fly316/PX4-Autopilot
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This commit is contained in:
Marvin Harms
2022-04-08 14:25:17 +02:00
parent 5d0763b2f2
commit 571e2077f3
3 changed files with 137 additions and 27 deletions
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src/modules/fw_dyn_soar_control/FixedwingPositionINDIControl.cpp
+110 -23
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@@ -42,10 +42,9 @@ using math::radians;
using matrix::Dcmf;
using matrix::Matrix;
using matrix::Eulerf;
using matrix::Euler;
using matrix::Quatf;
using matrix::Vector2f;
using matrix::Vector2d;
using matrix::AxisAnglef;
using matrix::Vector3f;
using matrix::Vector;
using matrix::wrap_pi;
@@ -149,20 +148,20 @@ FixedwingPositionINDIControl::_get_acceleration_ref(float t, float T)
return Vector3f{x, y, z}/powf(T,2);
}
Quatf
Dcmf
FixedwingPositionINDIControl::_get_attitude_ref(float t, float T)
{
Vector3f vel = _get_velocity_ref(t,T);
Vector3f vel_air = vel - _wind_estimate;
Vector3f acc = _get_acceleration_ref(t,T);
// add gravity
acc(2) += 9.81;
acc(2) += 9.81f;
// compute required force
Vector3f f = FW_MASS*acc;
Vector3f f = _param_fw_mass.get()*acc;
// compute force component projected onto lift axis
Vector3f vel_normalized = normalized(vel_air);
Vector3f vel_normalized = vel_air.normalized();
Vector3f f_lift = f - f*vel_normalized;
Vector3f f_lift_normalized = normalized(f_lift);
Vector3f lift_normalized = f_lift.normalized();
Vector3f wing_normalized = -vel_normalized.cross(lift_normalized);
// compute rotation matrix
Dcmf R_bi;
@@ -177,14 +176,11 @@ FixedwingPositionINDIControl::_get_attitude_ref(float t, float T)
R_bi(2,2) = lift_normalized(2);
// compute required AoA
Vector3f f_phi = R_bi*f_lift;
float AoA = (2*f_phi(2))/(1.223*0.4*powf(unit(vel_air),2)) - 0.356)/2.354;
float AoA = ((2.f*f_phi(2))/(1.223f*0.4f*(vel_air*vel_air)) - 0.356f)/2.354f;
// compute final rotation matrix
Euler e;
Euler(0, AoA, 0);
Dcmf R_pitch;
R_pitch(e);
Dcmf Rotation;
Rotation(R_pitch*R_bi);
Eulerf e(0.f, AoA, 0.f);
Dcmf R_pitch(e);
Dcmf Rotation(R_pitch*R_bi);
// switch from FRD to ENU frame
Rotation(1,0) *= -1;
Rotation(1,1) *= -1;
@@ -192,16 +188,107 @@ FixedwingPositionINDIControl::_get_attitude_ref(float t, float T)
Rotation(2,0) *= -1;
Rotation(2,1) *= -1;
Rotation(2,2) *= -1;
return 1;
return Rotation.transpose();
// compute quaternion
//Quatf q;
//q(transpose(Rotation));
//return q;
}
Vector3f
FixedwingPositionINDIControl::_get_angular_velocity_ref(float t, float T)
{
float dt = 0.001;
float t_lower = fmaxf(0.f,t-dt);
float t_upper = fminf(t+dt,1.f);
Dcmf R_i0 = _get_attitude_ref(t_lower, T);
Dcmf R_i1 = _get_attitude_ref(t_upper, T);
Dcmf R_10 = R_i1.transpose()*R_i0;
AxisAnglef w_01(R_10);
return -w_01.axis()*w_01.angle()/(T*(t_upper-t_lower));
}
Vector3f
FixedwingPositionINDIControl::_get_angular_acceleration_ref(float t, float T)
{
float dt = 0.001;
float t_lower = fmaxf(0.f,t-dt);
float t_upper = fminf(t+dt,1.f);
// compute roational velocity in inertial frame
Dcmf R_i0 = _get_attitude_ref(t_lower, T);
AxisAnglef w_0(R_i0*_get_angular_velocity_ref(t_lower, T));
// compute roational velocity in inertial frame
Dcmf R_i1 = _get_attitude_ref(t_upper, T);
AxisAnglef w_1(R_i1*_get_angular_velocity_ref(t_upper, T));
// compute gradient via finite differences
Vector3f dw_dt = (w_1.axis()*w_1.angle() - w_0.axis()*w_0.angle()) / (T*(t_upper-t_lower));
// transform back to body frame
return R_i0.transpose()*dw_dt;
}
float
FixedwingPositionINDIControl::_get_closest_t(Vector3f pos)
{
const uint n = 100;
Vector<float, n> distances;
// compute all distances
for(uint i=0; i<n; i++){
float t_ref = float(i)/n;
Vector3f pos_ref = _get_position_ref(t_ref);
distances(i) = (pos_ref - pos)*(pos_ref - pos);
}
// get index of smallest distance
float t = 0;
float min_dist = distances(0);
for(uint i=1; i<n; i++){
if(distances(i)<min_dist){
min_dist = distances(i);
t = float(i)/n;
}
}
return t;
}
Dcmf
FixedwingPositionINDIControl::_get_attitude(Vector3f vel, Vector3f f)
{
Vector3f vel_air = vel - _wind_estimate;
// compute force component projected onto lift axis
Vector3f vel_normalized = vel_air.normalized();
Vector3f f_lift = f - (f*vel_normalized)*vel_normalized;
Vector3f lift_normalized = f_lift.normalized();
