Orientation and Coordinate Frame Transformations
| dcm2euler_v000.m | DCM to Euler Angles |
| dcm2heading_v000.m | computes yaw angle from dcm |
| dcm2llh_v000.m | \(C_e^n\) (Earth to navigation frame DCM) to latitude, longitude, wander angle |
| dcm2quat_v000.m | Direction Cosine Matrix (DCM) to Quaternion |
| dcm2rot_v000.m | DCM to Rotation Vector |
| dir2euler_v000.m | Given a direction vector, computes the orientation (assumes roll=0) (e.g. Given the difference of 2 succesive GPS coordinates, computes the orientation of the vehicle assumung roll=0) |
| ecef2geo_v000.m | Converts ECEF (Earth centered Earth Fixed) position to Llh (Geodetic Position) and vice versa |
| euler2dcm_v000.m | Transforms Euler angles to DCM |
| llh2dcm_v000.m | Given latitude and longtitude and wander angle, computes \(C_n^e\) tranformation matrix (Navigation frame to ECEF DCM) |
| quat2dcm_v000.m | Convert quaternion into DCM |
| quat2rot_v000.m | Quaternion to Rotation Vector |
| quatmult_v001.m | Quaternion multiplication |
| quatrot_v000.m | Vector transformation using quaternions (rotate a vector given a quaternion) |
| rot2dcm_v000.m | Rotation vector to direction cosine matrix |
| rvec2quat_v000.m | Rotation vector to quaternion |