STM32四旋翼飞控定高算法，含源代码

ID:627837 · 发表于 2019-10-21 20:53

之前做电子设计竞赛做的定高算法，硬件是基于STM32F103的飞控，算法主要是串级PID，使用的是超声波测距模块。由于整个飞控工程比较大，现将核心算法贴出来供大家参考。

单片机源程序如下:

#include "height_ctrl.h"
#include "include.h"
#include "mymath.h"
extern float Thr_Weight;
extern Gravity V;//重力分量
/******************高度控制变量********************/
float height_ctrl_out;
float wz_acc;
float keepheight_thr;
/*-------------------------------------------------*/
/******************超声波变量********************/
#define ULTRA_SPEED 300 // mm/s
#define ULTRA_INT 300 // 积分幅度
u8 lock=0;
extern s8 ultra_start_f;
extern float US100_Alt_delta;
float exp_height_speed,exp_height;
float ultra_speed,ultra_speed_acc;
float ultra_dis_lpf;
float ultra_ctrl_out;
_st_height_pid_v ultra_ctrl;
_st_height_pid ultra_pid;
/*-------------------------------------------------*/
/******************速度环变量********************/
float wz_speed;
float wz_acc_mms2;
float tempacc_lpf;
u8 lock_spd_crl=0;
_st_height_pid_v wz_speed_pid_v;
_st_height_pid wz_speed_pid;
_st_height_pid ultra_wz_speed_pid;
_st_height_pid baro_wz_speed_pid;
/*-------------------------------------------------*/
/******************气压计变量********************/
float baro_height,baro_height_old;
#define BARO_SPEED 300 // mm/s
#define BARO_INT 300 // 积分幅度
u8 lock_BARO=0;//定高锁定当前以及清零用
#define BARO_SPEED_NUM 10
float baro_speed_arr[BARO_SPEED_NUM + 1];
#define ACC_SPEED_NUM 50
float acc_speed_arr[ACC_SPEED_NUM + 1];
float baro_dis_lpf,baro_dis_kalman;
float baro_ctrl_out;
_st_height_pid_v baro_ctrl;
_st_height_pid baro_pid;
u16 baro_cnt[2];
u16 acc_cnt[2];
float baro_speed,baro_speed_lpf;
float baro_height;
float Pressure_groud;
/*-------------------------------------------------*/
void Height_Ctrl(float T,float thr)
{
static u8 height_ctrl_start_f;
static float thr_lpf;
static float height_thr;
static float wz_acc_temp,wz_acc1;
static float hc_speed_i,wz_speed_0;
static float h_speed;
switch( height_ctrl_start_f )
{
case 0:
if( sensor.acc.averag.z > 7000 )//注意这里，指水平静态下的Z值要比这个大，表示水平垂直
{
height_ctrl_start_f = 1;
}
break;
case 1:
LockForKeepHigh(thr_lpf);//一旦切到控高模式，立即保存当前的距离值，油门值、相关清零。
if((flag.FlightMode==ULTRASONIC_High && lock==1 &&lock_spd_crl==0)|| (flag.FlightMode==ATMOSPHERE_High && lock_BARO==1 &&lock_spd_crl==0))
{
keepheight_thr=thr_lpf;
wz_speed_0=0;
hc_speed_i=0;
hc_speed_i=0;
wz_speed=0;
wz_speed_pid_v.err_old=0;
wz_speed_pid_v.err=0;
wz_speed_pid_v.err_i=0;
lock=2;
lock_BARO=2;
lock_spd_crl=1;
}
else if(flag.FlightMode==MANUAL_High)
{
lock=0;
lock_BARO=0;
lock_spd_crl=0;//切回手动模式后置零，以使下次进入定高模式是能顺利置零速度内环
}
height_thr = LIMIT( thr , 0, 700 );
thr_lpf += ( 1 / ( 1 + 1 / ( 2.0f *3.14f *T ) ) ) *( height_thr - thr_lpf );//对油门值低通滤波修正
userdata1[0]= thr_lpf;//调试用
/*下面的低通滤波用于测试对比效果，最终没有选用*/
