eff_scheduling_rotwing_nB.c

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/*
 * Copyright (C) 2023 Tomaso De Ponti <T.M.L.DePonti@tudelft.nl>
 *
 * This file is part of paparazzi
 *
 * paparazzi is free software; you can redistribute it and/or modify
 * it under the terms of the GNU General Public License as published by
 * the Free Software Foundation; either version 2, or (at your option)
 * any later version.
 *
 * paparazzi is distributed in the hope that it will be useful,
 * but WITHOUT ANY WARRANTY; without even the implied warranty of
 * MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE.  See the
 * GNU General Public License for more details.
 *
 * You should have received a copy of the GNU General Public License
 * along with paparazzi; see the file COPYING.  If not, see
 * <http://www.gnu.org/licenses/>.
 */

 
#include "modules/ctrl/eff_scheduling_rotwing_nB.h"
#include "generated/airframe.h"
#include "state.h"
#include "modules/actuators/actuators.h"
#include "modules/core/abi.h"
#include "filters/low_pass_filter.h"
#include "modules/ins/ins_ext_pose.h"
 
#define FORCE_ONELOOP
#ifdef FORCE_ONELOOP
#include "firmwares/rotorcraft/oneloop/oneloop_nB.h"
float actuator_state_filt_vect[EFF_MAT_COLS_NB] = {0};
#else
#include "firmwares/rotorcraft/stabilization/stabilization_indi.h"
#endif
 
#ifndef ROTWING_EFF_SCHED_IXX_BODY
#error "NO ROTWING_EFF_SCHED_IXX_BODY defined"
#endif
 
#ifndef ROTWING_EFF_SCHED_IYY_BODY
#error "NO ROTWING_EFF_SCHED_IYY_BODY defined"
#endif
 
#ifndef ROTWING_EFF_SCHED_IZZ
#error "NO ROTWING_EFF_SCHED_IZZ defined"
#endif
 
#ifndef ROTWING_EFF_SCHED_IXX_WING
#error "NO ROTWING_EFF_SCHED_IXX_WING defined"
#endif
 
#ifndef ROTWING_EFF_SCHED_IYY_WING
#error "NO ROTWING_EFF_SCHED_IYY_WING defined"
#endif
 
#ifndef ROTWING_EFF_SCHED_M
#error "NO ROTWING_EFF_SCHED_M defined"
#endif
 
bool manual_roll  = false;
bool manual_pitch = false;
bool manual_yaw   = false;
/* Effectiveness Matrix definition */
float G2_RW[EFF_MAT_COLS_NB]                       = {0};//ROTWING_EFF_SCHED_G2; //scaled by RW_G_SCALE
float G1_RW[EFF_MAT_ROWS_NB][EFF_MAT_COLS_NB]      = {0};//{ROTWING_EFF_SCHED_G1_ZERO, ROTWING_EFF_SCHED_G1_ZERO, ROTWING_EFF_SCHED_G1_THRUST, ROTWING_EFF_SCHED_G1_ROLL, ROTWING_EFF_SCHED_G1_PITCH, ROTWING_EFF_SCHED_G1_YAW}; //scaled by RW_G_SCALE 
float EFF_MAT_RW[EFF_MAT_ROWS_NB][EFF_MAT_COLS_NB] = {0};
float I_inv[3][3]                                  = {0};
static float flt_cut_a  = 1.0e-6;//1.0e-6;
static float flt_cut_ap = 2.0e-6;//2.0e-5; //2.0e-3
static float flt_cut    = 1.0e-6;//1.0e-5; //1.0e-4
 
struct FloatEulers eulers_zxy_RW_EFF;
static Butterworth2LowPass skew_filt; 
static Butterworth2LowPass phi_filt;
static Butterworth2LowPass theta_filt;
static Butterworth2LowPass psi_filt;
/* Temp variables*/
int G2_on = 0;
bool airspeed_fake_on = false;
float airspeed_fake = 0.0;
float ele_eff = 19.36; // (0.88*22.0);
float roll_eff = 8.9;//15.402;//3.835;//3.835;5.5
float yaw_eff  = 0.237; // 1.3171*0.390=0.514 or 0.659 and 0.812 (pitch - roll)
float ele_min = 0.0;
/* Define Forces and Moments tructs for each actuator*/
struct RW_Model RW;
 
int thrust_curve = 1.0;
float temp_mQ_k = 1.37; //Manual Value For Tuning2
inline void eff_scheduling_rotwing_update_wing_angle(void);
inline void eff_scheduling_rotwing_update_airspeed(void);
void  ele_pref_sched(void);
void  update_attitude(void);
void  sum_EFF_MAT_RW(void);
void  init_RW_Model(void);
void  calc_G1_G2_RW(void);  
float calc_thrust_curve(float k1, float k2, float k3, float u);
float calc_thrust_curve_d(float k1, float k2, float u);
void calc_all_thrust_curve(void);
void init_all_thrust_curve(void);

