Creating OMMs

An Orbit Mean-Elements Message (OMM) is represented by the OrbitMeanElementsMessage type. Although this structure follows the nested hierarchy defined by the CCSDS standard (header, metadata, and data), we can create a complete message using a single keyword constructor. It takes care of assembling the internal sections for us.

OrbitMeanElementsMessage(; kwargs...) -> OrbitMeanElementsMessage

Date Fields

The fields creation_date, epoch, and ref_frame_epoch must be provided as NanoDate objects so that the message can retain the sub-second precision usually present in orbit data. We can build a NanoDate from a string or from a Dates.DateTime:

julia> using NanoDates
julia> NanoDate("2025-12-30T18:12:04.533984")2025-12-30T18:12:04.533984
julia> NanoDate(DateTime(2025, 12, 30, 18, 12, 4))2025-12-30T18:12:04

Minimal Example

The keyword constructor requires the mandatory fields defined by the standard: the message originator, the object identification, the reference frame and time system, and the mean Keplerian elements. The following example creates the OMM for the Amazonia 1 satellite:

julia> omm = OrbitMeanElementsMessage(;
           # == Header ========================================================
           creation_date       = NanoDate("2025-12-30T23:36:37"),
           originator          = "18 SPCS",
       
           # == Metadata ======================================================
           object_name         = "AMAZONIA 1",
           object_id           = "2021-015A",
           center_name         = "EARTH",
           ref_frame           = "TEME",
           time_system         = "UTC",
           mean_element_theory = "SGP4",
       
           # == Mean Keplerian Elements =======================================
           epoch               = NanoDate("2025-12-30T18:12:04.533984"),
           mean_motion         = 14.40772474,
           eccentricity        = 0.00011240,
           inclination         = 98.3721,
           raan                = 75.0877,
           arg_of_pericenter   = 97.3772,
           mean_anomaly        = 262.7545,
       )OrbitMeanElementsMessage:
  Header
    Creation Date : 2025-12-30T23:36:37
    Originator    : 18 SPCS
  Body
  └─ Segment
     ├─ Metadata
     │    Object Name         : AMAZONIA 1
     │    Object ID           : 2021-015A
     │    Center Name         : EARTH
     │    Ref. Frame          : TEME
     │    Time System         : UTC
     │    Mean Element Theory : SGP4
     └─ Data
        └─ Mean Keplerian Elements
             Epoch              : 2025-12-30T18:12:04.533984
             Mean Motion        : 14.40772474 rev/day
             Eccentricity       : 0.0001124
             Inclination        : 98.3721°
             RA of Asc. Node    : 75.0877°
             Arg. of Pericenter : 97.3772°
             Mean Anomaly       : 262.7545°

Note

The mean elements section requires either mean_motion or semi_major_axis. All angular quantities (inclination, raan, arg_of_pericenter, and mean_anomaly) are expressed in degrees, following the CCSDS 502.0-B-3 convention.

Adding Optional Sections

The OMM standard defines several optional sections. They can be populated by passing the corresponding keywords. For example, we can add the TLE-related parameters and some spacecraft data:

julia> omm = OrbitMeanElementsMessage(;
           creation_date       = NanoDate("2025-12-30T23:36:37"),
           originator          = "18 SPCS",
           object_name         = "AMAZONIA 1",
           object_id           = "2021-015A",
           center_name         = "EARTH",
           ref_frame           = "TEME",
           time_system         = "UTC",
           mean_element_theory = "SGP4",
           epoch               = NanoDate("2025-12-30T18:12:04.533984"),
           mean_motion         = 14.40772474,
           eccentricity        = 0.00011240,
           inclination         = 98.3721,
           raan                = 75.0877,
           arg_of_pericenter   = 97.3772,
           mean_anomaly        = 262.7545,
       
           # == Spacecraft Data ===============================================
           mass                = 640.0,
           drag_area           = 8.5,
           drag_coeff          = 2.2,
       
