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IO.Astrodynamics.Net

Presentation

IO.Astrodynamics.Net is a .Net astrodynamics framework based on cspice toolkit(N 67) developped by the JPL and IO.Astrodynamics native library, it provides the best of both worlds :

C++ Velocity + .Net productivity = ❤️

This framework provides the following features :

• Work with JPL Spice kernels and stars
• Export simulation to Cosmographia
• PDS Archive management
  • Generate archive from object
  • Generate object from archive
  • Validate archive from Xml schemas
• Spacecraft propagator
  • Geopotentials model (Earth only)
  • Simplified atmospheric model (Earth and Mars only)
  • Solar radiation pressure
  • N-body perturbation
  • Impulsive maneuvers
  • Fuel balance
• Small body propagator
  • Geopotentials model (Earth only)
  • Simplified atmospheric model (Earth and Mars only)
  • Solar radiation pressure
  • N-body perturbation
• Compute and convert orbital parameters
  • State vector
  • Two lines elements
  • Equinoctial
  • Keplerian elements
• Compute and convert coordinates system
  • Equatorial
  • Horizontal
  • Planetodetic
  • Planetodentric
• Frame transformation
  • ICRF / J2000
  • Ecliptic J2000
  • Ecliptic B1950
  • Galactic
  • B1950
  • FK4
  • Body fixed frames and ITRF93 (High accuracy earth fixed frame)
• Configure spacecraft
  • Clock
  • Fuel tank
  • Engines
  • Instrument
• Impulse maneuvers :
  • Apogee height
  • Perigee height
  • Plane alignment
  • Combined maneuver
  • Apsidal alignment
  • Phasing
• Attitudes
  • Instrument pointing toward an object
  • Nadir
  • Zenith
  • Prograde
  • Retrograde
  • Zenith
• Surface site on any celestial body
• Evaluate launch opportunities
• Use or convert different time referential (Calendar, Julian, seconds from J2000, TDB, UTC, Local)
• Get celestial body information based on Naif kernels
• Find time windows based on distance constraints from spacecraft, celestial body or ground site
• Find time windows based on occultation constraints from spacecraft, celestial body or ground site
• Find time windows based on coordinate constraints from spacecraft, celestial body or ground site
• Find time windows based on illumination constraints from ground site.
• Find time windows when an object is in instrument field of view.
• Manipulate kernel files
• Math tools
  • Vector
  • Matrix
  • Quaternion
  • Lagrange interpolation
• Use the Framework through CLI (Command line interface)
  • Propagate small body and visualize it with Cosmographia
  • Sub observer point
  • Angular separation
  • Orientation
  • Orbital parameters converter
  • Frame converter
  • Time converter
  • Celestial body information
  • Find time windows from coordinate constraint
  • Find time windows from distance constraint
  • Find time windows from occultation constraint
  • Find time windows from field of view constraint
  • Find time windows from illumination constraint

Concept

IO.Astrodynamics is based on Spice concept

To work, this framework needs data (Ephemeris, Planetary constants, leap seconds, mission data, ...) these data can be found here

To use these data in the framework, just call this function :

//Load required kernels for computation
API.Instance.LoadKernels(new DirectoryInfo("<your path containing data>"));

When you use the propagation functionalities, you will have to provide an output path to reuse, if necessary, the data generated in another software.

Installation - Framework

This package is hosted by Nuget here. You can install it in your project with this command :

dotnet add package IO.Astrodynamics

Installation - CLI

dotnet tool install --global IO.Astrodynamics.CLI

Documentation about CLI here.

Quick start

//LET'S GO !
//In this example we'll get the moon state vector in ICRF frame relative to the earth without aberration

//Load required kernels for computation
API.Instance.LoadKernels(new DirectoryInfo("/home/spacer/Sources/SDK.Net/IO.Astrodynamics.Tests/Data/SolarSystem"));

//Create moon object
var moon = new CelestialBody(PlanetsAndMoons.MOON.NaifId);

//Get moon ephemeris
var ephemeris = moon.GetEphemeris(DateTimeExtension.J2000, moon.InitialOrbitalParameters.CenterOfMotion, Frame.ICRF, Aberration.None).ToStateVector();

//Display some informations
Console.WriteLine($"Position : {ephemeris.Position.ToString()}");
Console.WriteLine($"Velocity : {ephemeris.Velocity.ToString()}");

//You should have the following result : 
// Position : Vector3 { X = -291608384.6334355, Y = -266716833.39423338, Z = -76102487.09990202 }
// Velocity : Vector3 { X = 643.5313877190328, Y = -666.0876840916304, Z = -301.32570498227307 }

You can find more advanced examples here

Documentation

For more information you can read the wiki