#ifndef WING_ROTATION_CAN_ROTWING_ID
#define WING_ROTATION_CAN_ROTWING_ID ABI_BROADCAST
#endif
PRINT_CONFIG_VAR(WING_ROTATION_CAN_ROTWING_ID)
static abi_event wing_position_ev;
 
float skew_meas = 0.0;
static void wing_position_cb(uint8_t sender_id UNUSED, struct act_feedback_t *pos_msg, uint8_t num_act)
{
  for (int i=0; i<num_act; i++){
    if (pos_msg[i].set.position && (pos_msg[i].idx == SERVO_ROTATION_MECH_IDX))
    {
      skew_meas = 0.5 * M_PI - pos_msg[i].position;
      Bound(skew_meas, 0, 0.5 * M_PI);
    }
  }
}
 
#include "generated/modules.h"
PRINT_CONFIG_VAR(EFF_SCHEDULING_ROTWING_PERIODIC_FREQ)
void eff_scheduling_rotwing_init(void)
{
  init_RW_Model();
  update_attitude();
  AbiBindMsgACT_FEEDBACK(WING_ROTATION_CAN_ROTWING_ID, &wing_position_ev, wing_position_cb);
  float tau_skew = 1.0 / (2.0 * M_PI * 5.0);
  float tau_att = 1.0 / (2.0 * M_PI * 2.0);
  float sample_time = 1.0 / PERIODIC_FREQUENCY;
  init_butterworth_2_low_pass(&skew_filt, tau_skew, sample_time, 0.0);
  init_butterworth_2_low_pass(&phi_filt, tau_att, sample_time, 0.0);
  init_butterworth_2_low_pass(&theta_filt, tau_att, sample_time, 0.0);
  init_butterworth_2_low_pass(&psi_filt, tau_att, sample_time, 0.0);
}
 
void init_RW_Model(void)
{
  // Inertia and mass
  RW.I.b_xx = ROTWING_EFF_SCHED_IXX_BODY; // [kgm²] 
  RW.I.b_yy = ROTWING_EFF_SCHED_IYY_BODY; // [kgm²] 
  RW.I.w_xx = ROTWING_EFF_SCHED_IXX_WING; // [kgm²] 
  RW.I.w_yy = ROTWING_EFF_SCHED_IYY_WING; // [kgm²] 
  RW.I.xx   = (RW.I.b_xx + RW.I.w_xx);    // [kgm²]
  RW.I.yy   = RW.I.b_yy + RW.I.w_yy;      // [kgm²]
  RW.I.zz   = ROTWING_EFF_SCHED_IZZ;      // [kgm²]
  RW.m      = ROTWING_EFF_SCHED_M;        // [kg]
  
  // Init the thrust curves
  init_all_thrust_curve();
  // Motor Front
  RW.mF.dFdu  = ROTWING_EFF_SCHED_MF_dFdu / RW_G_SCALE;
  RW.mF.dMdu  = ROTWING_EFF_SCHED_MF_dMdu / RW_G_SCALE;
  RW.mF.dMdud = ROTWING_EFF_SCHED_MF_dMdud / (RW_G_SCALE * RW_G_SCALE);
  printf("RW.mF.dFdu: %f\n", RW.mF.dFdu);
  RW.mF.l     = ROTWING_EFF_SCHED_MF_l;
 
  // Motor Right
  RW.mR.dFdu  = ROTWING_EFF_SCHED_MR_dFdu / RW_G_SCALE;
  RW.mR.dMdu  = ROTWING_EFF_SCHED_MR_dMdu / RW_G_SCALE;
  RW.mR.dMdud = ROTWING_EFF_SCHED_MR_dMdud / (RW_G_SCALE * RW_G_SCALE);
  RW.mR.l     = ROTWING_EFF_SCHED_MR_l;
 
