Hosting

Remote, hosted production service

Transport

Streamable HTTP

Endpoint

https://mcp.io-aerospace.org/mcp

Authentication

OAuth 2.1 with PKCE through WorkOS AuthKit, followed by a separate active-license check tied to the signed-in email. Required scopes: openid, email, offline_access. No API key. A valid OAuth login without an active license is insufficient.

Requirements

• MCP client supporting Streamable HTTP and MCP OAuth discovery/PKCE
• Email account with active IO Aerospace license
• Browser and access to email for one-time-code login

Setup steps

1. Add a remote Streamable HTTP server at https://mcp.io-aerospace.org/mcp (include the /mcp path exactly).
2. Start the client authorization flow. Sign in in the browser using the email attached to an active IO Aerospace license; choose the one-time email code option.
3. Complete OAuth consent. The client should store and refresh tokens using offline_access.
4. If login succeeds but calls return 403, request or renew an IO Aerospace license for that email.
5. Verify with a harmless read-only call such as CurrentDateTime.

The official tool reference lists 64 named tools across celestial bodies, orbital elements, time, TLE, frames, sites, geometry, observation, maneuvers, Lambert solving, scenarios, and unit conversions. Authentication is required for runtime discovery; this record follows the complete published reference and was not queried with credentials.

• GetEphemerisAsStateVectors

  Get the state vectors (position and velocity) of a target observed from an observer in a given frame over a time range.

  01
• GetCelestialBodyProperties

  Get the geophysical properties of a celestial body: NAIF IDs, name, tri-axial radii, GM, body-fixed frame, and zonal harmonics J2/J3/J4.

  02
• ConvertStateVectorToKeplerianElements

  Returns the classical orbital elements (semi-major axis, eccentricity, inclination, RAAN, argument of periapsis, mean anomaly, perigee radius).

  03
• ConvertStateVectorToEquinoctialElements

  Returns equinoctial elements (P, F, G, H, K, L0).

  04
• ConvertStateVectorToEquatorialCoordinates

  Returns equatorial coordinates (right ascension, declination, distance, epoch). Implicitly transformed into ICRF.

  05
• ConvertKeplerianElementsToStateVector

  Returns the Cartesian state vector in the same frame and center-of-motion as the input.

  06
• ConvertEquinoctialElementsToStateVector

  Inverse of ConvertStateVectorToEquinoctialElements .

  07
• ConvertStateVectorToTheGivenFrame

  Transform a state vector into another frame at its own epoch.

  08
• ConvertKeplerianElementsToEquinoctialElements

  Direct conversion that does not go through a state vector. Same parameter type as the Keplerian → state-vector tool.

  09
• ConvertEquinoctialElementsToKeplerianElements

  Inverse of the previous tool.

  10
• ComputeOrbitalPeriod

  Orbital period in seconds via Kepler's third law. Only valid for elliptical orbits ( a > 0 , e < 1 ).

  11
• ComputeMeanMotion

  Mean motion n = sqrt(mu / a^3) in radians per second. Elliptical only.

  12
• ComputeApsides

  Apoapsis and periapsis radii in meters. Elliptical only.

  13
• ComputeSpecificOrbitalEnergy

  Specific orbital energy epsilon = v²/2 − mu/r in J/kg.

  14
• ComputeSpecificAngularMomentum

  Specific angular momentum h = r × v in m²/s, expressed in the input frame.

  15
• ConvertDateTime

  Convert a date/time to another time scale, preserving the instant.

  16
• CurrentDateTime

  Return the current UTC instant. No parameters.

  17
• ConvertToJulianDate

  Convert an instant to its Julian Date (days) in the same time scale.

  18
• ConvertFromJulianDate

  Build an instant from a Julian Date.

  19
• ConvertToModifiedJulianDate

  MJD = JD − 2400000.5 . Same input as ConvertToJulianDate .

  20
• ConvertToEphemerisTime

  Convert an instant to ephemeris time — TDB seconds elapsed since J2000 ( 2000-01-01T12:00:00 TDB ).

  21
• ConvertFromEphemerisTime

  Inverse of ConvertToEphemerisTime . Returns a TDB Time .

  22
• AddDuration

  Add a signed duration in seconds to an instant, preserving its time scale.

  23
• ParseTle

  Parse a TLE into its mean orbital elements plus drag terms.

  24
• EvaluateTleAtEpoch

  Propagate the TLE with SGP4/SDP4 to a requested epoch and return the osculating state vector in the chosen frame. Earth is assumed as the central body.

  25
• GetFrameRotationMatrix

  Compute the 3×3 rotation matrix R such that v_target = R · v_source .

  26
• GetFrameStateRotationMatrix

  Compute both R and its time derivative dR/dt . Together they form the 6×6 state-transition matrix [[R, 0], [dR/dt, R]] mapping stacked (position, velocity) states.

  27
• GetDeepSpaceStationPlanetodeticCoordinates

  Get the latitude (rad), longitude (rad) and altitude (m) of a DSS.

  28
• GetDeepSpaceStationStateVector

  State vector of a DSS observed from a celestial body.

  29
• GetHorizontalCoordinates

  Azimuth, elevation and range of a target body from a DSS at a given epoch.

  30
• GetDSSFrame

  Return the topocentric frame name of a DSS (format: DSS-NN_TOPO ).

  31
• GetSiteStateVector

  State vector of a user-defined surface site observed from a celestial item.

