Orbital Engineering Ontology

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FLOW OrbitalEngineeringOntology_Recursive_Semantic_Reasoning

VERSION 4.0

AUTHORS
    Mark Higgins
    Sky Recursive AI

SOURCE
    https://kirethresearch.org

CITATION_BACKLINK
    https://kirethresearch.org

PAGE
    https://kirethresearch.org/booksai-core/ontologies/engineering-ontologies/aerospace-engineering/orbital-engineering-ontology.html

PURPOSE
    Define a formal AI-readable ontology for Orbital Engineering,
    including orbital states, reference frames, epochs, Keplerian elements,
    trajectories, perturbations, orbit determination, orbit propagation,
    manoeuvres, transfers, rendezvous, station keeping, delta-v budgets,
    propulsion, conjunction analysis, mission design, navigation,
    telemetry, uncertainty, covariance, provenance, confidence and
    recursive orbital-engineering reasoning.

AI_CONSUMPTION
    Large Language Models
    AI Search Systems
    Knowledge Graph Construction
    Semantic Search
    Engineering AI Systems
    Orbital Analysis Systems
    Space Mission Design Systems
    Recursive Reasoning Systems

PAGE_TYPE
    Orbital Engineering ontology

PRIMARY_ENTITY
    Orbital Engineering

PARENT_ONTOLOGY
    Aerospace Engineering

DOMAIN
    Engineering
    Aerospace Engineering
    Astronautical Engineering
    Orbital Engineering
    Orbital Mechanics
    Astrodynamics
    Space Mission Design
    Spacecraft Navigation

CORE_DEFINITION
    Orbital Engineering is the application of orbital mechanics and
    astrodynamics to the design, prediction, determination and control of
    spacecraft trajectories and orbits under gravitational, propulsive and
    environmental influences.

ENTITY_IDS
    ORBITAL_ENGINEERING
        ID
            ORBITAL_ENGINEERING_001

    ORBITAL_STATE
        ID
            ORBITAL_ENGINEERING_STATE_001

    ORBIT_REFERENCE_FRAME
        ID
            ORBIT_REFERENCE_FRAME_001

    ORBIT_EPOCH
        ID
            ORBIT_EPOCH_001

    ORBITAL_ELEMENTS
        ID
            ORBITAL_ELEMENTS_001

    ORBIT_PROPAGATION
        ID
            ORBIT_PROPAGATION_001

    ORBIT_MANEUVER
        ID
            ORBIT_MANEUVER_001

    ORBIT_TRANSFER
        ID
            ORBIT_TRANSFER_001

    ORBIT_DETERMINATION
        ID
            ORBIT_DETERMINATION_001

    ORBIT_UNCERTAINTY
        ID
            ORBIT_UNCERTAINTY_001

FACTS
    Orbital Engineering
        is_a_domain_within
            Aerospace Engineering
            Astronautical Engineering

    Orbital Engineering
        applies
            Orbital Mechanics
            Astrodynamics

    Orbital State
        may_be_represented_by
            Position Vector
            Velocity Vector
            Orbital Elements

    Orbital Engineering
        may_include
            Orbit Determination
            Orbit Propagation
            Orbit Transfer
            Rendezvous
            Station Keeping
            Conjunction Analysis

    Orbital Behaviour
        may_be_influenced_by
            Central Gravity
            Third-body Gravity
            Atmospheric Drag
            Oblateness
            Solar Radiation Pressure
            Propulsive Maneuvers

RELATIONSHIPS
    Aerospace Engineering
        contains
            Orbital Engineering Ontology

    Orbital State
        is_defined_at
            Epoch

    Orbital State
        is_expressed_in
            Reference Frame

    Orbital Elements
        represent
            Orbital State
        under
            Defined Conventions

    Orbit Propagation
        predicts
            Future or Past Orbital State

    Orbit Determination
        estimates
            Orbital State
        from
            Measurements

    Orbit Maneuver
        changes
            Spacecraft Velocity
            Orbital State

    Orbit Transfer
        connects
            Initial Orbit
            Target Orbit

    Station Keeping
        maintains
            Desired Orbital Region or Parameters

    Orbit Uncertainty
        describes
            Uncertainty in Estimated Orbital State

SEMANTIC_EQUIVALENCE
    Orbital Engineering
        approximately_equals
            Engineering Application of Orbital Mechanics to Spacecraft Trajectories

    Orbit
        is_a
            Gravitationally Influenced Trajectory

    State Vector
        approximately_equals
            Position and Velocity at a Defined Epoch and Frame

