ecpi.common.mission.orbit Module¶
Created on August 26 2019
author: Philippe Bacon, APC/IN2P3/CNRS
Functions¶
direlev_to_xyz(p_direlev) |
Convert spherical coordinate with CNES convention to unit cartesian vector |
from_j2000_to_ecllos(v, q_j2000_sat[, mode]) |
Succesive transformations of a vector v in J2000 frame to ECLAIRs frame with appropriate quaternion. |
xyz_to_thetaphi(p_xyz) |
Convert unit cartesian vector to physical spherical coordinate convention |
Classes¶
AttitudeECLAIRs([p_frame_cat]) |
|
AttitudeVT([p_frame_cat]) |
doc CNES 6.1.1 inertial reference frame |
ECLAIRsGeom() |
All distance are in cm |
EclairsOrbit(orbit_filename, attitude_filename) |
Constructor |
InstruECLAIRs([show, p_file_mask, p_nb_pix]) |
Implementation of the ECLAIRs mask geometry. |