space debris re-entty calc
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Updated
Dec 7, 2019 - C++
space debris re-entty calc
Spacecraft atmospheric entry simulations using Python
Software development and engineering project for solving the spacecraft-moon-Earth three-body problem.
Full-ephemeris dynamics integration in Julia
An entry into to the world of spacecraft trajectory design and optimization. The problem statement is to capture two planetary systems with one launch from earth, which means the initial part of the trajectory of a spacecraft which separates into two has to be the same. After separation, one half of the spacecraft will capture Saturn after takin…
Simulate the orbital motion for a CubeSat (HokieNav) as part of a senior design project with VT's ECE department sponsored by The Aerospace Corporation.
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A library to track spacecraft, written in C/C++
A tool for planning flights from one celestial body in KSP to another
Fast, accessible, accurate orbit propagator for spacecraft
A proof-of-concept for building Orbiter spaceflight simulator addons in Rust
Trajectory optimization tools for lunar missions
Capstone project for Spacecraft Dynamics and Control course
Multi-rendezvous Spacecraft Trajectory Optimization with Beam P-ACO
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