mirror of https://github.com/ArduPilot/ardupilot
784 lines
24 KiB
C++
784 lines
24 KiB
C++
/*
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This program is free software: you can redistribute it and/or modify
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it under the terms of the GNU General Public License as published by
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the Free Software Foundation, either version 3 of the License, or
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(at your option) any later version.
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This program is distributed in the hope that it will be useful,
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but WITHOUT ANY WARRANTY; without even the implied warranty of
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MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the
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GNU General Public License for more details.
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You should have received a copy of the GNU General Public License
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along with this program. If not, see <http://www.gnu.org/licenses/>.
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*/
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/*
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parent class for aircraft simulators
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*/
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#include "SIM_Aircraft.h"
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#include <stdio.h>
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#include <sys/time.h>
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#include <unistd.h>
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#if defined(__CYGWIN__) || defined(__CYGWIN64__)
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#include <windows.h>
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#include <time.h>
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#include <mmsystem.h>
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#endif
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#include <AP_Logger/AP_Logger.h>
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#include <AP_Param/AP_Param.h>
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using namespace SITL;
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/*
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parent class for all simulator types
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*/
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Aircraft::Aircraft(const char *home_str, const char *frame_str) :
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ground_level(0.0f),
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frame_height(0.0f),
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dcm(),
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gyro(),
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gyro_prev(),
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ang_accel(),
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velocity_ef(),
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mass(0.0f),
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accel_body(0.0f, 0.0f, -GRAVITY_MSS),
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time_now_us(0),
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gyro_noise(radians(0.1f)),
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accel_noise(0.3f),
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rate_hz(1200.0f),
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autotest_dir(nullptr),
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frame(frame_str),
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#if defined(__CYGWIN__) || defined(__CYGWIN64__)
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min_sleep_time(20000)
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#else
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min_sleep_time(5000)
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#endif
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{
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// make the SIM_* variables available to simulator backends
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sitl = AP::sitl();
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if (!parse_home(home_str, home, home_yaw)) {
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::printf("Failed to parse home string (%s). Should be LAT,LON,ALT,HDG e.g. 37.4003371,-122.0800351,0,353\n", home_str);
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}
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::printf("Home: %f %f alt=%fm hdg=%f\n",
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home.lat*1e-7,
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home.lng*1e-7,
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home.alt*0.01,
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home_yaw);
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location = home;
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ground_level = home.alt * 0.01f;
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dcm.from_euler(0.0f, 0.0f, radians(home_yaw));
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set_speedup(1.0f);
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last_wall_time_us = get_wall_time_us();
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frame_counter = 0;
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// allow for orientation settings, such as with tailsitters
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enum ap_var_type ptype;
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ahrs_orientation = (AP_Int8 *)AP_Param::find("AHRS_ORIENTATION", &ptype);
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terrain = reinterpret_cast<AP_Terrain *>(AP_Param::find_object("TERRAIN_"));
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}
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/*
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parse a home string into a location and yaw
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*/
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bool Aircraft::parse_home(const char *home_str, Location &loc, float &yaw_degrees)
