mirror of
https://gitlab.com/lander-team/lander-cpp.git
synced 2025-06-16 15:17:23 +00:00
update include structure
This commit is contained in:
parent
24bf3f2102
commit
5233a9ef2e
10
.vscode/tasks.json
vendored
10
.vscode/tasks.json
vendored
@ -4,10 +4,10 @@
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{
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{
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"type": "cppbuild",
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"type": "cppbuild",
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"label": "Debug",
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"label": "Debug",
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"command": "C:\\Program Files\\mingw-w64\\x86_64-8.1.0-posix-seh-rt_v6-rev0\\mingw64\\bin\\g++.exe",
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"command": "g++",
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"args": [
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"args": [
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"-g",
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"-g",
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"${workspaceFolder}\\src\\*.cpp",
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"${workspaceFolder}\\src\\main.cpp",
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"-o",
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"-o",
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"${workspaceFolder}\\build\\debug\\${fileBasenameNoExtension}.exe",
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"${workspaceFolder}\\build\\debug\\${fileBasenameNoExtension}.exe",
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"-I",
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"-I",
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@ -23,14 +23,13 @@
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"kind": "build",
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"kind": "build",
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"isDefault": true
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"isDefault": true
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},
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},
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"detail": "compiler: \"C:\\Program Files\\mingw-w64\\x86_64-8.1.0-posix-seh-rt_v6-rev0\\mingw64\\bin\\g++.exe\""
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},
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},
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{
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{
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"type": "cppbuild",
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"type": "cppbuild",
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"label": "Release",
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"label": "Release",
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"command": "C:\\Program Files\\mingw-w64\\x86_64-8.1.0-posix-seh-rt_v6-rev0\\mingw64\\bin\\g++.exe",
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"command": "g++",
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"args": [
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"args": [
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"${workspaceFolder}\\src\\*.cpp",
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"${workspaceFolder}\\src\\main.cpp",
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"-o",
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"-o",
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"${workspaceFolder}\\build\\release\\${fileBasenameNoExtension}.exe",
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"${workspaceFolder}\\build\\release\\${fileBasenameNoExtension}.exe",
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"-I",
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"-I",
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@ -46,7 +45,6 @@
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"kind": "build",
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"kind": "build",
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"isDefault": true
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"isDefault": true
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},
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},
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"detail": "compiler: \"C:\\Program Files\\mingw-w64\\x86_64-8.1.0-posix-seh-rt_v6-rev0\\mingw64\\bin\\g++.exe\""
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}
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}
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]
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]
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}
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}
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429
include/sim.h
429
include/sim.h
@ -7,4 +7,431 @@ void TVC(struct sVars &, double g);
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void vehicleDynamics(struct sVars &, int t);
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void vehicleDynamics(struct sVars &, int t);
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void write2CSV(struct sVars &, std::fstream &outfile, int t);
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void write2CSV(struct sVars &, std::fstream &outfile, int t);
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double derivative(double x2, double x1, double dt);
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double derivative(double x2, double x1, double dt);
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double integral(double x2, double x1, double dt);
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double integral(double x2, double x1, double dt);
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void sim(struct sVars &Vars) {
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double g = -9.81;
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// defining a few random values here cause I'm lazy
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Vars.burnElapsed = 2000;
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Vars.m = Vars.m0;
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Vars.thrust_prev = 0;
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burnStartTimeCalc(Vars, g);
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// Deleting any previous output file
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if (remove("simOut.csv") != 0)
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perror("Error deleting file");
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else
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puts("File successfully deleted");
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// Define and open output file "simOut.csv"
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std::fstream outfile;
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outfile.open("simOut.csv", std::ios::app);
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// Output file header. These are the variables that we output - useful for
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// debugging
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outfile
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<< "t, x, y, z, vx, vy, vz, ax, ay, az, yaw, pitch, roll, yawdot, "
