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This article describes experimental research results of the electropneumatic clutch control device for the mechanical transmission. The aim is to assess electropneumatic clutch control device characteristics to regulate both mechanical and robotic transmission. The feature of the clutch control system having the electropneumatic actuator on the basis of a power cylinder is the use of a control module that consists of an acceleration valve and two electropneumatic valves. A new structural relationship between the electropneumatic clutch control device elements on the basis of the new acceleration valve design is suggested. The assessment of mass and dimension parameters of well-known devices and this electropneumatic clutch control device is provided. A new approach to choose automated clutch control system parameters taking into account the relay electropneumatic control system operation features is suggested.

The article presents problems of fault detection and isolation in AHRS systems for the Fly-By-Wire control system for general aviation. The system is currently being designed at the Rzeszów University of Technology. The idea of the system is to create a general aviation pilot-friendly aircraft. The FBW control system is equipped with three AHRSs. Their diagnostics is realized on three levels. The article describes hardware redundancy and software redundancy for AHRS systems and then shows how to use it for diagnostics. The article focuses especially on estimation techniques applied in research. For simulations data from flight tests were used.

This paper presents tests of Electromechanical Actuators (EMA) designed in the Department of Avionics and Control at the Rzeszow University of Technology. Also, the architecture of the laboratory stand as well as testing methods and obtained results are described. Furthermore, the paper discusses the in-flight test results of the complete set of servos installed as a part of the experimental Fly-By-Wire (FBW) control system on board of the PZL-110 “Koliber” aircraft.

In this paper, a concept is presented for a fly-by-wire (FBW) control system for general aviation aircraft. Fly-by-wire implies that the cockpit controls are not mechanically linked to aerodynamic surfaces but are used only as the commands generator for the automatic flight control system. The objective of the proposed concept for the control system is to assist pilots with limited aviation training by: 1) automatic stabilization of the aircraft's attitude, altitude, airspeed, and heading and 2) decoupling of the flight controls. Decoupling of the flight controls implies that a single cockpit control can independently control a single flight parameter. An example of this would be moving the control yoke/stick fore and aft results in a change in pitch angle without changing air speed, thus simplifying the control of the aircraft. It is in simplification of control to assist pilots with limited training that the proposed concept is particularly useful in general aviation.