🌏 📡 🌏 📡 LEOGPS - Satellite Navigation with GPS on Python!

这个算法用于无人机群避障一个加入机群的无人机，算法分为两种思路：(1)加入者的路径规划主动机动规避编队机群、(2)编队微调避让加入者。目前只做了第一种思路。唯一已知信息是原机群的运动轨迹F(x，y，z，t)|each plane，对于第一种思路：对于补位飞机唯一的输入参数是无人机编队时间帧和每架飞机的对应位置，即F(x，y，z，t)|each plane，输出参数是规划的单条路径。对于第二种思路：让正常飞行的编队可以保持在其原始轨迹周围(即，边界条件，规避机动范围<Δv球)，补位无人机穿越他们的空隙到达目标位置，输出为需要避碰的其他无人机的机动向量。第一种思路采用三维A*+分段局部规划

An open-source ROS 2 bridge for the Basilisk astrodynamics simulator enabling real-time spacecraft simulation and reusable autonomy software across simulation and hardware setups.

Interactive spacecraft rendezvous & proximity operations mission planner with 3D visualization. Implements Koenig-Guffanti-D'Amico (2017) state transition matrices for ROE propagation with J2 and drag perturbations.

Software for Absolute and Relative Motion Orbit Theories with Zonal and Tesseral Gravitational Harmonics

A ROS 2-based MPC controller for spacecraft control using Basilisk via the Basilisk-ROS 2 Bridge.

S2E user side repository for Formation Flying study

Astrodynamics toolkit for rendezvous and proximity operations (RPO) mission planning in Rust

Python SDK for ArduPilot multi-drone swarm orchestration. Formations, missions, async telemetry, SITL testing.

Comparing relative motion models for spacecraft formation flying in eccentric orbits: Wang-Yang closed-form, EROE linear plant, and Cowell truth propagator with J2/SRP perturbations and passive safety screening.

Closed-form impulsive control for spacecraft formation flying in eccentric orbits: Chernick-D'Amico controller implementation, J2/SRP perturbation analysis, Monte Carlo robustness, and boundedness assessment using EROE dynamics.

Minimum-Δv impulsive maneuver planning for spacecraft relative orbits - a finite-difference-verified Rust port of the Koenig & D'Amico (IEEE TAC 2020) fuel-optimal impulsive control algorithm.

Relative orbit analysis of TerraSAR-X and TanDEM-X using the Homogeneous Hill (Clohessy-Wiltshire) equations.

TypeScript library for spacecraft relative motion propagation. Implements Yamanaka-Ankersen (elliptical orbits) and Clohessy-Wiltshire (circular orbits) state transition matrices with RIC/LVLH frame support.