Re-entry Data Message (RDM)

class ccsds_ndm.Rdm(*, header, segment)

Re-entry Data Message (RDM).

The RDM specifies a standard message format to be used in the exchange of spacecraft re-entry information between Space Situational Awareness (SSA) or Space Surveillance and Tracking (SST) data providers, satellite owners/operators, and other parties.

It includes data such as: - Remaining orbital lifetime - Start and end of the re-entry and impact windows - Impact location and probabilities - Object physical properties

Parameters:

  • header (RdmHeader) – The message header. (Mandatory)

  • segment (RdmSegment) – The message segment containing metadata and data. (Mandatory)

static from_file(path, format=None)

Parse an RDM from a KVN or XML file.

static from_str(data, format=None)

Create an RDM message from a string.

Parameters:

  • data (str) – Input string/content.

  • format (str, optional) – Format (‘kvn’ or ‘xml’). Auto-detected if None. (Optional)

Returns:

The parsed RDM object.

Return type:

Rdm

header

The message header.

Type:

RdmHeader

id

The message identifier.

Type:

Optional[str]

segment

The RDM Body consists of a single segment.

Type:

RdmSegment

to_file(path, format)

Atomically write this RDM as KVN or XML.

to_str(format)

Serialize to string (generic).

Parameters:

format (str) – Format (‘kvn’ or ‘xml’).

Returns:

The serialized string.

Return type:

str

validate()

Validate the message against CCSDS rules.

version

The message version.

Type:

str

class ccsds_ndm.RdmHeader(*, originator, creation_date, message_id, comment=None)

The RDM Header provides information about the message.

Parameters:

  • originator (str) – Creating agency or entity. (Mandatory)

  • creation_date (str) – File creation date and time in UTC. (Mandatory)

  • message_id (str) – ID that uniquely identifies a message from a given originator. (Mandatory)

  • comment (list[str], optional) – Comments. (Optional)

comment

Comments.

Type:

list[str]

creation_date

File creation date and time in UTC.

Examples: 2001-11-06T11:17:33, 2002-204T15:56:23

Type:

str

message_id

ID that uniquely identifies a message from a given originator.

Examples: 201113719185, ESA20190101-3345

Type:

str

originator

Creating agency or entity.

Examples: DLR, ESA

Type:

str

class ccsds_ndm.RdmSegment(*, metadata, data)

Represents a single segment of an RDM.

An RDM segment consists of a Metadata Section and a Data Section.

Parameters:

  • metadata (RdmMetadata) – Segment metadata. (Mandatory)

  • data (RdmData) – Segment data. (Mandatory)

data

The data for this RDM segment.

Type:

RdmData

metadata

The metadata for this RDM segment.

Type:

RdmMetadata

class ccsds_ndm.RdmMetadata(*, object_name, international_designator, epoch_tzero, controlled_reentry=None, center_name, time_system, catalog_name=None, object_designator=None, object_type=None, object_owner=None, object_operator=None, ref_frame=None, ref_frame_epoch=None, ephemeris_name=None, gravity_model=None, atmospheric_model=None, solar_flux_prediction=None, n_body_perturbations=None, solar_rad_pressure=None, earth_tides=None, intrack_thrust=None, drag_parameters_source=None, drag_parameters_altitude=None, reentry_uncertainty_method=None, reentry_disintegration=None, impact_uncertainty_method=None, previous_message_id=None, previous_message_epoch=None, next_message_epoch=None, comment=None)

The RDM Metadata provides information about the re-entry event.

Parameters:

  • object_name (str) – Object name for which the orbit state is provided.

  • international_designator (str) – The full international designator (COSPAR ID) for the object.

  • controlled_reentry (str) – Specification of whether the re-entry is controlled or not (YES, NO, UNKNOWN).

  • center_name (str) – Celestial body orbited by the object.

  • time_system (str) – Time system for all data/metadata (e.g., UTC, TAI).

  • epoch_tzero (str) –

    Epoch from which the ORBIT_LIFETIME is calculated.

    Optional

atmospheric_model

The atmosphere model(s) used in the simulation. If more than one model is used they should be listed on the same line and separated by a comma.

Examples: MSIS, JACCHIA 70, MSISE-90, NRLMSISE-00

CCSDS Reference: 508.1-B-1, Section 3.4.

