Temat: flight testing - Katalog OPAC zbiorów

Skocz do pozycji: 1.

Tytuł:: Aerodynamic model identification of turboprop aircraft based on flight test data
Autorzy:: Muhammad, H.
Hariowibowo, H.
Powiązania:: https://bibliotekanauki.pl/articles/245880.pdf
Data publikacji:: 2013
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: turboprop aircraft
flight testing
parameter identification
Opis:: The aerodynamic model of an aircraft can be considered as a mathematical representation of the forces and moments acting on the aircraft. These forces and moments are usually approximated by polynomials as function of aircraft’s state variables. The coefficients in the polynomials are known as the aerodynamic parameters. These aerodynamic parameters are of importance in the evaluation of aircraft performance and stability-control characteristics of an aircraft. These parameters also can be used in the design of, for example, automatic flight control systems and mathematical model of flight simulator. This paper will discuss the principles of the aerodynamic model identification of the aircraft based on flight test data using parameter identification techniques. The paper starts with discussion of a mathematical model of an aircraft. Next, parameter identification techniques will be described. Two techniques often used for estimation of the aerodynamic parameters will be discussed. Results of the modelling and estimation of the aerodynamic parameters, state trajectory of the aircraft, bias errors in the instrumentation system, and calibration factors of the vane-angle of attack from flight test data of the N-250 turboprop aircraft will be presented in this paper. Original achievement of that paper is the mathematical model of a turboprop aircraft.
Źródło:: Journal of KONES; 2013, 20, 3; 275-282
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 2.

Tytuł:: Preliminary study of an airplane for electric propulsion testing at high altitudes
Autorzy:: Galinski, C.
Powiązania:: https://bibliotekanauki.pl/articles/246733.pdf
Data publikacji:: 2018
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: electric propulsion
flight testing
unmanned aerial vehicle
Opis:: Technology of photovoltaic cells and lithium batteries is being developed rapidly. As a result, attempts to build solar High Altitude Long Endurance (HALE) airplanes are more and more frequent. In the future, such airplanes may appear very useful for the economy because they may replace geostationary satellites in several applications. Unfortunately, data on altitude effect on photovoltaic cells and batteries performance are not easily available. Moreover, acquisition cost of cells is very high. Therefore, a tool for inexpensive testing of cells is needed. This article shows a study of very light unmanned airplane that could be used as a testbed for this purpose. Weight assumptions are presented together with concept of geometry and aerodynamic characteristics. Propulsion system is proposed, so also airplane performance is estimated. Finally, results are discussed leading to the conclusion. It appears that unmanned airplane with maximum take-off weight of 1.3 kg can climb to the altitude of 10 km within 4 hours during sunny summer day about the noon. However, only 30% of such days can be used because of strong winds blowing at high altitudes, quite small optimal airspeed of the airplane and constraints due to Air Traffic Management. Moreover, application of variable pitch propeller is recommended as well as some kind of take-off assist. For example, towing or take-off from the hill is desirable to avoid threats resulting from small climb rate.
Źródło:: Journal of KONES; 2018, 25, 3; 167-174
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 3.

Tytuł:: Identification of modal models of helicopters using in-flight measurements
Autorzy:: Uhl, T.
Lisowski, W.
Powiązania:: https://bibliotekanauki.pl/articles/280639.pdf
Data publikacji:: 2001
Wydawca:: Polskie Towarzystwo Mechaniki Teoretycznej i Stosowanej
Tematy:: in-flight testing
modal analysis
helicopter structure modelling
Opis:: The paper presents a new methodology of modal model identification based on in-operation system response measurements. This methodology consists in estimation of cross- and auto-correlation of acceleration acquired at all measuring points. The method was applied to helicopter modal model identification basing on in-flight measurenent results. The obtained model parameters have been compared with the ground modal test results. This comparison permits evaluting of level of each mode excitation during the operation and can be applied to structure modification and diagnostics.
Identyfikacja modeli modalnych śmigłowców na podstawie wyników badań w locie. W pracy przedstawiono nową metodykę identyfikacji modeli modalnych na podstawie mierzonych w czasie eksploatacji sygnałów odpowiedzi na działające wymuszenia.Metodyka opiera się na estymacji punktowych i wzajemnych funkcji korelacji sygnałów przyspieszenia drgań mierzonych w zbiorze punktów pomiarowych. Jako przykład zastosowania opisanych algorytmów rozważono wyniki identyfikacji modelu modalnego śmigłowca zidentyfikowanego na podstawie pomiarów dokonanych w czasie lotu. Wyestymowane wartości parametrów modelu zostały porównane z odpowiadającymi im wartościami wyestymowanymi na podstawie wyników testu naziemnego. Porównanie to pozwoliło na oszacowanie stopnia, w jakim poszczególne postacie drgań są wymuszane w danych warunkach lotu. Osiągnięte wyniki identyfikacji modelu modalnego śmigłowca w warunkach lotu mogą znaleźć zastosowanie w analizie modyfikacji strukturalnych oraz diagnostyce śmigłowca.
Źródło:: Journal of Theoretical and Applied Mechanics; 2001, 39, 1; 105-128
1429-2955
Pojawia się w:: Journal of Theoretical and Applied Mechanics
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 4.

