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MIT](https://img.shields.io/badge/License-MIT-blue.svg)](https://opensource.org/licenses/MIT)\n[![satelles/test](https://github.com/michealroberts/satelles/actions/workflows/test.yml/badge.svg)](https://github.com/michealroberts/satelles/actions/workflows/test.yml)\n\n# Satelles\n\nModern, type-safe, zero-dependency python library for TLE, OMM et al. handling and orbit propagation to accurately locate your satellites in the sky.\n\n## Installation\n\n```bash\nuv add satelles\n```\n\nor\n\nusing your preferred environment / package manager of choice, e.g., `poetry`, `conda` or `pip`:\n\n```bash\npip install satelles\n```\n\n```bash\npoetry add satelles\n```\n\n```bash\nconda install satelles\n```\n\n## Usage\n\n```python\nfrom datetime import datetime, timezone\n\nfrom satelles import TLE\n\nissTLE: str = \"\"\"        \n  1 25544U 98067A   20062.59097222  .00016717  00000-0  10270-3 0  9006\n  2 25544  51.6442 147.1064 0004607  95.6506 329.8285 15.49249062  2423\n\"\"\"\n\nsatellite = TLE(tle_string=issTLE).as_satellite()\n\nsatellite.at(when=datetime(2021, 5, 15, 0, 0, 0, tzinfo=timezone.utc))\n\n# Get the Earth Centric Inertial (ECI) coordinate of the satellite at the given time:\neci = satellite.eci_coordinate\n\n# Get the Equatorial Coordinate of the satellite at the given time:\nequatorial = satellite.equatorial_coordinate\n...\n```\n\nAs the API is fully typed, you can use your IDE's autocompletion to see all the available methods and properties.\n\nWe have also provided further usage examples in the [examples](./examples) directory.\n\n## Milestones\n\n- [X] Type-safe modern 3.6+ Python\n- [X] Fully unit tested\n- [X] Simpler API using Pydantic base models for validation\n- [X] Zero-external dependencies (pure Python 3.6+ with no external C/C++ dependencies)\n- [ ] Example API usage\n- [X] Fully supported Two-Line Element (TLE) parsing and operations\n- [ ] Fully supported Orbital Mean Elements Message (OMM) parsing and operations\n- [ ] Fully supported TLE to OMM conversion\n- [X] Fully supported Earth Centric Inertial (ECI) to Equatorial Coordinate System (ECS) conversion\n- [X] Fully supported Earth Centric Inertial (ECI) to Topocentric Coordinate System (TCS) conversion\n- [ ] Fully supported SPG4-XP propagation from TLE or OMM\n- [X] Fully supported symplectic Verlet numerical propagation\n- [X] Fully supported Runge-Kutta 4th order numerical propagation\n\n---\n\n### License\n\nThis project is licensed under the terms of the MIT license.\n","project_url":"https://awesome.ecosyste.ms/api/v1/projects/github.com%2Fmichealroberts%2Fsatelles","html_url":"https://awesome.ecosyste.ms/projects/github.com%2Fmichealroberts%2Fsatelles","lists_url":"https://awesome.ecosyste.ms/api/v1/projects/github.com%2Fmichealroberts%2Fsatelles/lists"}