Wyniki wyszukiwania - Biblioteka Nauki

1

Safety performance indicators assessment for small aircraft airframe systems

100%

Balicki W. , Głowacki P. , Loroch L.

Journal of KONES

|

2016

|

tom Vol. 23, No. 2

31--38

EN

Safety performance indicators are the parameters used for monitoring and assessing safety performance. Such factors are determined based on available safety databases, collected on government level (in Poland Civil Aviation Authority) or by aircraft operators. Aircraft system failure during different flight phases can cause an accident or an incident. Polish Civil Aviation Authority between other data bases manages two important ones called: European Coordination Centre for Aviation Incident Reporting Systems (ECCAIRS) and Aircraft Continuing Airworthiness Monitoring (ACAM).General Aviation (GA) operates mainly aircraft with MTOM<5700 kg powered by the single piston engine. At present, reliability of GA aircraft systems in Poland is unknown. Increasing size of this fleet in Poland requires taking necessary measures in order to establish safety risks and safety performance targets for GA fleet. The authors have performed processing of the data included in available databases analysing airframe failures based on criteria like: phases of flight, ATA chapters concerning aircraft systems and the category of occurrence. The goal of this article is to present method of the current reliability of GA aircraft systems assessment. The results of this analysis can support the decisions of supervisory authorities in the areas where security threats are most important also can help production organizations in identification of the aircraft systems, which required design changes.

2

The multi - objective optimization of the air transportation fleet structure

100%

Majka A.

|

tom Vol. 20, No. 4

261--268

EN

One of the most important factors in the development of modern civilization has become the increase in the significance of mobile and fast means of transportation of people and cargo. Aircraft as the fastest available means in the entire transportation system is the basis in places where the distance in the transportation of people is long and the travel time is short. The present work focuses on passenger transport in the European area using light transport aircraft, which may complement existing air transport and can become a real alternative to those who travel by other means of transport. The system of local transportation will become competitive in relation to other means of transport and will find its place on the market only when it has the highest indicators of efficiency. It can be reached by optimally obtaining passenger aircrafts fleet structure performing transportation tasks and optimizing its functioning. One of the basic problems is the rational selection and use of aircrafts, i.e. the minimization of their quantity while at the same time guarantee complete performance of transporting tasks. The selection of the best method of using the means of transport is connected with a large number of alternative variants, which makes it necessary to use special methods of searching for optimal solutions. The quality of the aircraft fleet should be estimated on the basis of several criteria when taking into account the difference in performing tasks. The way to design a competing aircraft fleet is to choose its characteristics by using advanced methods of multiple objective optimization. This work presents the methodology of the optimal designing of the aircraft fleet using the multitask character of the matter which is based on multiple objective mathematical programming in the concept of the set theory.

3

Wykorzystanie magistrali CAN w systemie pośredniego sterowania samolotem lekkim

75%

Pieniążek J. , Rzucidło P.

Szybkobieżne Pojazdy Gąsienicowe

|

2007

|

tom nr 2 (22)

91--98

PL

W artykule zaprezentowano rozwiązanie magistrali komunikacyjnych systemu SPS-1, które zostało zrealizowane jako projekt badawczy i przetestowane na samolocie PZL-110 „Koliber”. Struktura systemu sterowania samolotem bazuje na szybkiej magistrali CAN, którą zastosowano do komunikacji pomiędzy trzema komputerami sterującymi, urządzeniami pomiarowymi, jednostką sterującą pracą zespołu napędowego, sterownicą oraz pulpitem operatora. Dodatkowo zastosowano niezależną, zdwojoną wolną magistralę w podukładzie pozycjonowania płaszczyzn sterowych. W niniejszym opracowaniu przedstawiono również narzędzie do monitorowania magistrali CAN, które rozwijano równolegle z systemem pośredniego sterowania samolotem i wykorzystywano w kolejnych etapach prowadzonych nad nim prac. Głównym elementem systemu monitorującego jest oprogramowanie. Pozwala ono nie tylko na podgląd, rejestrację i wstępną obróbkę danych, lecz również umożliwia sterowanie poszczególnymi urządzeniami, symulację wybranych modułów sprzętowych oraz diagnostykę poszczególnych magistral.

EN

The solution of data transmission buses for purposes of SPS-1 indirect flight control system was presented in this work. SPS-1 was realized as research project and has been tested on the board of PZL-110 “Koliber” aircraft. The structure of control system bases on high-speed CAN bus, which has been applied for data transmission between three flight computers, measurement units, thrust control unit, side stick and operator console. Doubled low-speed CAN bus was applied for control surfaces actuation system additionally. The tool for monitoring of CAN buses has been also presented in this paper. CAN Monitor application was being developed simultaneously with indirect flight control system and utilized during particular levels of development. The main part of monitoring system is software. It allows for visualization, recording and preliminary data analysis as well as control of particular devices, simulation of selected devices and diagnostics of CAN buses.

4

Investigation of thermal interactions between elements of propulsion system and selected parts of the airplane skin in small aircrafts

51%

Łapka P. , Seredyński M. , Furmański P.

|

tom Vol. 39, no 3

45--61

EN

Development of new or upgrading of existing airplanes requires many different analyses, e.g., thermal, aerodynamical, structural, and safety. Similar studies were performed during re-design of two small aircrafts, which were equipped with new turboprop engines. In this paper thermo-fluid analyses of interactions of new propulsion systems with selected elements of airplane skin were carried out. Commercial software based numerical models were developed. Analyses of heat and fluid flow in the engine bay and nacelle of a single-engine airplane with a power unit in the front part of the fuselage were performed in the first stage. Subsequently, numerical simulations of thermal interactions between the hot exhaust gases, which leave the exhaust system close to the front landing gear, and the bottom part of the fuselage were investigated. Similar studies were carried out for the twin-engine airplane with power units mounted on the wings. In this case thermal interactions between the hot exhaust gases, which were flowing out below the wings, and the wing covers and flaps were studied. Simulations were carried out for different airplane configurations and operating conditions. The aim of these studies was to check if for the assumed airplane skin materials and the initially proposed airplane geometries, the cover destruction due to high temperature is likely. The results of the simulations were used to recommend some modifications of constructions of the considered airplanes.