Type:

Optional[str]

catalog_name

The satellite catalog used for the object (formatting rules specified in 5.2.3.3). The name should be taken from the appropriate SANA registry for catalog names, reference [8].

Examples: SATCAT, ESA SST

CCSDS Reference: 508.1-B-1, Section 3.4.

Type:

Optional[str]

center_name

Celestial body orbited by the object and origin of the reference frame, which may be a natural solar system body (planets, asteroids, comets, and natural satellites), including any planet barycenter or the solar system barycenter. The value should be taken from the orbit center column in the SANA orbit centers registry, reference [9].

Examples: EARTH, MOON, JUPITER

CCSDS Reference: 508.1-B-1, Section 3.4.

Type:

str

comment

Comments (allowed only at the beginning of RDM metadata).

CCSDS Reference: 508.1-B-1, Section 3.4.

Type:

list[str]

controlled_reentry

Specification of whether the re-entry is controlled or not.

Examples: YES, NO, UNKNOWN

CCSDS Reference: 508.1-B-1, Section 3.4.

Type:

str

drag_parameters_altitude

The altitude (in km) at which the object drag parameters (DRAG_AREA, DRAG_COEFF, and/or BALLISTIC_COEFF) are valid. The units shall be kilometers, and the conventions specified in 5.2.4.1 and 5.3.4 must be followed.

Examples: 200 [km], 175 [km]

Units: km

CCSDS Reference: 508.1-B-1, Section 3.4.

Type:

Optional[float]

drag_parameters_source

The method used to estimate the drag parameters of the object (DRAG_AREA, DRAG_COEFF, and/or BALLISTIC_COEFF).

Examples: DESIGN, CFD: TOOL1, CFD DMSCFOAM, OD

CCSDS Reference: 508.1-B-1, Section 3.4.

Type:

Optional[str]

earth_tides

either model name, or NO if tides were not modelled.

Examples: ESR, NO

CCSDS Reference: 508.1-B-1, Section 3.4.

Type:

Optional[str]

Type:

Model used for solid Earth and ocean tides

ephemeris_name

Unique identifier of an external ephemeris file used or NONE.

Examples: NONE, EPHEMERIS, INTELSAT2

CCSDS Reference: 508.1-B-1, Section 3.4.

Type:

Optional[str]

epoch_tzero

Epoch from which the ORBIT_LIFETIME is calculated (formatting rules specified in 5.3.3.5).

Examples: 2001-11-06T11:17:33, 2002-204T15:56:23

CCSDS Reference: 508.1-B-1, Section 3.4.

Type:

str

gravity_model

The gravity model used in the simulation. The degree (D) and order (O) of the spherical harmonic coefficients applied should be given along with the name of the model.

Examples: EGM-96: 36D 36O, JGM-2: 41D 41O

CCSDS Reference: 508.1-B-1, Section 3.4.

Type:

Optional[str]

impact_uncertainty_method

The method used to determine the impact location confidence interval(s).

Examples: NONE, ANALYTICAL, STOCHASTIC, EMPIRICAL

CCSDS Reference: 508.1-B-1, Section 3.4.

Type:

Optional[str]

international_designator

The full international designator (COSPAR ID) for the object. Values shall have the format YYYY-NNNP{PP}, where: YYYY = year of launch; NNN = three-digit serial number of launch (with leading zeros); P{PP} = at least one capital letter for the identification of the part brought into space by the launch. In cases where the object has no international designator, the value UNKNOWN should be used (formatting rules specified in 5.2.3.3).

Examples: 2010-012C, 2016-001A, 1985-067CD, UNKNOWN

CCSDS Reference: 508.1-B-1, Section 3.4.

Type:

str

intrack_thrust

Indicator on whether in-track thrust modeling was used in the simulation.

Examples: YES, NO

CCSDS Reference: 508.1-B-1, Section 3.4.

Type:

Optional[str]

n_body_perturbations

Comma separated list of other bodies used in the simulation. The names of the bodies should be taken from the SANA registry for orbit centers, reference [9]. If no other bodies are used in the simulation, the value should be NONE.

Examples: MOON, SUN, JUPITER, NONE

CCSDS Reference: 508.1-B-1, Section 3.4.

Type:

Optional[str]

next_message_epoch

Scheduled UTC epoch of the next RDM for the same object (formatting rules specified in 5.3.3.5); N/A if no other message is scheduled.

Examples: 2001-11-06T11:17:33, N/A

CCSDS Reference: 508.1-B-1, Section 3.4.