           # == TLE-Related Parameters ========================================
           norad_cat_id        = 47699,
           classification_type = 'U',
           element_set_number  = 999,
           rev_at_epoch        = 25439,
           bstar               = 0.0001533,
           mean_motion_dot     = 0.00000447,
           mean_motion_ddot    = 0.0,
       
           # == User-Defined Parameters =======================================
           user_defined_parameters = [
               "COUNTRY_CODE" => "BRAZ",
               "LAUNCH_DATE"  => "2021-02-28",
           ],
       )OrbitMeanElementsMessage:
  Header
    Creation Date : 2025-12-30T23:36:37
    Originator    : 18 SPCS
  Body
  └─ Segment
     ├─ Metadata
     │    Object Name         : AMAZONIA 1
     │    Object ID           : 2021-015A
     │    Center Name         : EARTH
     │    Ref. Frame          : TEME
     │    Time System         : UTC
     │    Mean Element Theory : SGP4
     └─ Data
        ├─ Mean Keplerian Elements
        │    Epoch              : 2025-12-30T18:12:04.533984
        │    Mean Motion        : 14.40772474 rev/day
        │    Eccentricity       : 0.0001124
        │    Inclination        : 98.3721°
        │    RA of Asc. Node    : 75.0877°
        │    Arg. of Pericenter : 97.3772°
        │    Mean Anomaly       : 262.7545°
        ├─ Spacecraft Parameters
        │    Mass             : 640.0 kg
        │    Drag Area        : 8.5 m²
        │    Drag Coefficient : 2.2
        ├─ TLE Related Parameters
        │    Classification Type : U
        │    NORAD Cat ID        : 47699
        │    Element Set Number  : 999
        │    Rev at Epoch        : 25439
        │    Bstar               : 0.0001533
        │    ∂(Mean Motion)/∂t   : 4.47e-6 rev/day²
        │    ∂²(Mean Motion)/∂t² : 0.0 rev/day³
        └─ User-Defined Parameters
             COUNTRY_CODE : BRAZ
             LAUNCH_DATE  : 2021-02-28

Copying and Modifying a Message

Since OrbitMeanElementsMessage is immutable, we can create a modified copy of an existing message by passing it to the constructor together with the keywords we want to override. The remaining fields are copied from the original message:

julia> new_omm = OrbitMeanElementsMessage(omm; originator = "SATELLITE TOOLBOX")OrbitMeanElementsMessage:
  Header
    Creation Date : 2025-12-30T23:36:37
    Originator    : SATELLITE TOOLBOX
  Body
  └─ Segment
     ├─ Metadata
     │    Object Name         : AMAZONIA 1
     │    Object ID           : 2021-015A
     │    Center Name         : EARTH
     │    Ref. Frame          : TEME
     │    Time System         : UTC
     │    Mean Element Theory : SGP4
     └─ Data
        ├─ Mean Keplerian Elements
        │    Epoch              : 2025-12-30T18:12:04.533984
        │    Mean Motion        : 14.40772474 rev/day
        │    Eccentricity       : 0.0001124
        │    Inclination        : 98.3721°
        │    RA of Asc. Node    : 75.0877°
        │    Arg. of Pericenter : 97.3772°
        │    Mean Anomaly       : 262.7545°
        ├─ Spacecraft Parameters
        │    Mass             : 640.0 kg
        │    Drag Area        : 8.5 m²
        │    Drag Coefficient : 2.2
        ├─ TLE Related Parameters
        │    Classification Type : U
        │    NORAD Cat ID        : 47699
        │    Element Set Number  : 999
        │    Rev at Epoch        : 25439
        │    Bstar               : 0.0001533
        │    ∂(Mean Motion)/∂t   : 4.47e-6 rev/day²
        │    ∂²(Mean Motion)/∂t² : 0.0 rev/day³
        └─ User-Defined Parameters
             COUNTRY_CODE : BRAZ
             LAUNCH_DATE  : 2021-02-28
julia> new_omm.header.originator"SATELLITE TOOLBOX"

Available Keywords

The following table lists all keywords accepted by the constructor. Fields marked as required must always be provided.