  // Motor Back
  RW.mB.dFdu  = ROTWING_EFF_SCHED_MB_dFdu / RW_G_SCALE;
  RW.mB.dMdu  = ROTWING_EFF_SCHED_MB_dMdu / RW_G_SCALE;
  RW.mB.dMdud = ROTWING_EFF_SCHED_MB_dMdud / (RW_G_SCALE * RW_G_SCALE);
  RW.mB.l     = ROTWING_EFF_SCHED_MB_l;
 
  // Motor Left
  RW.mL.dFdu  = ROTWING_EFF_SCHED_ML_dFdu / RW_G_SCALE;
  RW.mL.dMdu  = ROTWING_EFF_SCHED_ML_dMdu / RW_G_SCALE;
  RW.mL.dMdud = ROTWING_EFF_SCHED_ML_dMdud / (RW_G_SCALE * RW_G_SCALE);
  RW.mL.l     = ROTWING_EFF_SCHED_ML_l;
 
  // Motor Pusher
  RW.mP.dFdu  = ROTWING_EFF_SCHED_MP_dFdu / RW_G_SCALE;
  RW.mP.dMdu  = ROTWING_EFF_SCHED_MP_dMdu / RW_G_SCALE;
  RW.mP.dMdud = ROTWING_EFF_SCHED_MP_dMdud / (RW_G_SCALE * RW_G_SCALE);
  RW.mP.l     = ROTWING_EFF_SCHED_MP_l;     
 
  // Elevator
  RW.ele.dFdu    = ele_eff / (RW_G_SCALE * RW_G_SCALE); // [N  / pprz]   old value: 24.81 29.70
  RW.ele.dMdu    = 0;                                 // [Nm / pprz]
  RW.ele.dMdud   = 0;                                 // [Nm / pprz]
  RW.ele.l       = 0.85;                              // [m]    
  RW.ele_pref    = 0;           
  // Rudder
  RW.rud.dFdu   = 1.2015 / (RW_G_SCALE * RW_G_SCALE); // [N  / pprz] 
  RW.rud.dMdu   = 0;                                 // [Nm / pprz]
  RW.rud.dMdud  = 0;                                 // [Nm / pprz]
  RW.rud.l      = 0.88;                              // [m]        
  // Aileron
  RW.ail.dFdu   = 7.678 / (RW_G_SCALE * RW_G_SCALE); // [N  / pprz] (1.88 * 4.084)
  RW.ail.dMdu   = 0;                                 // [Nm / pprz]
  RW.ail.dMdud  = 0;                                 // [Nm / pprz]
  RW.ail.l      = 0.68;                              // [m]        
  // Flaperon
  RW.flp.dFdu   = 10.825 / (RW_G_SCALE * RW_G_SCALE); // [N  / pprz] (1.88 * 5.758)
  RW.flp.dMdu   = 0;                                 // [Nm / pprz]
  RW.flp.dMdud  = 0;                                 // [Nm / pprz]
  RW.flp.l      = 0.36;                              // [m]     
  // Lift: k0 the v²+ k1 the sin² v² + k2 sin² v²
  RW.wing.k0    = 0.336 + 0.0507 + 0.102;
  RW.wing.k1    = 0.616;
  RW.wing.k2    = 0.121;
  // Initialize attitude
  RW.att.phi    = 0.0;
  RW.att.theta  = 0.0; 
  RW.att.psi    = 0.0; 
  RW.att.sphi   = 0.0; 
  RW.att.cphi   = 0.0; 
  RW.att.stheta = 0.0; 
  RW.att.ctheta = 0.0; 
  RW.att.spsi   = 0.0; 
  RW.att.cpsi   = 0.0;
  // Initialize skew variables to quad values
  RW.skew.rad   = 0.0; // ABI input
  RW.skew.deg   = 0.0;
  RW.skew.cosr  = 1.0;
  RW.skew.sinr  = 0.0;
  RW.skew.cosr2 = 1.0;
  RW.skew.sinr2 = 0.0;
  RW.skew.sinr3 = 0.0;
  // Initialize airspeed
  RW.as  = 0.0;
  RW.as2 = 0.0;
}
 
