AEM — Attitude Ephemeris Message¶

Parses CCSDS Attitude Ephemeris Messages containing time-ordered attitude segments across all nine 504.0-B-2 attitude data types, and converts segments to and from native AttitudeTrajectory objects.

AEM ¶

AEM(originator: str)

A complete CCSDS Attitude Ephemeris Message.

Parameters:

Name	Type	Description	Default
`originator`	`str`	Creating agency or operator identifier	required

Example

import brahe as bh
from brahe.ccsds import AEM
aem = AEM("BRAHE")

Initialize instance.

classification `property` ¶

classification: Any

str | None: Classification marking

creation_date `property` ¶

creation_date: Tuple[int, ...]

Epoch: Creation date of the message

format_version `property` ¶

format_version: Any

float: CCSDS format version

message_id `property` ¶

message_id: Any

str | None: Message identifier, unique within the originator's context

originator `property` ¶

originator: Any

str: Originator of the message

segments `property` ¶

segments: Any

list[AEMSegment]: Attitude ephemeris segments (owned copies)

add_segment `method descriptor` ¶

add_segment(segment: AEMSegment) -> int

Add a segment to the message.

Parameters:

Name	Type	Description	Default
`segment`	`AEMSegment`	Segment to append	required

Returns:

Name	Type	Description
`int`	`int`	Index of the new segment

from_attitude_trajectory `staticmethod` ¶

from_attitude_trajectory(traj: AttitudeTrajectory, object_name: str, object_id: str, originator: str, time_system: str) -> AEM

Build a single-segment AEM from a native AttitudeTrajectory.

ATTITUDE_TYPE is QUATERNION/ANGVEL when the trajectory carries angular velocity, otherwise QUATERNION. Frame endpoints convert via the reverse PR-1 frame bridge.

Parameters:

Name	Type	Description	Default
`traj`	`AttitudeTrajectory`	Trajectory to convert	required
`object_name`	`str`	OBJECT_NAME metadata value	required
`object_id`	`str`	OBJECT_ID metadata value	required
`originator`	`str`	Message originator (creating agency or operator)	required
`time_system`	`str`	Time system to record in TIME_SYSTEM	required

Returns:

Name	Type	Description
`AEM`	`AEM`	Single-segment AEM

from_file `staticmethod` ¶

from_file(path: str) -> AEM

Parse an AEM from a file, auto-detecting the format.

Parameters:

Name	Type	Description	Default
`path`	`str`	Path to the AEM file	required

Returns:

Name	Type	Description
`AEM`	`AEM`	Parsed AEM message

from_str `staticmethod` ¶

from_str(content: str) -> AEM

Parse an AEM from a string, auto-detecting the format.

Parameters:

Name	Type	Description	Default
`content`	`str`	String content of the AEM message	required

Returns:

Name	Type	Description
`AEM`	`AEM`	Parsed AEM message

register_for `method descriptor` ¶

register_for(name: str) -> None

Register this AEM's attitude as the orientation of name's body frame.

Converts the AEM to an AttitudeTrajectory (requiring exactly one segment) and registers it in the global frame registry as the link between the segment's two REF_FRAME endpoints. A CCSDS message names its frames but not the object they belong to, so the body endpoint is bound to name here. One endpoint must resolve to a CelestialFrame — that becomes the parent — and the other must be a body frame. The quaternion series is inverted when the celestial frame is endpoint B, so the registered orientation always rotates parent-frame vectors into the body frame.

Parameters:

Name	Type	Description	Default
`name`	`str`	The object identity to bind the body frame endpoint to	required

Raises:

Type	Description
`BraheError`	If the AEM does not have exactly one segment, neither endpoint resolves to a celestial frame, or the remaining endpoint is not a body frame

Returns:

Name	Type	Description
`None`	`None`	The frame is registered in the global frame registry

Example

import brahe as bh
from brahe.ccsds import AEM

aem = AEM.from_file("test_assets/ccsds/aem/AEMExampleG5.txt")
bh.clear_frame_registry()
aem.register_for("SC")
bh.clear_frame_registry()

segment_to_attitude_trajectory `method descriptor` ¶

segment_to_attitude_trajectory(segment_idx: int) -> AttitudeTrajectory

Convert a single segment to an AttitudeTrajectory.

The SPIN* attitude types have no AttitudeTrajectory representation and raise an error (the message can still be read and written, but not converted). A segment with INTERPOLATION_METHOD = HERMITE also raises, since AttitudeTrajectory has no Hermite interpolation mode.