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{
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char *saveptr = nullptr;
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char *s = strdup(home_str);
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if (!s) {
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free(s);
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::printf("No home string supplied\n");
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return false;
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}
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char *lat_s = strtok_r(s, ",", &saveptr);
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if (!lat_s) {
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free(s);
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::printf("Failed to parse latitude\n");
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return false;
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}
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char *lon_s = strtok_r(nullptr, ",", &saveptr);
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if (!lon_s) {
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free(s);
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::printf("Failed to parse longitude\n");
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return false;
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}
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char *alt_s = strtok_r(nullptr, ",", &saveptr);
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if (!alt_s) {
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free(s);
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::printf("Failed to parse altitude\n");
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return false;
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}
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char *yaw_s = strtok_r(nullptr, ",", &saveptr);
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if (!yaw_s) {
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free(s);
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::printf("Failed to parse yaw\n");
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return false;
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}
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loc = {};
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loc.lat = static_cast<int32_t>(strtod(lat_s, nullptr) * 1.0e7);
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loc.lng = static_cast<int32_t>(strtod(lon_s, nullptr) * 1.0e7);
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loc.alt = static_cast<int32_t>(strtod(alt_s, nullptr) * 1.0e2);
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if (loc.lat == 0 && loc.lng == 0) {
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// default to CMAC instead of middle of the ocean. This makes
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// SITL in MissionPlanner a bit more useful
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loc.lat = -35.363261*1e7;
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loc.lng = 149.165230*1e7;
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loc.alt = 584*100;
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}
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yaw_degrees = strtof(yaw_s, nullptr);
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free(s);
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return true;
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}
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/*
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return difference in altitude between home position and current loc
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*/
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float Aircraft::ground_height_difference() const
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{
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float h1, h2;
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if (sitl &&
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sitl->terrain_enable && terrain &&
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terrain->height_amsl(home, h1, false) &&
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terrain->height_amsl(location, h2, false)) {
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return h2 - h1;
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}
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return 0.0f;
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}
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void Aircraft::set_precland(SIM_Precland *_precland) {
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precland = _precland;
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precland->set_default_location(home.lat * 1.0e-7f, home.lng * 1.0e-7f, static_cast<int16_t>(get_home_yaw()));
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}
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/*
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return current height above ground level (metres)
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*/
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float Aircraft::hagl() const
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{
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return (-position.z) + home.alt * 0.01f - ground_level - frame_height - ground_height_difference();
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}
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/*
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return true if we are on the ground
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*/
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bool Aircraft::on_ground() const
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{
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return hagl() <= 0.001f; // prevent bouncing around ground
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}
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/*
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update location from position
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*/
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void Aircraft::update_position(void)
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{
