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The paper presents the results of the final phase of the project, namely flight tests, aimed at developing a stabilisation system utilizing trim tabs for the PZL-130 Orlik turboprop military trainer aircraft.

The proposed flight stabilisation system was developed using modern techniques of model-based design, automatic code generation and software and hardware-in-the-loop testing. The project progressed to the flight testing stage, enabling the assessment of the control system’s quality and its final calibration.

Analysis of the results obtained during flight tests confirmed the high quality of the stabilisation system. Specifically, the anticipated accuracy of both longitudinal and lateral channel stabilisation was achieved.

The proposed flight stabilisation system, utilizing trim tabs, offers several advantages over classic automatic flight systems in terms of weight, energy consumption, structural simplicity and obviates the need for primary control modifications on the aircraft. It was developed using modern techniques of model-based design, automatic code generation and hardware-in-the-loop simulations.

A standard automatic flight control system – autopilot – will become required equipment of the future aircraft, operating in the common sky. For a specific group of aircraft, they are too expensive and too energy-consuming solutions. This paper aims to present the concept of an automatic flight control system that overcomes those limitations.

The proposed automatic flight control system uses the trim tabs in all prime flight controlling surfaces: elevator, ailerons and rudder, for stabilizing and controlling the steady flights of an aircraft.

The results of an aeroplane flight controlled with the use of trim tabs simulation tests and remarks have been presented and discussed. The simulation was conducted in real-time hardware in the loop environment. The stabilization of the flight was achieved in performed test scenarios.

The possibility to control an aircraft with coordinated deflections of the trimming surfaces is a beneficial alternate to those currently used and can be recommended for use in the next-generation aircraft.

This paper aims to present a concept of an automatic directional control system of remotely piloted aerial system (RPAS) during the taxiing phase. In particular, it shows the initial stages of the control laws synthesis – mathematical model and simulation of taxiing aircraft. Several reasons have emerged in recent years that make the automation of taxiing an important design challenge including decreased safety, performance and pilot workload.

The adapted methodology follows the model-based design approach in which the control system and the aircraft are mathematically modelled to allow control laws synthesis. The computer simulations are carried out to analyse the model behaviour.

Chosen methodology and modelling technique, especially tire-ground contact model, resulted in a taxing aircraft model that can be used for directional control law synthesis. Aerodynamic forces and moments were identified in the wind tunnel tests for the full range of the slip angle. Simulations allowed to compute the critical speeds for different taxiway conditions in a 90° turn.

The results can be used for the taxi directional control law synthesis and simulation of the control system. The computed critical speeds can be treated as safety limits.

The taxi directional control system has not been introduced to the RPAS yet. Therefore, the model of taxiing aircraft including aerodynamic characteristics for the full range of the slip angle has a big value in the process of design and implementation of the future auto taxi systems. Moreover, computed speed safety limits can be used by designers and standard creators.

This paper aims to present a concept of an automatic directional control system of remotely piloted aerial system (RPAS) during the taxiing phase. In particular, it shows the initial stages of the control laws synthesis-mathematical model and simulation of taxiing aircraft. Several reasons have emerged in recent years that make the automation of taxiing an important design challenge including decreased safety, performance and pilot workload.

The adapted methodology follows the model-based design approach in which the control system and the aircraft are mathematically modelled to allow control laws synthesis. The computer simulations are carried out to analyse the model behaviour.

Chosen methodology and modelling technique, especially tire-ground contact model, resulted in a taxiing aircraft model that can be used for directional control law synthesis. Aerodynamic forces and moments were identified in the wind tunnel tests for the full range of the slip angle. Simulations allowed to compute the critical speeds for different taxiway conditions in a 90° turn.

The results can be used for the taxi directional control law synthesis and simulation of the control system. The computed critical speeds can be treated as a safety limits.

The taxi directional control system has not been introduced to the RPAS yet. Therefore, the model of taxiing aircraft including aerodynamic characteristics for the full range of the slip angle has a big value in the process of design and implementation of the future auto taxi systems. Moreover, computed speed safety limits can be used by designers and standards creators.