/*Update the attitude*/
void  update_attitude(void)
{
  float_eulers_of_quat_zxy(&eulers_zxy_RW_EFF, stateGetNedToBodyQuat_f());
  update_butterworth_2_low_pass(&phi_filt, eulers_zxy_RW_EFF.phi);
  update_butterworth_2_low_pass(&theta_filt, eulers_zxy_RW_EFF.theta);
  update_butterworth_2_low_pass(&psi_filt, eulers_zxy_RW_EFF.psi);
  RW.att.phi    = phi_filt.o[0];//eulers_zxy_RW_EFF.phi;
  RW.att.theta  = theta_filt.o[0];//eulers_zxy_RW_EFF.theta;
  RW.att.psi    = psi_filt.o[0];//eulers_zxy_RW_EFF.psi;
  //printf("Attitude filt: %f %f %f\n", RW.att.phi, RW.att.theta, RW.att.psi);
  RW.att.sphi   = sinf(RW.att.phi);
  RW.att.cphi   = cosf(RW.att.phi);
  RW.att.stheta = sinf(RW.att.theta);
  RW.att.ctheta = cosf(RW.att.theta);
  RW.att.spsi   = sinf(RW.att.psi);
  RW.att.cpsi   = cosf(RW.att.psi);
}
/* Function to precalculate once some constant effectiveness values to improve efficiency*/
void calc_G1_G2_RW(void)
{
  // Inertia
  int x = 0;
  int y = 1;
  int z = 2;
  float sigma = (RW.I.b_xx*RW.I.b_yy + RW.I.b_xx*RW.I.w_yy*RW.skew.cosr2 + RW.I.b_yy*RW.I.w_xx*RW.skew.cosr2 + RW.I.w_xx*RW.I.w_yy*RW.skew.cosr4 + RW.I.b_xx*RW.I.w_xx*RW.skew.sinr2 + RW.I.b_yy*RW.I.w_yy*RW.skew.sinr2 + RW.I.w_xx*RW.I.w_yy*RW.skew.sinr4 + 2*RW.I.w_xx*RW.I.w_yy*RW.skew.cosr2*RW.skew.sinr2);
  I_inv[x][x] = (RW.I.w_yy*RW.skew.cosr2 + RW.I.w_xx*RW.skew.sinr2 + RW.I.b_yy)/(sigma);
  I_inv[x][y] = (RW.skew.cosr*RW.skew.sinr*(RW.I.w_xx - RW.I.w_yy))/sigma;
  I_inv[x][z] = 0.0;
  I_inv[y][x] = I_inv[x][y];
  I_inv[y][y] = (RW.I.w_xx*RW.skew.cosr2 + RW.I.w_yy*RW.skew.sinr2 + RW.I.b_xx)/sigma;
  I_inv[y][z] = 0.0;
  I_inv[z][x] = 0.0;
  I_inv[z][y] = 0.0;
  I_inv[z][z] = 1/RW.I.zz;
  // Calc motor and control effectiveness
  calc_all_thrust_curve();
 
  float sigma1 = I_inv[y][y]*RW.skew.sinr - I_inv[x][y]*RW.skew.cosr;
  float sigma2 = I_inv[x][x]*RW.skew.cosr - I_inv[x][y]*RW.skew.sinr;
  // Motor Front
  G1_RW[RW_aZ][COMMAND_MOTOR_FRONT]  = -RW.mF.dFdu / RW.m;
  G1_RW[RW_ap][COMMAND_MOTOR_FRONT]  =  (RW.mF.dFdu * RW.mF.l) * I_inv[x][y];
  G1_RW[RW_aq][COMMAND_MOTOR_FRONT]  =  (RW.mF.dFdu * RW.mF.l) * I_inv[y][y];
  G1_RW[RW_ar][COMMAND_MOTOR_FRONT]  = -RW.mF.dMdu  * I_inv[z][z];
  G2_RW[COMMAND_MOTOR_FRONT]         = -G2_on*RW.mF.dMdud * I_inv[z][z] * PERIODIC_FREQUENCY;
  // Motor Right
  G1_RW[RW_aZ][COMMAND_MOTOR_RIGHT]  = -RW.mR.dFdu / RW.m;
  G1_RW[RW_ap][COMMAND_MOTOR_RIGHT]  = -RW.mR.dFdu * RW.mR.l * sigma2;
  G1_RW[RW_aq][COMMAND_MOTOR_RIGHT]  =  RW.mR.dFdu * RW.mR.l * sigma1;
  G1_RW[RW_ar][COMMAND_MOTOR_RIGHT]  =  RW.mR.dMdu  * I_inv[z][z];
  G2_RW[COMMAND_MOTOR_RIGHT]         =  G2_on*RW.mR.dMdud * I_inv[z][z] * PERIODIC_FREQUENCY;
  // Motor Back
  G1_RW[RW_aZ][COMMAND_MOTOR_BACK]   = -RW.mB.dFdu / RW.m;
  G1_RW[RW_ap][COMMAND_MOTOR_BACK]   = -(RW.mB.dFdu * RW.mB.l) * I_inv[x][y];
  G1_RW[RW_aq][COMMAND_MOTOR_BACK]   = -(RW.mB.dFdu * RW.mB.l) * I_inv[y][y];
  G1_RW[RW_ar][COMMAND_MOTOR_BACK]   = -RW.mB.dMdu  * I_inv[z][z];
  G2_RW[COMMAND_MOTOR_BACK]          = -G2_on*RW.mB.dMdud * I_inv[z][z] * PERIODIC_FREQUENCY;
  // Motor Left
  G1_RW[RW_aZ][COMMAND_MOTOR_LEFT]   = -RW.mL.dFdu / RW.m;
  G1_RW[RW_ap][COMMAND_MOTOR_LEFT]   =  RW.mL.dFdu * RW.mL.l * sigma2;
  G1_RW[RW_aq][COMMAND_MOTOR_LEFT]   = -RW.mL.dFdu * RW.mL.l * sigma1;
  G1_RW[RW_ar][COMMAND_MOTOR_LEFT]   =  RW.mL.dMdu  * I_inv[z][z];
  G2_RW[COMMAND_MOTOR_LEFT]          =  G2_on*RW.mL.dMdud * I_inv[z][z] * PERIODIC_FREQUENCY;
 