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location = home;
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location.offset(position.x, position.y);
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location.alt = static_cast<int32_t>(home.alt - position.z * 100.0f);
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#if 0
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// logging of raw sitl data
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Vector3f accel_ef = dcm * accel_body;
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AP::logger().Write("SITL", "TimeUS,VN,VE,VD,AN,AE,AD,PN,PE,PD", "Qfffffffff",
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AP_HAL::micros64(),
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velocity_ef.x, velocity_ef.y, velocity_ef.z,
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accel_ef.x, accel_ef.y, accel_ef.z,
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position.x, position.y, position.z);
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#endif
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}
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/*
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update body magnetic field from position and rotation
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*/
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void Aircraft::update_mag_field_bf()
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{
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// get the magnetic field intensity and orientation
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float intensity;
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float declination;
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float inclination;
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AP_Declination::get_mag_field_ef(location.lat * 1e-7f, location.lng * 1e-7f, intensity, declination, inclination);
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// create a field vector and rotate to the required orientation
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Vector3f mag_ef(1e3f * intensity, 0.0f, 0.0f);
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Matrix3f R;
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R.from_euler(0.0f, -ToRad(inclination), ToRad(declination));
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mag_ef = R * mag_ef;
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// calculate frame height above ground
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const float frame_height_agl = fmaxf((-position.z) + home.alt * 0.01f - ground_level, 0.0f);
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if (!sitl) {
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// running example program
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return;
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}
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// calculate scaling factor that varies from 1 at ground level to 1/8 at sitl->mag_anomaly_hgt
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// Assume magnetic anomaly strength scales with 1/R**3
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float anomaly_scaler = (sitl->mag_anomaly_hgt / (frame_height_agl + sitl->mag_anomaly_hgt));
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anomaly_scaler = anomaly_scaler * anomaly_scaler * anomaly_scaler;
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// add scaled anomaly to earth field
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mag_ef += sitl->mag_anomaly_ned.get() * anomaly_scaler;
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// Rotate into body frame
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mag_bf = dcm.transposed() * mag_ef;
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// add motor interference
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mag_bf += sitl->mag_mot.get() * battery_current;
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}
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/* advance time by deltat in seconds */
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void Aircraft::time_advance()
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{
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// we only advance time if it hasn't been advanced already by the
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// backend
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if (last_time_us == time_now_us) {
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time_now_us += frame_time_us;
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}
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last_time_us = time_now_us;
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if (use_time_sync) {
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sync_frame_time();
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}
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}
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/* setup the frame step time */
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void Aircraft::setup_frame_time(float new_rate, float new_speedup)
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{
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rate_hz = new_rate;
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target_speedup = new_speedup;
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frame_time_us = static_cast<uint64_t>(1.0e6f/rate_hz);
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scaled_frame_time_us = frame_time_us/target_speedup;
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last_wall_time_us = get_wall_time_us();
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achieved_rate_hz = rate_hz;
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}
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/* adjust frame_time calculation */
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void Aircraft::adjust_frame_time(float new_rate)
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{
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if (!is_equal(rate_hz, new_rate)) {
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rate_hz = new_rate;
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frame_time_us = static_cast<uint64_t>(1.0e6f/rate_hz);