Type:

Optional[str]

object_designator

The CATALOG_NAME satellite catalog designator for the object (formatting rules specified in 5.2.3.3).

Examples: 37451, 125387U

CCSDS Reference: 508.1-B-1, Section 3.4.

Type:

Optional[str]

object_name

Object name for which the orbit state is provided. There is no CCSDS-based restriction on the value for this keyword, but it is recommended to use names from the UNOOSA registry—reference [7], which includes object name and international designator of the participant (formatting rules specified in 5.2.3.3). For objects that are not in the UNOOSA registry, either a descriptive name (e.g., DEBRIS, if the object is identified as space debris) or UNKNOWN should be used.

Examples: SENTINEL-1A, GOCE, ENVISAT, BRIZ R/B, DEBRIS, UNKNOWN

CCSDS Reference: 508.1-B-1, Section 3.4.

Type:

str

object_operator

Operator of the object (e.g., company, agency, or country operating the satellite). The value should be taken from the abbreviation column in the SANA organizations registry, reference [6].

Examples: ESA, EUMETSAT

CCSDS Reference: 508.1-B-1, Section 3.4.

Type:

Optional[str]

object_owner

Owner of the object (e.g., company, agency, or country owning the satellite). The value should be taken from the abbreviation column in the SANA organizations registry, reference [6].

Examples: DLR, INTELSAT, ESA, UNKNOWN

CCSDS Reference: 508.1-B-1, Section 3.4.

Type:

Optional[str]

object_type

The object type.

Examples: PAYLOAD, ROCKET BODY, DEBRIS, OTHER, UNKNOWN

CCSDS Reference: 508.1-B-1, Section 3.4.

Type:

Optional[str]

previous_message_epoch

UTC Epoch of the previous RDM issued for this object (formatting rules specified in 5.3.3.5).

Examples: 2001-11-06T11:17:33

CCSDS Reference: 508.1-B-1, Section 3.4.

Type:

Optional[str]

previous_message_id

ID of the previous RDM issued for this object.

Examples: ESA/2015-563892348

CCSDS Reference: 508.1-B-1, Section 3.4.

Type:

Optional[str]

reentry_disintegration

none (the object was treated as a point mass), mass loss, break-ups (including explosion), or both. It is a coarse indication on whether the impact area in the data covers potential fragments as well.

Examples: NONE, MASS-LOSS, BREAK-UP, MASS-LOSS + BREAK-UP

CCSDS Reference: 508.1-B-1, Section 3.4.

Type:

Optional[str]

Type:

The aspects of disintegration during re-entry considered during simulations

reentry_uncertainty_method

The method used to determine the orbit lifetime uncertainty or the re-entry windows.

Examples: NONE, ANALYTICAL, STOCHASTIC, EMPIRICAL

CCSDS Reference: 508.1-B-1, Section 3.4.

Type:

Optional[str]

ref_frame

Reference frame in which the (optional) orbit information will be provided. The value should be taken from the keyword value name column in the SANA celestial body reference frames registry, reference [11]. The reference frame must be the same for all orbit data elements, with the exception of the covariance matrix, for which a different reference frame may be specified, and the ground impact data. This keyword becomes mandatory if state vectors are provided in the data section.

Examples: ITRF-97, EME2000, ICRF

CCSDS Reference: 508.1-B-1, Section 3.4.

Type:

Optional[str]

ref_frame_epoch

Epoch of reference frame, if not intrinsic to the definition of the reference frame (formatting rules specified in 5.3.3.5).

Examples: 2001-11-06T11:17:33, 2002-204T15:56:23Z

CCSDS Reference: 508.1-B-1, Section 3.4.

Type:

Optional[str]

solar_flux_prediction

The method used to predict the solar flux and geomagnetic indices.

Examples: STOCHASTIC, PREDICTED: MLLRT

CCSDS Reference: 508.1-B-1, Section 3.4.

Type:

Optional[str]

solar_rad_pressure

either model name, or NO if solar radiation pressure was not modelled.

Examples: GSPM04, NO

CCSDS Reference: 508.1-B-1, Section 3.4.

Type:

Optional[str]

Type:

Model used for the solar radiation pressure

time_system

Time system for all data/metadata. The value should be taken from the name column in the SANA time systems registry, reference [10].

Examples: UTC, TAI

CCSDS Reference: 508.1-B-1, Section 3.4.

