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Pricing

Start with the open-source framework at no cost. Upgrade to Professional for adaptive high-precision propagation and direct support, or use the SaaS tier to access the full engine from any language without managing kernels or infrastructure.

Community

Edition

Free

    • Velocity Verlet symplectic fixed-step integrator

    • EGM2008 geopotential gravity up to degree/order 70

    • Atmospheric drag with atmosphere-relative velocity (body co-rotation accounted for), dynamic mass ratio

    • Solar Radiation Pressure (cannonball model, Cr configurable, continuous shadow fraction handles penumbra, annular and total eclipse)

    • N-body perturbations (any combination of celestial bodies as point masses)

    • Dynamic mass tracking (fuel consumption across maneuvers)

    • Impulsive maneuver support during propagation

    • SGP4/SDP4 propagation from Two-Line Elements

    • State Vector (position + velocity)

    • Keplerian elements (mean and osculating)

    • Equinoctial elements

    • TLE (Two-Line Elements), parse, generate, fit from state vector

    • CCSDS OMM (Orbit Mean-elements Message)  read/write, NDM/XML format, bidirectional OMM ↔ TLE conversion

    • CCSDS OPM (Orbit Parameter Message), read/write with state vectors, Keplerian elements, covariance, maneuvers, user-defined parameters; bidirectional OPM ↔ Spacecraft

    • Apogee height change

    • Perigee height change

    • Plane alignment (inclination/RAAN)

    • Apsidal alignment (rotate line of apsides)

    • Phasing maneuver (orbital period adjustment)

    • Combined maneuver (simultaneous plane change + height change)

    • Lambert transfer solver (multi-revolution)

    • Launch window computation to reach a target orbit

    • Instrument pointing to target (ground site, celestial body)

    • Nadir pointing

    • Zenith pointing

    • Prograde pointing

    • Retrograde pointing

    • TRIAD attitude (fully constrained 3-DOF, eliminates roll ambiguity) — single instrument, dual instrument, or explicit vector overloads

    • Distance constraint windows

    • Occultation windows (spacecraft/body by another body)

    • Illumination condition windows (day/night/penumbra)

    • Coordinate constraint windows

    • Instrument Field-of-View windows (when a target enters/exits FoV)

    • Spacecraft definition (dry mass, fuel mass, sectional area, solar radiation coefficient)

    • Instruments (circular and rectangular FoV, boresight and reference vector)

    • Fuel tanks (capacity, initial fill)

    • Engines (Isp, thrust, linked fuel tank)

    • Spacecraft clock (SCLK)

    • Payload definition

    • Full SPICE ephemeris access for all bodies with available kernels (planets, moons, small bodies, spacecraft)

    • Sub-observer point computation

    • Angular separation computation

    • Illumination angle computation (incidence, emission, phase)

    • Shadow fraction computation

    • Body orientation and angular velocity

    • ICRF / J2000

    • Ecliptic (J2000 and B1950)

    • TEME

    • Galactic

    • FK4

    • Body-fixed / ITRF93

    • Equatorial, Horizontal, Planetodetic, Planetographic

    • UTC, TDB, TAI, TDT, GPS, Local

    • Calendar, Julian Date, J2000 epoch

    • Full conversion between all systems

    • Earth: U.S. Standard Atmosphere 1976 (simple, altitude-only)

    • Earth: NRLMSISE-00 (high-fidelity, with space weather  auto-selected when full context available)

    • Mars: Standard analytical model

    • Site definition (geodetic coordinates on a body)

    • Visibility window computation (above horizon)

    • Azimuth, elevation, range computation

    • Range rate computation

    • Recursive kernel loading from directory

    • Support for: ephemeris (SPK), orientation (CK), planetary constants (PCK), leap seconds (LSK), spacecraft clocks (SCLK), frames (FK), instrument (IK)

    • Star catalog support

    • PDS4 archive generation

    • Object materialization

    • XML schema validation (PDS4_PDS_1K00)

    • Full scenario export to Cosmographia format (spacecraft trajectories, sensors, ground sites, observations, SPICE loader)

    • 3D vectors and matrices

    • Quaternions (SLERP/LERP)

    • Planes

    • Lagrange interpolation

    • Jacobian computation

    • Geodesy-normalized associated Legendre functions with derivatives

    • ...

Professional

Edition

Early adopters : 99€ 149€ / user / month

Includes all community features

    • Adaptative step propagator

    • Albedo radiation pressure

    • Thermal radiation pressure

    • GCRF

    • CIRS

    • TIRS

    • Conjunction Assessment

    • Screening

    • Collision risk

    • Avoidance maneuver

    • CCSDS CDM (read/write)

    • Batch propagator

    • Monte Carlo

    • Email support (business hours, 48h initial response target)

    • 1 named support contact per license

    • GitHub Issues priority triage (Pro issues flagged and addressed before community)

Astrodynamics

AI MCP Server

Early adopters : 29€ / user / month

    • Simulate a full mission scenario​

    • Solve Lambert's problem

    • Convert state vector to Keplerian elements

    • Convert state vector to Equinoctial elements

    • Convert state vector to Equatorial coordinates

    • Convert Keplerian elements to state vector

    • Convert Equinoctial elements to state vector

    • Convert state vector to the given frame

    • Convert mean anomaly to eccentric anomaly

    • Convert eccentric anomaly to true anomaly

    • Convert mean anomaly to true anomaly

    • Convert true anomaly to mean anomaly

    • Convert Keplerian elements to Equinoctial elements

    • Convert Equinoctial elements to Keplerian elements

    • Compute orbital period

    • Compute orbital mean motion

    • Compute apsides

    • Compute specific orbital energy

    • Compute specific angular momentum

    • Ephemeris

    • Celestial body properties

    • Compute angular separation

    • Compute angular size

    • Compute sub-observer point

    • Compute light time

    • Compute range rate

    • Compute phase angle

    • Compute illumination fraction

    • Find datetime windows when a coordinate constraint is met

    • Find datetime windows when a distance constraint is met

    • Find datetime windows when an occulting constraint or eclipse is met

    • Find datetime windows when an angular separation constraint is met

    • Find datetime windows when a phase-angle constraint is met

    • Find datetime windows when a target's elevation from an arbitrary surface site satisfies a constraint​

    • Parse TLE

    • Evaluate TLE at epoch

    • Get planetodetic coordinates of a deep space station (DSS)

    • Get state vector of a deep space station (DSS)

    • Get horizontal coordinates of a celestial body from a deep space station (DSS)

    • Get the frame of a deep space station (DSS)

    • Get the state vector of an arbitrary surface site

    • Get horizontal coordinates from an arbitrary surface site

    • Get the topocentric frame name of a site

    • Convert planetodetic coordinates to body-fixed Cartesian

    • Convert body-fixed Cartesian coordinates to planetodetic

    • Compute the sub-spacecraft point

    • Frame rotation matrix

    • Frame state rotation matrix

    • Convert date time

    • Current date time

    • Convert to/from julian date

    • Convert to/from modified Julian date 

    • Convert to/from ephemeris date

    • Add duration

    • Convert degrees to arcseconds

    • Convert arcseconds to degrees

    • Convert radians to arcseconds

    • Convert arcseconds to radians

    • Convert meters to astronomical units

    • Convert astronomical units to meters

    • Convert meters to parsec

    • Convert parsec to meters

    • Convert meters to light years

    • Convert light years to meters

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