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"pitchdot, rolldot, yawddot, pitchddot, rollddot, I11, I22, I33, "
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"I11dot, I22dot, I33dot, Servo1, Servo2, m, thrust, burnElapsed, Fz, "
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"LQRx, LQRy"
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<< std::endl;
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// Start Sim
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for (int t = 0; t < Vars.simTime; t++) {
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thrustSelection(Vars, t);
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lqrCalc(Vars);
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TVC(Vars, g);
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vehicleDynamics(Vars, t);
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write2CSV(Vars, outfile, t);
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}
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outfile.close();
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}
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void burnStartTimeCalc(struct sVars &Vars, double g) {
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double v = Vars.vz;
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double h = 0;
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double dt = 0.001;
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double a, j, m, thrust;
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for (double i = 0.148; i < 3.450; i = i + dt) {
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m = Vars.m0 - i * Vars.mdot;
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if ((i > 0.147) & (i < 0.420))
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thrust = 65.165 * i - 2.3921;
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else if ((i > 0.419) & (i < 3.383))
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thrust = 0.8932 * pow(i, 6) - 11.609 * pow(i, 5) + 60.739 * pow(i, 4) -
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162.99 * pow(i, 3) + 235.6 * pow(i, 2) - 174.43 * i + 67.17;
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else if ((i > 3.382) & (i < 3.46))
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thrust = -195.78 * i + 675.11;
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v = (((thrust / m) + g) * dt) + v;
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h = v * dt + h;
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}
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Vars.z = h + (pow(v, 2) / (2 * -g)); // starting height
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Vars.vb = v; // terminal velocity
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double burnStartTime = Vars.vb / -g;
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Vars.simTime = (Vars.tb + burnStartTime) * 1000;
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}
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void thrustSelection(struct sVars &Vars, int t) {
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double tol = 0.001; // 0.001 seems to be a nice tolerance
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// Check to see if current velocity is close to the F15's total velocity
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bool b_burnStart = (Vars.vb < (1 + tol) * Vars.vz * -1) &
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(Vars.vb > (1 - tol) * Vars.vz * -1);
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if (Vars.burnElapsed != 2000) {
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// determine where in the thrust curve we're at based on elapsed burn time
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// as well as current mass
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Vars.burnElapsed = (t - Vars.burnStart) / 1000;
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Vars.m = Vars.m0 - (Vars.mdot * Vars.burnElapsed);
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}
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else if (b_burnStart) {
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// Start burn
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Vars.burnStart = t;
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Vars.burnElapsed = 0;
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}
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else
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Vars.burnElapsed = 2000; // arbitrary number to ensure we don't burn
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if ((Vars.burnElapsed > 0.147) & (Vars.burnElapsed < 0.420))
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Vars.thrust = 65.165 * Vars.burnElapsed - 2.3921;
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else if ((Vars.burnElapsed > 0.419) & (Vars.burnElapsed < 3.383))
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Vars.thrust =
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0.8932 * pow(Vars.burnElapsed, 6) - 11.609 * pow(Vars.burnElapsed, 5) +
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60.739 * pow(Vars.burnElapsed, 4) - 162.99 * pow(Vars.burnElapsed, 3) +
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235.6 * pow(Vars.burnElapsed, 2) - 174.43 * Vars.burnElapsed + 67.17;
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else if ((Vars.burnElapsed > 3.382) & (Vars.burnElapsed < 3.46))
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Vars.thrust = -195.78 * Vars.burnElapsed + 675.11;
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}
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void lqrCalc(struct sVars &Vars) {
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Vars.I11 = Vars.m * ((1 / 12) * pow(Vars.vehicleHeight, 2) +
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pow(Vars.vehicleRadius, 2) / 4);
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Vars.I22 = Vars.m * ((1 / 12) * pow(Vars.vehicleHeight, 2) +
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pow(Vars.vehicleRadius, 2) / 4);
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Vars.I33 = Vars.m * 0.5 * pow(Vars.vehicleRadius, 2);
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/*
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double n = sqrt(398600 / pow(6678, 3));
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double k1 = (Vars.I22 - Vars.I33) / Vars.I11;
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double k2 = (Vars.I11 - Vars.I33) / Vars.I22;
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double k3 = (Vars.I22 - Vars.I11) / Vars.I33;
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double R11 = pow(10, 2);
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double R22 = pow(10, 2);
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double R33 = pow(10, 2);
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double F11 = -2 * pow(n, 2) * 4 * k1;
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double F22 = -2 * pow(n, 2) * 3 * k2;
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double F33 = -2 * pow(n, 2) * k3;
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double G31 = n * (1 - k1);
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double G13 = n * (k3 - 1);
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double d = 0.5;
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/*
