✅作者简介热爱科研的Matlab仿真开发者擅长毕业设计辅导、数学建模、数据处理、程序设计科研仿真。完整代码获取 定制创新 论文复现点击Matlab科研工作室 关注我领取海量matlab电子书和数学建模资料个人信条做科研博学之、审问之、慎思之、明辨之、笃行之是为博学慎思明辨笃行。 内容介绍一、引言四旋翼飞行器因其结构简单、机动性强在航拍、物流、监测等领域得到广泛应用。深入理解其六自由度动力学特性并设计有效的 PID 控制系统对于实现四旋翼飞行器的稳定、精准飞行至关重要。通过动力学仿真我们能够模拟飞行器在各种情况下的运动状态为 PID 控制器的设计与优化提供依据。二、六自由度四旋翼动力学模型一基本假设与坐标系定义基本假设假设四旋翼飞行器为刚体忽略其弹性变形旋翼产生的升力和扭矩与旋翼转速呈线性关系不考虑空气压缩性等复杂空气动力学效应。⛳️ 运行结果 部分代码function dydt Motion_ABC(t, y, Omega_hover, I, m, g, l, k, b)% Get phi, theta, psi, p, q, and rphi y(7); theta y(8); psi y(9);p y(10); q y(11); r y(12);% Create omega for rotorsOmega Omega_hover * ones(4,1);% If statements to find Omegaif t 1Omega Omega_hover 70 * sin(2*pi*t/4);Omega ones(4,1) * Omega;elseif t 2Omega Omega_hover - 77 * sin(2*pi*t/4);Omega ones(4,1) * Omega;elseif t 3Omega(2) sqrt(Omega_hover^2 - 70^2 * sin(2*pi*(t-2)/4));Omega(4) sqrt(Omega_hover^2 70^2 * sin(2*pi*(t-2)/4));elseif t 4Omega(2) sqrt(Omega_hover^2 70^2 * sin(2*pi*(t-2)/4));Omega(4) sqrt(Omega_hover^2 - 70^2 * sin(2*pi*(t-2)/4));elseif t 5Omega(1) sqrt(Omega_hover^2 - 70^2 * sin(2*pi*(t-4)/4));Omega(3) sqrt(Omega_hover^2 70^2 * sin(2*pi*(t-4)/4));elseOmega(1) sqrt(Omega_hover^2 70^2 * sin(2*pi*(t-4)/4));Omega(3) sqrt(Omega_hover^2 - 70^2 * sin(2*pi*(t-4)/4));end% Get T and TauT k * sum(Omega.^2);L k * l * (-Omega(2)^2 Omega(4)^2);M k * l * (-Omega(1)^2 Omega(3)^2);N b * (Omega(1)^2 - Omega(2)^2 Omega(3)^2 - Omega(4)^2);Tau [L; M; N];% Rotation matrix (inertial to body)C_IB [ cos(theta)*cos(psi), cos(theta)*sin(psi), -sin(theta);sin(phi)*sin(theta)*cos(psi)-cos(phi)*sin(psi), sin(phi)*sin(theta)*sin(psi)cos(phi)*cos(psi), sin(phi)*cos(theta);cos(phi)*sin(theta)*cos(psi)sin(phi)*sin(psi), cos(phi)*sin(theta)*sin(psi)-sin(phi)*cos(psi), cos(phi)*cos(theta)];% Body to inertial rotationC_BI C_IB;Thrust C_BI(:,3);% Get r double dotr_dd [0;0;-g] (T/m) * Thrust;% Get w and Omega_dotw [p; q; r];Omega_dot I \ ( - cross(w, I*w) Tau);% Euler angle ratesA [1, sin(phi)*tan(theta), cos(phi)*tan(theta);0, cos(phi), -sin(phi);0, sin(phi)/cos(theta), cos(phi)/cos(theta)];Euler A \ w;if t 4Euler(1) 0;end% dydtdydt zeros(12,1);dydt(1:3) y(4:6);dydt(4:6) r_dd;dydt(7:9) Euler;dydt(10:12) Omega_dot;end 参考文献更多免费数学建模和仿真教程关注领取