  // Aileron
  float Mx_a = RW.ail.dFdu * RW.as2 * RW.ail.l * RW.skew.sinr3;
  float My_a = RW.ail.dFdu * RW.as2 * RW.ail.l * (RW.skew.cosr-RW.skew.cosr3);
  G1_RW[RW_ap][COMMAND_AILERONS]     =  Mx_a * I_inv[x][x] + My_a * I_inv[x][y];
  G1_RW[RW_aq][COMMAND_AILERONS]     =  Mx_a * I_inv[x][y] + My_a * I_inv[y][y];
  // Lift and thrust
  RW.wing.dLdtheta                =  (RW.wing.k0 + RW.wing.k1 * RW.skew.sinr2) * RW.as2;
  Bound(RW.wing.dLdtheta, 0.0, 1300.0);
  RW.wing.L                       =  RW.wing.k0 * RW.att.theta * RW.as2 + RW.wing.k1 * RW.att.theta * RW.skew.sinr2 * RW.as2 + RW.wing.k2 * RW.skew.sinr2 * RW.as2;
  Bound(RW.wing.L, 0.0, 350.0);
  RW.P                            = 0;//actuator_state_1l[COMMAND_MOTOR_PUSHER] * RW.mP.dFdu;
}
 
void eff_scheduling_rotwing_periodic(void)
{
  update_attitude();
  eff_scheduling_rotwing_update_wing_angle();
  eff_scheduling_rotwing_update_airspeed();
  ele_pref_sched();
  calc_G1_G2_RW();
  sum_EFF_MAT_RW();
}
 

 
 
void sum_EFF_MAT_RW(void) {
  
  // Thrust and Pusher force estimation
  float L      = RW.wing.L / RW.m;          // Lift specific force
  float dLdtheta = RW.wing.dLdtheta / RW.m; // Lift specific force derivative with pitch
  float T      = RW.T / RW.m;             //  Thrust specific force. Minus gravity is a guesstimate.
  float P      = RW.P / RW.m;               // Pusher specific force
  float T_L    = T + L * RW.att.ctheta;     // Thrust and Lift term
  float P_L    = P + L * RW.att.stheta;     // Pusher and Lift term
  // Kept for consistency with eff_scheduling_rotwing_V2, not used by the nB effectiveness
  (void)dLdtheta;
  (void)T_L;
  (void)P_L;
  int i = 0;
  int j = 0;
 
