SatelliteCameraViewer.ISSAttitude module
ISSAttitude - ISS International Space Station functions
- class SatelliteCameraViewer.ISSAttitude.ISSAttitude[source]
Bases:
objectISSAttitude - ISS International Space Station functions
Methods
apply_tea_to_quaternion(q, tea_deg)Apply TEA yaw/pitch/roll offsets to a base attitude quaternion.
docking_port_vector_eci(port_name, ...)Body-frame unit vectors for ISS docking ports.
iss_in_eclipse(r_eci)Returns True if ISS is in Earth's umbra (full shadow).
lvlh_frame(r_eci, v_eci)propagate_from_tle(tle_line1, tle_line2)solar_beta_angle(r_eci, v_eci)In orbital mechanics, the beta angle (β) is the angle between a satellite's orbital plane around Earth and the geocentric position of the Sun.
tea_offsets_deg([port_config])TEA values from NASA ISS Motion Control System documentation: Current +XVV TEA: yaw=-4 deg, roll=0.9 deg Pitch varies from -12 to -2 deg depending on visiting vehicles.
xvv_attitude_quaternion(r_eci, v_eci)Construct quaternion for XVV attitude:
- classmethod apply_tea_to_quaternion(q, tea_deg)[source]
Apply TEA yaw/pitch/roll offsets to a base attitude quaternion.
- classmethod docking_port_vector_eci(port_name, quaternion_xyzw)[source]
Body-frame unit vectors for ISS docking ports. Based on ISS body axes defined in ESA reference frames.
- Parameters:
port_name – ISS port name
- classmethod iss_in_eclipse(r_eci)[source]
Returns True if ISS is in Earth’s umbra (full shadow).
- Parameters:
r_eci – ISS position vector (km)
- classmethod lvlh_frame(r_eci, v_eci)[source]
- Parameters:
r_eci (float) – ECI position.
v_eci (float) – ECI velocity.
- Returns:
Returns LVLH frame unit vectors from ECI position and velocity. Based on ESA ISS Reference Frames: Z_LVLH = -r_hat (nadir or -zenith) Y_LVLH = -h_hat (opposite orbit normal) X_LVLH = Y × Z (velocity direction)
- Return type:
dict
- classmethod propagate_from_tle(tle_line1: str, tle_line2: str)[source]
- Parameters:
tle_line1 (str) – TLE line one.
tle_line2 (str) – TLE line one.
- Returns:
A tuple (r_eci_km in Km, v_eci_km_s in Km/s) from a two-line TLE.
- Return type:
(float, float)
- classmethod solar_beta_angle(r_eci, v_eci)[source]
In orbital mechanics, the beta angle (β) is the angle between a satellite’s orbital plane around Earth and the geocentric position of the Sun. The beta angle determines the percentage of time that a satellite in low Earth orbit (LEO) spends in direct sunlight, absorbing solar radiation
Yearly Variation: The ISS beta angle fluctuates between roughly -75 and +75 degrees over a 60-day precession period and on an annual cycle.