ecpi.common.mission.orbit Module¶

Created on August 26 2019

author: Philippe Bacon, APC/IN2P3/CNRS

Functions¶

`direlev_to_xyz`(p_direlev[, deg])	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.
`thetaphi_to_direlev`(p_thetaphi)	Assume theta and phi are given in deg
`xyz_to_thetaphi`(p_xyz)	Convert unit cartesian vector to physical spherical coordinate convention

`AttitudeECLAIRs`([p_frame_cat, no_biais])	Attitude for ECLAIRs instrument
`AttitudeVT`([p_frame_cat, no_biais])	Attitude for VT instrument
`ECLAIRsGeom`()	Class to write/save geometric parameters of ECLAIRs in the file of the mask
`EclairsOrbit`(orbit_filename, attitude_filename)	Orbital computations for ECLAIRs instrument
`InstruECLAIRs`([p_file_mask, p_nb_pix])	Implementation of the ECLAIRs mask geometry.