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scaled_frame_time_us = frame_time_us/target_speedup;
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}
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}
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/*
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try to synchronise simulation time with wall clock time, taking
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into account desired speedup
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This tries to take account of possible granularity of
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get_wall_time_us() so it works reasonably well on windows
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*/
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void Aircraft::sync_frame_time(void)
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{
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frame_counter++;
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uint64_t now = get_wall_time_us();
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if (frame_counter >= 40 &&
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now > last_wall_time_us) {
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const float rate = frame_counter * 1.0e6f/(now - last_wall_time_us);
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achieved_rate_hz = (0.99f*achieved_rate_hz) + (0.01f * rate);
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if (achieved_rate_hz < rate_hz * target_speedup) {
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scaled_frame_time_us *= 0.999f;
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} else {
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scaled_frame_time_us /= 0.999f;
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}
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#if 0
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::printf("achieved_rate_hz=%.3f rate=%.2f rate_hz=%.3f sft=%.1f\n",
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static_cast<double>(achieved_rate_hz),
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static_cast<double>(rate),
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static_cast<double>(rate_hz),
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static_cast<double>(scaled_frame_time_us));
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#endif
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const uint32_t sleep_time = static_cast<uint32_t>(scaled_frame_time_us * frame_counter);
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if (sleep_time > min_sleep_time) {
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usleep(sleep_time);
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}
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last_wall_time_us = now;
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frame_counter = 0;
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}
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}
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/* add noise based on throttle level (from 0..1) */
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void Aircraft::add_noise(float throttle)
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{
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gyro += Vector3f(rand_normal(0, 1),
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rand_normal(0, 1),
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rand_normal(0, 1)) * gyro_noise * fabsf(throttle);
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accel_body += Vector3f(rand_normal(0, 1),
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rand_normal(0, 1),
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rand_normal(0, 1)) * accel_noise * fabsf(throttle);
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}
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/*
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normal distribution random numbers
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See
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http://en.literateprograms.org/index.php?title=Special:DownloadCode/Box-Muller_transform_%28C%29&oldid=7011
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*/
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double Aircraft::rand_normal(double mean, double stddev)
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{
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static double n2 = 0.0;
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static int n2_cached = 0;
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if (!n2_cached) {
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double x, y, r;
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do
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{
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x = 2.0 * rand()/RAND_MAX - 1;
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y = 2.0 * rand()/RAND_MAX - 1;
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r = x*x + y*y;
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} while (is_zero(r) || r > 1.0);
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const double d = sqrt(-2.0 * log(r)/r);
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const double n1 = x * d;
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n2 = y * d;
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const double result = n1 * stddev + mean;
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n2_cached = 1;
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return result;
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} else {
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n2_cached = 0;
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return n2 * stddev + mean;
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}
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}
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/*
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fill a sitl_fdm structure from the simulator state
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*/
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void Aircraft::fill_fdm(struct sitl_fdm &fdm)
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{
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if (use_smoothing) {
