SatelliteCameraViewer.SatelliteCamera.CameraAttitude module

CameraAttitude

CameraAttitude model

class SatelliteCameraViewer.SatelliteCamera.CameraAttitude.Attitude

Bases: object

pitch_deg: float = 0.0

roll_deg: float = 0.0

yaw_deg: float = 0.0

class SatelliteCameraViewer.SatelliteCamera.CameraAttitude.CameraAttitude(sat_quat_body_to_eci: Quaternion = None, sat_attitude: Attitude = None, cam_attitude: Attitude = None)

Bases: object

Full attitude model: - Satellite orientation in ECI (as quaternion or yaw/pitch/roll) - Camera mounting offsets (yaw/pitch/roll) - Produces final camera->ECI quaternion

Attributes:

cam_attitude

quat_cam_to_eci

quat_cam_to_eci

sat_attitude

sat_quat_body_to_eci

Methods

cam_to_eci()
quaternion_nadir_pointing(r_eci_km)	Compute camera->ECI quaternion for nadir pointing.
quaternion_pointing_ground(lat_deg, lon_deg, ...)	Compute camera->ECI quaternion that points +Z_cam at a ground location.
quaternion_pointing_radec(ra_deg, dec_deg, ...)	Compute camera->ECI quaternion that points +Z_cam at a given RA/Dec target.
quaternion_velocity_pointing(r_eci_km, ...)	Compute camera->ECI quaternion for velocity-vector pointing.
quaternion_wxyz([qw, qx, qy, qz])	quaternion
teme_to_gcrs_vector(r_teme_km, obs_time)	Convert a TEME position vector to GCRS (ECI) using Astropy.

cam_attitude: Attitude = None

cam_to_eci()

property quat_cam_to_eci

classmethod quaternion_nadir_pointing(r_eci_km)

Compute camera->ECI quaternion for nadir pointing. r_eci_km: satellite position in ECI (km), shape (3,)

Returns: quaternion [w, x, y, z]

classmethod quaternion_pointing_ground(lat_deg, lon_deg, obs_time, r_sat_gcrs_km)

Compute camera->ECI quaternion that points +Z_cam at a ground location. lat_deg, lon_deg: ground target in degrees r_sat_gcrs_km: satellite position in GCRS (km)

classmethod quaternion_pointing_radec(ra_deg, dec_deg, obs_time)

Compute camera->ECI quaternion that points +Z_cam at a given RA/Dec target.

classmethod quaternion_velocity_pointing(r_eci_km, v_eci_km_s)

Compute camera->ECI quaternion for velocity-vector pointing. r_eci_km: satellite position in ECI (km) v_eci_km_s: satellite velocity in ECI (km/s)

Returns: quaternion [w, x, y, z]

classmethod quaternion_wxyz(qw: float = 1.0, qx: float = 0.0, qy: float = 0.0, qz: float = 0.0) → Quaternion

quaternion

sat_attitude: Attitude = None

sat_quat_body_to_eci: Quaternion = None

classmethod teme_to_gcrs_vector(r_teme_km, obs_time)

Convert a TEME position vector to GCRS (ECI) using Astropy. r_teme_km: (3,) km vector Returns: (3,) km vector in GCRS

class SatelliteCameraViewer.SatelliteCamera.CameraAttitude.Quaternion(qw: float = 1.0, qx: float = 0.0, qy: float = 0.0, qz: float = 0.0)

Bases: object

A satellite quaternion body (or attitude quaternion) is a 4-component mathematical tool q = [q0,q1,q2,q3] or q = [s,v] used to represent the 3D orientation (attitude) of a satellite’s body-fixed frame relative to a reference frame. https://en.wikipedia.org/wiki/Quaternions_and_spatial_rotation

Attributes:

w

wxyz

x

y

z

qw: float = 1.0

qx: float = 0.0

qy: float = 0.0

qz: float = 0.0

property w

property wxyz

property x

property y

property z