Keyword	Type	Section	Required
`header_comments`	`Vector{String}`	Header
`classification`	`String`	Header
`creation_date`	`NanoDate`	Header	✅
`originator`	`String`	Header	✅
`message_id`	`String`	Header
`metadata_comments`	`Vector{String}`	Metadata
`object_name`	`String`	Metadata	✅
`object_id`	`String`	Metadata	✅
`center_name`	`String`	Metadata	✅
`ref_frame`	`String`	Metadata	✅
`ref_frame_epoch`	`NanoDate`	Metadata
`time_system`	`String`	Metadata	✅
`mean_element_theory`	`String`	Metadata	✅
`data_comments`	`Vector{String}`	Data
`mean_elements_comments`	`Vector{String}`	Mean Elements
`epoch`	`NanoDate`	Mean Elements	✅
`semi_major_axis`	`Float64`	Mean Elements	✅ ^[1]
`mean_motion`	`Float64`	Mean Elements	✅ ^[1]
`eccentricity`	`Float64`	Mean Elements	✅
`inclination`	`Float64`	Mean Elements	✅
`raan`	`Float64`	Mean Elements	✅
`arg_of_pericenter`	`Float64`	Mean Elements	✅
`mean_anomaly`	`Float64`	Mean Elements	✅
`GM`	`Float64`	Mean Elements
`spacecraft_parameters_comments`	`Vector{String}`	Spacecraft Data
`mass`	`Float64`	Spacecraft Data
`solar_rad_area`	`Float64`	Spacecraft Data
`solar_rad_coeff`	`Float64`	Spacecraft Data
`drag_area`	`Float64`	Spacecraft Data
`drag_coeff`	`Float64`	Spacecraft Data
`tle_parameters_comments`	`Vector{String}`	TLE Parameters
`ephemeris_type`	`Int`	TLE Parameters
`classification_type`	`Char`	TLE Parameters
`norad_cat_id`	`Int`	TLE Parameters
`element_set_number`	`Int`	TLE Parameters
`rev_at_epoch`	`Int`	TLE Parameters
`bstar`	`Float64`	TLE Parameters
`bterm`	`Float64`	TLE Parameters
`mean_motion_dot`	`Float64`	TLE Parameters
`mean_motion_ddot`	`Float64`	TLE Parameters
`agom`	`Float64`	TLE Parameters
`covariance_matrix`	`OmmCovarianceMatrix`	Covariance Matrix
`user_defined_parameters`	`Vector{Pair{String, String}}`	User-Defined

Comment keywords accept vectors because each XML section may contain multiple COMMENT elements. data_comments applies directly to <data>, while mean_elements_comments applies to <meanElements>.

If any TLE-related parameter is supplied, mean_motion_dot is required. Exactly one of bstar or bterm, and exactly one of mean_motion_ddot or agom, must also be supplied. The constructor throws ArgumentError when these constraints are not met.

Covariance Matrix

The OMM standard defines an optional covariance matrix section. It is represented by the OmmCovarianceMatrix type, which stores the 21 unique upper-triangular elements of the symmetric 6×6 matrix, along with an optional comment and reference frame:

