Integrated wing design with adaptive control surfaces

This paper presents the development and testing of a novel fault tolerant adaptive control system based on a bio-inspired immunity-based mechanism applied to an aircraft fighter model. The proposed baseline control laws use a non-linear dynamic inversion and model reference adaptive control on the inner loops of the aircraft dynamics. In this new approach, the baseline controllers are augmented with an artificial immune system mechanism that relies on a direct compensation inspired primarily by the biological immune system response. The effectiveness of the approach is demonstrated through a full 6 degrees-of-freedom aircraft model interfaced with a Flight gear environment. The performance of the proposed control laws are investigated under a novel set of performance metrics, which quantify the level of input activity from the pilot and from the control surfaces in order to ensure the stability and performance of the aircraft under different actuator and structural failures. Optimization of the parameters of the artificial immunity system is performed using a genetic algorithm. The results show that the optimized fault tolerant adaptive control laws improve significantly the failure rejection using minimum pilot input and control surfaces activity under upset flight conditions.

Download Full-text

Aircraft control with the use of model reference adaptive control

Aircraft Engineering and Aerospace Technology ◽

10.1108/aeat-11-2020-0248 ◽

2021 ◽

Vol ahead-of-print (ahead-of-print) ◽

Author(s):

Grzegorz Henryk Kopecki

Keyword(s):

Adaptive Control ◽

Control Systems ◽

Model Reference Adaptive Control ◽

Unmanned Aircraft ◽

Neutral Position ◽

Aircraft Control ◽

Model Reference ◽

Content Type ◽

Model Reference Adaptive ◽

Control Surfaces

Purpose Indirect (fly-by-wire) control systems for general aviation aircraft and unmanned aircraft vehicles (UAV) control systems enable the decoupling of control surfaces. This method of aircraft control is different from classical approach. The purpose of the article is to show the aircraft can be controlled even if the control control surfaces are blocked. Design/methodology/approach The concept discussed here relies on model reference adaptive control. The approach presented requires modifications of aircraft linearized model. In this paper, an example of roll angle control is shown. Findings During simulations the system worked properly with control surfaces partially blocked, if the blockage appeared close to neutral position. Exemplary simulations are shown in the text. Practical implications The solution presented was implemented on a UAV autopilot. Hardware in the loop simulations were performed, which shows the potential of practical usage. Originality/value Aircraft control, as discussed in this paper, gives the possibility of aircraft control and stable flight before a fault is detected, which increases the safety level.

Download Full-text