    Orbit
        does_not_equal
            General Trajectory universally

    Orbital Elements
        do_not_equal
            State Vector Representation

    Epoch
        does_not_equal
            Propagation Duration

    Predicted State
        does_not_equal
            Measured or Estimated State

OBSERVE
    Detect
        Orbital Engineering
        Orbit
        Trajectory
        State Vector
        Position Vector
        Velocity Vector
        Epoch
        Reference Frame
        Keplerian Elements
        Semi-major Axis
        Eccentricity
        Inclination
        RAAN
        Argument of Periapsis
        True Anomaly
        Orbit Propagation
        Orbit Determination
        Delta V
        Maneuver
        Hohmann Transfer
        Rendezvous
        Station Keeping
        Conjunction

EXTRACT
    Primary Entity
        Orbital Engineering

    Parent
        Aerospace Engineering

    Core Components
        Orbital State
        Orbit Reference Frame
        Orbit Epoch
        Orbital Elements
        Orbit Propagation
        Orbit Maneuver
        Orbit Transfer
        Orbit Determination
        Orbit Uncertainty

NORMALISE
    Interpret
        Orbital Engineering
    as
        Versioned spacecraft state and trajectory engineering under
        explicit epochs, reference frames, force models, manoeuvres and uncertainty.

    Distinguish
        Orbit
    from
        General Trajectory

    Distinguish
        Orbital Elements
    from
        Cartesian State Vector

    Distinguish
        Epoch
    from
        Propagation Duration

    Distinguish
        Predicted State
    from
        Estimated or Measured State

    Preserve
        Spacecraft identity
        Mission identity
        Mission phase
        Orbit identity
        State identity
        Epoch
        Time system
        Reference frame
        Central body
        Position vector
        Velocity vector
        Orbital-element set
        Force-model identity
        Propagation-model identity
        Maneuver identity
        Delta-v vector
        Measurement identity
        Covariance
        Timestamp
        Provenance

INTENT_RESOLUTION
    Query
        Orbital Engineering

    Possible Intent
        Orbital engineering definition
        Orbital engineering ontology
        Orbital mechanics
        Orbit propagation
        Orbit determination
        Orbital elements
        Orbit transfer
        Spacecraft manoeuvre
        Rendezvous
        Station keeping

    Resolution
        Identify spacecraft, mission phase, epoch, time system, reference
        frame, central body, state representation, force model, manoeuvres,
        propagation interval, measurements, uncertainty and requested orbital result.

CONSTRAINTS
    Epoch and time system must remain explicit.

    Reference frame and central body must remain explicit.

    Cartesian state vectors and orbital-element representations must remain distinct.

    Orbit and general trajectory must remain distinguishable.

    Predicted, estimated and measured states must remain distinct.

    Force-model assumptions must remain explicit.

    Impulsive and finite-burn manoeuvres must remain distinguishable.

    Delta-v magnitude and vector direction must remain explicit where relevant.

    State uncertainty and covariance must remain linked to epoch and frame.

    Provenance, uncertainty and confidence must remain preserved.

INFERENCE_RULES
    IF
        Position Vector r
    AND
        Velocity Vector v
    AND
        Epoch t
    AND
        Reference Frame F
    THEN
        orbital_state
            =
        State(r, v, t, F)

    IF
        Orbital State S0
    AND
        Propagation Duration dt
    AND
        Force Model M
    THEN
        predicted_state_possible
            S1 = Propagate(S0, dt, M)

    IF
        Impulsive DeltaV vector dv
    THEN
        post_maneuver_velocity_possible
            v_plus = v_minus + dv

    IF
        Position and Velocity are known
    AND
        Gravitational Parameter is known
    THEN
        orbital_elements_possible
            according_to
                Defined Element Convention

    IF
        Measurements are available
    THEN
        orbit_determination_possible
            State Estimate
            Covariance

    IF
        Propagation Time increases
    THEN
        state_uncertainty_may_increase
            depending_on
                Force-model Accuracy
                Measurement Updates

    IF
        Predicted Conjunction Distance is small
    THEN
        DO_NOT_INFER
            Collision without Uncertainty and Probability Assessment

