Pawel Rzucidlo

Safety enhanced digital flight control system

Purpose – The purpose of this paper is to describe the general idea, design, and implementation of control system for general aviation aircraft which reduces pilot workload.Design/methodology/approach – Proposed indirect flight control system framework is intended to simplify piloting, reduce pilot workload, and allow low‐end general aviation aircraft to operate under deteriorated meteorological conditions. Classical control theory is used for the design of the flight control laws. Although not inherently robust, controllers with classical control logic are made sufficiently stable using a correct and updated controller structure.Findings – Despite controversies between perception of a modern manned aerial vehicle and limitations imposed by legacy airworthiness codes it is shown that a pilot workload reducing system can be successfully implemented onboard of a low‐end general aviation aircraft.Research limitations/implications – Hi‐level control laws and optimization of handling qualities can lead to unfa...

Algorithms of Measurement System for a Micro UAV

The article presents a measurement system for a micro UAV designed at the Department of Avionics and Control Systems of Rzeszów University of Technology. Since the project is based on earlier projects, e.g.[[[[1[[[1, the introduction begins with their short presentation [they are mentioned in the introduction firs. Then, the current project is discussed. The major objective of the project is to create a miniature autopilot cooperating with navigation units, data transmission units and measurement units. The system is based on Polish technological solutions. The autopilot is designed as a single unit, however the system is open and it allows you to use different elements. The system development is also possible. In-flight testing will be realized with the use of two unmanned flying platforms equipped with an electrical engine and a piston engine. The total mass of the platforms is 5 kg and 25 kg respectively. The article presents the structure of the control and navigation system and then, the structure of the measurement system. The measurement units consist of a GPS receiver, an attitude and heading reference system (AHRS) and an air data computer (ADC). Similar configuration is used in other micro UAV solutions, such as Micropilot or Kestrel. Then, algorithms of the measurement system are described. Navigation is based on GPS data with a DGPS (Differential GPS) advanced module. If the measurement information is complete, GPS data are used to correct measurements from other units. The system estimates wind disturbances and calculates accelerometers errors. In the case of missing GPS signals implementation of low-cost sensors may lead to significant measurement errors, and hence navigation only by means of the INS is impossible. In such a case, navigation is realized with the use of an inertial navigation system (INS), the magnetic heading measurement and ADC. AHRS unit algorithms use quaternion algebra for attitude calculation. For correction, complementary filtering is implemented [, [. The correction signal for the attitude (pitch and roll angles) is calculated with the use of acceleration measurements. Measurements of accelerations and yaw rates are used for the correction switching mechanism, since in dynamic states signals calculated from accelerations cannot be used for correction. Heading is corrected by means of magnetic heading measurement. ADC algorithms are based on typical aerodynamic dependences.

Problems of Monitoring in the Fly-by-Wire System for Small Aircraft

The article presents problems of monitoring a Fly-by-Wire control system mounted on the board of experimental general aviation aircraft. The system is being designed at the Rzeszow University of Technology, Department of Avionics and Control. The idea of the system is to make a pilot-friendly small general aviation aircraft. First flight test results are very promising. The data transmission system is realized with the use of the CAN bus. Every system element has its own microprocessor and sends data to the bus. The data recording was made with the use of movable PC with specialized software. The monitoring system records all data at a hard disc and makes visualization. Parameters of the control system were observed and used by the system operator during flight tests. Two different transmission protocols were tested. The idea of the first protocol, called CANres, is to connect three different data from one module of FBW system equipment. The second tested protocol was CANaerospace. The idea of this protocol is to send one data in one frame. Problems of data acquisition in both protocols, as well as the description of practical problems concerned with software and transmission protocol that appeared during tests are presented in the article.

Integration of optical measurement methods with flight parameter measurement systems

During the AIM (advanced in-flight measurement techniques) and AIM2 projects, innovative modern techniques were developed. The purpose of the AIM project was to develop optical measurement techniques dedicated for flight tests. Such methods give information about aircraft elements deformation, thermal loads or pressure distribution, etc. In AIM2 the development of optical methods for flight testing was continued. In particular, this project aimed at the development of methods that could be easily applied in flight tests in an industrial setting. Another equally important task was to guarantee the synchronization of the classical measuring system with cameras. The PW-6U glider used in flight tests was provided by the Rzeszow University of Technology. The glider had all the equipment necessary for testing the IPCT (image pattern correlation technique) and IRT (infrared thermometry) methods. Additionally, equipment adequate for the measurement of typical flight parameters, registration and analysis has been developed. This article describes the designed system, as well as presenting the systems application during flight tests. Additionally, the results obtained in flight tests show certain limitations of the IRT method as applied.