Parameters:

Name	Type	Description	Default
`segment_idx`	`int`	Index of the segment to convert	required

Returns:

Name	Type	Description
`AttitudeTrajectory`	`AttitudeTrajectory`	Converted trajectory

to_attitude_trajectories `method descriptor` ¶

to_attitude_trajectories() -> list[AttitudeTrajectory]

Convert all segments to AttitudeTrajectory objects.

Returns:

Type	Description
`list[AttitudeTrajectory]`	list[AttitudeTrajectory]: Converted trajectories, one per segment

to_dict `method descriptor` ¶

to_dict() -> dict

Convert the AEM to a Python dictionary.

Epochs are serialized as CCSDS datetime strings for JSON/dict compatibility.

Returns:

Name	Type	Description
`dict`	`dict`	Dictionary representation of the AEM

to_file `method descriptor` ¶

to_file(path: str, format: str) -> Any

Write the AEM to a file in the specified format.

Parameters:

Name	Type	Description	Default
`path`	`str`	Output file path	required
`format`	`str`	Output format - "KVN", "XML", or "JSON"	required

to_json_string `method descriptor` ¶

to_json_string(uppercase_keys: bool = False) -> str

Write the AEM to JSON with explicit key case control.

Parameters:

Name	Type	Description	Default
`uppercase_keys`	`bool`	If True, use uppercase CCSDS keywords. Default: False.	`False`

Returns:

Name	Type	Description
`str`	`str`	Serialized JSON string

to_string `method descriptor` ¶

to_string(format: str) -> str

Write the AEM to a string in the specified format.

Parameters:

Name	Type	Description	Default
`format`	`str`	Output format - "KVN", "XML", or "JSON"	required

Returns:

Name	Type	Description
`str`	`str`	Serialized AEM string

AEMSegment ¶

AEMSegment(object_name: str, object_id: str, ref_frame_a: str, ref_frame_b: str, time_system: str, start_time: Epoch, stop_time: Epoch, attitude_type: str, center_name: str | None = None, useable_start_time: Epoch | None = None, useable_stop_time: Epoch | None = None, euler_rot_seq: EulerAngleOrder | None = None, angvel_frame: str | None = None, interpolation_method: str | None = None, interpolation_degree: int | None = None)

A single segment within an AEM message: metadata plus a time-ordered sequence of attitude states.

Parameters:

Name	Type	Description	Default
`object_name`	`str`	Spacecraft name	required
`object_id`	`str`	International designator	required
`ref_frame_a`	`str`	Frame defining the transformation start point	required
`ref_frame_b`	`str`	Frame defining the transformation end point	required
`time_system`	`str`	Time system for all epochs in this segment	required
`start_time`	`Epoch`	Start of the total time span covered by the data block	required
`stop_time`	`Epoch`	End of the total time span covered by the data block	required
`attitude_type`	`str`	Attitude representation for this segment's data, e.g. `"QUATERNION"`, `"QUATERNION/ANGVEL"`, `"EULER_ANGLE"`, `"SPIN"`	required
`center_name`	`str \| None`	Celestial body the object is centered on (e.g. "EARTH")	`None`
`useable_start_time`	`Epoch \| None`	Start of the useable (interpolation-safe) span	`None`
`useable_stop_time`	`Epoch \| None`	End of the useable (interpolation-safe) span	`None`
`euler_rot_seq`	`EulerAngleOrder \| None`	Euler rotation sequence; required iff attitude_type is one of the Euler angle types	`None`
`angvel_frame`	`str \| None`	Frame in which angular velocity components are expressed; required iff attitude_type is one of the `/ANGVEL` types, and must equal ref_frame_a or ref_frame_b	`None`
`interpolation_method`	`str \| None`	Recommended interpolation method - "LINEAR", "HERMITE", or "LAGRANGE"	`None`
`interpolation_degree`	`int \| None`	Interpolation polynomial degree; required iff interpolation_method is present	`None`

Raises:

Type	Description
`ValueError`	If `time_system` does not name a CCSDS time system.
`BraheError`	If `attitude_type` or `interpolation_method` does not name a value the CCSDS ADM defines.