//wz_acc += ( 1 / ( 1 + 1 / ( 8 *3.14f *T ) ) ) *my_deathzoom( (V.z *(sensor.acc.averag.z- sensor.acc.quiet.z) + V.x *sensor.acc.averag.x + V.y *sensor.acc.averag.y - wz_acc),100 );//
//wz_acc_mms2 = (float)(wz_acc/8192.0f) *9800 ;
//加速度的静态零点是读取的EEPROM数据，但是每次飞行都可能不一样，能每次起飞前校准一次最好，可以单独校准Z轴的，自行设计程序
wz_acc_temp = V.z *(sensor.acc.averag.z- sensor.acc.quiet.z) + V.x *sensor.acc.averag.x + V.y *sensor.acc.averag.y;//
Moving_Average( wz_acc_temp,acc_speed_arr,ACC_SPEED_NUM,acc_cnt ,&wz_acc1 );
tempacc_lpf= (float)(wz_acc1/8192.0f) *9800;//9800 *T;由于是+-4G共8G，65535/8g=8192 g，加速度，mms2毫米每平方秒
if(abs(tempacc_lpf)<50)tempacc_lpf=0;//简单消除下噪声
userdata1[2]=tempacc_lpf;
wz_speed_0 += tempacc_lpf *T;//加速度计积分成速度
if( ultra_start_f == 1 )////不管是啥模式，只要更新了超声波数据就进行运算
{
Ultra_dataporcess(15.0f*TT);
ultra_start_f=2;
}
if(baro_start_f==1)//不管是啥模式，只要更新了气压数据就进行运算
{
Baro_dataporcess(8.0f*TT); //8.0f*TT这么长时间更新一次气压计数据
userdata2[10]=baro_height;//Baro_Height_Source
baro_dis_delta=baro_height-baro_dis_old;
baro_dis_old=baro_height;//气压计速度可以继续优化，这里比较粗糙
//Moving_Average( (float)( baro_dis_delta/(8.0f*TT)),baro_speed_arr,BARO_SPEED_NUM,baro_cnt ,&baro_speed ); //单位mm/s
userdata1[11]=baro_speed_lpf=0.4* baro_dis_delta/(8.0f*TT);//baro_speed这里乘以系数以削减该值
baro_start_f=2;
}
if(flag.FlightMode==ULTRASONIC_High)
{
h_speed=ultra_speed;
wz_speed_0 = 0.99 *wz_speed_0 + 0.01*h_speed;//超声波垂直速度互补滤波
}
else if(flag.FlightMode==ATMOSPHERE_High)
{
h_speed=baro_speed_lpf;
wz_speed_0 = 0.99 *wz_speed_0 + 0.01*h_speed;//气压计垂直速度互补滤波，系数可调
}
userdata1[3] =h_speed;//h_speed是高度环传到速度环的实测高度方向速度【但可能是错误的，气压计速度不可靠】
userdata1[4]=wz_speed_0;//调试用
hc_speed_i += 0.4f *T *( h_speed - wz_speed );//速度偏差积分，乘以了0.4系数
hc_speed_i = LIMIT( hc_speed_i, -500, 500 );//积分限幅
userdata1[5] =hc_speed_i;//这个没显示
wz_speed_0 += ( 1 / ( 1 + 1 / ( 0.1f *3.14f *T ) ) ) *( h_speed - wz_speed_0 ) ;//0.1实测速度修正加速度算的速度
userdata1[6] = wz_speed=wz_speed_0 + hc_speed_i;//经过修正的速度+经过限幅的增量式速度积分
if( flag.FlightMode == ATMOSPHERE_High)
{
if(baro_start_f==2)//说明有新数据且被上面移动均值滤波使用过了
{
baro_start_f = -1;
Baro_Ctrl(8.0f*TT,thr_lpf);
}
height_speed_ctrl(T,keepheight_thr,baro_ctrl_out,baro_speed_lpf);
}
if( flag.FlightMode == ULTRASONIC_High)
{
height_speed_ctrl(T,keepheight_thr,ultra_ctrl_out,ultra_speed);//系数原来是0.4
if( ultra_start_f == 2 )//超声波数据更新了且被运算了
{
Ultra_Ctrl(15.0f*TT,thr_lpf);//realtime是周期为 TT 秒的，#define TT 0.0025//控制周期2.5ms
ultra_start_f = -1;
}
}
/*******************************************控制高度输出********************************************/
if(flag.FlightMode==ULTRASONIC_High || flag.FlightMode==ATMOSPHERE_High || flag.FlightMode==ACC_High)//注意这里，模式
{
height_ctrl_out = wz_speed_pid_v.pid_out;
}
else
{
height_ctrl_out = thr;
}
userdata2[0]=exp_height;
break;
default: break;
}
}
void WZ_Speed_PID_Init()
{
ultra_wz_speed_pid.kp = 0.25;// //超声波定高的速度环PID，会被EEPROM里的重新赋值的
ultra_wz_speed_pid.ki = 0.08; //0.12