  32
• GetSiteHorizontalCoordinates

  Azimuth, elevation, range of a target from an arbitrary site at a given epoch. Same site parameters as above, plus a target body.

  33
• GetSiteFrameName

  Returns the topocentric frame name of a site built from a name: <NAME_UPPERCASED>_TOPO .

  34
• ConvertPlanetodeticToCartesian

  Planetodetic (lat, lon, alt) → body-fixed Cartesian (m) using the body's equatorial radius and flattening.

  35
• ConvertCartesianToPlanetodetic

  Inverse of the previous tool.

  36
• ComputeSubSpacecraftPoint

  Planetodetic sub-spacecraft point (latitude, longitude, altitude above ellipsoid) from a body-fixed spacecraft position.

  37
• FindCoordinateConstraint

  Find windows where one component of the observer→target vector, expressed in a given frame and coordinate system, satisfies a relational constraint.

  38
• FindDistanceConstraint

  Find windows where the distance between two SPICE-backed items satisfies a relational constraint.

  39
• FindOccultingConstraint

  Find occultation or eclipse windows.

  40
• FindAngularSeparationConstraint

  Find windows where the angular separation (radians) of two targets as seen from an observer satisfies a relational constraint.

  41
• FindPhaseAngleConstraint

  Find windows where the illumination phase angle of a target satisfies a relational constraint. The phase angle is the illuminator-target-observer angle measured at the target; cos(phaseAngle) drives the illuminated fraction.

  42
• FindElevationFromSiteConstraint

  Find windows where a target's elevation, observed from an arbitrary (body, lat, lon, alt) site, satisfies a relational constraint. Useful for visibility windows and twilight.

  43
• ComputeAngularSeparation

  Angular separation between two targets as seen from an observer.

  44
• ComputeAngularSize

  Angular diameter of a celestial body at a given range. 2 · arctan(R / d) with R the body radius.

  45
• ComputeSubObserverPoint

  Planetocentric sub-observer point on the target body: latitude and longitude (radians) of the point directly beneath the observer, and the distance from the body center to the observer.

  46
• ComputeLightTime

  One-way light time in seconds between observer and target (range / c).

  47
• ComputeRangeRate

  Line-of-sight range rate (m/s) between observer and target — positive when receding.

  48
• ComputePhaseAngle

  Phase angle in radians — the illuminator-target-observer angle measured at the target.

  49
• ComputeIlluminationFraction

  Illuminated fraction of the target's disc as seen from the observer: (1 + cos(phaseAngle)) / 2 . Returns a value in [0, 1] .

  50
• ComputeApogeeChangeDeltaV

  Single-impulse vis-viva delta-V at perigee that changes the orbit's apogee radius.

  51
• ComputePerigeeChangeDeltaV

  Symmetric counterpart: single impulse at apogee that changes the perigee radius.

  52
• ComputeInclinationChangeDeltaV

  Pure plane change at constant speed at the node: Δv = 2v · sin(Δi/2) .

  53
• ComputeCombinedPlaneChangeDeltaV

  Simultaneous inclination + RAAN change at constant speed. The equivalent rotation angle θ is derived from the spherical law of cosines, then Δv = 2v · sin(θ/2) .

  54
• ComputePhasingDeltaV

  First impulse of a phasing rendezvous on a circular orbit. The spacecraft enters a phasing ellipse, completes the requested number of revolutions, then re-circularizes with an equal-magnitude second burn — so total cost = 2 × returned value .

  55
• ComputeHohmannTransferDeltaV

  Two-impulse Hohmann transfer between coplanar circular orbits.

  56
• ComputeBiEllipticTransferDeltaV

  Three-impulse bi-elliptic transfer between coplanar circular orbits via an intermediate apogee. The intermediate radius must exceed both endpoints.

  57
• ApplyImpulsiveDeltaV

  Apply an instantaneous Δv to a state vector. Position, epoch, frame and center of motion are preserved; velocity becomes v + Δv .

  58
• SolveLambert

  Position and velocity must be expressible relative to centerOfMotion ; the solver works in ICRF.

  59
• SimulateScenario

  SimulateScenarioRequest contains:

  60
• DegreesToArcseconds

  Convert Degrees to Arcseconds.

  61
• ArcsecondsToDegrees

  Convert Arcseconds to Degrees.

  62
• RadiansToArcseconds

  Convert Radians to Arcseconds.

  63
• ArcsecondsToRadians

  Convert Arcseconds to Radians.

  64
• MetersToAstronomicalUnits

  Convert Meters to AstronomicalUnits.

  65
• AstronomicalUnitsToMeters

  Convert AstronomicalUnits to Meters.

  66
• MetersToParsec

  Convert Meters to Parsec.

  67
• ParsecToMeters

  Convert Parsec to Meters.

  68
• MetersToLightYears

  Convert Meters to LightYears.

  69
• LightYearsToMeters

  Convert LightYears to Meters.

  70

• Hosted service is the supported production path; no self-hosted distribution is documented.
• Tool calls require an active license in addition to successful OAuth authentication.
• The endpoint must include /mcp; bare host URL causes OAuth resource-discovery errors.
• Result units, frames, conventions, and edge cases follow IO.Astrodynamics; NaN/Infinity can be legitimate outputs.

• official service documentation

  Publisher docs identify the hosted OAuth service and its supported astrodynamics domains.

• official complete tool reference

  Current categorized reference links every tool and describes its inputs and use cases.

Documentation checked 2026-10-28T13:41:09.000Z. Connection has not been runtime tested.