Example

import brahe as bh
from brahe.ccsds import AEMSegment
t0 = bh.Epoch.from_datetime(2024, 1, 1, 0, 0, 0.0, 0.0, bh.TimeSystem.UTC)
t1 = t0 + 60.0
segment = AEMSegment(
    "SAT1", "2024-001A", "EME2000", "SC_BODY_1", "UTC", t0, t1, "QUATERNION"
)

Initialize instance.

angvel_frame `property` ¶

angvel_frame: Any

str | None: Frame in which angular velocity components are expressed, or None unless attitude_type is one of the /ANGVEL types

attitude_type `property` ¶

attitude_type: Any

str: Attitude representation and accompanying derivative/rate data for this segment

center_name `property` ¶

center_name: Any

str | None: Celestial body the object is centered on

comments `property` ¶

comments: Any

list[str]: Comments associated with the data block (before the first state)

euler_rot_seq `property` ¶

euler_rot_seq: Any

EulerAngleOrder | None: Euler rotation sequence, or None unless attitude_type is one of the Euler angle types

interpolation_degree `property` ¶

interpolation_degree: Any

int | None: Interpolation polynomial degree

interpolation_method `property` ¶

interpolation_method: Any

str | None: Recommended interpolation method for this data block

metadata_comments `property` ¶

metadata_comments: ndarray

list[str]: Metadata section comments

object_id `property` ¶

object_id: Any

str: International designator

object_name `property` ¶

object_name: Any

str: Spacecraft name

ref_frame_a `property` ¶

ref_frame_a: Any

str: Frame defining the transformation start point

ref_frame_b `property` ¶

ref_frame_b: Any

str: Frame defining the transformation end point

start_time `property` ¶

start_time: Any

Epoch: Start of the total time span covered by the data block

states `property` ¶

states: ndarray

list[AEMAttitudeState]: Time-ordered attitude states (owned copies)

stop_time `property` ¶

stop_time: Any

Epoch: End of the total time span covered by the data block

time_system `property` ¶

time_system: Any

str: Time system for all epochs in this segment

useable_start_time `property` ¶

useable_start_time: Any

Epoch | None: Start of the useable (interpolation-safe) span

useable_stop_time `property` ¶

useable_stop_time: Any

Epoch | None: End of the useable (interpolation-safe) span

add_state `method descriptor` ¶

add_state(state: AEMAttitudeState) -> int

Append an attitude state to this segment.

Parameters:

Name	Type	Description	Default
`state`	`AEMAttitudeState`	Attitude state to append	required

Returns:

Name	Type	Description
`int`	`int`	Index of the new state

Raises:

Type	Description
`BraheError`	If the state's attitude type does not match the segment's attitude_type, or its epoch is not strictly after the last state's epoch

AEMAttitudeState ¶

AEMAttitudeState()

A single AEM ephemeris line: an epoch plus attitude data at that epoch.

Construct with the static method matching the desired ATTITUDE_TYPE (from_quaternion, from_quaternion_derivative, from_quaternion_angvel, from_euler_angle, from_euler_angle_derivative, from_euler_angle_angvel, from_spin, from_spin_nutation, from_spin_nutation_mom). Unlike APMSpin, the spin constructors take no AngleFormat conversion: pass radian values directly.

Example

import brahe as bh
from brahe.ccsds import AEMAttitudeState
epoch = bh.Epoch.from_datetime(2024, 1, 1, 0, 0, 0.0, 0.0, bh.TimeSystem.UTC)
state = AEMAttitudeState.from_quaternion(epoch, bh.Quaternion(1.0, 0.0, 0.0, 0.0))

Initialize instance.

angular_velocity `property` ¶

angular_velocity: Any

numpy.ndarray | None: Angular velocity vector [x, y, z] in rad/s, or None unless attitude_type is one of the /ANGVEL variants

attitude_type `property` ¶

attitude_type: Any

str: ATTITUDE_TYPE token matching this state's variant (e.g. "QUATERNION", "QUATERNION/ANGVEL", "SPIN/NUTATION_MOM")

derivative `property` ¶

derivative: Any

numpy.ndarray | None: Quaternion time derivative [q0_dot, q1_dot, q2_dot, q3_dot] (scalar-first), in 1/s, or None unless attitude_type is "QUATERNION/DERIVATIVE"

epoch `property` ¶

epoch: Any

Epoch: Epoch of this attitude state

euler_angles `property` ¶

euler_angles: float

EulerAngle | None: Euler angles (with rotation sequence), or None unless attitude_type is one of the EULER_ANGLE* variants