ultra_wz_speed_pid.kd = 8;
baro_wz_speed_pid.kp = 0.1;// 气压定高的速度环PID，会被EEPROM里的重新赋值的
baro_wz_speed_pid.ki = 0.06;
baro_wz_speed_pid.kd = 8;//1.4*10，在计算式乘以了10，已删除
wz_speed_pid.kp = 0.1;//速度环默认PID，真正用不到被重新赋值
wz_speed_pid.ki = 0.08;
wz_speed_pid.kd = 8;
}
void height_speed_ctrl(float T,float thr_keepheight,float exp_z_speed,float h_speed)
{
userdata1[1] = thr_keepheight;
//wz_speed被用于参与超声波高度D运算
userdata1[7]=wz_speed_pid_v.err = wz_speed_pid.kp *( exp_z_speed - wz_speed );//
userdata1[8]=wz_speed_pid_v.err_d = wz_speed_pid.kd * (-tempacc_lpf) *T;//(wz_speed_pid_v.err - wz_speed_pid_v.err_old);
//wz_speed_pid_v.err_i += wz_speed_pid.ki *wz_speed_pid_v.err *T;
wz_speed_pid_v.err_i += wz_speed_pid.ki *( exp_z_speed - h_speed ) *T;//期望速度与实际速度误差积分
wz_speed_pid_v.err_i = LIMIT(wz_speed_pid_v.err_i,-Thr_Weight *200,Thr_Weight *200);
userdata1[9]=wz_speed_pid_v.err_i;
wz_speed_pid_v.pid_out = thr_keepheight + Thr_Weight *LIMIT((wz_speed_pid.kp *exp_z_speed + wz_speed_pid_v.err + wz_speed_pid_v.err_d + wz_speed_pid_v.err_i),-300,300);//积分原来没有乘wz_speed_pid.kp
userdata1[10]=wz_speed_pid_v.pid_out-thr_keepheight;
wz_speed_pid_v.err_old = wz_speed_pid_v.err;
}
void Baro_PID_Init()
{
baro_pid.kp = 0.15;//气压定高的高度位置环PID，会被EEPROM里的重新赋值的
baro_pid.ki = 0;
baro_pid.kd = 1.5; //2.5
}
void Baro_dataporcess(float T)
{
float baro_dis_tmp;
baro_dis_tmp = Moving_Median(2,5,baro_height);//对超声波测量的距离进行移动中位值滤波
if( baro_dis_tmp < Baro_MAX_Height )
{
if( ABS(baro_dis_tmp - baro_dis_lpf) < 100 )
{
baro_dis_lpf += ( 1 / ( 1 + 1 / ( 2.0f *3.14f *T ) ) ) *(baro_dis_tmp - baro_dis_lpf) ;
}
else if( ABS(baro_dis_tmp - baro_dis_lpf) < 500 )
{
baro_dis_lpf += ( 1 / ( 1 + 1 / ( 1.0f *3.14f *T ) ) ) *(baro_dis_tmp- baro_dis_lpf) ;
}
else
{
baro_dis_lpf += ( 1 / ( 1 + 1 / ( 0.5f *3.14f *T ) ) ) *(baro_dis_tmp- baro_dis_lpf) ;
}
}
userdata2[2]=baro_dis_lpf;//调试用
userdata2[3]+= ( 1 / ( 1 + 1 / ( 1.0f *3.14f *T ) ) ) *(Baro_Height_Source- userdata2[3]) ;//调试用
userdata2[4]=baro_speed;//调试用
}
void Baro_Ctrl(float T,float thr)
{
exp_height_speed = BARO_SPEED *my_deathzoom_2(thr - 500,100)/400.0f; //20这里具体根据自己起飞油门定，油门控制高度+-ULTRA_SPEEDmm / s
exp_height_speed = LIMIT(exp_height_speed ,-BARO_SPEED,BARO_SPEED);
if( exp_height > Baro_MAX_Height )//限定高度，可以根据实际修改
{
if( exp_height_speed > 0 )
{
exp_height_speed = 0;
}
}
else if( exp_height < Baro_MIN_Height )
{
if( exp_height_speed < 0 )
{
exp_height_speed = 0;
}
}
exp_height += exp_height_speed *T;//累积期望高度，因为期望速度可能改变了
baro_ctrl.err = baro_pid.kp*(exp_height - baro_dis_lpf);//baro_dis_lpfmm 对高度误差乘以Kp
userdata2[5]=baro_ctrl.err;
baro_ctrl.err_i += baro_pid.ki *baro_ctrl.err *T;//对高度误差积分
userdata2[6]=baro_ctrl.err_i = LIMIT(baro_ctrl.err_i,-Thr_Weight *BARO_INT,Thr_Weight *BARO_INT);//积分限幅，融合了油门权重
//对于D，融合了加速度计运算得到的距离
userdata2[7]=0.4f *(baro_ctrl.err - baro_ctrl.err_old);