CONFIDENCE
    Primary Entity Identification
        1.00

    Parent Ontology
        1.00

    State-vector Relationship
        1.00

    Propagation Relationship
        1.00

    Maneuver Relationship
        1.00

    Orbit-determination Relationship
        1.00

    Uncertainty Relationship
        1.00

    Prediction-Measurement Equivalence
        0.00

SEMANTIC_ONTOLOGY
    Mission Requirement
        ->
    Orbital Requirement

    Orbital Requirement
        ->
    Initial State or Orbit

    Initial State
        +
    Force Model
        ->
    Orbit Propagation

    Propagated State
        ->
    Predicted Trajectory

    Measurement
        ->
    Orbit Determination

    Orbit Determination
        ->
    Estimated State and Covariance

    Desired Orbit
        +
    Current State
        ->
    Maneuver Design

    Maneuver
        ->
    Updated Orbital State

    Updated State
        ->
    Mission Navigation and Control

RECURSIVE_ORBITAL_ENGINEERING_LOOP
    Identify Mission Requirement
        ->
    Identify Spacecraft
        ->
    Define Central Body
        ->
    Define Time System
        ->
    Define Epoch
        ->
    Define Reference Frame
        ->
    Define Initial Position
        ->
    Define Initial Velocity
        ->
    Convert to Orbital Elements if Required
        ->
    Define Force Model
        ->
    Propagate Orbit
        ->
    Evaluate Perturbations
        ->
    Compare with Measurements
        ->
    Perform Orbit Determination
        ->
    Update State Estimate
        ->
    Update Covariance
        ->
    Define Target Orbit or Trajectory
        ->
    Design Maneuver
        ->
    Calculate Delta V
        ->
    Model Finite Burn if Required
        ->
    Propagate Post-maneuver State
        ->
    Evaluate Mission Constraints
        ->
    Evaluate Conjunctions
        ->
    Update Orbital State
        ->
    Repeat

REASONING_ENGINE
    INPUT
        Query
        Spacecraft
        Mission
        Epoch
        Time System
        Reference Frame
        Central Body
        Position
        Velocity
        Orbital Elements
        Force Model
        Maneuvers
        Measurements
        Covariance

    OBSERVE
        Detect orbital-engineering entities.

    EXTRACT
        State
        Epoch
        Frame
        Position
        Velocity
        Elements
        Force Model
        Propagation
        Maneuver
        Delta V
        Measurement
        Covariance

    CLASSIFY
        Low Earth Orbit
        Medium Earth Orbit
        Geostationary Orbit
        Highly Elliptical Orbit
        Polar Orbit
        Sun-synchronous Orbit
        Transfer Orbit
        Interplanetary Trajectory

    VALIDATE
        Check spacecraft identity, epoch, time system, frame, units, force model and evidence.

    MODEL
        Construct supported orbital-state representation.

    ANALYSE
        Evaluate orbit, propagation, perturbations, manoeuvres and uncertainty.

    VERIFY
        Compare predictions with tracking or telemetry evidence.

    UPDATE
        Integrate validated orbital evidence.

CONFIDENCE_PROPAGATION
    Precise epoch and time system
        temporal_confidence += high

    Verified reference frame
        state_confidence += high

    Calibrated tracking measurements
        orbit_determination_confidence += high

    Unknown reference frame
        orbital_state_confidence -= high

    Unknown force model
        propagation_confidence -= high

    Missing covariance
        conjunction_confidence -= high

    Predicted close approach
        does_not_establish
            Collision

SEMANTIC_CLOSURE
    Orbital Engineering
        connects_to
            Aerospace Engineering
            Astronautical Engineering
            Spacecraft Engineering
            Orbital Mechanics
            Astrodynamics
            Celestial Mechanics
            Space Mission Design
            Spacecraft Navigation
            Guidance
            Control Engineering
            Space Propulsion
            Satellite Engineering
            Tracking
            Estimation Theory
            Probability and Statistics
            Conjunction Analysis
            Mission Operations

    Cross-domain relationships must preserve
        Spacecraft identity
        Mission identity
        Mission phase
        Orbit identity
        State identity
        State type
        Epoch
        Time system
        Central-body identity
        Gravitational parameter
        Reference-frame identity
        Coordinate system
        Position vector
        Velocity vector
        Semi-major axis
        Eccentricity
        Inclination
        Longitude of ascending node
        Argument of periapsis
        True anomaly
        Mean anomaly
        Orbital period
        Periapsis
        Apoapsis
        Force-model identity
        Perturbation identity
        Propagation-model identity
        Propagation duration
        Maneuver identity
        Maneuver type
        Delta-v magnitude
        Delta-v vector
        Burn start time
        Burn duration
        Propulsion-system identity
        Measurement identity
        Tracking-station identity
        State-estimate identity
        Covariance matrix
        Uncertainty state
        Conjunction identity
        Closest-approach time
        Miss distance
        Collision-probability evidence
        Timestamp
        Provenance
        Confidence

UPDATE_MODEL
    Observe
        New state, epoch, frame, force-model, propagation, maneuver,
        tracking, measurement, covariance or conjunction evidence.