momentum_alpha `property` ¶

momentum_alpha: Any

float | None: Right ascension of the angular momentum vector, in radians, or None unless attitude_type is "SPIN/NUTATION_MOM"

momentum_delta `property` ¶

momentum_delta: Any

float | None: Declination of the angular momentum vector, in radians, or None unless attitude_type is "SPIN/NUTATION_MOM"

nutation `property` ¶

nutation: Any

float | None: Nutation angle, in radians, or None unless attitude_type is "SPIN/NUTATION"

nutation_period `property` ¶

nutation_period: Any

float | None: Nutation period, in seconds, or None unless attitude_type is "SPIN/NUTATION"

nutation_phase `property` ¶

nutation_phase: Any

float | None: Inertial nutation phase, in radians, or None unless attitude_type is "SPIN/NUTATION"

nutation_vel `property` ¶

nutation_vel: Any

float | None: Angular velocity of the spin axis around the momentum vector, in rad/s, or None unless attitude_type is "SPIN/NUTATION_MOM"

quaternion `property` ¶

quaternion: Any

Quaternion | None: Attitude quaternion, or None unless attitude_type is one of the QUATERNION* variants

rates `property` ¶

rates: Any

numpy.ndarray | None: Angle rates [angle_1_dot, angle_2_dot, angle_3_dot] in rad/s, in the same sequence order as euler_angles.order, or None unless attitude_type is "EULER_ANGLE/DERIVATIVE"

spin_alpha `property` ¶

spin_alpha: Any

float | None: Right ascension of the spin axis in ref_frame_a, in radians, or None unless attitude_type is one of the SPIN* variants

spin_angle `property` ¶

spin_angle: float

float | None: Phase angle about the spin axis, in radians, or None unless attitude_type is one of the SPIN* variants

spin_angle_vel `property` ¶

spin_angle_vel: float

float | None: Angular velocity about the spin axis, in rad/s, or None unless attitude_type is one of the SPIN* variants

spin_delta `property` ¶

spin_delta: Any

float | None: Declination of the spin axis in ref_frame_a, in radians, or None unless attitude_type is one of the SPIN* variants

from_euler_angle `staticmethod` ¶

from_euler_angle(epoch: Epoch, angles: EulerAngle) -> AEMAttitudeState

Construct an EULER_ANGLE attitude state.

Parameters:

Name	Type	Description	Default
`epoch`	`Epoch`	Epoch of this attitude state	required
`angles`	`EulerAngle`	Euler angles (with rotation sequence) from ref_frame_a to ref_frame_b	required

Returns:

Name	Type	Description
`AEMAttitudeState`	`AEMAttitudeState`	New attitude state

from_euler_angle_angvel `staticmethod` ¶

from_euler_angle_angvel(epoch: Epoch, angles: EulerAngle, angular_velocity: ndarray) -> AEMAttitudeState

Construct an EULER_ANGLE/ANGVEL attitude state.

Parameters:

Name	Type	Description	Default
`epoch`	`Epoch`	Epoch of this attitude state	required
`angles`	`EulerAngle`	Euler angles (with rotation sequence) from ref_frame_a to ref_frame_b	required
`angular_velocity`	`ndarray`	Angular velocity vector [x, y, z], expressed in the segment's ANGVEL_FRAME. Units: rad/s	required

Returns:

Name	Type	Description
`AEMAttitudeState`	`AEMAttitudeState`	New attitude state

from_euler_angle_derivative `staticmethod` ¶

from_euler_angle_derivative(epoch: Epoch, angles: EulerAngle, rates: ndarray) -> AEMAttitudeState

Construct an EULER_ANGLE/DERIVATIVE attitude state.

Parameters:

Name	Type	Description	Default
`epoch`	`Epoch`	Epoch of this attitude state	required
`angles`	`EulerAngle`	Euler angles (with rotation sequence) from ref_frame_a to ref_frame_b	required
`rates`	`ndarray`	Angle rates [angle_1_dot, angle_2_dot, angle_3_dot], in the same sequence order as `angles.order`. Units: rad/s	required

Returns:

Name	Type	Description
`AEMAttitudeState`	`AEMAttitudeState`	New attitude state

from_quaternion `staticmethod` ¶

from_quaternion(epoch: Epoch, quaternion: Quaternion) -> AEMAttitudeState

Construct a QUATERNION attitude state.

