solver (Universal Variables).
  • Earth–Mars launch window porkchop plot generator.
  • Multi-leg patched-conic gravity assist optimizer (e.g., Earth–Venus–Mars transfer).

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Verification

• Full unit test suite covering integrators, coordinate frames, Lambert solvers, and gravity assist turn angles (tests/test_*.py).