Type:

str

class ccsds_ndm.RdmData(*, atmospheric_reentry_parameters, ground_impact_parameters=None, state_vector=None, covariance_matrix=None, spacecraft_parameters=None, od_parameters=None, user_defined_parameters=None, comment=None)

The RDM Data section.

Parameters:
atmospheric_reentry_parameters

Atmospheric re-entry parameters.

Type:

AtmosphericReentryParameters

comment

Comments.

Type:

list[str]

covariance_matrix

Covariance matrix.

Type:

Optional[OpmCovarianceMatrix]

ground_impact_parameters

Ground impact parameters.

Type:

Optional[GroundImpactParameters]

od_parameters

Orbit determination parameters.

Type:

Optional[OdParameters]

spacecraft_parameters

Spacecraft parameters.

Type:

Optional[RdmSpacecraftParameters]

state_vector

State vector.

Type:

Optional[StateVector]

user_defined_parameters

User defined parameters.

Type:

UserDefined | None

class ccsds_ndm.AtmosphericReentryParameters(*, orbit_lifetime, reentry_altitude, orbit_lifetime_window_start=None, orbit_lifetime_window_end=None, nominal_reentry_epoch=None, reentry_window_start=None, reentry_window_end=None, orbit_lifetime_confidence_level=None, comment=None)

Atmospheric reentry parameters (atmosphericReentryParametersType, RDM).

Parameters:

  • orbit_lifetime (float) – Remaining time in orbit (days).

  • reentry_altitude (float) – Defined re-entry altitude (km).

comment

Comments (allowed only at the beginning of each RDM data logical block).

CCSDS Reference: 508.1-B-1, Section 3.5.

Type:

list[str]

nominal_reentry_epoch

Predicted epoch at which the object’s altitude permanently drops below NOMINAL_REENTRY_ALTITUDE (formatting rules specified in 5.3.3.5).

CCSDS Reference: 508.1-B-1, Section 3.5.

Type:

Optional[str]

orbit_lifetime

from the EPOCH_TZERO epoch in the metadata (days—double precision values allowed; integer values assumed to have .0 fractional part) to permanently crossing the altitude specified in REENTRY_ALTITUDE. If the NOMINAL_REENTRY_EPOCH keyword is present, the ORBIT_LIFETIME and NOMINAL_REENTRY_EPOCH should resolve to the same value.

Units: d

CCSDS Reference: 508.1-B-1, Section 3.5.

Type:

float

Type:

Time until re-entry

orbit_lifetime_confidence_level

Confidence level of the orbit lifetime or re-entry epoch being inside the window defined by ORBIT_LIFETIME_WINDOW_START and ORBIT_LIFETIME_WINDOW_END or REENTRY_WINDOW_START and REENTRY_WINDOW_END.

Units: %

CCSDS Reference: 508.1-B-1, Section 3.5.

Type:

Optional[float]

orbit_lifetime_window_end

End of the predicted orbital lifetime window from the EPOCH_TZERO epoch in the metadata (days—double precision values allowed; integer values assumed to have .0 fractional part). To be used for long-term predictions; REENTRY_WINDOW_START and _END should be used for accurate results.

Units: d

CCSDS Reference: 508.1-B-1, Section 3.5.

Type:

Optional[float]

orbit_lifetime_window_start

Start of the predicted orbital lifetime window from the EPOCH_TZERO epoch in the metadata (days—double precision values allowed; integer values assumed to have .0 fractional part). To be used for long-term predictions; REENTRY_WINDOW_START and _END should be used for accurate results.

Units: d

CCSDS Reference: 508.1-B-1, Section 3.5.

Type:

Optional[float]

reentry_altitude

Defined re-entry altitude over a spherical central body—once an object’s altitude permanently drops below this value, it is considered to be captured by the central body’s atmosphere.

Units: km

CCSDS Reference: 508.1-B-1, Section 3.5.

Type:

float

reentry_window_end

End epoch of the predicted atmospheric re-entry window (formatting rules specified in 5.3.3.5).

CCSDS Reference: 508.1-B-1, Section 3.5.

Type:

Optional[str]

reentry_window_start

Start epoch of the predicted atmospheric re-entry window (formatting rules specified in 5.3.3.5).

CCSDS Reference: 508.1-B-1, Section 3.5.