Parameters:

Name	Type	Description	Default
`epoch`	`Epoch`	Epoch of this attitude state	required
`quaternion`	`Quaternion`	Attitude quaternion from ref_frame_a to ref_frame_b	required

Returns:

Name	Type	Description
`AEMAttitudeState`	`AEMAttitudeState`	New attitude state

from_quaternion_angvel `staticmethod` ¶

from_quaternion_angvel(epoch: Epoch, quaternion: Quaternion, angular_velocity: ndarray) -> AEMAttitudeState

Construct a QUATERNION/ANGVEL attitude state.

Parameters:

Name	Type	Description	Default
`epoch`	`Epoch`	Epoch of this attitude state	required
`quaternion`	`Quaternion`	Attitude quaternion from ref_frame_a to ref_frame_b	required
`angular_velocity`	`ndarray`	Angular velocity vector [x, y, z], expressed in the segment's ANGVEL_FRAME. Units: rad/s	required

Returns:

Name	Type	Description
`AEMAttitudeState`	`AEMAttitudeState`	New attitude state

from_quaternion_derivative `staticmethod` ¶

from_quaternion_derivative(epoch: Epoch, quaternion: Quaternion, derivative: ndarray) -> AEMAttitudeState

Construct a QUATERNION/DERIVATIVE attitude state.

Parameters:

Name	Type	Description	Default
`epoch`	`Epoch`	Epoch of this attitude state	required
`quaternion`	`Quaternion`	Attitude quaternion from ref_frame_a to ref_frame_b	required
`derivative`	`ndarray`	Quaternion time derivative [q0_dot, q1_dot, q2_dot, q3_dot] (scalar-first), in 1/s	required

Returns:

Name	Type	Description
`AEMAttitudeState`	`AEMAttitudeState`	New attitude state

from_spin `staticmethod` ¶

from_spin(epoch: Epoch, spin_alpha: float, spin_delta: float, spin_angle: float, spin_angle_vel: float) -> AEMAttitudeState

Construct a SPIN attitude state (simple, non-nutating spin).

Parameters:

Name	Type	Description	Default
`epoch`	`Epoch`	Epoch of this attitude state	required
`spin_alpha`	`float`	Right ascension of the spin axis in ref_frame_a, in radians	required
`spin_delta`	`float`	Declination of the spin axis in ref_frame_a, in radians	required
`spin_angle`	`float`	Phase angle about the spin axis, in radians	required
`spin_angle_vel`	`float`	Angular velocity about the spin axis, in rad/s	required

Returns:

Name	Type	Description
`AEMAttitudeState`	`AEMAttitudeState`	New attitude state

from_spin_nutation `staticmethod` ¶

from_spin_nutation(epoch: Epoch, spin_alpha: float, spin_delta: float, spin_angle: float, spin_angle_vel: float, nutation: float, nutation_period: float, nutation_phase: float) -> AEMAttitudeState

Construct a SPIN/NUTATION attitude state.

Parameters:

Name	Type	Description	Default
`epoch`	`Epoch`	Epoch of this attitude state	required
`spin_alpha`	`float`	Right ascension of the spin axis in ref_frame_a, in radians	required
`spin_delta`	`float`	Declination of the spin axis in ref_frame_a, in radians	required
`spin_angle`	`float`	Phase angle about the spin axis, in radians	required
`spin_angle_vel`	`float`	Angular velocity about the spin axis, in rad/s	required
`nutation`	`float`	Nutation angle, in radians	required
`nutation_period`	`float`	Nutation period, in seconds	required
`nutation_phase`	`float`	Inertial nutation phase, in radians	required

Returns:

Name	Type	Description
`AEMAttitudeState`	`AEMAttitudeState`	New attitude state

from_spin_nutation_mom `staticmethod` ¶

from_spin_nutation_mom(epoch: Epoch, spin_alpha: float, spin_delta: float, spin_angle: float, spin_angle_vel: float, momentum_alpha: float, momentum_delta: float, nutation_vel: float) -> AEMAttitudeState

Construct a SPIN/NUTATION_MOM attitude state.