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The following calculations are based on output of LQR.m to avoid working
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with matrices in C++ Please see .m file for details on calculation.
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Algorithm taken from LQR wikipedia page:
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https://en.wikipedia.org/wiki/Algebraic_Riccati_equation#Solution
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*/
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/*
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double gain = 0.25;
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double K11 =
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-1 * gain *
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(Vars.I33 * pow(abs(F33), 2) * pow(abs(Vars.I33), 4) * pow(abs(R33), 2) +
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R33 * pow(abs(G31), 2) * pow(abs(Vars.I33), 2) + Vars.I33) /
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(R11 * d * Vars.I11 *
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(pow(abs(F33), 2) * pow(abs(Vars.I33), 4) * pow(abs(R33), 2) + 1));
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double K22 = -1 * gain * Vars.I33 / (R22 * d * Vars.I22);
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double K33 =
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-1 * gain *
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(Vars.I33 *
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(Vars.I33 * pow(abs(F11), 2) * pow(abs(Vars.I11), 4) * pow(abs(R11), 2) +
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R11 * pow(abs(G13), 2) * pow(abs(Vars.I11), 2) + Vars.I33)) /
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(R33 * d * pow(abs(Vars.I33), 2) *
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(pow(abs(F11), 2) * pow(abs(Vars.I11), 4) * pow(abs(R11), 2) + 1));
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double K34 =
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gain * (R11 * pow(abs(Vars.I11), 2) * G13) /
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(R33 * Vars.I33 *
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(pow(abs(F11), 2) * pow(abs(Vars.I11), 4) * pow(abs(R11), 2) + 1));
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double K16 =
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gain * (R33 * pow(abs(Vars.I33), 2) * G31) /
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(R11 * Vars.I11 *
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(pow(abs(F33), 2) * pow(abs(Vars.I33), 4) * pow(abs(R33), 2) + 1));
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// Matrix Multiply K with [YPR/2; w123] column vector and divide by moment arm
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Vars.LQRx = (K11 * Vars.yaw / 2 + K16 * Vars.rolldot) / Vars.momentArm;
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Vars.LQRy = (K22 * Vars.pitch / 2) / Vars.momentArm;
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*/
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// Paste in Values from gainCalc.m
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double K11 = 39.54316;
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double K12 = 0.00000;
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double K13 = -0.00000;
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double K14 = 39.55769;
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double K15 = 0.00000;
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double K16 = 0.00000;
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double K21 = 0.00000;
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double K22 = 39.54316;
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double K23 = 0.00000;
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double K24 = 0.00000;
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double K25 = 39.55769;
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double K26 = 0.00000;
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double K31 = 0.00000;
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double K32 = 0.00000;
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double K33 = 39.54316;
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double K34 = 0.00000;
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double K35 = 0.00000;
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double K36 = 39.54394;
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double gain =
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0.25 *
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pow(10, -4); // changing exponenet drastically changes results of LQR
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// Matrix Multiply K with [YPR/2; w123] column vector and divide by moment arm
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Vars.LQRx =
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gain *
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((K12 * Vars.pitch) / 2 + K15 * Vars.pitchdot + (K13 * Vars.roll) / 2 +
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K16 * Vars.rolldot + (K11 * Vars.yaw) / 2 + K14 * Vars.yawdot) /
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-Vars.momentArm;
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Vars.LQRy =
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gain *
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((K22 * Vars.pitch) / 2 + K25 * Vars.pitchdot + (K23 * Vars.roll) / 2 +
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K26 * Vars.rolldot + (K21 * Vars.yaw) / 2 + K24 * Vars.yawdot) /
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-Vars.momentArm;
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// LQR Force limiter X
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if (Vars.LQRx > Vars.thrust)
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Vars.LQRx = Vars.thrust;
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else if (Vars.LQRx < -1 * Vars.thrust)
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Vars.LQRx = -1 * Vars.thrust;
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// LQR Force limiter Y
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if (Vars.LQRy > Vars.thrust)
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Vars.LQRy = Vars.thrust;
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else if (Vars.LQRy < -1 * Vars.thrust)
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Vars.LQRy = -1 * Vars.thrust;
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}
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void TVC(struct sVars &Vars, double g) {
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|
if (Vars.thrust < 1) {
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// Define forces and moments for t = 0
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Vars.Fx = 0;
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Vars.Fy = 0;
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Vars.Fz = g * Vars.m0;
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Vars.momentX = 0;
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Vars.momentY = 0;
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Vars.momentZ = 0;
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}
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else {