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smooth_sensors();
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}
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fdm.timestamp_us = time_now_us;
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if (fdm.home.lat == 0 && fdm.home.lng == 0) {
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// initialise home
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fdm.home = home;
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}
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fdm.latitude = location.lat * 1.0e-7;
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fdm.longitude = location.lng * 1.0e-7;
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fdm.altitude = location.alt * 1.0e-2;
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fdm.heading = degrees(atan2f(velocity_ef.y, velocity_ef.x));
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fdm.speedN = velocity_ef.x;
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fdm.speedE = velocity_ef.y;
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fdm.speedD = velocity_ef.z;
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fdm.xAccel = accel_body.x;
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fdm.yAccel = accel_body.y;
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fdm.zAccel = accel_body.z;
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fdm.rollRate = degrees(gyro.x);
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fdm.pitchRate = degrees(gyro.y);
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fdm.yawRate = degrees(gyro.z);
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fdm.angAccel.x = degrees(ang_accel.x);
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fdm.angAccel.y = degrees(ang_accel.y);
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fdm.angAccel.z = degrees(ang_accel.z);
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float r, p, y;
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dcm.to_euler(&r, &p, &y);
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fdm.rollDeg = degrees(r);
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fdm.pitchDeg = degrees(p);
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fdm.yawDeg = degrees(y);
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fdm.quaternion.from_rotation_matrix(dcm);
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fdm.airspeed = airspeed_pitot;
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fdm.battery_voltage = battery_voltage;
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fdm.battery_current = battery_current;
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fdm.rpm1 = rpm1;
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fdm.rpm2 = rpm2;
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fdm.rcin_chan_count = rcin_chan_count;
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fdm.range = range;
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memcpy(fdm.rcin, rcin, rcin_chan_count * sizeof(float));
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fdm.bodyMagField = mag_bf;
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// copy laser scanner results
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fdm.scanner.points = scanner.points;
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fdm.scanner.ranges = scanner.ranges;
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if (smoothing.enabled) {
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fdm.xAccel = smoothing.accel_body.x;
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fdm.yAccel = smoothing.accel_body.y;
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fdm.zAccel = smoothing.accel_body.z;
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fdm.rollRate = degrees(smoothing.gyro.x);
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fdm.pitchRate = degrees(smoothing.gyro.y);
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fdm.yawRate = degrees(smoothing.gyro.z);
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fdm.speedN = smoothing.velocity_ef.x;
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fdm.speedE = smoothing.velocity_ef.y;
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fdm.speedD = smoothing.velocity_ef.z;
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fdm.latitude = smoothing.location.lat * 1.0e-7;
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fdm.longitude = smoothing.location.lng * 1.0e-7;
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fdm.altitude = smoothing.location.alt * 1.0e-2;
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}
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if (ahrs_orientation != nullptr) {
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enum Rotation imu_rotation = (enum Rotation)ahrs_orientation->get();
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if (imu_rotation != ROTATION_NONE) {
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Matrix3f m = dcm;
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Matrix3f rot;
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rot.from_rotation(imu_rotation);
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m = m * rot.transposed();
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m.to_euler(&r, &p, &y);
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fdm.rollDeg = degrees(r);
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fdm.pitchDeg = degrees(p);
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fdm.yawDeg = degrees(y);
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fdm.quaternion.from_rotation_matrix(m);
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}
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}
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if (!is_equal(last_speedup, float(sitl->speedup)) && sitl->speedup > 0) {
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set_speedup(sitl->speedup);
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last_speedup = sitl->speedup;
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}
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}
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uint64_t Aircraft::get_wall_time_us() const
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{
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#if defined(__CYGWIN__) || defined(__CYGWIN64__)
