spacecraft-trajectories

There are 17 repositories under spacecraft-trajectories topic.

  • lfsimoes/beam_paco__gtoc5

    Multi-rendezvous Spacecraft Trajectory Optimization with Beam P-ACO

    Language:Jupyter Notebook27407

  • thomasantony/orbiter-rs

    A proof-of-concept for building Orbiter spaceflight simulator addons in Rust

    Language:Rust13202

  • amyinorbit/reentry.py

    Spacecraft atmospheric entry simulations using Python

    Language:Python9300

  • Ornstein89/paraview_orbit

    ParaView template project for orbital data visualization (orbits, trajectory points, ground station field of view)

    Language:Python9100

  • cauabernardino/mars_mission

    Capstone project for Spacecraft Dynamics and Control course

    Language:Python5102

  • dcf21/satellite_log

    A quick-and-dirty SQL database for storing the historical orbital elements of satellites, including a script for trawling data from Celestrak and Space Track to populate the database.

    Language:Python4301

  • utat-ss/hypernova

    Fast, accessible, accurate orbit propagator for spacecraft

    Language:C4011

  • motokimura/SCTracker

    A library to track spacecraft, written in C/C++

    Language:C++3201
  • trajectorize

    itchono/trajectorize

    A tool for planning flights from one celestial body in KSP to another

    Language:Python2151

  • Jual6332/Geospatial-Software-Design-Matlab

    Software development and engineering project for solving the spacecraft-moon-Earth three-body problem.

    Language:MATLAB2330

  • openlunar/trajectory

    Trajectory optimization tools for lunar missions

    Language:HCL2252

  • resuldagdanov/voyage-to-mars

    Designing an interplanetary trajectory to planet Mars :full_moon:

    Language:MATLAB2200

  • JulesGL/polimi_SGN

    Spacecraft Guidance and Navigation Assignments from Politecnico Di Milano 2022

    Language:MATLAB10

  • Nomurad/reentry_deb

    space debris re-entty calc

    Language:C++1100

  • SalianJr/Bachelor_Thesis

    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 taking a fly-by from Jupiter, whereas the other half will capture Jupiter. Possible location of separation of the two halves of the spacecraft ( in terms of days from launch ) is found out.

    Language:Python1110

  • 3allan/HokieNav-Orbit

    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.

    Language:MATLAB0100

  • Yuricst/FullEphemerisPropagator.jl

    Full-ephemeris dynamics integration in Julia

    Language:Jupyter Notebook10