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// Convert servo position to degrees for comparison to max allowable
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Vars.xServoDegs = (180 / 3.1416) * asin(Vars.LQRx / Vars.thrust);
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// Servo position limiter
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if (Vars.xServoDegs > Vars.maxServo)
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Vars.xServoDegs = Vars.maxServo;
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else if (Vars.xServoDegs < -1 * Vars.maxServo)
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Vars.xServoDegs = -1 * Vars.maxServo;
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// Convert servo position to degrees for comparison to max allowable
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Vars.yServoDegs = (180 / 3.1416) * asin(Vars.LQRy / Vars.thrust);
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// Servo position limiter
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if (Vars.yServoDegs > Vars.maxServo)
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Vars.yServoDegs = Vars.maxServo;
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else if (Vars.yServoDegs < -1 * Vars.maxServo)
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Vars.yServoDegs = -1 * Vars.maxServo;
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// Vector math to aqcuire thrust vector components
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Vars.Fx = Vars.thrust * sin(Vars.xServoDegs * (3.1416 / 180));
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Vars.Fy = Vars.thrust * sin(Vars.yServoDegs * (3.1416 / 180));
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Vars.Fz = sqrt(pow(Vars.thrust, 2) - (pow(Vars.Fx, 2) + pow(Vars.Fy, 2))) +
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(Vars.m * g);
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|
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// Calculate moment created by Fx and Fy
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Vars.momentX = Vars.Fx * Vars.momentArm;
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Vars.momentY = Vars.Fy * Vars.momentArm;
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Vars.momentZ = 0;
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|
}
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|
}
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|
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|
void vehicleDynamics(struct sVars &Vars, int t) {
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// Idot
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|
if (t < 1) {
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|
Vars.I11dot = 0;
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Vars.I22dot = 0;
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|
Vars.I33dot = 0;
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} else {
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Vars.I11dot = derivative(Vars.I11, Vars.I11prev, Vars.stepSize);
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Vars.I22dot = derivative(Vars.I22, Vars.I22prev, Vars.stepSize);
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Vars.I33dot = derivative(Vars.I33, Vars.I33prev, Vars.stepSize);
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}
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// pdot, qdot, rdot
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||||||
|
Vars.yawddot = (Vars.momentX - Vars.I11dot * Vars.yawdot +
|
||||||
|
Vars.I22 * Vars.pitchdot * Vars.rolldot -
|
||||||
|
Vars.I33 * Vars.pitchdot * Vars.rolldot) /
|
||||||
|
Vars.I11;
|
||||||
|
Vars.pitchddot = (Vars.momentY - Vars.I22dot * Vars.pitchdot -
|
||||||
|
Vars.I11 * Vars.rolldot * Vars.yawdot +
|
||||||
|
Vars.I33 * Vars.rolldot * Vars.yawdot) /
|
||||||
|
Vars.I22;
|
||||||
|
Vars.rollddot = (Vars.momentZ - Vars.I33dot * Vars.rolldot +
|
||||||
|
Vars.I11 * Vars.pitchdot * Vars.yawdot -
|
||||||
|
Vars.I22 * Vars.pitchdot * Vars.yawdot) /
|
||||||
|
Vars.I33;
|
||||||
|
|
||||||
|
if (t < 1) {
|
||||||
|
Vars.x = 0;
|
||||||
|
Vars.y = 0;
|
||||||
|
|
||||||
|
Vars.ax = 0;
|
||||||
|
Vars.ay = 0;
|
||||||
|
Vars.az = Vars.Fz / Vars.m0;
|
||||||
|
}
|
||||||
|
|
||||||
|
else {
|
||||||
|
// p, q, r
|
||||||
|
Vars.yawdot = integral(Vars.yawddot, Vars.yawdotPrev, Vars.stepSize);
|
||||||
|
Vars.pitchdot = integral(Vars.pitchddot, Vars.pitchdotPrev, Vars.stepSize);
|
||||||
|
Vars.rolldot = integral(Vars.rollddot, Vars.rolldotPrev, Vars.stepSize);
|
||||||
|
|
||||||
|
// ax ay az
|
||||||
|
Vars.ax =
|
||||||
|
(Vars.Fx / Vars.m) + (Vars.pitchdot * Vars.vz - Vars.rolldot * Vars.vy);
|
||||||
|
Vars.ay =
|
||||||
|
(Vars.Fy / Vars.m) + (Vars.rolldot * Vars.vx - Vars.vz * Vars.yawdot);
|
||||||
|
Vars.az =
|
||||||
|
(Vars.Fz / Vars.m) + (Vars.vy * Vars.yawdot - Vars.pitchdot * Vars.vx);
|
||||||
|
|
||||||
|
// vx vy vz in Body frame
|
||||||
|
Vars.vx = integral(Vars.ax, Vars.vxPrev, Vars.stepSize);
|
||||||
|
Vars.vy = integral(Vars.ay, Vars.vyPrev, Vars.stepSize);
|
||||||
|
Vars.vz = integral(Vars.az, Vars.vzPrev, Vars.stepSize);
|
||||||
|
|
||||||
|
// Xe
|
||||||
|
Vars.x = integral(Vars.vx, Vars.xPrev, Vars.stepSize);
|
||||||
|
Vars.y = integral(Vars.vy, Vars.yPrev, Vars.stepSize);
|
||||||
|
Vars.z = integral(Vars.vz, Vars.zPrev, Vars.stepSize);
|
||||||
|
|
||||||
|
// Euler Angles
|
||||||
|
Vars.phidot = Vars.yawdot + (Vars.pitchdot * sin(Vars.yaw) +
|
||||||
|
Vars.rolldot * cos(Vars.yaw)) *
|
||||||
|
(sin(Vars.pitch) / cos(Vars.pitch));
|
||||||
|
Vars.thetadot =
|
||||||
|
Vars.pitchdot * cos(Vars.yaw) - Vars.rolldot * sin(Vars.pitch);
|
||||||
|
Vars.psidot =
|
||||||
|
(Vars.pitchdot * sin(Vars.yaw) + Vars.rolldot * cos(Vars.yaw)) /
|
||||||
|
cos(Vars.pitch);
|
||||||
|
|
||||||
|
Vars.yaw = integral(Vars.phidot, Vars.yawPrev, Vars.stepSize);
|
||||||
|
Vars.pitch = integral(Vars.thetadot, Vars.pitchPrev, Vars.stepSize);
|
||||||
|
Vars.roll = integral(Vars.psidot, Vars.rollPrev, Vars.stepSize);
|
||||||
|
}
|
||||||
|
|
||||||
|
// Set "prev" values for next timestep
|
||||||
|
Vars.I11prev = Vars.I11;
|
||||||
|
Vars.I22prev = Vars.I22;
|
||||||
|
Vars.I33prev = Vars.I33;
|
||||||
|
|
||||||
|
Vars.yawPrev = Vars.yaw;
|
||||||
|
Vars.pitchPrev = Vars.pitch;
|
||||||
|
Vars.rollPrev = Vars.roll;
|
||||||
|
|
||||||
|
Vars.yawdotPrev = Vars.yawdot;
|
||||||
|
Vars.pitchdotPrev = Vars.pitchdot;
|
||||||
|
Vars.rolldotPrev = Vars.rolldot;
|
||||||
|
|
||||||
|
Vars.yawddotPrev = Vars.yawddot;
|
||||||
|
Vars.pitchddotPrev = Vars.pitchddot;
|
||||||
|
Vars.rollddotPrev = Vars.rollddot;
|
||||||
|
|
||||||
|
Vars.axPrev = Vars.ax;
|
||||||
|
Vars.ayPrev = Vars.ay;
|
||||||
|
Vars.azPrev = Vars.az;
|
||||||
|
|
||||||
|
Vars.vxPrev = Vars.vx;
|
||||||
|
Vars.vyPrev = Vars.vy;
|
||||||
|
Vars.vzPrev = Vars.vz;
|
||||||
|
|
||||||
|
Vars.xPrev = Vars.x;
|
||||||
|
Vars.yPrev = Vars.y;
|
||||||
|
Vars.zPrev = Vars.z;
|
||||||
|
}
|
||||||
|
|
||||||
|
void write2CSV(struct sVars &Vars, std::fstream &outfile, int t) {
|
||||||
|
// writing to output file
|
||||||
|
outfile << t << ", ";
|
||||||
|
|
||||||
|
outfile << Vars.x << ", ";
|
||||||
|
outfile << Vars.y << ", ";
|
||||||
|
outfile << Vars.z << ", ";
|
||||||
|
|
||||||
|
outfile << Vars.vx << ", ";
|
||||||
|
outfile << Vars.vy << ", ";
|
||||||
|
outfile << Vars.vz << ", ";
|
||||||
|
|
||||||
