Development of a 6 Degrees of Freedom (6DOF) Flight Dynamics Model for the Airbus A320

MATLAB-based rigid-body flight dynamics model capturing full translational and rotational aircraft motion

Overview

This project involved the development of a six degrees of freedom (6DOF) flight dynamics model for the Airbus A320 using MATLAB. The model captures the complete rigid-body motion of the aircraft, including all translational (surge, sway, heave) and rotational (roll, pitch, yaw) dynamics, enabling time-domain simulation of realistic aircraft trajectories.

The objective was to integrate aerodynamic modeling, rigid-body dynamics, and kinematics into a unified framework capable of simulating aircraft response under prescribed aerodynamic forces and moments.

Aircraft Geometry and Aerodynamic Data

Aircraft geometry and reference parameters were based on publicly available Airbus A320 data. Aerodynamic coefficients for lift, drag, and pitching moment were sourced from established databases and literature and implemented as functions of angle of attack.

Aircraft geometry reference and aerodynamic coefficient data used to model lift, drag, and pitching moment behavior.

Mathematical Model

The model solves the nonlinear 6DOF equations of motion for a rigid aircraft body:

  • Translational dynamics: Newton’s second law in body axes
  • Rotational dynamics: Euler’s equations for rigid-body rotation
  • Kinematics: body-to-inertial frame transformation using Euler angles

At each time step, aerodynamic forces and moments are computed from the current state and used to propagate the aircraft motion forward in time.

Simulation Results

The model outputs full state histories, including aircraft position, velocity components, and attitude angles.

Simulated three-dimensional aircraft trajectory generated by the 6DOF flight dynamics model.

Translational Motion

The translational velocity components demonstrate physically consistent behavior for forward flight.

Body-axis translational velocities showing surge, sway, and heave response over time.

Rotational Motion

Attitude angles evolve according to applied aerodynamic moments and rigid-body coupling.

Roll, pitch, and yaw angle histories generated from the rotational equations of motion.

Key Capabilities

  • Full nonlinear 6DOF rigid-body dynamics
  • Aerodynamic force and moment modeling
  • Body-to-inertial coordinate transformations
  • Time-domain trajectory simulation
  • Modular structure suitable for control integration

Limitations

  • Aerodynamic coefficients are quasi-static and do not include unsteady effects
  • No control surface deflections or propulsion modeling in the current version
  • Euler angle representation introduces singularities at high pitch angles

Future Work

Planned extensions to this project include:

  • Migration to Simulink using the Aerospace Blockset
  • Integration of control laws and autopilot architectures
  • Inclusion of propulsion and control surface dynamics
  • Real-time 3D visualization of aircraft motion
  • Linearization for stability and control analysis

Takeaways

This project demonstrates a complete implementation of aircraft rigid-body flight dynamics from first principles. It provides a strong foundation for flight simulation, guidance and control development, and autopilot testing, and is directly extensible to higher-fidelity simulation environments.

Tools and Techniques

  • MATLAB
  • Rigid-body dynamics
  • Aircraft flight dynamics
  • Numerical integration
  • Aerodynamic modeling