Pawel Rzucidlo, Grzegorz Henryk Kopecki, Klaus deGroot, Anna Kucaba-Pietal, Robert Smusz, Mariusz Szewczyk and Marek Szumski
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.
Abstract
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.
Details
Keywords
Albert Zajdel, Cezary Szczepański, Maciej Filipowicz, Mariusz Krawczyk and Michal Welcer
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…
Abstract
Purpose
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.
Design/methodology/approach
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.
Findings
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.
Originality/value
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.