baro_ctrl.err_d = baro_pid.kd *( 0.6f *(-wz_speed*T) + 0.4f *(baro_ctrl.err - baro_ctrl.err_old) );
userdata2[8]=baro_ctrl.err_d;
baro_ctrl.pid_out = baro_ctrl.err + baro_ctrl.err_i + baro_ctrl.err_d;
baro_ctrl.pid_out = LIMIT(baro_ctrl.pid_out,-300,300);
userdata2[9]=baro_ctrl_out = baro_ctrl.pid_out;
baro_ctrl.err_old = baro_ctrl.err;
}
void Ultra_PID_Init()
{
ultra_pid.kp = 0.5;//超声波定高的高度位置环PID，会被EEPROM里的重新赋值的
ultra_pid.ki = 0;
ultra_pid.kd = 2.5; //2.5
}
void Ultra_dataporcess(float T)
{
float ultra_sp_tmp,ultra_dis_tmp;
ultra_dis_tmp = Moving_Median(1,5,US100_Alt);//对超声波测量的距离进行移动中位值滤波
userdata2[1]=ultra_dis_tmp;
if( ultra_dis_tmp < Ultrasonic_MAX_Height )
{
if( ABS(ultra_dis_tmp - ultra_dis_lpf) < 100 )
{
ultra_dis_lpf += ( 1 / ( 1 + 1 / ( 4.0f *3.14f *T ) ) ) *(ultra_dis_tmp - ultra_dis_lpf) ;
}
else if( ABS(ultra_dis_tmp - ultra_dis_lpf) < 200 )
{
ultra_dis_lpf += ( 1 / ( 1 + 1 / ( 2.2f *3.14f *T ) ) ) *(ultra_dis_tmp- ultra_dis_lpf) ;
}
else if( ABS(ultra_dis_tmp - ultra_dis_lpf) < 400 )
{
ultra_dis_lpf += ( 1 / ( 1 + 1 / ( 1.2f *3.14f *T ) ) ) *(ultra_dis_tmp- ultra_dis_lpf) ;
}
else
{
ultra_dis_lpf += ( 1 / ( 1 + 1 / ( 0.2f *3.14f *T ) ) ) *(ultra_dis_tmp- ultra_dis_lpf) ;
}
}
//注意超声波测量的距离的时效性问题，避免反复被计算
ultra_sp_tmp = Moving_Median(0,5,US100_Alt_delta/T); //对超声波测距出来两次之间距离差计算的速度中值滤波 ultra_delta/T;
if( ultra_dis_tmp < Ultrasonic_MAX_Height )//小于3米,注意这里，万一超出了呢？
{
if( ABS(ultra_sp_tmp) < 100 )//运动速度小于100mm/s
{
ultra_speed += ( 1 / ( 1 + 1 / ( 4 *3.14f *T ) ) ) * ( (float)(ultra_sp_tmp) - ultra_speed );
}//ultra_speed会传递给速度环，作为当前速度的反馈,原来是4
else
{
ultra_speed += ( 1 / ( 1 + 1 / ( 1.0f *3.14f *T ) ) ) * ( (float)(ultra_sp_tmp) - ultra_speed );
}//系数越大作用越小，原来是1
}
}
void Ultra_Ctrl(float T,float thr)
{
exp_height_speed = ULTRA_SPEED *my_deathzoom_2(thr - 500,100)/300.0f; //20这里具体根据自己起飞油门定，油门控制高度+-ULTRA_SPEEDmm / s
exp_height_speed = LIMIT(exp_height_speed ,-ULTRA_SPEED,ULTRA_SPEED);
if( exp_height > Ultrasonic_MAX_Height )//超出超声波高度稳定范围则不执行
{
if( exp_height_speed > 0 )
{
exp_height_speed = 0;
}
}
else if( exp_height < Ultrasonic_MIN_Height )
{
if( exp_height_speed < 0 )
{
exp_height_speed = 0;
}
}
exp_height += exp_height_speed *T;//累积期望高度，因为期望速度可能改变了
ultra_ctrl.err = ( ultra_pid.kp*(exp_height - ultra_dis_lpf) );//mm 对高度误差乘以Kp
userdata2[5]=ultra_ctrl.err;
ultra_ctrl.err_i += ultra_pid.ki *ultra_ctrl.err *T;//对高度误差积分
userdata2[6]=ultra_ctrl.err_i = LIMIT(ultra_ctrl.err_i,-Thr_Weight *ULTRA_INT,Thr_Weight *ULTRA_INT);//积分限幅，融合了油门权重
//对于D，融合了加速度计运算得到的距离
userdata2[7]=0.4f *(ultra_ctrl.err_old - ultra_ctrl.err);
……………………
…………限于本文篇幅余下代码请从51黑下载附件…………

复制代码

所有资料51hei提供下载:

height_ctrl.rar (4.54 KB, 下载次数: 97)

ID:604530 · 发表于 2019-11-2 11:53

楼主你好能不能简单分享一下定高是PID的参数测定方法吗

帐号		自动登录	找回密码
密码			立即注册

STM32四旋翼飞控定高算法，含源代码

评分