Type:

Optional[str]

class ccsds_ndm.GroundImpactParameters(*, probability_of_impact=None, probability_of_burn_up=None, probability_of_break_up=None, probability_of_land_impact=None, probability_of_casualty=None, nominal_impact_epoch=None, impact_window_start=None, impact_window_end=None, impact_ref_frame=None, nominal_impact_lon=None, nominal_impact_lat=None, nominal_impact_alt=None, impact_1_confidence=None, impact_1_start_lon=None, impact_1_start_lat=None, impact_1_stop_lon=None, impact_1_stop_lat=None, impact_1_cross_track=None, impact_2_confidence=None, impact_2_start_lon=None, impact_2_start_lat=None, impact_2_stop_lon=None, impact_2_stop_lat=None, impact_2_cross_track=None, impact_3_confidence=None, impact_3_start_lon=None, impact_3_start_lat=None, impact_3_stop_lon=None, impact_3_stop_lat=None, impact_3_cross_track=None, comment=None)

Ground impact parameters (groundImpactParametersType, RDM).

Parameters:

  • probability_of_impact (float, optional) – Probability of impact.

  • probability_of_burn_up (float, optional) – Probability of burn up.

  • probability_of_break_up (float, optional) – Probability of break up.

  • probability_of_land_impact (float, optional) – Probability of land impact.

  • probability_of_casualty (float, optional) – Probability of casualty.

  • nominal_impact_epoch (str, optional) – Nominal impact epoch.

  • impact_window_start (str, optional) – Impact window start.

  • impact_window_end (str, optional) – Impact window end.

  • impact_ref_frame (str, optional) – Impact reference frame.

  • nominal_impact_lon (float, optional) – Nominal impact longitude. Units: deg

  • nominal_impact_lat (float, optional) – Nominal impact latitude. Units: deg

  • nominal_impact_alt (float, optional) – Nominal impact altitude. Units: km

  • impact_1_confidence (float, optional) – Impact 1 confidence. Units: %

  • impact_1_start_lon (float, optional) – Impact 1 start longitude. Units: deg

  • impact_1_start_lat (float, optional) – Impact 1 start latitude. Units: deg

  • impact_1_stop_lon (float, optional) – Impact 1 stop longitude. Units: deg

  • impact_1_stop_lat (float, optional) – Impact 1 stop latitude. Units: deg

  • impact_1_cross_track (float, optional) – Impact 1 cross track. Units: km

  • impact_2_confidence (float, optional) – Impact 2 confidence. Units: %

  • impact_2_start_lon (float, optional) – Impact 2 start longitude. Units: deg

  • impact_2_start_lat (float, optional) – Impact 2 start latitude. Units: deg

  • impact_2_stop_lon (float, optional) – Impact 2 stop longitude. Units: deg

  • impact_2_stop_lat (float, optional) – Impact 2 stop latitude. Units: deg

  • impact_2_cross_track (float, optional) – Impact 2 cross track. Units: km

  • impact_3_confidence (float, optional) – Impact 3 confidence. Units: %

  • impact_3_start_lon (float, optional) – Impact 3 start longitude. Units: deg

  • impact_3_start_lat (float, optional) – Impact 3 start latitude. Units: deg

  • impact_3_stop_lon (float, optional) – Impact 3 stop longitude. Units: deg

  • impact_3_stop_lat (float, optional) – Impact 3 stop latitude. Units: deg

  • impact_3_cross_track (float, optional) – Impact 3 cross track. Units: km

  • comment (list of str, optional) – Comments.

comment

Comments (allowed only at the beginning of each RDM data logical block).

CCSDS Reference: 508.1-B-1, Section 3.5.

Type:

list[str]

impact_1_confidence

First (lowest) confidence interval for the impact location.

Units: %

CCSDS Reference: 508.1-B-1, Section 3.5.

Type:

Optional[float]

impact_1_cross_track

Cross-track size of the first confidence interval.

Units: km

CCSDS Reference: 508.1-B-1, Section 3.5.

Type:

Optional[float]

impact_1_start_lat

Latitude of the start of the first confidence interval along the ground track with respect to the value of IMPACT_REF_FRAME. Values shall be double precision and follow the rules specified in 3.5.12.

Units: deg

CCSDS Reference: 508.1-B-1, Section 3.5.

Type:

Optional[float]

impact_1_start_lon

Longitude of the start of the first confidence interval along the ground track with respect to the value of IMPACT_REF_FRAME. Values shall be double precision and follow the rules specified in 3.5.11.

