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Active Sidestick Control Integration for Enhanced Aircraft Flight Envelope Protection

Çağrı Ege Altunkaya, Fatih Erol, Akın Çatak, Volkan Mert, Pierluigi Capone, Şükrü Akif Ertürk, Emre Koyuncu

TL;DR

This work tackles the integration of Active Sidestick Control (ACS) with Envelope Protection (EP) and Pilot-Induced Oscillation (PIO) prevention for high-performance aircraft. It develops an integrated framework combining Incremental Nonlinear Dynamic Inversion (INDI)–based angular-rate control with a two-way ACS interface inside a real-time, representative aircraft simulation modeled after an F-16, including a STIRLING Dynamics Compact Stick and a Low-Force ACS. EP for angular rates, AoA/load factor, and bank angle is implemented via restorative actions (S-I to S-IV) and tested in a real-time simulation environment, demonstrating that envelope violations can be prevented even under aggressive pilot commands. Preliminary results indicate the framework operates with real-time performance, two-way ACS communication, and tangible improvements in safety and controllability, while highlighting latency and integration challenges to address in further work.

Abstract

The design of Envelope and Pilot-Induced Oscillation (PIO) Protection Features, and Failure Cases detection and prevention using Active Control Sidestick (ACS) is a challenging task. While helping the pilot to respect the envelope limitations also in failure scenarios and, therefore, increasing mission effectiveness, these features may have a significant impact on the aircraft's agility. ACS characteristics are investigated in an integrated environment. A set of effective and flexible control laws based on Incremental Nonlinear Dynamic Inversion have been developed in a state-of-the-art aircraft simulation model and coupled with a two-ways communication with the selected ACS. The model can run in real-time in a fixed-based simulator composed of representative cockpit and out-of-the-window.

Active Sidestick Control Integration for Enhanced Aircraft Flight Envelope Protection

TL;DR

This work tackles the integration of Active Sidestick Control (ACS) with Envelope Protection (EP) and Pilot-Induced Oscillation (PIO) prevention for high-performance aircraft. It develops an integrated framework combining Incremental Nonlinear Dynamic Inversion (INDI)–based angular-rate control with a two-way ACS interface inside a real-time, representative aircraft simulation modeled after an F-16, including a STIRLING Dynamics Compact Stick and a Low-Force ACS. EP for angular rates, AoA/load factor, and bank angle is implemented via restorative actions (S-I to S-IV) and tested in a real-time simulation environment, demonstrating that envelope violations can be prevented even under aggressive pilot commands. Preliminary results indicate the framework operates with real-time performance, two-way ACS communication, and tangible improvements in safety and controllability, while highlighting latency and integration challenges to address in further work.

Abstract

The design of Envelope and Pilot-Induced Oscillation (PIO) Protection Features, and Failure Cases detection and prevention using Active Control Sidestick (ACS) is a challenging task. While helping the pilot to respect the envelope limitations also in failure scenarios and, therefore, increasing mission effectiveness, these features may have a significant impact on the aircraft's agility. ACS characteristics are investigated in an integrated environment. A set of effective and flexible control laws based on Incremental Nonlinear Dynamic Inversion have been developed in a state-of-the-art aircraft simulation model and coupled with a two-ways communication with the selected ACS. The model can run in real-time in a fixed-based simulator composed of representative cockpit and out-of-the-window.
Paper Structure (17 sections, 10 equations, 11 figures)

This paper contains 17 sections, 10 equations, 11 figures.

Table of Contents

  1. Introduction
  2. Problem Statement
  3. Integrated Active Sidestick Control System
  4. Aircraft Model
  5. Equations of Motion
  6. Aerodynamics
  7. Actuators
  8. Flight Control
  9. Active Sidestick Control
  10. Flight Envelope Protection
  11. Pitch, Roll, and Yaw Rate Protection
  12. Angle of Attack and Load Factor Protection
  13. Bank Angle Protection
  14. Simulation Setup and Results
  15. Aircraft Simulator Setup
  16. ...and 2 more sections

Figures (11)

  • Figure 1: Force Feel Characteristics Curve and Enable Flags
  • Figure 2: The ACS Parameter Identification
  • Figure 3: The angle of attack and load factor protection scheme: four main components, S-I/II/III/IV.
  • Figure 4: The bank angle protection scheme: four main components, S-I/II/III/IV.
  • Figure 5: F-16 3D CAD Model used in the Simulation Environment and Terrain Map Model in UNITY®
  • ...and 6 more figures