ACwing FC firmware
STM32WB55: attitude IEKF, altitude Kalman filter, flight core, protocol v2
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tlm_state_t Struct Reference

#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
 

Detailed Description

Definition at line 55 of file telemetry.h.

Field Documentation

◆ seq

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().

◆ t_us

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().

◆ q

float tlm_state_t::q[4]

body->world, [w x y z]

Definition at line 58 of file telemetry.h.

Referenced by tlm_build_state().

◆ bias

float tlm_state_t::bias[3]

rad/s

Definition at line 59 of file telemetry.h.

Referenced by tlm_build_state().

◆ acc

float tlm_state_t::acc[3]

g, body frame

Definition at line 60 of file telemetry.h.

Referenced by tlm_build_state().

◆ gyro

float tlm_state_t::gyro[3]

rad/s

Definition at line 61 of file telemetry.h.

Referenced by tlm_build_state().

◆ mag

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().

◆ flags

uint8_t tlm_state_t::flags

Definition at line 63 of file telemetry.h.

Referenced by tlm_build_state().


The documentation for this struct was generated from the following file: