CCSDS Astrodynamics & Space Telemetry (`.oem`, `.opm`, `.omm`, `.xtce`)

@modelscript/ccsds (languages/ccsds) provides comprehensive compiler, trajectory propagation, and verification support for the Consultative Committee for Space Data Systems (CCSDS) and OMG XML Telemetric & Command Exchange (XTCE) standards.

Supported Extensions & Standards

Extension	Standard / Specification	Engineering Domain
`.oem`	CCSDS 502.0-B-2 Orbit Ephemeris Message	Time-tagged position and velocity state vector ephemerides
`.opm`	CCSDS 502.0-B-2 Orbit Parameter Message	Osculating Keplerian orbital elements and maneuvers
`.omm`	CCSDS 502.0-B-2 Orbit Mean-Elements Message	Mean orbital elements (SGP4/SDP4 TLE compatible)
`.xtce`, `.xml`	OMG XTCE v1.2 Telemetric & Command Exchange	Bit-level satellite telemetry decommutation and commanding

Key Capabilities

1. Perturbed 6-DOF Cowell Orbit Propagator

Integrates high-fidelity gravitational and environmental perturbations in Cartesian J2000 / GCRF coordinates: $\ddot{r} = - \frac{μ}{r^{3}} r + a_{J_{2}} + a_{drag} + a_{SRP} + a_{3rd}$
$J_{2}$ Earth Oblateness: Evaluates central body oblateness forces from zonal harmonic coefficients.
Atmospheric Drag: Exponential barometric and Jacchia-Roberts atmospheric density models coupled with satellite cross-sectional area and drag coefficient $C_{D}$ .
Solar Radiation Pressure (SRP): Cannonball radiation pressure models with cylindrical and dual-cone solar eclipse shadowing.
Third-Body Gravitation: Lunar and solar ephemeris gravitational perturbations.

2. OMG XTCE Bit-Packing & Decommutation Engine

Parses hierarchical <TelemetryMetaData>, <ParameterSet>, <ContainerSet>, and <SequenceContainer> schemas.
Validates bit-level alignments, integer sign encodings (twos-complement, sign-magnitude), IEEE 754 float packaging, and calibrated polynomial transfer functions.

3. Direct DAE Lowering

Compiles orbital states and spacecraft attitudes directly into @modelscript/runtime's DAEBuilder SoA linear memory arena for joint trajectory and attitude determination simulations.

4. Polyglot Projections & TGG Mappings

Modelica Export (ccsdsToModelica): Generates continuous Modelica 3.x space flight models compatible with orbital physics libraries.
SysML v2 Mission Architecture (ccsdsToSysml): Projects ground station contacts, communication downlink schedules, and orbit maintenance requirements into SysML v2 part def and requirement def hierarchies.

Static Analysis & Pre-Flight Linter Rules

The CCSDS analyzer enforces space mission integrity and flight safety constraints (M8201–M8208):

8 rules7 error1 warning Run with msx ccsds lint

Code	Rule	Severity	Message
`M8201`	`sub-orbital-impact-trajectory`	error	Sub-orbital pericenter radius `<rp>` km is below Earth radius `<earthRadius>` km, resulting in atmospheric re-entry or impact.
`M8202`	`telemetry-bit-packing-overlap`	error	Telemetry bit packing overlap in container '`<containerName>`': entry '`<entryName>`' starts at bit `<bitOffset>` before previous entry '`<prevEntry>`' ends at bit `<endBit>`.
`M8203`	`hyperbolic-unbounded-orbit`	warning	Orbit eccentricity `<eccentricity>` indicates a hyperbolic or parabolic trajectory.
`M8204`	`unrecognized-reference-frame`	error	Unrecognized or non-inertial reference frame '`<refFrame>`'.
`M8205`	`missing-epoch-timestamp`	error	Ephemeris point missing valid timestamp at index `<index>`.
`M8206`	`non-monotonic-ephemeris-epochs`	error	Ephemeris timestamp '`<epoch>`' is not strictly greater than previous timestamp '`<prevEpoch>`'.
`M8207`	`duplicate-parameter-name`	error	Duplicate telemetry parameter declaration for '`<paramName>`'.
`M8208`	`negative-spacecraft-mass`	error	Spacecraft mass `<massKg>` kg must be strictly positive.

Generated from languages/ccsds/src/lints/rules.ts. All languages →

CLI Usage

bash

# Lint an Orbit Ephemeris Message or XTCE container definition
msx ccsds lint mission_orbit.oem
msx ccsds lint satellite_telemetry.xtce

# Propagate trajectory and lower to DAE linear memory
msx ccsds to-dae orbit.opm --duration 86400 --step 60

# Project orbital state vectors into Modelica simulation code
msx ccsds to-modelica orbit.opm -o OrbitDynamics.mo

# Export orbital mission constraints to SysML v2 requirements
msx ccsds to-sysml orbit.omm -o OrbitRequirements.sysml

CCSDS Astrodynamics & Space Telemetry (.oem, .opm, .omm, .xtce) ​

Supported Extensions & Standards ​

Key Capabilities ​

1. Perturbed 6-DOF Cowell Orbit Propagator ​

2. OMG XTCE Bit-Packing & Decommutation Engine ​

3. Direct DAE Lowering ​

4. Polyglot Projections & TGG Mappings ​

Static Analysis & Pre-Flight Linter Rules ​

CLI Usage ​