  for (i = 0; i < EFF_MAT_COLS_NB; i++) {
    switch (i) {
    case (COMMAND_MOTOR_FRONT):
    case (COMMAND_MOTOR_BACK):
    case (COMMAND_MOTOR_RIGHT):     
    case (COMMAND_MOTOR_LEFT):
      EFF_MAT_RW[RW_aN][i] = (RW.att.cpsi * RW.att.stheta + RW.att.ctheta * RW.att.sphi   * RW.att.spsi) * G1_RW[RW_aZ][i];
      EFF_MAT_RW[RW_aE][i] = (RW.att.spsi * RW.att.stheta - RW.att.cpsi   * RW.att.ctheta * RW.att.sphi) * G1_RW[RW_aZ][i];
      EFF_MAT_RW[RW_aD][i] = (RW.att.cphi * RW.att.ctheta                                              ) * G1_RW[RW_aZ][i];
      EFF_MAT_RW[RW_ap][i] = (G1_RW[RW_ap][i])                                       ;
      EFF_MAT_RW[RW_aq][i] = (G1_RW[RW_aq][i])                                       ;
      EFF_MAT_RW[RW_ar][i] = (G1_RW[RW_ar][i] + G2_RW[i])  ;
      break;  
    case (COMMAND_AILERONS):
      EFF_MAT_RW[RW_aN][i] = 0.0;
      EFF_MAT_RW[RW_aE][i] = 0.0;
      EFF_MAT_RW[RW_aD][i] = 0.0;
      EFF_MAT_RW[RW_ap][i] = G1_RW[RW_ap][i];
      EFF_MAT_RW[RW_aq][i] = G1_RW[RW_aq][i];
      EFF_MAT_RW[RW_ar][i] = G1_RW[RW_ar][i];                             
      break;     
    case (COMMAND_ROLL):
      EFF_MAT_RW[RW_aN][i] = (-RW.att.cphi * RW.att.ctheta * RW.att.spsi * T);
      EFF_MAT_RW[RW_aE][i] = ( RW.att.cphi * RW.att.ctheta * RW.att.cpsi * T);
      EFF_MAT_RW[RW_aD][i] = ( RW.att.sphi * RW.att.ctheta * T);
      EFF_MAT_RW[RW_ap][i] = 0.0;
      EFF_MAT_RW[RW_aq][i] = 0.0;
      EFF_MAT_RW[RW_ar][i] = 0.0;  
      break;
    case (COMMAND_PITCH):
      EFF_MAT_RW[RW_aN][i] = (-(RW.att.ctheta * RW.att.cpsi - RW.att.sphi * RW.att.stheta * RW.att.spsi) * T);
      EFF_MAT_RW[RW_aE][i] = (-(RW.att.ctheta * RW.att.spsi + RW.att.sphi * RW.att.stheta * RW.att.cpsi) * T);
      EFF_MAT_RW[RW_aD][i] = ( RW.att.stheta * RW.att.cphi * T)                                           ;
      EFF_MAT_RW[RW_ap][i] = 0.0;
      EFF_MAT_RW[RW_aq][i] = 0.0;
      EFF_MAT_RW[RW_ar][i] = 0.0;
      break;
    default:
      break;
    }
  }
  for (i = 0; i < EFF_MAT_ROWS_NB; i++) {
    for(j = 0; j < EFF_MAT_COLS_NB; j++) {
      float abs = fabs(EFF_MAT_RW[i][j]);
      switch (i) {
        case (RW_aN):
        case (RW_aE):
        case (RW_aD):
          if (abs < flt_cut_a) {
            EFF_MAT_RW[i][j] = 0.0;
          }
          break;
        case (RW_aq):
        case (RW_ar):
          if (abs < flt_cut) {
            EFF_MAT_RW[i][j] = 0.0;
          }
          break;
        case (RW_ap):
          if (abs < flt_cut_ap) {
            EFF_MAT_RW[i][j] = 0.0;
          }
          break;
      }
    }
  }
  if(manual_roll){
    //EFF_MAT_RW[RW_ap][1] = -0.012149; 
    //EFF_MAT_RW[RW_ap][3] = 0.012149;
    //EFF_MAT_RW[RW_ap][1] = -roll_eff/1000.0; 
    //EFF_MAT_RW[RW_ap][3] =  roll_eff/1000.0;
    EFF_MAT_RW[RW_ap][0] = 0.0006;
    EFF_MAT_RW[RW_ap][2] = -0.0006;
  }
  if(manual_pitch){
    EFF_MAT_RW[RW_aq][0] = 0.001708; 
    EFF_MAT_RW[RW_aq][2] = -0.001708;
  }
  if(manual_yaw){
    EFF_MAT_RW[RW_ar][0] = -0.000421; 
    EFF_MAT_RW[RW_ar][1] = 0.000421;
    EFF_MAT_RW[RW_ar][2] = -0.000421;
    EFF_MAT_RW[RW_ar][3] = 0.000421;
    //G2_RW[0] = -2.1e-5;
    //G2_RW[1] = 2.1e-5;
    //G2_RW[2] = -2.1e-5;
    //G2_RW[3] = 2.1e-5;
  }
}
 