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static DWORD tPrev;
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static uint64_t last_ret_us;
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if (tPrev == 0) {
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tPrev = timeGetTime();
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return 0;
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}
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DWORD now = timeGetTime();
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last_ret_us += (uint64_t)((now - tPrev)*1000UL);
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tPrev = now;
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return last_ret_us;
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#else
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struct timeval tp;
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gettimeofday(&tp, nullptr);
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return static_cast<uint64_t>(tp.tv_sec * 1.0e6 + tp.tv_usec);
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#endif
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}
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/*
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set simulation speedup
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*/
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void Aircraft::set_speedup(float speedup)
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{
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setup_frame_time(rate_hz, speedup);
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}
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/*
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update the simulation attitude and relative position
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*/
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void Aircraft::update_dynamics(const Vector3f &rot_accel)
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{
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const float delta_time = frame_time_us * 1.0e-6f;
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// update rotational rates in body frame
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gyro += rot_accel * delta_time;
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gyro.x = constrain_float(gyro.x, -radians(2000.0f), radians(2000.0f));
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gyro.y = constrain_float(gyro.y, -radians(2000.0f), radians(2000.0f));
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gyro.z = constrain_float(gyro.z, -radians(2000.0f), radians(2000.0f));
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// estimate angular acceleration using a first order difference calculation
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// TODO the simulator interface should provide the angular acceleration
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ang_accel = (gyro - gyro_prev) / delta_time;
|
|
gyro_prev = gyro;
|
|
|
|
// update attitude
|
|
dcm.rotate(gyro * delta_time);
|
|
dcm.normalize();
|
|
|
|
Vector3f accel_earth = dcm * accel_body;
|
|
accel_earth += Vector3f(0.0f, 0.0f, GRAVITY_MSS);
|
|
|
|
// if we're on the ground, then our vertical acceleration is limited
|
|
// to zero. This effectively adds the force of the ground on the aircraft
|
|
if (on_ground() && accel_earth.z > 0) {
|
|
accel_earth.z = 0;
|
|
}
|
|
|
|
// work out acceleration as seen by the accelerometers. It sees the kinematic
|
|
// acceleration (ie. real movement), plus gravity
|
|
accel_body = dcm.transposed() * (accel_earth + Vector3f(0.0f, 0.0f, -GRAVITY_MSS));
|
|
|
|
// new velocity vector
|
|
velocity_ef += accel_earth * delta_time;
|
|
|
|
const bool was_on_ground = on_ground();
|
|
// new position vector
|
|
position += velocity_ef * delta_time;
|
|
|
|
// velocity relative to air mass, in earth frame
|
|
velocity_air_ef = velocity_ef + wind_ef;
|
|
|
|
// velocity relative to airmass in body frame
|
|
velocity_air_bf = dcm.transposed() * velocity_air_ef;
|
|
|
|
// airspeed
|
|
airspeed = velocity_air_ef.length();
|
|
|
|
// airspeed as seen by a fwd pitot tube (limited to 120m/s)
|
|
airspeed_pitot = constrain_float(velocity_air_bf * Vector3f(1.0f, 0.0f, 0.0f), 0.0f, 120.0f);
|
|
|
|
// constrain height to the ground
|
|
if (on_ground()) {
|
|
if (!was_on_ground && AP_HAL::millis() - last_ground_contact_ms > 1000) {
|
|
printf("Hit ground at %f m/s\n", velocity_ef.z);
|
|
last_ground_contact_ms = AP_HAL::millis();
|
|
}
|
|
position.z = -(ground_level + frame_height - home.alt * 0.01f + ground_height_difference());
|
|
|
|
switch (ground_behavior) {
|
|
case GROUND_BEHAVIOR_NONE:
|
|
break;
|
|
case GROUND_BEHAVIOR_NO_MOVEMENT: {
|
|
// zero roll/pitch, but keep yaw
|
|
float r, p, y;
|
|
dcm.to_euler(&r, &p, &y);
|
|
dcm.from_euler(0.0f, 0.0f, y);
|
|
// no X or Y movement
|
|
velocity_ef.x = 0.0f;
|
|
velocity_ef.y = 0.0f;
|
|
if (velocity_ef.z > 0.0f) {
|
|
velocity_ef.z = 0.0f;
|
|
}
|
|
gyro.zero();
|
|
use_smoothing = true;
|
|
break;
|
|
}
|
|
case GROUND_BEHAVIOR_FWD_ONLY: {
|
|
// zero roll/pitch, but keep yaw
|
|
float r, p, y;
|
|
dcm.to_euler(&r, &p, &y);
|
|
dcm.from_euler(0.0f, 0.0f, y);
|
|
// only fwd movement
|
|
Vector3f v_bf = dcm.transposed() * velocity_ef;
|
|
v_bf.y = 0.0f;
|
|
if (v_bf.x < 0.0f) {
|
|
v_bf.x = 0.0f;
|
|
}
|
|
velocity_ef = dcm * v_bf;
|
|
if (velocity_ef.z > 0.0f) {
|
|
velocity_ef.z = 0.0f;
|
|
}
|
|
gyro.zero();
|
|
use_smoothing = true;
|
|
break;
|
|
}
|
|
case GROUND_BEHAVIOR_TAILSITTER: {
|
|
// point straight up
|
|
float r, p, y;
|
|
dcm.to_euler(&r, &p, &y);
|
|
dcm.from_euler(0.0f, radians(90), y);
|
|
// no movement
|
|
if (accel_earth.z > -1.1*GRAVITY_MSS) {
|
|
velocity_ef.zero();
|
|
}
|
|
gyro.zero();
|
|
use_smoothing = true;
|
|
break;
|
|
}
|
|
}
|
|
}
|
|
}
|
|
|
|
/*
|
|
update wind vector
|
|
*/
|
|
void Aircraft::update_wind(const struct sitl_input &input)
|
|
{
|
|
// wind vector in earth frame
|
|
wind_ef = Vector3f(cosf(radians(input.wind.direction))*cosf(radians(input.wind.dir_z)),
|
|
sinf(radians(input.wind.direction))*cosf(radians(input.wind.dir_z)),
|
|
sinf(radians(input.wind.dir_z))) * input.wind.speed;
|
|
|
|
const float wind_turb = input.wind.turbulence * 10.0f; // scale input.wind.turbulence to match standard deviation when using iir_coef=0.98
