Attitude Parameter Message (APM)¶
- class ccsds_ndm.Apm(header, segment)¶
Attitude Parameter Message (APM).
An APM specifies the attitude state of a single object at a specified epoch. This message is suited to interagency exchanges that involve automated interaction and/or human interaction, and/or human interaction, and do not require high-fidelity dynamic modeling.
The APM requires the use of a propagation technique to determine the attitude state at times different from the specified epoch.
- static from_file(path, format=None)¶
- static from_str(data, format=None)¶
- header¶
Attitude Parameter Message (APM).
An APM specifies the attitude state of a single object at a specified epoch. This message is suited to interagency exchanges that involve automated interaction and/or human interaction, and/or human interaction, and do not require high-fidelity dynamic modeling.
The APM requires the use of a propagation technique to determine the attitude state at times different from the specified epoch.
- Type:
- segment¶
APM Segment.
- Type:
- to_file(path, format, validate=True)¶
Write to file.
- to_str(format, validate=True)¶
Serialize to string.
- class ccsds_ndm.ApmMetadata(object_name, object_id, time_system=None, center_name=None, comment=None)¶
APM Metadata Section.
- center_name¶
Celestial body orbited by the object, which may be a natural solar system body (planets, asteroids, comets, and natural satellites), including any planet barycenter or the solar system barycenter. The set of allowed values is described in annex B, subsection B8.
Examples: EARTH, BARYCENTER, MOON
- Type:
str | None
- comment¶
Comments (allowed only at the beginning of the APM Metadata before OBJECT_NAME). Each comment line shall begin with this keyword.
Examples: This is a comment.
- object_id¶
Spacecraft identifier of the object corresponding to the attitude data to be given. While there is no CCSDS-based restriction on the value for this keyword, it is recommended to use international designators from the UN Office of Outer Space Affairs (reference [ADM-2]). Recommended values have the format YYYY-NNNP{PP}, where: YYYY = Year of launch. NNN = Three digit serial number of launch in year YYYY (with leading zeros). P{PP} = At least one letter for the identification of the part brought into space by the launch. In cases in which the asset is not listed in reference [ADM-2], the UN Office of Outer Space Affairs designator index format is not used, or the content cannot be disclosed, the value should be set to UNKNOWN.
Examples: 2000-052A
- Type:
- object_name¶
Spacecraft name for which the attitude state is provided. While there is no CCSDS-based restriction on the value for this keyword, it is recommended to use names from the UN Office of Outer Space Affairs designator index (reference [ADM-2], which include object name and international designator). When OBJECT_NAME is not known or cannot be disclosed, the value should be set to UNKNOWN.
Examples: EUTELSAT W1, MARS PATHFINDER, UNKNOWN
- Type:
- class ccsds_ndm.ApmData(epoch, quaternion_state=None, euler_angle_state=None, angular_velocity=None, spin=None, inertia=None, maneuver_parameters=None, comment=None)¶
APM Data Section.
- angular_velocity¶
Angular velocity vector.
- Type:
- comment¶
One or more comment line(s). Each comment line shall begin with this keyword.
- euler_angle_state¶
Euler angle elements. All mandatory elements of the logical block are to be provided if the block is present. (See annex F for conventions and further detail.)
- Type:
- inertia¶
Inertia. All mandatory elements are to be provided if the block is present. (See annex F for conventions and further detail.)
- Type:
- maneuver_parameters¶
Maneuver Parameters.
- Type:
- quaternion_state¶
Attitude quaternion. All mandatory elements are to be provided if the block is present. (See annex F for conventions and further detail.)
- Type:
Parameter Blocks¶
- class ccsds_ndm.ManeuverParameters(man_epoch_start, man_duration, man_ref_frame, man_tor_1, man_tor_2, man_tor_3, man_delta_mass=None, comment=None)¶
Maneuver Parameters (Repeat for each maneuver).
References: - CCSDS 502.0-B-3, Section 3.2.4 (OPM Data Section)
- man_delta_mass¶
Mass change during maneuver (value is < 0)
Units: kg
Note: The CCSDS standard text describes this value as strictly negative (< 0). This implementation follows the underlying schema type and allows non-positive values (<= 0) for interoperability.
- Type:
Optional[float]
- man_ref_frame¶
Reference frame in which the velocity increment vector data are given. The user must select from the accepted set of values indicated in 3.2.4.11.
- Type:
- class ccsds_ndm.InertiaState(inertia_ref_frame, ixx, iyy, izz, ixy, ixz, iyz, comment)¶
Inertia block.
All mandatory elements are to be provided if the block is present. (See annex F for conventions and further detail.)
- comment¶
One or more comment line(s). Each comment line shall begin with this keyword.
- inertia_ref_frame¶
Coordinate system for the inertia tensor. The set of allowed values is described in annex B, subsection B3.
- Type: