Tomasz Rogalski

The new conception of the laboratory testing of the FBW control system for small aircraft

The paper presents conception and practical realization of laboratory testing of control system for small aircraft. The stand used in these tests is prepared in Matlab and Simulink environment. Usage of xPC and RTW modules enables the system to perform “Hardware in the loop” real time tests including tests with pilots. As a hardware PC computer equipped with specialized boards, including A/C, C/A, converters and RS232, LPT, CAN 2B data lines was used. The main task of presented stand is to make possible tests of control system introducing new conception of aircraft controlling (e.g. smart control and decoupled control techniques).

Flight Simulator as a Tool for Flight Control System Synthesis and Handling Qualities Research

At the Department of Avionics and Control Systems problems of aeronautical control systems have been dealt with for years. Several different kinds of aeronautical control systems have been designed, prototyped and tested. These control systems are intended for general aviation aircraft and unmanned aircraft. During all research projects computer simulations and laboratory tests were made. However, since in some cases such tests were insufficient, in-flight tests were conducted leading to a series of reliable results. The in-flight tests were made with the use of M-20 Mewa aircraft (autopilot for a GA aircraft) and PZL-110 Koliber aircraft (control system for UAV and indirect flight control system for a GA aircraft). Nevertheless, in-flight testing is very expensive and problematic. To avoid some problems appearing during in-flight tests and their preparation, a simulator – which is normally used for professional pilot training – can be used. The Aviation Training Center of the Rzeszów University of Technology possesses the ALSIM AL-200 MCC flight simulator. We have started preparing this simulator for the research. It is possible to control the simulated aircraft with the use of an external control system. The solution proposed enables testing the aircraft control algorithms, indirect control laws (e.g. control laws modifying handling qualities), as well as testing and assessment of the students’ pilotage skills. Moreover, the solution makes it possible to conduct tests connected with aircraft control, crew management, crew cooperation and flight safety. The simulator allows us to test dangerous situations, which – because of safety reasons – is impossible during in-flight testing. This paper presents modifications to the simulator’s hardware and additional software, which enable the described research.

The Selected Innovative Solutions in UAV Control Systems Technologies

The paper presents selected original solutions concerning UAV control systems technologies. The paper does not describe general theories and global technical solutions used in UAV’s technologies. It presents some tricks created and developed at Rzeszow University of Technology. Presented solutions have been developed and implemented into real control systems. They main goal is to improve control precision and increase system functionality. Results presented in this paper have been collected during real flight tests of different classes of UAVs.

A concept of voice guided general aviation aircraft

The paper presents a concept of an airborne control system assisting the pilot, which differs from classical approaches. This is the concept of voice commanded control system. The paper analyzes the feasibility of realization of aircraft control system with the speech recognition module for general aviation aircraft. Authors try to define the main rules, which must be observed to design and operate such systems. The main functionality levels of the presented control system are defined and discussed. The use of voice commands for the direct controlling of the flight of the plane is also presented and analyzed in details. The paper discusses several types of voice commands a pilot could use to control the plane. The main requirements voice commands must meet are defined and discussed. The last section contains the short description of the experimental control system which can be the base for developing an experimental voice controlled general aviation aircraft.

Control system for medium‐sized flying target

Abstract The research team from Control and Avionics Department of Rzeszow University of Technology (RUT) has been working on control systems for many types of flying objects for years. Experiences the team has had during their activity have helped create the control algorithms for a medium‐size flying target (MSFT). Researchers from RUT, together with the small aviation company EUROTECH, have been working on a flying target for artillery. This paper gives a generic view of the system, including airborne and on‐ground parts. But this paper mainly presents the control system that is mounted on the MSFT. The paper describes the generic conception of the control system of the flying target, including control laws used in the control system of the MSFT. Results of simulations and real flight data are also presented.

The training rate of aircraft handling quality evaluation scale

Purpose – The purpose of this paper is to present the sample result of researches under original conception of the aircraft handling qualities evaluation scale. It allows rating and comparing of different control algorithms implemented into the control system in the simple way.Design/methodology/approach – The presented handling qualities evaluation scale takes into consideration two main elements to generate the grade of the tested control law. These are: pilots workload during typical flight phases and the second is precision of control the pilot reaches controlling the plane.Findings – The paper presents possibilities of using of the proposed methodology. Also contributions of its use are described.Practical implications – The presented methodology can be applied to evaluate and compare handling qualities of different control algorithms supporting pilots.Originality/value – This paper presents original conception of handling qualities evaluation scale for aircraft equipped with fly‐by‐wire control system.

ARINC 653 Based Time-Critical Application for European SCARLETT Project

The SCAlable & ReconfigurabLe Electronics plaTforms and Tools project (SCARLETT) was started by European Commission to develop the concept of IMA 2G Avionics. The paper mentions the main objectives of the SCARLET project and presents a sample time-critical application developed for it. The time-critical application is an ARINC 653 based and is a part of a distributed control system working in AFDX network environment. Its task is to control an elevator’s actuator of a typical airliner. The paper presents the structure of the application, its timing schedule, and dedicated control algorithms and error detection mechanism built-in it. Selected application tests conclude the paper.

The possibilities of chosen applications of control and navigation systems in general aviation aircraft and unmanned air vehicles

Abstract The development of informatics and sensor techniques has extended the possibilities of flight parameter measurement. It allows for extensive modification of control and navigation systems in air vehicles. This advance can also be noticed in the research of the Department of Avionics and Control at the Faculty of Mechanical Engineering and Aeronautics, Rzeszow University of Technology. Research in the area of digital flight control systems was initiated at the Department of Avionics and Control over twenty years ago.

The cheap air data computer for aviation applications

Purpose – To present both the construction and sample applications of the small, low‐cost air data computer (ADC) with CAN interface, which has been designed at Avionics Department of Rzeszow Technical University.Design/methodology/approach – The ADC has been developed as a partial task during realization of few aviation projects. It uses cheap piesoresistive pressure sensors with digital temperature compensation to calculate following flight data: altitude, airspeed computed in two ways as instrumental airspeed and true airspeed, altitude rate, and atmosphere parameters: pressure, temperature and air density. This device is small and lightweight then it can be used on boards of both small aircraft and unmanned flying vehicles.Findings – This paper provides information about designed ADCs measurements accuracy. Also it informs about possibilities of the presented device uses.Practical implications – The lightweight low‐cost ADC can reduce both price and weight of complete control systems different types ...

Precision of Pilotage as a Function of Pilot Information Workload

The multidisciplinary development of aviation engineering has been observing for last years. New technologies in aviation control systems, airframes and engines have come together with modern theories describing and defining interaction between pilot and airplane Modern principles of minimal pilot’s workload define integral features of aircraft-human systems as a the most desirable in fact. They concern both classical planes and Unmanned Aerial Vehicles also. But unfortunately it doesn’t solve all problems of human’s workload during different flight and missions tasks. Many research team all over the World have wanted to satisfy pilots and operators expectations, with regard to information they require, and have started research how to provide all necessary information decreasing humans’s informational workload simultaneously. They have tried to solve this problem in two main ways so far. The first solution assumes research over methods of data relaying from avionic systems to pilots/operators including cockpit or ground station arrangement and instrument layout and their influence on human’s workload. The second solution focuses on definition, design and realization new specialized gauges. Some research centers have started research to explain how the form and amount of information providing to pilot/UAV operator impact on his activity and precision of flight tasks. There is the definition of so called “Critical Task” (CT) among results of those research. CT is defined as the task with maximal complexity level which still enables pilot to perform the task with desired precision in terms of some kind of environment e.g: cockpit arrangement, form and amount of provided information. The paper presents algorithms of preparation the Critical Task with the use CAISE method. Definitions of two basic terms for CAISE method: functions and entities are used to define and project a flight maneuver or a series of flight maneuvers recognized as CT. Sample CT created with the use of CAISE method are presented in this paper.