Hil simulation of a light aircraft flight control system

This paper presents the hardware-in-the-loop simulations of a hybrid flight control system for a light aircraft consisting of mechanical, electromechanical and digital components. The simulation was performed at a light aircraft simulation lab SimStar at Brno University of Technology. The aim was the validation and verification of the operational suitability of the flight control systems peripherals - electromechanical actuators, autopilot mode selection panel and a primary flight display. The investigated peripheral devices were connected to SimStars network using CANaero communication protocol. The simulations were focused on the real time automatic flight control modes operational scenarios.

Monitoring and data acquisition system for experimental general aviation fly‐by‐wire aircraft

Abstract A CAN data bus was used in a project of an experimental Fly‐by‐Wire control system (SPS‐1) mounted on board a PZL‐110 “Koliber” general aviation aircraft. This solution allows the free communication between flight control computers and individual modules of the system. The monitoring of the bus state and data frames is useful during particular hardware tests, system integration, laboratory and in‐flight tests. This report intends to present the specific monitor tool developed with the to SPS‐1. The main part of the CAN monitoring system is software. It realizes acquisition, visualization and conversion of stored data. The monitoring software operates with devices used by an experimental control system and connected to the bus. Particular devices are assigned to separate windows. The operator can control the SPS‐1 system through specialized windows or by virtual cockpit. Apart from this, the CAN monitor controls and simulates selected modules of the SPS‐1 system and works as the bus diagnostics tool.

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.

Analysis of Interactions between Pilot-Operator and Advanced Flight Control System

This work discusses the application of techniques serving the purpose of prediction and detection of unfavorable man-machine interactions. Prediction criteria of Pilot Induced Oscillations (PIO) were applied during design process of experimental multi-modal fly-by-wire control system for small light aircraft. Estimated PIO susceptibility was further verified during real-time simulations and flight tests. The verification process included subjective pilot/operator expert opinions and the results obtained from the automatic detectors, used for the PIO identification in long sets of recorded data. The general idea of the detection algorithms is based on the Fast Fourier Transform (FFT). These are being presented in this paper in a form of detection applications along with the results of the flight experiments.

Electro‐mechanical actuators for general aviation fly‐by‐wire aircraft

Abstract A long‐term goal for general aviation aircraft is to reduce or eliminate the use of fluid power systems such as hydraulics from the aircraft. Power‐By‐Wire (PBW) technology seems to be the next major step in the development of aircraft control. In this solution, control power comes directly from the aircraft electrical system to the Electro‐Mechanical Actuator (EMA), which includes the electric motor, controller and gearbox. EMAs have the potential to be more efficient, less complicated, less expensive, and more faults tolerant than actuators based on hydraulic systems.

Data acquisition system for PW-6U in flight boundary layer mapping

Purpose This paper aims to describe an idea for an integration process and tests of flight parameters measurement system, which supports infrared thermography (IRT) boundary layer mapping. Design/methodology/approach The study of flow changes in the boundary layer with the use of IRT requires registration of the thermal images of the selected area of a wing or the fuselage, as well as synchronous recording of flight parameters. These tasks were realized by the supplementary measurement system mounted on the PW-6U glider. Two examples of the determination of the laminar-turbulent transition areas on the left wing of a PW-6U glider are also presented in the paper. Findings Optical methods can be used in several research areas, for example, aerodynamics and strength analysis. For instance, the measurement of the infrared radiation from surfaces with the use of IRT can be used for the measurement, with high accuracy, of surface temperature distribution. Moreover, the thermography is used for the analysis of the boundary layer. Performed in-flight experiments confirm the possibility of practical usage of the IRT method even on the board of a glider. Practical implications The use of optical methods will, in many cases, be less expensive than assembly of an additional measurement and data acquisition systems. Implementation of optical methods for industrial purposes has many advantages, and, hence, they will probably become very common in the future. Originality/value The study introduces advanced measurement and visualization techniques in general aviation.