Tytuł:: Solid Rocket Boosters Separation System Development for the ILR-33 Amber 2K Rocket
Autorzy:: Kierski, Jan
Pazik, Arthur
Cieśliński, Dawid
Powiązania:: https://bibliotekanauki.pl/articles/36828091.pdf
Data publikacji:: 2023
Wydawca:: Sieć Badawcza Łukasiewicz - Instytut Lotnictwa
Tematy:: sounding rocket
solid rocket booster
ILR-33 AMBER 2K
modelling
flight dynamics
ground testing
Opis:: The paper presents the development process of the solid rocket boosters (SRBs) separation system of the ILR-33 AMBER 2K rocket. A redesign of the system was required due to the development of new, larger SRBs. The main system requirements were transmission of forces and moments between the SRBs and the main stage, execution of the separation process at a given moment in flight and mechanical integration simplification. A set of aerodynamics calculations were performed. With the use of computational fluid dynamics software, forces acting on the booster during separation for several angles of attack, as well as the critical booster deflection angle, have been determined. Next, a mathematical model was created to define the load spectrum acting on the system during the flight and separation phases, covering both static and dynamic loads. All the internal and external force sources were considered. A series of motion dynamics simulations were conducted for representative flight cases. Then, the system operational parameters were verified with the use of dedicated ground test facilities. Necessary calibrations of the mathematical model were then implemented, leading to a high level of confidence with the empirical data obtained, thereby leading to a successful system qualification for the flight campaign.
Źródło:: Transactions on Aerospace Research; 2023, 3 (272); 16-27
0509-6669
2545-2835
Pojawia się w:: Transactions on Aerospace Research
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 5.

Tytuł:: Impact of pilots’ tiredness on the outcome of psychological testing
Autorzy:: Socha, Vladimir
Hanakova, Lenka
Freigang, Michal
Kraus, Jakub
Stojic, Slobodan
Socha, Lubos
Hanak, Peter
Powiązania:: https://bibliotekanauki.pl/articles/375429.pdf
Data publikacji:: 2019
Wydawca:: Politechnika Śląska. Wydawnictwo Politechniki Śląskiej
Tematy:: human factors
fatigue
psychological testing
performance
pilot
flight symulator
wskaźniki ludzkie
zmęczenie
test psychologiczny
wydajność
symulator lotu
Opis:: Presented work is primarily oriented on the experimental verification of the influence of fatigue on the psychological condition of the flying personnel, using psychological and performance tests. For the evaluation of a pilot performance, the 24 hours experiment was conducted. In total, eight subjects participated in the experimental measurements. Eight participants went through several tests, including simulator flights, to investigate the effects of the fatigue on the results of psychological measurements. Measurements included workload evaluation, using NASA task load evaluation concept and performance testing, using the so-called OR-test. Significant statistical differences between measurements performed during 24 hours were not found in the case of NASA task load Scores. In the case of OR-test, Friedman ANOVA and subsequent post-hoc analysis show that the greatest decrease in performance was observed in approximately 22 hours of wakefulness, i.e. approximately in half of the measuring process. The concept of 24-hour measurements for the quantification of fatigue is not commonly used yet as well as objectivization using performance testing. As the apparent effect of fatigue is mainly on performance testing results, it can be argued that this work could serve as a basis for further studies on fatigue. Also, it could serve as a support for introducing new pilots' psychological testing procedures in the future, which could contribute to current efforts to improve aviation safety.
Źródło:: Transport Problems; 2019, 14, 2; 55-67
1896-0596
2300-861X
Pojawia się w:: Transport Problems
Dostawca treści:: Biblioteka Nauki

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