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FIX: parser velocity error

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This commit is contained in:
M.A. Gomez 2023-02-15 20:13:54 +01:00
parent 08c68d4af9
commit 3f348aabd9
1 changed files with 9 additions and 5 deletions
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10
src/algorithms/PVT/libs/vtl_engine.cc
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@ -166,7 +166,7 @@ bool Vtl_Engine::vtl_loop(Vtl_Data& new_data)
// rhoDot2_pri(i)=(rhoDot_pri(i)-rhoDot_pri_old(i))/kf_dt;
}
// Kalman estimation (measurement update)
test = kf_measurements(kf_yerr, new_data.sat_number, rho_pri, rhoDot_pri, rhoDot_pri, new_data.pr_m, new_data.doppler_hz, kf_x);
test = kf_measurements(kf_yerr, new_data.sat_number, rho_pri, rhoDot_pri, rhoDot_pri*0, new_data.pr_m, new_data.doppler_hz, kf_x);
kf_P_x = kf_F * kf_P_x * kf_F.t() + kf_Q; // state error covariance prediction
// Kalman filter update step
@ -208,7 +208,7 @@ bool Vtl_Engine::vtl_loop(Vtl_Data& new_data)
// sample code
trk_cmd.carrier_phase_rads = 0; // difficult of calculation
trk_cmd.carrier_freq_hz = doppler_hz_filt(channel); //+ kf_x(7)/Lambda_GPS_L1; // this is el doppler WITHOUTH sintony correction
trk_cmd.carrier_freq_rate_hz_s = 0;//-(a_x(channel)*kf_x(6)+a_y(channel)*kf_x(7)+a_z(channel)*kf_x(8))/ Lambda_GPS_L1;
trk_cmd.carrier_freq_rate_hz_s =-(a_x(channel)*kf_x(6)+a_y(channel)*kf_x(7)+a_z(channel)*kf_x(8))/ Lambda_GPS_L1;
trk_cmd.code_phase_chips = kf_yerr(channel)/SPEED_OF_LIGHT_M_S*1023e3;
trk_cmd.enable_carrier_nco_cmd = true;
trk_cmd.enable_code_nco_cmd = true;
@ -367,7 +367,9 @@ bool Vtl_Engine::model3DoF(double &acc_x,double &acc_y,double &acc_z,arma::mat k
double densidad=1.0;
double ballistic_coef = 0.007;
//vector velocidad
u_vec = kf_x.rows(4, 6);
kf_x.print("kf_x: ");
u_vec = kf_x.rows(3, 5);
// u_vec.print("u_vec");
// double u=sqrt(pow(kf_x(4),2)+pow(kf_x(5),2)+pow(kf_x(6),2));
//modulo de la velocidad
@ -391,10 +393,12 @@ bool Vtl_Engine::model3DoF(double &acc_x,double &acc_y,double &acc_z,arma::mat k
// % ballistic_coef is Cd0/mass_rocket;
// ballistic_coef=CD0/mass_rocket;
Empuje = EmpujeLkTable(t_disparo);
cout<<"Empuje: "<<Empuje<<endl;
acc_vec = -(GNSS_PI*densidad*diam_cohete*diam_cohete/8)*ballistic_coef*u*u_dir
+gravity_ECEF+Empuje*u_dir;
acc_vec.print("acc_vec");
// % return
acc_x = acc_vec(0);
acc_y = acc_vec(1);