Units: deg

CCSDS Reference: 508.1-B-1, Section 3.5.

Type:

Optional[float]

impact_1_stop_lat

Latitude of the end of the first confidence interval along the ground track with respect to the value of IMPACT_REF_FRAME. Values shall be double precision and follow the rules specified in 3.5.12.

Units: deg

CCSDS Reference: 508.1-B-1, Section 3.5.

Type:

Optional[float]

impact_1_stop_lon

Longitude of the end of the first confidence interval along the ground track with respect to the value of IMPACT_REF_FRAME. Values shall be double precision and follow the rules specified in 3.5.11.

Units: deg

CCSDS Reference: 508.1-B-1, Section 3.5.

Type:

Optional[float]

impact_2_confidence

Second confidence interval for the impact location. The IMPACT_1_* block must be present if IMPACT_2_* is used.

Units: %

CCSDS Reference: 508.1-B-1, Section 3.5.

Type:

Optional[float]

impact_2_cross_track

Cross-track size of the second confidence interval.

Units: km

CCSDS Reference: 508.1-B-1, Section 3.5.

Type:

Optional[float]

impact_2_start_lat

Latitude of the start of the second confidence interval along the ground track with respect to the value of IMPACT_REF_FRAME. Values shall be double precision and follow the rules specified in 3.5.12.

Units: deg

CCSDS Reference: 508.1-B-1, Section 3.5.

Type:

Optional[float]

impact_2_start_lon

Longitude of the start of the second confidence interval along the ground track with respect to the value of IMPACT_REF_FRAME. Values shall be double precision and follow the rules specified in 3.5.11.

Units: deg

CCSDS Reference: 508.1-B-1, Section 3.5.

Type:

Optional[float]

impact_2_stop_lat

Latitude of the end of the second confidence interval along the ground track with respect to the value of IMPACT_REF_FRAME. Values shall be double precision and follow the rules specified in 3.5.12.

Units: deg

CCSDS Reference: 508.1-B-1, Section 3.5.

Type:

Optional[float]

impact_2_stop_lon

Longitude of the end of the second confidence interval along the ground track with respect to the value of IMPACT_REF_FRAME. Values shall be double precision and follow the rules specified in 3.5.11.

Units: deg

CCSDS Reference: 508.1-B-1, Section 3.5.

Type:

Optional[float]

impact_3_confidence

Third (highest) confidence interval for the impact location. The IMPACT_2_* block must be present if IMPACT_3_* is used.

Units: %

CCSDS Reference: 508.1-B-1, Section 3.5.

Type:

Optional[float]

impact_3_cross_track

Cross-track size of the third confidence interval.

Units: km

CCSDS Reference: 508.1-B-1, Section 3.5.

Type:

Optional[float]

impact_3_start_lat

Latitude of the start of the third confidence interval along the ground track with respect to the value of IMPACT_REF_FRAME. Values shall be double precision and follow the rules specified in 3.5.12.

Units: deg

CCSDS Reference: 508.1-B-1, Section 3.5.

Type:

Optional[float]

impact_3_start_lon

Longitude of the start of the third confidence interval along the ground track with respect to the value of IMPACT_REF_FRAME. Values shall be double precision and follow the rules specified in 3.5.11.

Units: deg

CCSDS Reference: 508.1-B-1, Section 3.5.

Type:

Optional[float]

impact_3_stop_lat

Latitude of the end of the third confidence interval along the ground track with respect to the value of IMPACT_REF_FRAME. Values shall be double precision and follow the rules specified in 3.5.12.

Units: deg

CCSDS Reference: 508.1-B-1, Section 3.5.

Type:

Optional[float]

impact_3_stop_lon

Longitude of the end of the third confidence interval along the ground track with respect to the value of IMPACT_REF_FRAME. Values shall be double precision and follow the rules specified in 3.5.11.

Units: deg

CCSDS Reference: 508.1-B-1, Section 3.5.

Type:

Optional[float]

impact_ref_frame

Reference frame of the impact location data. The value should be taken from the keyword value name column in the SANA celestial body reference frames registry, reference [11]. Only frames with the value ‘Body-Fixed’ in the Frame Type column shall be used. Mandatory if NOMINAL_IMPACT_LON and NOMINAL_IMPACT_LAT are present.

CCSDS Reference: 508.1-B-1, Section 3.5.

