/// -*- tab-width: 4; Mode: C++; c-basic-offset: 4; indent-tabs-mode: nil -*-
/*
   This program 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 3 of the License, or
   (at your option) any later version.

   This program 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 this program.  If not, see <http://www.gnu.org/licenses/>.
 */
/*
  very simple plane simulator class. Not aerodynamically accurate,
  just enough to be able to debug control logic for new frame types
*/

#include "SIM_Plane.h"

#include <stdio.h>

using namespace SITL;

Plane::Plane(const char *home_str, const char *frame_str) :
    Aircraft(home_str, frame_str)
{
    mass = 1.0f;

    /*
       scaling from motor power to Newtons. Allows the plane to hold
       vertically against gravity when the motor is at hover_throttle
    */
    thrust_scale = (mass * GRAVITY_MSS) / hover_throttle;
    frame_height = 0.1f;
}

/*
  the following functions are from last_letter
  https://github.com/Georacer/last_letter/blob/master/last_letter/src/aerodynamicsLib.cpp
  many thanks to Georacer!
 */
float Plane::liftCoeff(float alpha) const
{
    const float alpha0 = coefficient.alpha_stall;
    const float M = coefficient.mcoeff;
    const float c_lift_0 = coefficient.c_lift_0;
    const float c_lift_a0 = coefficient.c_lift_a;
    
	double sigmoid = ( 1+exp(-M*(alpha-alpha0))+exp(M*(alpha+alpha0)) ) / (1+exp(-M*(alpha-alpha0))) / (1+exp(M*(alpha+alpha0)));
	double linear = (1.0-sigmoid) * (c_lift_0 + c_lift_a0*alpha); //Lift at small AoA
	double flatPlate = sigmoid*(2*copysign(1,alpha)*pow(sin(alpha),2)*cos(alpha)); //Lift beyond stall

	float result  = linear+flatPlate;
	return result;
}

float Plane::dragCoeff(float alpha) const
{
    const float b = coefficient.b;
    const float s = coefficient.s;
    const float c_drag_p = coefficient.c_drag_p;
    const float c_lift_0 = coefficient.c_lift_0;
    const float c_lift_a0 = coefficient.c_lift_a;
    const float oswald = coefficient.oswald;
    
	double AR = pow(b,2)/s;
	double c_drag_a = c_drag_p + pow(c_lift_0+c_lift_a0*alpha,2)/(M_PI*oswald*AR);

	return c_drag_a;
}

// Torque calculation function
Vector3f Plane::getTorque(float inputAileron, float inputElevator, float inputRudder, const Vector3f &force) const
{
    const float alpha = angle_of_attack;
    const float s = coefficient.s;
    const float c = coefficient.c;
    const float b = coefficient.b;
    const float c_l_0 = coefficient.c_l_0;
    const float c_l_b = coefficient.c_l_b;
    const float c_l_p = coefficient.c_l_p;
    const float c_l_r = coefficient.c_l_r;
    const float c_l_deltaa = coefficient.c_l_deltaa;
    const float c_l_deltar = coefficient.c_l_deltar;
    const float c_m_0 = coefficient.c_m_0;
    const float c_m_a = coefficient.c_m_a;
    const float c_m_q = coefficient.c_m_q;
    const float c_m_deltae = coefficient.c_m_deltae;
    const float c_n_0 = coefficient.c_n_0;
    const float c_n_b = coefficient.c_n_b;
    const float c_n_p = coefficient.c_n_p;
    const float c_n_r = coefficient.c_n_r;
    const float c_n_deltaa = coefficient.c_n_deltaa;
    const float c_n_deltar = coefficient.c_n_deltar;
    const Vector3f &CGOffset = coefficient.CGOffset;
    
    float rho = air_density;

	//read angular rates
	double p = gyro.x;
	double q = gyro.y;
	double r = gyro.z;

	//calculate aerodynamic torque
	double qbar = 1.0/2.0*rho*pow(airspeed,2)*s; //Calculate dynamic pressure
	double la, na, ma;
	if (is_zero(airspeed))
	{
		la = 0;
		ma = 0;
		na = 0;
	}
	else
	{
		la = qbar*b*(c_l_0 + c_l_b*beta + c_l_p*b*p/(2*airspeed) + c_l_r*b*r/(2*airspeed) + c_l_deltaa*inputAileron + c_l_deltar*inputRudder);
		ma = qbar*c*(c_m_0 + c_m_a*alpha + c_m_q*c*q/(2*airspeed) + c_m_deltae*inputElevator);
		na = qbar*b*(c_n_0 + c_n_b*beta + c_n_p*b*p/(2*airspeed) + c_n_r*b*r/(2*airspeed) + c_n_deltaa*inputAileron + c_n_deltar*inputRudder);
	}


