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ACwing FC firmware
STM32WB55: attitude IEKF, altitude Kalman filter, flight core, protocol v2
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#include <telemetry.h>
Data Fields | |
| uint16_t | seq |
| filter sample index (0 = initial state R0) | |
| uint32_t | t_us |
| filter time: sum of the dt actually used | |
| float | q [4] |
| body->world, [w x y z] | |
| float | bias [3] |
| rad/s | |
| float | acc [3] |
| g, body frame | |
| float | gyro [3] |
| rad/s | |
| float | mag [3] |
| uT, body frame, hard-iron already removed | |
| uint8_t | flags |
Definition at line 55 of file telemetry.h.
| uint16_t tlm_state_t::seq |
filter sample index (0 = initial state R0)
Definition at line 56 of file telemetry.h.
Referenced by tlm_build_state().
| uint32_t tlm_state_t::t_us |
filter time: sum of the dt actually used
Definition at line 57 of file telemetry.h.
Referenced by tlm_build_state().
| float tlm_state_t::q[4] |
| float tlm_state_t::bias[3] |
| float tlm_state_t::acc[3] |
| float tlm_state_t::gyro[3] |
| float tlm_state_t::mag[3] |
uT, body frame, hard-iron already removed
Definition at line 62 of file telemetry.h.
Referenced by tlm_build_state().
| uint8_t tlm_state_t::flags |
Definition at line 63 of file telemetry.h.
Referenced by tlm_build_state().