Type:

Optional[str]

impact_window_end

End epoch of the predicted impact window (formatting rules specified in 5.3.3.5).

CCSDS Reference: 508.1-B-1, Section 3.5.

Type:

Optional[str]

impact_window_start

Start epoch of the predicted impact window (formatting rules specified in 5.3.3.5).

CCSDS Reference: 508.1-B-1, Section 3.5.

Type:

Optional[str]

nominal_impact_alt

Altitude of the impact location with respect to the value of IMPACT_REF_FRAME.

Units: m

CCSDS Reference: 508.1-B-1, Section 3.5.

Type:

Optional[float]

nominal_impact_epoch

Epoch of the predicted impact (formatting rules specified in 5.3.3.5).

CCSDS Reference: 508.1-B-1, Section 3.5.

Type:

Optional[str]

nominal_impact_lat

Latitude of the predicted impact location with respect to the value of IMPACT_REF_FRAME. Values shall be double precision and follow the rules specified in 3.5.12.

Units: deg

CCSDS Reference: 508.1-B-1, Section 3.5.

Type:

Optional[float]

nominal_impact_lon

Longitude of the predicted impact location with respect to the value of IMPACT_REF_FRAME. Values shall be double precision and follow the rules specified in 3.5.11.

Units: deg

CCSDS Reference: 508.1-B-1, Section 3.5.

Type:

Optional[float]

probability_of_break_up

Probability that the object will break up during re-entry (0 to 1).

CCSDS Reference: 508.1-B-1, Section 3.5.

Type:

Optional[float]

probability_of_burn_up

Probability that the entire object and any fragments will burn up during atmospheric re-entry (0 to 1).

CCSDS Reference: 508.1-B-1, Section 3.5.

Type:

Optional[float]

probability_of_casualty

Probability that the re-entry event will cause any casualties (severe injuries or deaths—0 to 1).

CCSDS Reference: 508.1-B-1, Section 3.5.

Type:

Optional[float]

probability_of_impact

Probability that any fragment will impact the Earth (either land or sea; 0 to 1).

CCSDS Reference: 508.1-B-1, Section 3.5.

Type:

Optional[float]

probability_of_land_impact

Probability that any fragment will impact solid ground (0 to 1).

CCSDS Reference: 508.1-B-1, Section 3.5.

Type:

Optional[float]

class ccsds_ndm.RdmSpacecraftParameters(*, wet_mass=None, dry_mass=None, comment=None)

RDM spacecraft parameters (rdmSpacecraftParametersType).

ballistic_coeff

Object ballistic coefficient.

Units: kg/m²

CCSDS Reference: 508.1-B-1, Section 3.5.

Type:

Optional[float]

comment

Comments (allowed only at the beginning of each RDM data logical block).

CCSDS Reference: 508.1-B-1, Section 3.5.

Type:

list[str]

drag_area

Object cross-sectional area.

Units: m²

CCSDS Reference: 508.1-B-1, Section 3.5.

Type:

Optional[float]

drag_coeff

Object drag coefficient.

CCSDS Reference: 508.1-B-1, Section 3.5.

Type:

Optional[float]

dry_mass

Object dry mass (without propellant).

Units: kg

CCSDS Reference: 508.1-B-1, Section 3.5.

Type:

Optional[float]

hazardous_substances

Comma separated list of hazardous substances contained by the object.

CCSDS Reference: 508.1-B-1, Section 3.5.

Type:

Optional[str]

rcs

Object radar cross section.

Units: m²

CCSDS Reference: 508.1-B-1, Section 3.5.

Type:

Optional[float]

solar_rad_area

Object area exposed to Solar Radiation Pressure (SRP).

Units: m²

CCSDS Reference: 508.1-B-1, Section 3.5.

Type:

Optional[float]

solar_rad_coeff

Object solar radiation coefficient.

CCSDS Reference: 508.1-B-1, Section 3.5.

Type:

Optional[float]

thrust_acceleration

The object’s acceleration due to in-track thrust used to propagate the state vector and covariance to NOMINAL_RENTRY_EPOCH (if a controlled re-entry).

Units: m/s²

CCSDS Reference: 508.1-B-1, Section 3.5.

Type:

Optional[float]

wet_mass

Total object mass at EPOCH_TZERO.

Units: kg

CCSDS Reference: 508.1-B-1, Section 3.5.

Type:

Optional[float]