|
|
const float iir_coef = 0.98f; // filtering high frequencies from turbulence
|
|
|
|
if (wind_turb > 0 && !on_ground()) {
|
|
|
|
turbulence_azimuth = turbulence_azimuth + (2 * rand());
|
|
|
|
turbulence_horizontal_speed =
|
|
static_cast<float>(turbulence_horizontal_speed * iir_coef+wind_turb * rand_normal(0, 1) * (1 - iir_coef));
|
|
|
|
turbulence_vertical_speed = static_cast<float>((turbulence_vertical_speed * iir_coef) + (wind_turb * rand_normal(0, 1) * (1 - iir_coef)));
|
|
|
|
wind_ef += Vector3f(
|
|
cosf(radians(turbulence_azimuth)) * turbulence_horizontal_speed,
|
|
sinf(radians(turbulence_azimuth)) * turbulence_horizontal_speed,
|
|
turbulence_vertical_speed);
|
|
}
|
|
}
|
|
|
|
/*
|
|
smooth sensors for kinematic consistancy when we interact with the ground
|
|
*/
|
|
void Aircraft::smooth_sensors(void)
|
|
{
|
|
uint64_t now = time_now_us;
|
|
Vector3f delta_pos = position - smoothing.position;
|
|
if (smoothing.last_update_us == 0 || delta_pos.length() > 10) {
|
|
smoothing.position = position;
|
|
smoothing.rotation_b2e = dcm;
|
|
smoothing.accel_body = accel_body;
|
|
smoothing.velocity_ef = velocity_ef;
|
|
smoothing.gyro = gyro;
|
|
smoothing.last_update_us = now;
|
|
smoothing.location = location;
|
|
printf("Smoothing reset at %.3f\n", now * 1.0e-6f);
|
|
return;
|
|
}
|
|
const float delta_time = (now - smoothing.last_update_us) * 1.0e-6f;
|
|
if (delta_time < 0 || delta_time > 0.1) {
|
|
return;
|
|
}
|
|
|
|
// calculate required accel to get us to desired position and velocity in the time_constant
|
|
const float time_constant = 0.1f;
|
|
Vector3f dvel = (velocity_ef - smoothing.velocity_ef) + (delta_pos / time_constant);
|
|
Vector3f accel_e = dvel / time_constant + (dcm * accel_body + Vector3f(0.0f, 0.0f, GRAVITY_MSS));
|
|
const float accel_limit = 14 * GRAVITY_MSS;
|
|
accel_e.x = constrain_float(accel_e.x, -accel_limit, accel_limit);
|
|
accel_e.y = constrain_float(accel_e.y, -accel_limit, accel_limit);
|
|
accel_e.z = constrain_float(accel_e.z, -accel_limit, accel_limit);
|
|
smoothing.accel_body = smoothing.rotation_b2e.transposed() * (accel_e + Vector3f(0.0f, 0.0f, -GRAVITY_MSS));
|
|
|
|
// calculate rotational rate to get us to desired attitude in time constant
|
|
Quaternion desired_q, current_q, error_q;
|
|
desired_q.from_rotation_matrix(dcm);
|
|
desired_q.normalize();
|
|
current_q.from_rotation_matrix(smoothing.rotation_b2e);
|
|
current_q.normalize();
|
|
error_q = desired_q / current_q;
|
|
error_q.normalize();
|
|
|
|
Vector3f angle_differential;
|
|
error_q.to_axis_angle(angle_differential);
|
|
smoothing.gyro = gyro + angle_differential / time_constant;
|
|
|
|
float R, P, Y;
|
|
smoothing.rotation_b2e.to_euler(&R, &P, &Y);
|
|
float R2, P2, Y2;
|
|
dcm.to_euler(&R2, &P2, &Y2);
|
|
|
|
#if 0
|
|
AP::logger().Write("SMOO", "TimeUS,AEx,AEy,AEz,DPx,DPy,DPz,R,P,Y,R2,P2,Y2",
|
|
"Qffffffffffff",
|
|
AP_HAL::micros64(),
|
|
degrees(angle_differential.x),
|
|
degrees(angle_differential.y),
|
|
degrees(angle_differential.z),
|
|
delta_pos.x, delta_pos.y, delta_pos.z,
|
|
degrees(R), degrees(P), degrees(Y),
|
|
degrees(R2), degrees(P2), degrees(Y2));
|
|
#endif
|
|
|
|
|
|
// integrate to get new attitude
|
|
smoothing.rotation_b2e.rotate(smoothing.gyro * delta_time);
|
|
smoothing.rotation_b2e.normalize();
|
|
|
|
// integrate to get new position
|
|
smoothing.velocity_ef += accel_e * delta_time;
|
|
smoothing.position += smoothing.velocity_ef * delta_time;
|
|
|
|
smoothing.location = home;
|
|
smoothing.location.offset(smoothing.position.x, smoothing.position.y);
|
|
smoothing.location.alt = static_cast<int32_t>(home.alt - smoothing.position.z * 100.0f);
|
|
|
|
smoothing.last_update_us = now;
|
|
smoothing.enabled = true;
|
|
}
|
|
|
|
/*
|
|
return a filtered servo input as a value from -1 to 1
|
|
servo is assumed to be 1000 to 2000, trim at 1500
|
|
*/
|
|
float Aircraft::filtered_idx(float v, uint8_t idx)
|
|
{
|
|
if (sitl->servo_speed <= 0) {
|
|
return v;
|
|
}
|
|
const float cutoff = 1.0f / (2 * M_PI * sitl->servo_speed);
|
|
servo_filter[idx].set_cutoff_frequency(cutoff);
|
|
return servo_filter[idx].apply(v, frame_time_us * 1.0e-6f);
|
|
}
|
|
|
|
|
|
/*
|
|
return a filtered servo input as a value from -1 to 1
|
|
servo is assumed to be 1000 to 2000, trim at 1500
|
|
*/
|
|
float Aircraft::filtered_servo_angle(const struct sitl_input &input, uint8_t idx)
|
|
{
|
|
const float v = (input.servos[idx] - 1500)/500.0f;
|
|
return filtered_idx(v, idx);
|
|
}
|
|
|
|
/*
|
|
return a filtered servo input as a value from 0 to 1
|
|
servo is assumed to be 1000 to 2000
|
|
*/
|
|
float Aircraft::filtered_servo_range(const struct sitl_input &input, uint8_t idx)
|
|
{
|
|
const float v = (input.servos[idx] - 1000)/1000.0f;
|
|
return filtered_idx(v, idx);
|
|
}
|
|
|
|
// extrapolate sensors by a given delta time in seconds
|
|
void Aircraft::extrapolate_sensors(float delta_time)
|
|
{
|
|
Vector3f accel_earth = dcm * accel_body;
|
|
accel_earth.z += GRAVITY_MSS;
|
|
|
|
dcm.rotate(gyro * delta_time);
|
|
dcm.normalize();
|
|
|
|
// work out acceleration as seen by the accelerometers. It sees the kinematic
|
|
// acceleration (ie. real movement), plus gravity
|
|
accel_body = dcm.transposed() * (accel_earth + Vector3f(0,0,-GRAVITY_MSS));
|
|
|
|
// new velocity and position vectors
|
|
velocity_ef += accel_earth * delta_time;
|
|
position += velocity_ef * delta_time;
|
|
velocity_air_ef = velocity_ef + wind_ef;
|
|
velocity_air_bf = dcm.transposed() * velocity_air_ef;
|
|
}
|
|
|
|
void Aircraft::update_external_payload(const struct sitl_input &input)
|
|
{
|
|
external_payload_mass = 0;
|
|
|
|
// update sprayer
|
|
if (sprayer && sprayer->is_enabled()) {
|
|
sprayer->update(input);
|
|
external_payload_mass += sprayer->payload_mass();
|
|
}
|
|
|
|
// update grippers
|
|
if (gripper && gripper->is_enabled()) {
|
|
gripper->set_alt(hagl());
|
|
gripper->update(input);
|
|
external_payload_mass += gripper->payload_mass();
|
|
}
|
|
if (gripper_epm && gripper_epm->is_enabled()) {
|
|
gripper_epm->update(input);
|
|
external_payload_mass += gripper_epm->payload_mass();
|
|
}
|
|
|
|
// update parachute
|
|
if (parachute && parachute->is_enabled()) {
|
|
parachute->update(input);
|
|
// TODO: add drag to vehicle, presumably proportional to velocity
|
|
}
|
|
|
|
if (precland && precland->is_enabled()) {
|
|
precland->update(get_location(), get_position());
|
|
}
|
|
}
|