julia> cov = OmmCovarianceMatrix(;
           cov_ref_frame = "ITRF",
           cx_x           = 1.0,
           cy_x           = 2.0,
           cy_y           = 3.0,
           cz_x           = 4.0,
           cz_y           = 5.0,
           cz_z           = 6.0,
           cx_dot_x       = 7.0,
           cx_dot_y       = 8.0,
           cx_dot_z       = 9.0,
           cx_dot_x_dot   = 10.0,
           cy_dot_x       = 11.0,
           cy_dot_y       = 12.0,
           cy_dot_z       = 13.0,
           cy_dot_x_dot   = 14.0,
           cy_dot_y_dot   = 15.0,
           cz_dot_x       = 16.0,
           cz_dot_y       = 17.0,
           cz_dot_z       = 18.0,
           cz_dot_x_dot   = 19.0,
           cz_dot_y_dot   = 20.0,
           cz_dot_z_dot   = 21.0,
       )OmmCovarianceMatrix(String[], "ITRF", 1.0, 2.0, 3.0, 4.0, 5.0, 6.0, 7.0, 8.0, 9.0, 10.0, 11.0, 12.0, 13.0, 14.0, 15.0, 16.0, 17.0, 18.0, 19.0, 20.0, 21.0)
julia> omm = OrbitMeanElementsMessage(omm; covariance_matrix = cov)OrbitMeanElementsMessage:
  Header
    Creation Date : 2025-12-30T23:36:37
    Originator    : 18 SPCS
  Body
  └─ Segment
     ├─ Metadata
     │    Object Name         : AMAZONIA 1
     │    Object ID           : 2021-015A
     │    Center Name         : EARTH
     │    Ref. Frame          : TEME
     │    Time System         : UTC
     │    Mean Element Theory : SGP4
     └─ Data
        ├─ Mean Keplerian Elements
        │    Epoch              : 2025-12-30T18:12:04.533984
        │    Mean Motion        : 14.40772474 rev/day
        │    Eccentricity       : 0.0001124
        │    Inclination        : 98.3721°
        │    RA of Asc. Node    : 75.0877°
        │    Arg. of Pericenter : 97.3772°
        │    Mean Anomaly       : 262.7545°
        ├─ Spacecraft Parameters
        │    Mass             : 640.0 kg
        │    Drag Area        : 8.5 m²
        │    Drag Coefficient : 2.2
        ├─ TLE Related Parameters
        │    Classification Type : U
        │    NORAD Cat ID        : 47699
        │    Element Set Number  : 999
        │    Rev at Epoch        : 25439
        │    Bstar               : 0.0001533
        │    ∂(Mean Motion)/∂t   : 4.47e-6 rev/day²
        │    ∂²(Mean Motion)/∂t² : 0.0 rev/day³
        ├─ Covariance Matrix
        │    Ref. Frame   : ITRF
        │    CX_X         : 1.0 km²
        │    CY_X         : 2.0 km²
        │    CY_Y         : 3.0 km²
        │    CZ_X         : 4.0 km²
        │    CZ_Y         : 5.0 km²
        │    CZ_Z         : 6.0 km²
        │    CX_DOT_X     : 7.0 km²/s
        │    CX_DOT_Y     : 8.0 km²/s
        │    CX_DOT_Z     : 9.0 km²/s
        │    CX_DOT_X_DOT : 10.0 km²/s²
        │    CY_DOT_X     : 11.0 km²/s
        │    CY_DOT_Y     : 12.0 km²/s
        │    CY_DOT_Z     : 13.0 km²/s
        │    CY_DOT_X_DOT : 14.0 km²/s²
        │    CY_DOT_Y_DOT : 15.0 km²/s²
        │    CZ_DOT_X     : 16.0 km²/s
        │    CZ_DOT_Y     : 17.0 km²/s
        │    CZ_DOT_Z     : 18.0 km²/s
        │    CZ_DOT_X_DOT : 19.0 km²/s²
        │    CZ_DOT_Y_DOT : 20.0 km²/s²
        │    CZ_DOT_Z_DOT : 21.0 km²/s²
        └─ User-Defined Parameters
             COUNTRY_CODE : BRAZ
             LAUNCH_DATE  : 2021-02-28
julia> omm.body.segment.data.covariance_matrix.cov_ref_frame"ITRF"

1At least one of semi_major_axis or mean_motion must be provided.