|
outfile << Vars.ax << ", ";
|
||||||
|
outfile << Vars.ay << ", ";
|
||||||
|
outfile << Vars.az << ", ";
|
||||||
|
|
||||||
|
outfile << Vars.yaw * 180 / 3.1416 << ", ";
|
||||||
|
outfile << Vars.pitch * 180 / 3.1416 << ", ";
|
||||||
|
outfile << Vars.roll * 180 / 3.1416 << ", ";
|
||||||
|
|
||||||
|
outfile << Vars.yawdot * 180 / 3.1416 << ", ";
|
||||||
|
outfile << Vars.pitchdot * 180 / 3.1416 << ", ";
|
||||||
|
outfile << Vars.rolldot * 180 / 3.1416 << ", ";
|
||||||
|
|
||||||
|
outfile << Vars.yawddot * 180 / 3.1416 << ", ";
|
||||||
|
outfile << Vars.pitchddot * 180 / 3.1416 << ", ";
|
||||||
|
outfile << Vars.rollddot * 180 / 3.1416 << ", ";
|
||||||
|
|
||||||
|
outfile << Vars.I11 << ", ";
|
||||||
|
outfile << Vars.I22 << ", ";
|
||||||
|
outfile << Vars.I33 << ", ";
|
||||||
|
|
||||||
|
outfile << Vars.I11dot << ", ";
|
||||||
|
outfile << Vars.I22dot << ", ";
|
||||||
|
outfile << Vars.I33dot << ", ";
|
||||||
|
|
||||||
|
outfile << Vars.xServoDegs << ", ";
|
||||||
|
outfile << Vars.yServoDegs << ", ";
|
||||||
|
|
||||||
|
outfile << Vars.m << ", ";
|
||||||
|
outfile << Vars.thrust << ", ";
|
||||||
|
outfile << Vars.burnElapsed << ", ";
|
||||||
|
outfile << Vars.Fz << ", ";
|
||||||
|
|
||||||
|
outfile << Vars.LQRx << ", ";
|
||||||
|
outfile << Vars.LQRy << std::endl;
|
||||||
|
}
|
||||||
|
|
||||||
|
double derivative(double x2, double x1, double dt) {
|
||||||
|
double dxdt = (x2 - x1) / (dt / 1000);
|
||||||
|
return dxdt;
|
||||||
|
}
|
||||||
|
|
||||||
|
double integral(double x, double y, double dt) {
|
||||||
|
double integ = (x * dt / 1000) + y;
|
||||||
|
return integ;
|
||||||
|
}
|
||||||
@ -1,6 +1,10 @@
|
|||||||
|
#include <cmath>
|
||||||
|
#include <fstream>
|
||||||
|
#include <iostream>
|
||||||
|
#include <stdio.h>
|
||||||
|
|
||||||
#include "sVars.h"
|
#include "sVars.h"
|
||||||
#include "sim.h"
|
#include "sim.h"
|
||||||
#include <iostream>
|
|
||||||
|
|
||||||
void sim(struct sVars &);
|
void sim(struct sVars &);
|
||||||
|
|
||||||
|
|||||||
432
src/sim.cpp
432
src/sim.cpp
@ -1,432 +0,0 @@
|
|||||||
#include "sim.h"
|
|
||||||
#include <cmath>
|
|
||||||
#include <fstream>
|
|
||||||
#include <iostream>
|
|
||||||
#include <stdio.h>
|
|
||||||
|
|
||||||
void sim(struct sVars &Vars) {
|
|
||||||
double g = -9.81;
|
|
||||||
|
|
||||||
// defining a few random values here cause I'm lazy
|
|
||||||
Vars.burnElapsed = 2000;
|
|
||||||
Vars.m = Vars.m0;
|
|
||||||
Vars.thrust_prev = 0;
|
|
||||||
|
|
||||||
burnStartTimeCalc(Vars, g);
|
|
||||||
|
|
||||||
// Deleting any previous output file
|
|
||||||
if (remove("simOut.csv") != 0)
|
|
||||||
perror("Error deleting file");
|
|
||||||
else
|
|
||||||
puts("File successfully deleted");
|
|
||||||
|
|
||||||
// Define and open output file "simOut.csv"
|
|
||||||
std::fstream outfile;
|
|
||||||
outfile.open("simOut.csv", std::ios::app);
|
|
||||||
|
|
||||||
// Output file header. These are the variables that we output - useful for
|
|
||||||
// debugging
|
|
||||||
outfile
|
|
||||||
<< "t, x, y, z, vx, vy, vz, ax, ay, az, yaw, pitch, roll, yawdot, "
|
|
||||||
"pitchdot, rolldot, yawddot, pitchddot, rollddot, I11, I22, I33, "
|
|
||||||
"I11dot, I22dot, I33dot, Servo1, Servo2, m, thrust, burnElapsed, Fz, "
|
|
||||||
"LQRx, LQRy"
|
|
||||||
<< std::endl;
|
|
||||||
|
|
||||||
// Start Sim
|
|
||||||
for (int t = 0; t < Vars.simTime; t++) {
|
|
||||||
thrustSelection(Vars, t);
|
|
||||||
lqrCalc(Vars);
|
|
||||||
TVC(Vars, g);
|
|
||||||
vehicleDynamics(Vars, t);
|
|
||||||
write2CSV(Vars, outfile, t);
|
|
||||||
}
|
|
||||||
|
|
||||||
outfile.close();
|
|
||||||
}
|
|
||||||
|
|
||||||
void burnStartTimeCalc(struct sVars &Vars, double g) {
|
|
||||||
double v = Vars.vz;
|
|
||||||
double h = 0;
|
|
||||||
double dt = 0.001;
|
|
||||||
double a, j, m, thrust;
|
|
||||||
|
|
||||||
for (double i = 0.148; i < 3.450; i = i + dt) {
|
|
||||||
m = Vars.m0 - i * Vars.mdot;
|
|
||||||
|
|
||||||
if ((i > 0.147) & (i < 0.420))
|
|
||||||
thrust = 65.165 * i - 2.3921;
|
|
||||||
|
|
||||||
else if ((i > 0.419) & (i < 3.383))
|
|
||||||
thrust = 0.8932 * pow(i, 6) - 11.609 * pow(i, 5) + 60.739 * pow(i, 4) -
|
|
||||||
162.99 * pow(i, 3) + 235.6 * pow(i, 2) - 174.43 * i + 67.17;
|
|
||||||
|
|
||||||
else if ((i > 3.382) & (i < 3.46))
|
|
||||||
thrust = -195.78 * i + 675.11;
|
|
||||||
|
|
||||||
v = (((thrust / m) + g) * dt) + v;
|
|
||||||
h = v * dt + h;
|
|
||||||
}
|
|
||||||
|
|
||||||
Vars.z = h + (pow(v, 2) / (2 * -g)); // starting height
|
|
||||||
Vars.vb = v; // terminal velocity
|
|
||||||
|
|
||||||
double burnStartTime = Vars.vb / -g;
|
|
||||||
Vars.simTime = (Vars.tb + burnStartTime) * 1000;
|
|
||||||
}
|
|
||||||
|
|
||||||
void thrustSelection(struct sVars &Vars, int t) {
|
|
||||||
double tol = 0.001; // 0.001 seems to be a nice tolerance
|
|
||||||
|
|
||||||
// Check to see if current velocity is close to the F15's total velocity
|
|
||||||
bool b_burnStart = (Vars.vb < (1 + tol) * Vars.vz * -1) &
|
|
||||||
(Vars.vb > (1 - tol) * Vars.vz * -1);
|
|
||||||
|
|
||||||
if (Vars.burnElapsed != 2000) {
|
|
||||||
// determine where in the thrust curve we're at based on elapsed burn time
|
|
||||||
// as well as current mass
|
|
||||||
Vars.burnElapsed = (t - Vars.burnStart) / 1000;
|
|
||||||
Vars.m = Vars.m0 - (Vars.mdot * Vars.burnElapsed);
|
|
||||||
}
|
|
||||||
|
|
||||||
else if (b_burnStart) {
|
|
||||||
// Start burn
|
|
||||||
Vars.burnStart = t;
|
|
||||||
Vars.burnElapsed = 0;
|
|
||||||
}
|
|
||||||
|
|
||||||
else
|
|
||||||
Vars.burnElapsed = 2000; // arbitrary number to ensure we don't burn
|
|
||||||
|
|
||||||
if ((Vars.burnElapsed > 0.147) & (Vars.burnElapsed < 0.420))
|
|
||||||
Vars.thrust = 65.165 * Vars.burnElapsed - 2.3921;
|
|
||||||
|
|
||||||
else if ((Vars.burnElapsed > 0.419) & (Vars.burnElapsed < 3.383))
|
|
||||||
Vars.thrust =
|
|
||||||
0.8932 * pow(Vars.burnElapsed, 6) - 11.609 * pow(Vars.burnElapsed, 5) +
|
|
||||||
60.739 * pow(Vars.burnElapsed, 4) - 162.99 * pow(Vars.burnElapsed, 3) +
|
|
||||||
235.6 * pow(Vars.burnElapsed, 2) - 174.43 * Vars.burnElapsed + 67.17;
|
|
||||||
|
|
||||||
else if ((Vars.burnElapsed > 3.382) & (Vars.burnElapsed < 3.46))
|
|
||||||
Vars.thrust = -195.78 * Vars.burnElapsed + 675.11;
|
|
||||||
}
|
|
||||||
|
|
||||||
void lqrCalc(struct sVars &Vars) {
|
|
||||||
|
|
||||||
Vars.I11 = Vars.m * ((1 / 12) * pow(Vars.vehicleHeight, 2) +
|
|
||||||
pow(Vars.vehicleRadius, 2) / 4);
|
|
||||||
Vars.I22 = Vars.m * ((1 / 12) * pow(Vars.vehicleHeight, 2) +
|
|
||||||
pow(Vars.vehicleRadius, 2) / 4);
|
|
||||||
Vars.I33 = Vars.m * 0.5 * pow(Vars.vehicleRadius, 2);
|
|
||||||
|
|
||||||
/*
|
|
||||||
|
|
||||||
double n = sqrt(398600 / pow(6678, 3));
|
|
||||||
double k1 = (Vars.I22 - Vars.I33) / Vars.I11;
|
|
||||||
double k2 = (Vars.I11 - Vars.I33) / Vars.I22;
|
|
||||||
double k3 = (Vars.I22 - Vars.I11) / Vars.I33;
|
|
||||||
|
|
||||||
double R11 = pow(10, 2);
|
|
||||||
double R22 = pow(10, 2);
|
|
||||||
double R33 = pow(10, 2);
|
|
||||||
|
|
||||||
double F11 = -2 * pow(n, 2) * 4 * k1;
|
|
||||||
double F22 = -2 * pow(n, 2) * 3 * k2;
|
|
||||||
double F33 = -2 * pow(n, 2) * k3;
|
|
||||||
|
|
||||||
double G31 = n * (1 - k1);
|
|
||||||
double G13 = n * (k3 - 1);
|
|
||||||
|
|
||||||
double d = 0.5;
|
|
||||||
/*
|
|
||||||
The following calculations are based on output of LQR.m to avoid working
|
|
||||||
with matrices in C++ Please see .m file for details on calculation.