	// Add torque to to force misalignment with CG
	// r x F, where r is the distance from CoG to CoL
	la +=  CGOffset.y * force.z - CGOffset.z * force.y;
	ma += -CGOffset.x * force.z + CGOffset.z * force.x;
	na += -CGOffset.y * force.x + CGOffset.x * force.y;

	return Vector3f(la, ma, na);
}

// Force calculation function from last_letter
Vector3f Plane::getForce(float inputAileron, float inputElevator, float inputRudder) const
{
    const float alpha = angle_of_attack;
    const float c_drag_q = coefficient.c_drag_q;
    const float c_lift_q = coefficient.c_lift_q;
    const float s = coefficient.s;
    const float c = coefficient.c;
    const float b = coefficient.b;
    const float c_drag_deltae = coefficient.c_drag_deltae;
    const float c_lift_deltae = coefficient.c_lift_deltae;
    const float c_y_0 = coefficient.c_y_0;
    const float c_y_b = coefficient.c_y_b;
    const float c_y_p = coefficient.c_y_p;
    const float c_y_r = coefficient.c_y_r;
    const float c_y_deltaa = coefficient.c_y_deltaa;
    const float c_y_deltar = coefficient.c_y_deltar;
    
    float rho = air_density;

	//request lift and drag alpha-coefficients from the corresponding functions
	double c_lift_a = liftCoeff(alpha);
	double c_drag_a = dragCoeff(alpha);

	//convert coefficients to the body frame
	double c_x_a = -c_drag_a*cos(alpha)+c_lift_a*sin(alpha);
	double c_x_q = -c_drag_q*cos(alpha)+c_lift_q*sin(alpha);
	double c_z_a = -c_drag_a*sin(alpha)-c_lift_a*cos(alpha);
	double c_z_q = -c_drag_q*sin(alpha)-c_lift_q*cos(alpha);

	//read angular rates
	double p = gyro.x;
	double q = gyro.y;
	double r = gyro.z;

	//calculate aerodynamic force
	double qbar = 1.0/2.0*rho*pow(airspeed,2)*s; //Calculate dynamic pressure
	double ax, ay, az;
	if (is_zero(airspeed))
	{
		ax = 0;
		ay = 0;
		az = 0;
	}
	else
	{
		ax = qbar*(c_x_a + c_x_q*c*q/(2*airspeed) - c_drag_deltae*cos(alpha)*fabs(inputElevator) + c_lift_deltae*sin(alpha)*inputElevator);
		// split c_x_deltae to include "abs" term
		ay = qbar*(c_y_0 + c_y_b*beta + c_y_p*b*p/(2*airspeed) + c_y_r*b*r/(2*airspeed) + c_y_deltaa*inputAileron + c_y_deltar*inputRudder);
		az = qbar*(c_z_a + c_z_q*c*q/(2*airspeed) - c_drag_deltae*sin(alpha)*fabs(inputElevator) - c_lift_deltae*cos(alpha)*inputElevator);
		// split c_z_deltae to include "abs" term
	}
    return Vector3f(ax, ay, az);
}

void Plane::calculate_forces(const struct sitl_input &input, Vector3f &rot_accel, Vector3f &body_accel)
{
    float aileron  = (input.servos[0]-1500)/500.0f;
    float elevator = (input.servos[1]-1500)/500.0f;
    float rudder   = (input.servos[3]-1500)/500.0f;
    float throttle = constrain_float((input.servos[2]-1000)/1000.0f, 0, 1);
    
    float thrust     = throttle;

    // calculate angle of attack
    angle_of_attack = atan2f(velocity_bf.z, velocity_bf.x);
    beta = atan2f(velocity_bf.y,velocity_bf.x);
    
    Vector3f force = getForce(aileron, elevator, rudder);
    rot_accel = getTorque(aileron, elevator, rudder, force);

    // velocity in body frame
    velocity_bf = dcm.transposed() * velocity_ef;
    
    // scale thrust to newtons
    thrust *= thrust_scale;

    accel_body = Vector3f(thrust/mass, 0, 0);
    accel_body += force;

    // add some noise
    add_noise(thrust / thrust_scale);
}
    
/*
  update the plane simulation by one time step
 */
void Plane::update(const struct sitl_input &input)
{
    Vector3f rot_accel;

    calculate_forces(input, rot_accel, accel_body);
    
    update_dynamics(rot_accel);
    
    // update lat/lon/altitude
    update_position();
}