Parameters:

Name	Type	Description	Default
`epoch`	`Epoch`	Epoch of this attitude state	required
`spin_alpha`	`float`	Right ascension of the spin axis in ref_frame_a, in radians	required
`spin_delta`	`float`	Declination of the spin axis in ref_frame_a, in radians	required
`spin_angle`	`float`	Phase angle about the spin axis, in radians	required
`spin_angle_vel`	`float`	Angular velocity about the spin axis, in rad/s	required
`momentum_alpha`	`float`	Right ascension of the angular momentum vector, in radians	required
`momentum_delta`	`float`	Declination of the angular momentum vector, in radians	required
`nutation_vel`	`float`	Angular velocity of the spin axis around the momentum vector, in rad/s	required

Returns:

Name	Type	Description
`AEMAttitudeState`	`AEMAttitudeState`	New attitude state

AEM — Attitude Ephemeris Message¶

AEM ¶

classification property ¶

creation_date property ¶

format_version property ¶

message_id property ¶

originator property ¶

segments property ¶

add_segment method descriptor ¶

from_attitude_trajectory staticmethod ¶

from_file staticmethod ¶

from_str staticmethod ¶

register_for method descriptor ¶

segment_to_attitude_trajectory method descriptor ¶

to_attitude_trajectories method descriptor ¶

to_dict method descriptor ¶

to_file method descriptor ¶

to_json_string method descriptor ¶

to_string method descriptor ¶

AEMSegment ¶

angvel_frame property ¶

attitude_type property ¶

center_name property ¶

comments property ¶

euler_rot_seq property ¶

interpolation_degree property ¶

interpolation_method property ¶

metadata_comments property ¶

object_id property ¶

object_name property ¶

ref_frame_a property ¶

ref_frame_b property ¶

start_time property ¶

states property ¶

stop_time property ¶

time_system property ¶

useable_start_time property ¶

useable_stop_time property ¶

add_state method descriptor ¶

AEMAttitudeState ¶

angular_velocity property ¶

attitude_type property ¶

derivative property ¶

epoch property ¶

euler_angles property ¶

momentum_alpha property ¶

momentum_delta property ¶

nutation property ¶

nutation_period property ¶

nutation_phase property ¶

nutation_vel property ¶

quaternion property ¶

rates property ¶

spin_alpha property ¶

spin_angle property ¶

spin_angle_vel property ¶

spin_delta property ¶

from_euler_angle staticmethod ¶

from_euler_angle_angvel staticmethod ¶

from_euler_angle_derivative staticmethod ¶

from_quaternion staticmethod ¶

from_quaternion_angvel staticmethod ¶

from_quaternion_derivative staticmethod ¶

from_spin staticmethod ¶

from_spin_nutation staticmethod ¶

from_spin_nutation_mom staticmethod ¶

See Also¶

classification `property` ¶

creation_date `property` ¶

format_version `property` ¶

message_id `property` ¶

originator `property` ¶

segments `property` ¶

add_segment `method descriptor` ¶

from_attitude_trajectory `staticmethod` ¶

from_file `staticmethod` ¶

from_str `staticmethod` ¶

register_for `method descriptor` ¶

segment_to_attitude_trajectory `method descriptor` ¶

to_attitude_trajectories `method descriptor` ¶

to_dict `method descriptor` ¶

to_file `method descriptor` ¶

to_json_string `method descriptor` ¶

to_string `method descriptor` ¶

angvel_frame `property` ¶

attitude_type `property` ¶

center_name `property` ¶

comments `property` ¶

euler_rot_seq `property` ¶

interpolation_degree `property` ¶

interpolation_method `property` ¶

metadata_comments `property` ¶

object_id `property` ¶

object_name `property` ¶

ref_frame_a `property` ¶

ref_frame_b `property` ¶

start_time `property` ¶

states `property` ¶

stop_time `property` ¶

time_system `property` ¶

useable_start_time `property` ¶

useable_stop_time `property` ¶

add_state `method descriptor` ¶

angular_velocity `property` ¶

attitude_type `property` ¶

derivative `property` ¶

epoch `property` ¶

euler_angles `property` ¶

momentum_alpha `property` ¶

momentum_delta `property` ¶

nutation `property` ¶

nutation_period `property` ¶

nutation_phase `property` ¶

nutation_vel `property` ¶

quaternion `property` ¶

rates `property` ¶

spin_alpha `property` ¶

spin_angle `property` ¶

spin_angle_vel `property` ¶

spin_delta `property` ¶

from_euler_angle `staticmethod` ¶

from_euler_angle_angvel `staticmethod` ¶

from_euler_angle_derivative `staticmethod` ¶

from_quaternion `staticmethod` ¶

from_quaternion_angvel `staticmethod` ¶

from_quaternion_derivative `staticmethod` ¶

from_spin `staticmethod` ¶

from_spin_nutation `staticmethod` ¶

from_spin_nutation_mom `staticmethod` ¶