void eff_scheduling_rotwing_update_wing_angle(void)
{
  // Calculate sin and cosines of rotation
  update_butterworth_2_low_pass(&skew_filt, skew_meas);
  RW.skew.rad   = skew_filt.o[0];
  RW.skew.deg   = RW.skew.rad / M_PI * 180.;
  RW.skew.cosr  = cosf(RW.skew.rad);
  RW.skew.sinr  = sinf(RW.skew.rad);
  RW.skew.cosr2 = RW.skew.cosr * RW.skew.cosr;
  RW.skew.sinr2 = RW.skew.sinr * RW.skew.sinr;
  RW.skew.sinr3 = RW.skew.sinr2 * RW.skew.sinr;
  RW.skew.cosr3 = RW.skew.cosr2 * RW.skew.cosr;
  RW.skew.cosr4 = RW.skew.cosr2 * RW.skew.cosr2;
  RW.skew.sinr4 = RW.skew.sinr2 * RW.skew.sinr2;
#ifdef INS_EXT_VISION_ROTATION
  // Define an INS external pose quaternion rotation from the wing rotation angle
  struct FloatEulers rot_e = {0, 0, RW.skew.rad};
  float_quat_of_eulers(&ins_ext_vision_rot, &rot_e);
#endif
 
}
static float sim_time = 0.0f;
void eff_scheduling_rotwing_update_airspeed(void)
{
  struct FloatRates *body_rates = stateGetBodyRates_f();
  RW.as = body_rates->r*0.5; //stateGetAirspeed_f(); FIXME
  float sgn_as = copysignf(1.0,RW.as);
  BoundAbs(RW.as,30.);
  RW.as2 = sgn_as * RW.as * RW.as;
  BoundAbs(RW.as2, 900.);
  if(airspeed_fake_on) {
    //float freq = 0.5;
    //float amp = 3.0;
    sim_time += 0.002f;
    RW.as = airspeed_fake ;//+ amp * sinf(2.0 * M_PI * freq * time);
    RW.as2 = RW.as * RW.as;
  } else {
    sim_time = 0.0f;
  }
}
 
void ele_pref_sched(void)
{
  if (RW.as > ELE_MIN_AS){
    RW.ele_pref = (ZERO_ELE_PPRZ - ele_min) / (ELE_MAX_AS - ELE_MIN_AS) * (RW.as - ELE_MIN_AS) + ele_min;
    Bound(RW.ele_pref,ele_min,ZERO_ELE_PPRZ);
  } else {
    RW.ele_pref = ele_min;
  }
}
 
float calc_thrust_curve(float k1, float k2, float k3, float u){
  return k1*u*u + k2*u + k3;
}
 
float calc_thrust_curve_d(float k1, float k2, float u){
  float out= 2.0*k1*u + k2;
  Bound(out, 1.0e-3, 1.0e-2);
  return out;
}
 