Vector3f wing_normalized = -vel_normalized.cross(lift_normalized);
// compute rotation matrix
Dcmf R_bi;
R_bi(0,0) = vel_normalized(0);
R_bi(0,1) = vel_normalized(1);
R_bi(0,2) = vel_normalized(2);
R_bi(1,0) = wing_normalized(0);
R_bi(1,1) = wing_normalized(1);
R_bi(1,2) = wing_normalized(2);
R_bi(2,0) = lift_normalized(0);
R_bi(2,1) = lift_normalized(1);
R_bi(2,2) = lift_normalized(2);
// compute required AoA
Vector3f f_phi = R_bi*f_lift;
float AoA = ((2.f*f_phi(2))/(1.223f*0.4f*(vel_air*vel_air)) - 0.356f)/2.354f;
// compute final rotation matrix
Eulerf e(0.f, AoA, 0.f);
Dcmf R_pitch(e);
Dcmf Rotation(R_pitch*R_bi);
// switch from FRD to ENU frame
Rotation(1,0) *= -1;
Rotation(1,1) *= -1;
Rotation(1,2) *= -1;
Rotation(2,0) *= -1;
Rotation(2,1) *= -1;
Rotation(2,2) *= -1;
return Rotation.transpose();
}
int FixedwingPositionINDIControl::custom_command(int argc, char *argv[])
{
src/modules/fw_dyn_soar_control/FixedwingPositionINDIControl.hpp
+25 -2
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@@ -116,6 +116,28 @@ private:
vehicle_local_position_s _local_pos {}; ///< vehicle local position
vehicle_status_s _vehicle_status {}; ///< vehicle status
// parameter struct
DEFINE_PARAMETERS(
// aircraft params
(ParamFloat<px4::params::FW_MASS>) _param_fw_mass,
(ParamFloat<px4::params::FW_WING_AREA>) _param_fw_wing_area,
(ParamFloat<px4::params::RHO>) _param_rho
// aerodynamic params
/*
(ParamFloat<px4::params::C_l0>) _param_fw_c_l0,
(ParamFloat<px4::params::C_l1>) _param_fw_c_l1,
(ParamFloat<px4::params::C_d0>) _param_fw_c_d0,
(ParamFloat<px4::params::C_d1>) _param_fw_c_d1,
(ParamFloat<px4::params::C_d2>) _param_fw_c_d2,
// filter params
(ParamFloat<px4::params::FILTER_A1>) _param_filter_a1,
(ParamFloat<px4::params::FILTER_A2>) _param_filter_a2,
(ParamFloat<px4::params::FILTER_B1>) _param_filter_b1,
(ParamFloat<px4::params::FILTER_B2>) _param_filter_b2,
(ParamFloat<px4::params::FILTER_B3>) _param_filter_b3
*/
)
perf_counter_t _loop_perf; ///< loop performance counter
@@ -152,11 +174,11 @@ private:
Vector3f _get_position_ref(float t=0); // get the reference position on the current path, at normalized time t in [0,1]
Vector3f _get_velocity_ref(float t=0, float T=1); // get the reference velocity on the current path, at normalized time t in [0,1], with an intended cycle time of T
Vector3f _get_acceleration_ref(float t=0, float T=1); // get the reference acceleration on the current path, at normalized time t in [0,1], with an intended cycle time of T
Quatf _get_attitude_ref(float t=0, float T=1); // get the reference attitude on the current path, at normalized time t in [0,1], with an intended cycle time of T
Dcmf _get_attitude_ref(float t=0, float T=1); // get the reference attitude on the current path, at normalized time t in [0,1], with an intended cycle time of T
Vector3f _get_angular_velocity_ref(float t=0, float T=1); // get the reference angular velocity on the current path, at normalized time t in [0,1], with an intended cycle time of T
Vector3f _get_angular_acceleration_ref(float t=0, float T=1); // get the reference angular acceleration on the current path, at normalized time t in [0,1], with an intended cycle time of T
float _get_closest_t(Vector3f pos); // get the normalized time, at which the reference path is closest to the current position
Quatf _get_attitude(Vector3f vel, Vector3f f); // get the attitude to produce force f while flying with velocity vel
Dcmf _get_attitude(Vector3f vel, Vector3f f); // get the attitude to produce force f while flying with velocity vel
void _compute_NDI_control_input(Vector3f pos, Vector3f vel, Vector3f acc, Quatf att, Vector3f omega, Vector3f alpha);
void _compute_INDI_control_input(Vector3f pos, Vector3f vel, Vector3f acc, Quatf att, Vector3f omega, Vector3f alpha);
@@ -183,6 +205,7 @@ private:
std::array<Vector3f, 3> _a_list;
std::array<Vector3f, 3> _f_lpf_list;
std::array<Vector3f, 3> _a_lpf_list;
};
src/modules/fw_dyn_soar_control/fw_dyn_soar_control_params.c
+2 -2
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@@ -43,8 +43,8 @@ PARAM_DEFINE_FLOAT(FW_WING_AREA, 0.4f);
* @unit
* @min 0.5
* @max 1.225
* @decimal 2
* @increment 0.01
* @decimal 3
* @increment 0.001
* @group FW DYN SOAR Control
*/
PARAM_DEFINE_FLOAT(RHO, 1.223f);