Main Content


Guidance model for fixed-wing UAVs


A fixedwing object represents a reduced-order guidance model for an unmanned aerial vehicle (UAV). The model approximates the behavior of a closed-loop system consisting of an autopilot controller and a fixed-wing kinematic model for 3-D motion.

For multirotor UAVs, see multirotor.


model = fixedwing creates a fixed-wing motion model with double precision values for inputs, outputs, and configuration parameters of the guidance model.

model = fixedwing(DataType) specifies the data type precision (DataType property) for the inputs, outputs, and configurations parameters of the guidance model.


expand all

Name of the UAV, used to differentiate it from other models in the workspace, specified as a string scalar.

Example: "myUAV1"

Data Types: string

UAV controller configuration, specified as a structure of parameters. Specify these parameters to tune the internal control behavior of the UAV. Specify the proportional (P) and derivative (D) gains for the dynamic model and other UAV parameters. The structure for fixed-wing UAVs contains these fields with defaults listed:

  • 'PDRoll' - [3402.97 116.67]

  • 'PHeight' - 3.9

  • 'PFlightPathAngle' - 39

  • 'PAirspeed' - 0.39

  • 'FlightPathAngleLimits' - [-pi/2 pi/2] ([min max] angle in radians)

Example: struct('PDRoll',[3402.97,116.67],'PHeight',3.9,'PFlightPathAngle',39,'PAirSpeed',0.39,'FlightPathAngleLimits',[-pi/2 pi/2])

Data Types: struct

This property is read-only.

UAV guidance model type, specified as 'FixedWingGuidance'.

Input and output numeric data types, specified as either 'double' or 'single'. Choose the data type based on possible software or hardware limitations.

Object Functions

controlControl commands for UAV
derivativeTime derivative of UAV states
environmentEnvironmental inputs for UAV
stateUAV state vector


collapse all

This example shows how to use the fixedwing guidance model to simulate the change in state of a UAV due to a command input.

Create the fixed-wing guidance model.

model = fixedwing;

Set the air speed of the vehicle by modifying the structure from the state function.

s = state(model);
s(4) = 5; % 5 m/s

Specify a control command, u, that maintains the air speed and gives a roll angle of pi/12.

u = control(model);
u.RollAngle = pi/12;
u.AirSpeed = 5;

Create a default environment without wind.

e = environment(model);

Compute the time derivative of the state given the current state, control command, and environment.

sdot = derivative(model,s,u,e);

Simulate the UAV state using ode45 integration. The y field outputs the fixed-wing UAV states based on this simulation.

simOut = ode45(@(~,x)derivative(model,x,u,e), [0 50], s);
ans = 1×2

     8   904

Plot the change in roll angle based on the simulation output. The roll angle is the 7th row of the simOut.y output.


You can also plot the fixed-wing trajectory using plotTransforms. Create the translation and rotation vectors from the simulated state. Downsample (every 30th element) and transpose the simOut elements, and convert the Euler angles to quaternions. Specify the mesh as the fixedwing.stl file and the positive Z-direction as "down". The displayed view shows the UAV making a constant turn based on the constant roll angle.

downsample = 1:30:size(simOut.y,2);
translations = simOut.y(1:3,downsample)'; % xyz-position
rotations = eul2quat([simOut.y(5,downsample)',simOut.y(6,downsample)',simOut.y(7,downsample)']); % ZYX Euler
hold on
plot3(simOut.y(1,:),-simOut.y(2,:),simOut.y(3,:),'--b') % full path
xlim([-10.0 10.0])
ylim([-20.0 5.0])
zlim([-0.5 4.00])
view([-45 90])
hold off

More About

expand all


[1] Randal W. Beard and Timothy W. McLain. "Chapter 9." Small Unmanned Aircraft Theory and Practice, NJ: Princeton University Press, 2012.

Extended Capabilities

C/C++ Code Generation
Generate C and C++ code using MATLAB® Coder™.

Version History

Introduced in R2018b