|
|
||||||
Algorithm taken from LQR wikipedia page:
|
|
||||||
https://en.wikipedia.org/wiki/Algebraic_Riccati_equation#Solution
|
|
||||||
*/
|
|
||||||
/*
|
|
||||||
double gain = 0.25;
|
|
||||||
|
|
||||||
double K11 =
|
|
||||||
-1 * gain *
|
|
||||||
(Vars.I33 * pow(abs(F33), 2) * pow(abs(Vars.I33), 4) * pow(abs(R33), 2) +
|
|
||||||
R33 * pow(abs(G31), 2) * pow(abs(Vars.I33), 2) + Vars.I33) /
|
|
||||||
(R11 * d * Vars.I11 *
|
|
||||||
(pow(abs(F33), 2) * pow(abs(Vars.I33), 4) * pow(abs(R33), 2) + 1));
|
|
||||||
double K22 = -1 * gain * Vars.I33 / (R22 * d * Vars.I22);
|
|
||||||
double K33 =
|
|
||||||
-1 * gain *
|
|
||||||
(Vars.I33 *
|
|
||||||
(Vars.I33 * pow(abs(F11), 2) * pow(abs(Vars.I11), 4) * pow(abs(R11), 2) +
|
|
||||||
R11 * pow(abs(G13), 2) * pow(abs(Vars.I11), 2) + Vars.I33)) /
|
|
||||||
(R33 * d * pow(abs(Vars.I33), 2) *
|
|
||||||
(pow(abs(F11), 2) * pow(abs(Vars.I11), 4) * pow(abs(R11), 2) + 1));
|
|
||||||
double K34 =
|
|
||||||
gain * (R11 * pow(abs(Vars.I11), 2) * G13) /
|
|
||||||
(R33 * Vars.I33 *
|
|
||||||
(pow(abs(F11), 2) * pow(abs(Vars.I11), 4) * pow(abs(R11), 2) + 1));
|
|
||||||
double K16 =
|
|
||||||
gain * (R33 * pow(abs(Vars.I33), 2) * G31) /
|
|
||||||
(R11 * Vars.I11 *
|
|
||||||
(pow(abs(F33), 2) * pow(abs(Vars.I33), 4) * pow(abs(R33), 2) + 1));
|
|
||||||
|
|
||||||
// Matrix Multiply K with [YPR/2; w123] column vector and divide by moment arm
|
|
||||||
Vars.LQRx = (K11 * Vars.yaw / 2 + K16 * Vars.rolldot) / Vars.momentArm;
|
|
||||||
Vars.LQRy = (K22 * Vars.pitch / 2) / Vars.momentArm;
|
|
||||||
|
|
||||||
*/
|
|
||||||
|
|
||||||
// Paste in Values from gainCalc.m
|
|
||||||
double K11 = 39.54316;
|
|
||||||
double K12 = 0.00000;
|
|
||||||
double K13 = -0.00000;
|
|
||||||
double K14 = 39.55769;
|
|
||||||
double K15 = 0.00000;
|
|
||||||
double K16 = 0.00000;
|
|
||||||
double K21 = 0.00000;
|
|
||||||
double K22 = 39.54316;
|
|
||||||
double K23 = 0.00000;
|
|
||||||
double K24 = 0.00000;
|
|
||||||
double K25 = 39.55769;
|
|
||||||
double K26 = 0.00000;
|
|
||||||
double K31 = 0.00000;
|
|
||||||
double K32 = 0.00000;
|
|
||||||
double K33 = 39.54316;
|
|
||||||
double K34 = 0.00000;
|
|
||||||
double K35 = 0.00000;
|
|
||||||
double K36 = 39.54394;
|
|
||||||
|
|
||||||
double gain =
|
|
||||||
0.25 *
|
|
||||||
pow(10, -4); // changing exponenet drastically changes results of LQR
|
|
||||||
|
|
||||||
// Matrix Multiply K with [YPR/2; w123] column vector and divide by moment arm
|
|
||||||
Vars.LQRx =
|
|
||||||
gain *
|
|
||||||
((K12 * Vars.pitch) / 2 + K15 * Vars.pitchdot + (K13 * Vars.roll) / 2 +
|
|
||||||
K16 * Vars.rolldot + (K11 * Vars.yaw) / 2 + K14 * Vars.yawdot) /
|
|
||||||
-Vars.momentArm;
|
|
||||||
Vars.LQRy =
|
|
||||||
gain *
|
|
||||||
((K22 * Vars.pitch) / 2 + K25 * Vars.pitchdot + (K23 * Vars.roll) / 2 +
|
|
||||||
K26 * Vars.rolldot + (K21 * Vars.yaw) / 2 + K24 * Vars.yawdot) /
|
|
||||||
-Vars.momentArm;
|
|
||||||
|
|
||||||
// LQR Force limiter X
|
|
||||||
if (Vars.LQRx > Vars.thrust)
|
|
||||||
Vars.LQRx = Vars.thrust;
|
|
||||||
else if (Vars.LQRx < -1 * Vars.thrust)
|
|
||||||
Vars.LQRx = -1 * Vars.thrust;
|
|
||||||
|
|
||||||
// LQR Force limiter Y
|
|
||||||
if (Vars.LQRy > Vars.thrust)
|
|
||||||
Vars.LQRy = Vars.thrust;
|
|
||||||
else if (Vars.LQRy < -1 * Vars.thrust)
|
|
||||||
Vars.LQRy = -1 * Vars.thrust;
|
|
||||||
}
|
|
||||||
|
|
||||||
void TVC(struct sVars &Vars, double g) {
|
|
||||||
if (Vars.thrust < 1) {
|
|
||||||
// Define forces and moments for t = 0
|
|
||||||
Vars.Fx = 0;
|
|
||||||
Vars.Fy = 0;
|
|
||||||
Vars.Fz = g * Vars.m0;
|
|
||||||
|
|
||||||
Vars.momentX = 0;
|
|
||||||
Vars.momentY = 0;
|
|
||||||
Vars.momentZ = 0;
|
|
||||||
}
|
|
||||||
|
|
||||||
else {
|
|
||||||