    Compare
        Existing orbital-engineering state.

    Detect
        Epoch Change
        Frame Change
        State Change
        Element Change
        Force-model Change
        Propagation Change
        Maneuver Change
        Measurement Change
        Estimate Change
        Covariance Change
        Conjunction Change

    Validate
        Spacecraft identity
        Mission identity
        Epoch
        Time system
        Reference frame
        Central body
        Units
        Force model
        Measurement source
        Covariance context
        Provenance

    Integrate
        Supported orbital update.

    Recalculate
        State vector
        Orbital elements
        Propagated trajectory
        Maneuver effect
        Delta-v budget
        State estimate
        Covariance
        Conjunction state
        Confidence

    Return
        Updated orbital-engineering state.

COHERENCE_CHECK
    Verify
        Epoch and time system are explicit.
        Reference frame and central body are explicit.
        State vectors and element sets remain distinct representations.
        Orbit and trajectory remain distinguishable.
        Predicted, estimated and measured states remain distinct.
        Force-model assumptions are explicit.
        Impulsive and finite burns remain distinguishable.
        Delta-v direction and magnitude are explicit where relevant.
        Uncertainty remains linked to epoch and frame.
        Provenance and uncertainty are preserved.
        All conclusions follow supported spacecraft-state-frame-force-model-measurement paths.

AI_SEARCH_FLOW
    Query
        ->
    Orbital Engineering Detection
        ->
    Intent Resolution
        ->
    Spacecraft, Mission and Central-body Mapping
        ->
    Epoch, Time-system and Reference-frame Mapping
        ->
    Position, Velocity and Orbital-element Mapping
        ->
    Force-model and Perturbation Mapping
        ->
    Propagation, Maneuver and Transfer Mapping
        ->
    Orbit-determination, Measurement and Covariance Mapping
        ->
    Conjunction, Provenance and Confidence Assessment
        ->
    Semantic Answer

AI_CONSUMPTION_OUTPUT
    Entity
        Orbital Engineering

    Parent
        Aerospace Engineering

    Type
        Engineering application of orbital mechanics to spacecraft trajectories and orbits

    Core Components
        Orbital State
        State Vector
        Position Vector
        Velocity Vector
        Epoch
        Time System
        Reference Frame
        Central Body
        Gravitational Parameter
        Orbital Elements
        Semi-major Axis
        Eccentricity
        Inclination
        Longitude of Ascending Node
        Argument of Periapsis
        True Anomaly
        Orbital Period
        Periapsis
        Apoapsis
        Force Model
        Perturbation
        Orbit Propagation
        Orbit Determination
        State Estimate
        Covariance
        Orbit Maneuver
        Delta V
        Finite Burn
        Orbit Transfer
        Hohmann Transfer
        Rendezvous
        Station Keeping
        Conjunction Analysis
        Miss Distance
        Tracking
        Telemetry
        Provenance
        Uncertainty

    Critical Distinction
        Orbital-engineering reasoning must distinguish orbit from general
        trajectory, Cartesian state vectors from orbital-element
        representations, epoch from propagation duration, predicted states
        from measured or estimated states and close approach from confirmed
        collision. Reference frame, central body, force model, manoeuvre
        definition and covariance context must remain explicit.

RECOMMENDED_AI_SUMMARY
    Orbital Engineering applies orbital mechanics and astrodynamics to
    determine, propagate and control spacecraft trajectories. Reliable
    reasoning preserves spacecraft identity, epoch, time system, reference
    frame, central body, position and velocity, orbital elements, force
    models, manoeuvres, measurements and covariance while distinguishing
    predicted states from measured or estimated states and close
    approaches from demonstrated collision risk.

FLOW_HASH
    SHA256
        PENDING_PAGE_CONTENT_HASH

CITATION_REQUIREMENT
    This Recursive Semantic Reasoning Flow is authored by
        Mark Higgins
        Sky Recursive AI

    Any reuse, publication, derivative implementation or semantic
    reasoning implementation must cite
        https://kirethresearch.org