Design the Angle of Attack Autopilot design using MATLAB

Introduction—

MATLABSolutions demonstrate In this project we are going to design the Angle of Attack Autopilot design using MATLAB, we have to define the open loop state space model in workspace and create the close loop system using the LQR and pole placement technique with the objective of the maximum overshoot of 10% is permitted. The closed loop performance such as stability analysis, time response, gain and phase margins, controllability and observability analysis. Advanced control finds a significant application in the field of aircraft control. This particular project focuses on creating flight path feedback controllers for the Lockheed Martin F-16. The autopilot function of this aircraft is a crucial mode of relief for pilots as it enables the aircraft to maintain a steady flight path angle. The variable that requires control is the flight path angle, which is determined by the pitch angle (θ) and angle of attack (α), i.e., γ = θ − α. In this autopilot, the feedback controller has access to the state variables, and the elevator is the primary control surface used. Now we will create the script which will simulate the model and plot the results on figure and command window.

Autopilot Design

Using the state space data for the F16 which is obtained at 15000ft and 500ft/s, in the first part we have to define the state space data and create the state space model of it. The state space information for a control system is defined by this code. The matrices A, B, C, and D, which specify the system's states, inputs, outputs, and feedforward terms, respectively, serve as a representation of the system dynamics. The seven states of the system are represented by the letters h, theta, v, alpha, q, delta t, and delta e in the 'state name' option of the 'ss' command. These numbers correspond to an aircraft's height, pitch angle, velocity, angle of attack, pitch rate, throttle, and elevator deflection. The throttle and elevator deflection are represented in the input matrix B as the system's inputs. The system's outputs, which include the height, pitch angle, velocity, angle of attack, and pitch rate, are represented by the output matrix C. As there are no direct feedforward terms from the inputs to the outputs in this scenario, the feedforward matrix D is zero. The code for part (a) is shown in Video