// Convert servo position to degrees for comparison to max allowable
|
|
||||||
Vars.xServoDegs = (180 / 3.1416) * asin(Vars.LQRx / Vars.thrust);
|
|
||||||
|
|
||||||
// Servo position limiter
|
|
||||||
if (Vars.xServoDegs > Vars.maxServo)
|
|
||||||
Vars.xServoDegs = Vars.maxServo;
|
|
||||||
else if (Vars.xServoDegs < -1 * Vars.maxServo)
|
|
||||||
Vars.xServoDegs = -1 * Vars.maxServo;
|
|
||||||
|
|
||||||
// Convert servo position to degrees for comparison to max allowable
|
|
||||||
Vars.yServoDegs = (180 / 3.1416) * asin(Vars.LQRy / Vars.thrust);
|
|
||||||
|
|
||||||
// Servo position limiter
|
|
||||||
if (Vars.yServoDegs > Vars.maxServo)
|
|
||||||
Vars.yServoDegs = Vars.maxServo;
|
|
||||||
else if (Vars.yServoDegs < -1 * Vars.maxServo)
|
|
||||||
Vars.yServoDegs = -1 * Vars.maxServo;
|
|
||||||
|
|
||||||
// Vector math to aqcuire thrust vector components
|
|
||||||
Vars.Fx = Vars.thrust * sin(Vars.xServoDegs * (3.1416 / 180));
|
|
||||||
Vars.Fy = Vars.thrust * sin(Vars.yServoDegs * (3.1416 / 180));
|
|
||||||
Vars.Fz = sqrt(pow(Vars.thrust, 2) - (pow(Vars.Fx, 2) + pow(Vars.Fy, 2))) +
|
|
||||||
(Vars.m * g);
|
|
||||||
|
|
||||||
// Calculate moment created by Fx and Fy
|
|
||||||
Vars.momentX = Vars.Fx * Vars.momentArm;
|
|
||||||
Vars.momentY = Vars.Fy * Vars.momentArm;
|
|
||||||
Vars.momentZ = 0;
|
|
||||||
}
|
|
||||||
}
|
|
||||||
|
|
||||||
void vehicleDynamics(struct sVars &Vars, int t) {
|
|
||||||
// Idot
|
|
||||||
if (t < 1) {
|
|
||||||
Vars.I11dot = 0;
|
|
||||||
Vars.I22dot = 0;
|
|
||||||
Vars.I33dot = 0;
|
|
||||||
} else {
|
|
||||||
Vars.I11dot = derivative(Vars.I11, Vars.I11prev, Vars.stepSize);
|
|
||||||
Vars.I22dot = derivative(Vars.I22, Vars.I22prev, Vars.stepSize);
|
|
||||||
Vars.I33dot = derivative(Vars.I33, Vars.I33prev, Vars.stepSize);
|
|
||||||
}
|
|
||||||
|
|
||||||
// pdot, qdot, rdot
|
|
||||||
Vars.yawddot = (Vars.momentX - Vars.I11dot * Vars.yawdot +
|
|
||||||
Vars.I22 * Vars.pitchdot * Vars.rolldot -
|
|
||||||
Vars.I33 * Vars.pitchdot * Vars.rolldot) /
|
|
||||||
Vars.I11;
|
|
||||||
Vars.pitchddot = (Vars.momentY - Vars.I22dot * Vars.pitchdot -
|
|
||||||
Vars.I11 * Vars.rolldot * Vars.yawdot +
|
|
||||||
Vars.I33 * Vars.rolldot * Vars.yawdot) /
|
|
||||||
Vars.I22;
|
|
||||||
Vars.rollddot = (Vars.momentZ - Vars.I33dot * Vars.rolldot +
|
|
||||||
Vars.I11 * Vars.pitchdot * Vars.yawdot -
|
|
||||||
Vars.I22 * Vars.pitchdot * Vars.yawdot) /
|
|
||||||
Vars.I33;
|
|
||||||
|
|
||||||
if (t < 1) {
|
|
||||||
Vars.x = 0;
|
|
||||||
Vars.y = 0;
|
|
||||||
|
|
||||||
Vars.ax = 0;
|
|
||||||
Vars.ay = 0;
|
|
||||||
Vars.az = Vars.Fz / Vars.m0;
|
|
||||||
}
|
|
||||||
|
|
||||||
else {
|
|
||||||
// p, q, r
|
|
||||||
Vars.yawdot = integral(Vars.yawddot, Vars.yawdotPrev, Vars.stepSize);
|
|
||||||
Vars.pitchdot = integral(Vars.pitchddot, Vars.pitchdotPrev, Vars.stepSize);
|
|
||||||
Vars.rolldot = integral(Vars.rollddot, Vars.rolldotPrev, Vars.stepSize);
|
|
||||||
|
|
||||||
// ax ay az
|
|
||||||
Vars.ax =
|
|
||||||
(Vars.Fx / Vars.m) + (Vars.pitchdot * Vars.vz - Vars.rolldot * Vars.vy);
|
|
||||||
Vars.ay =
|
|
||||||
(Vars.Fy / Vars.m) + (Vars.rolldot * Vars.vx - Vars.vz * Vars.yawdot);
|
|
||||||
Vars.az =
|
|
||||||
(Vars.Fz / Vars.m) + (Vars.vy * Vars.yawdot - Vars.pitchdot * Vars.vx);
|
|
||||||
|
|
||||||
// vx vy vz in Body frame
|
|
||||||
Vars.vx = integral(Vars.ax, Vars.vxPrev, Vars.stepSize);
|
|
||||||
Vars.vy = integral(Vars.ay, Vars.vyPrev, Vars.stepSize);
|
|
||||||
Vars.vz = integral(Vars.az, Vars.vzPrev, Vars.stepSize);
|
|
||||||
|
|
||||||
// Xe
|
|
||||||
Vars.x = integral(Vars.vx, Vars.xPrev, Vars.stepSize);
|
|
||||||
Vars.y = integral(Vars.vy, Vars.yPrev, Vars.stepSize);
|
|
||||||
Vars.z = integral(Vars.vz, Vars.zPrev, Vars.stepSize);