void calc_all_thrust_curve(void){
  switch(thrust_curve){
    case(0):
      // Curve calculated at the Current Motor State
      RW.mF.dFdu = calc_thrust_curve_d(ROTWING_EFF_SCHED_MF_k1, ROTWING_EFF_SCHED_MF_k2, actuator_state_1l[COMMAND_MOTOR_FRONT]);
      RW.mR.dFdu = calc_thrust_curve_d(ROTWING_EFF_SCHED_MR_k1, ROTWING_EFF_SCHED_MR_k2, actuator_state_1l[COMMAND_MOTOR_RIGHT]);
      RW.mB.dFdu = calc_thrust_curve_d(ROTWING_EFF_SCHED_MB_k1, ROTWING_EFF_SCHED_MB_k2, actuator_state_1l[COMMAND_MOTOR_BACK]) ;
      RW.mL.dFdu = calc_thrust_curve_d(ROTWING_EFF_SCHED_ML_k1, ROTWING_EFF_SCHED_ML_k2, actuator_state_1l[COMMAND_MOTOR_LEFT]) ;
      break;
    case(1):
      // Curve statically calculated at 50% throttle
      RW.mF.dFdu = calc_thrust_curve_d(ROTWING_EFF_SCHED_MF_k1, ROTWING_EFF_SCHED_MF_k2, 4800.0);
      RW.mR.dFdu = calc_thrust_curve_d(ROTWING_EFF_SCHED_MR_k1, ROTWING_EFF_SCHED_MR_k2, 4800.0);
      RW.mB.dFdu = calc_thrust_curve_d(ROTWING_EFF_SCHED_MB_k1, ROTWING_EFF_SCHED_MB_k2, 4800.0);
      RW.mL.dFdu = calc_thrust_curve_d(ROTWING_EFF_SCHED_ML_k1, ROTWING_EFF_SCHED_ML_k2, 4800.0);
      break;
    case(2):
      // Manual thrust for tuning
      RW.mF.dFdu = calc_thrust_curve_d(ROTWING_EFF_SCHED_MF_k1, ROTWING_EFF_SCHED_MF_k2, 4800.0);
      RW.mR.dFdu = temp_mQ_k/RW_G_SCALE;
      RW.mB.dFdu = calc_thrust_curve_d(ROTWING_EFF_SCHED_MB_k1, ROTWING_EFF_SCHED_MB_k2, 4800.0);;
      RW.mL.dFdu = temp_mQ_k/RW_G_SCALE;
      break;
  }
  // T = k1*u^2 + k2*u + k3-----|k1                      | k2                     | k3                     | u
  //float T_mF = calc_thrust_curve(ROTWING_EFF_SCHED_MF_k1, ROTWING_EFF_SCHED_MF_k2, ROTWING_EFF_SCHED_MF_k3, actuator_state_1l[COMMAND_MOTOR_FRONT]);
  //float T_mR = calc_thrust_curve(ROTWING_EFF_SCHED_MR_k1, ROTWING_EFF_SCHED_MR_k2, ROTWING_EFF_SCHED_MR_k3, actuator_state_1l[COMMAND_MOTOR_RIGHT]);
  //float T_mB = calc_thrust_curve(ROTWING_EFF_SCHED_MB_k1, ROTWING_EFF_SCHED_MB_k2, ROTWING_EFF_SCHED_MB_k3, actuator_state_1l[COMMAND_MOTOR_BACK]);
  //float T_mL = calc_thrust_curve(ROTWING_EFF_SCHED_ML_k1, ROTWING_EFF_SCHED_ML_k2, ROTWING_EFF_SCHED_ML_k3, actuator_state_1l[COMMAND_MOTOR_LEFT]);
  RW.T = RW.m*9.81/(RW.att.cphi * RW.att.ctheta);//T_mF + T_mR + T_mB + T_mL;
  Bound(RW.T, 30.0, 180.0);
}
 
void init_all_thrust_curve(void){
  // dTdu    = 2*k1*u + k2--------|k1                      | k2                      | u
  RW.mF.dFdu = calc_thrust_curve_d(ROTWING_EFF_SCHED_MF_k1, ROTWING_EFF_SCHED_MF_k2, 4800.0);
  RW.mR.dFdu = calc_thrust_curve_d(ROTWING_EFF_SCHED_MR_k1, ROTWING_EFF_SCHED_MR_k2, 4800.0);
  RW.mB.dFdu = calc_thrust_curve_d(ROTWING_EFF_SCHED_MB_k1, ROTWING_EFF_SCHED_MB_k2, 4800.0);
  RW.mL.dFdu = calc_thrust_curve_d(ROTWING_EFF_SCHED_ML_k1, ROTWING_EFF_SCHED_ML_k2, 4800.0);
  // T = k1*u^2 + k2*u + k3-------|k1                     | k2                    | k3                     | u
  float T_mF = calc_thrust_curve(ROTWING_EFF_SCHED_MF_k1, ROTWING_EFF_SCHED_MF_k2, ROTWING_EFF_SCHED_MF_k3, 4800.0);
  float T_mR = calc_thrust_curve(ROTWING_EFF_SCHED_MR_k1, ROTWING_EFF_SCHED_MR_k2, ROTWING_EFF_SCHED_MR_k3, 4800.0);
  float T_mB = calc_thrust_curve(ROTWING_EFF_SCHED_MB_k1, ROTWING_EFF_SCHED_MB_k2, ROTWING_EFF_SCHED_MB_k3, 4800.0);
  float T_mL = calc_thrust_curve(ROTWING_EFF_SCHED_ML_k1, ROTWING_EFF_SCHED_ML_k2, ROTWING_EFF_SCHED_ML_k3, 4800.0);
  RW.T = T_mF + T_mR + T_mB + T_mL;
  Bound(RW.T, 0.0, 180.0);
}