|
|
||||||
|
|
||||||
// Euler Angles
|
|
||||||
Vars.phidot = Vars.yawdot + (Vars.pitchdot * sin(Vars.yaw) +
|
|
||||||
Vars.rolldot * cos(Vars.yaw)) *
|
|
||||||
(sin(Vars.pitch) / cos(Vars.pitch));
|
|
||||||
Vars.thetadot =
|
|
||||||
Vars.pitchdot * cos(Vars.yaw) - Vars.rolldot * sin(Vars.pitch);
|
|
||||||
Vars.psidot =
|
|
||||||
(Vars.pitchdot * sin(Vars.yaw) + Vars.rolldot * cos(Vars.yaw)) /
|
|
||||||
cos(Vars.pitch);
|
|
||||||
|
|
||||||
Vars.yaw = integral(Vars.phidot, Vars.yawPrev, Vars.stepSize);
|
|
||||||
Vars.pitch = integral(Vars.thetadot, Vars.pitchPrev, Vars.stepSize);
|
|
||||||
Vars.roll = integral(Vars.psidot, Vars.rollPrev, Vars.stepSize);
|
|
||||||
}
|
|
||||||
|
|
||||||
// Set "prev" values for next timestep
|
|
||||||
Vars.I11prev = Vars.I11;
|
|
||||||
Vars.I22prev = Vars.I22;
|
|
||||||
Vars.I33prev = Vars.I33;
|
|
||||||
|
|
||||||
Vars.yawPrev = Vars.yaw;
|
|
||||||
Vars.pitchPrev = Vars.pitch;
|
|
||||||
Vars.rollPrev = Vars.roll;
|
|
||||||
|
|
||||||
Vars.yawdotPrev = Vars.yawdot;
|
|
||||||
Vars.pitchdotPrev = Vars.pitchdot;
|
|
||||||
Vars.rolldotPrev = Vars.rolldot;
|
|
||||||
|
|
||||||
Vars.yawddotPrev = Vars.yawddot;
|
|
||||||
Vars.pitchddotPrev = Vars.pitchddot;
|
|
||||||
Vars.rollddotPrev = Vars.rollddot;
|
|
||||||
|
|
||||||
Vars.axPrev = Vars.ax;
|
|
||||||
Vars.ayPrev = Vars.ay;
|
|
||||||
Vars.azPrev = Vars.az;
|
|
||||||
|
|
||||||
Vars.vxPrev = Vars.vx;
|
|
||||||
Vars.vyPrev = Vars.vy;
|
|
||||||
Vars.vzPrev = Vars.vz;
|
|
||||||
|
|
||||||
Vars.xPrev = Vars.x;
|
|
||||||
Vars.yPrev = Vars.y;
|
|
||||||
Vars.zPrev = Vars.z;
|
|
||||||
}
|
|
||||||
|
|
||||||
void write2CSV(struct sVars &Vars, std::fstream &outfile, int t) {
|
|
||||||
// writing to output file
|
|
||||||
outfile << t << ", ";
|
|
||||||
|
|
||||||
outfile << Vars.x << ", ";
|
|
||||||
outfile << Vars.y << ", ";
|
|
||||||
outfile << Vars.z << ", ";
|
|
||||||
|
|
||||||
outfile << Vars.vx << ", ";
|
|
||||||
outfile << Vars.vy << ", ";
|
|
||||||
outfile << Vars.vz << ", ";
|
|
||||||
|
|
||||||
outfile << Vars.ax << ", ";
|
|
||||||
outfile << Vars.ay << ", ";
|
|
||||||
outfile << Vars.az << ", ";
|
|
||||||
|
|
||||||
outfile << Vars.yaw * 180 / 3.1416 << ", ";
|
|
||||||
outfile << Vars.pitch * 180 / 3.1416 << ", ";
|
|
||||||
outfile << Vars.roll * 180 / 3.1416 << ", ";
|
|
||||||
|
|
||||||
outfile << Vars.yawdot * 180 / 3.1416 << ", ";
|
|
||||||
outfile << Vars.pitchdot * 180 / 3.1416 << ", ";
|
|
||||||
outfile << Vars.rolldot * 180 / 3.1416 << ", ";
|
|
||||||
|
|
||||||
outfile << Vars.yawddot * 180 / 3.1416 << ", ";
|
|
||||||
outfile << Vars.pitchddot * 180 / 3.1416 << ", ";
|
|
||||||
outfile << Vars.rollddot * 180 / 3.1416 << ", ";
|
|
||||||
|
|
||||||
outfile << Vars.I11 << ", ";
|
|
||||||
outfile << Vars.I22 << ", ";
|
|
||||||
outfile << Vars.I33 << ", ";
|
|
||||||
|
|
||||||
outfile << Vars.I11dot << ", ";
|
|
||||||
outfile << Vars.I22dot << ", ";
|
|
||||||
outfile << Vars.I33dot << ", ";
|
|
||||||
|
|
||||||
outfile << Vars.xServoDegs << ", ";
|
|
||||||
outfile << Vars.yServoDegs << ", ";
|
|
||||||
|
|
||||||
outfile << Vars.m << ", ";
|
|
||||||
outfile << Vars.thrust << ", ";
|
|
||||||
outfile << Vars.burnElapsed << ", ";
|
|
||||||
outfile << Vars.Fz << ", ";
|
|
||||||
|
|
||||||
outfile << Vars.LQRx << ", ";
|
|
||||||
outfile << Vars.LQRy << std::endl;
|
|
||||||
}
|
|
||||||
|
|
||||||
double derivative(double x2, double x1, double dt) {
|
|
||||||
double dxdt = (x2 - x1) / (dt / 1000);
|
|
||||||
return dxdt;
|
|
||||||
}
|
|
||||||
|
|
||||||
double integral(double x, double y, double dt) {
|
|
||||||
double integ = (x * dt / 1000) + y;
|
|
||||||
return integ;
|
|
||||||
}
|
|
||||||
Loading…
x
Reference in New Issue
Block a user