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1

Initial Analysis of Helicopter Impact on Hospital Helipads

Krzymień Wiesław, Cieślak Sławomir

Transactions on Aerospace Research

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2019

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Nr 3 (256)

14--23

EN

The need to quickly provide assistance to victims of accidents or seriously ill has created the need for the construction of helipads at selected hospitals. Their operation and the conditions of use are governed by regulation of the Ministry of Health on Hospital Emergency Ward (SOR) and rules required by the Civil Aviation Authority. The direct vicinity of the helipads causes impact of landing and departing helicopters on buildings, people and hospital equipment as well as the construction of the airfield. This article presents vibroacoustic impact of helicopters on helipads’ measurement methods and the results of the preliminary measurements to estimate the impact of Helicopter Air Rescue (LPR) on adjacent buildings and surroundings.

PL

Potrzeba szybkiego udzielania pomocy poszkodowanym w wypadkach lub ciężko chorym stworzyło potrzebę budowy lądowisk przy wybranych szpitalach - ich działanie i warunki eksploatacji reguluje Rozporządzenie MZ w sprawie szpitalnego oddziału ratunkowego (SOR) oraz przepisy wymagane przez Urząd Lotnictwa Cywilnego. Bezpośrednie sąsiedztwo lądowisk powoduje oddziaływanie lądujących i startujących śmigłowców na budynki oraz na ludzi i sprzęt szpitalny a także na konstrukcję lądowiska. W artykule przedstawiono czynniki oddziaływania wibroakustycznego śmigłowców na lądowiskach wyniesionych, metody pomiarowe oraz wyniki wstępnych pomiarów mające na celu oszacowanie wpływu śmigłowców Lotniczego Pogotowia Ratunkowego (LPR) na sąsiadujące budynki i otoczenie.

2

Theoretical and experimental investigation of a ground resonance phenomenon for the ILX-27 UAV helicopter

Kowaleczko G., Gorecki T.

Journal of KONES

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2017

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Vol. 24, No. 4

91--98

EN

Ground resonance is an unbalance of the helicopter main rotor rotation caused by its asymmetry. Whilst the helicopter is in contact with the ground this asymmetry generates a divergent and often destructive oscillations of the helicopter structure. These oscillations are self-excited. This paper present results of both theoretical and experimental investigations of this phenomenon. They were dedicated to the new polish UAV helicopter ILX-27. The theoretical analysis were done with commercial software ANSYS using Finite Element Method. The virtual model of the helicopter model accurately reproduced the geometry of all elements of the helicopter and was easy to modify to simulate various kinds of damages. Calculations were done for the following cases: C1 – the helicopter standing on the ground with zero thrust of the rotor, C2 = C1 + helicopter with additional support of the rotor mast, C3 = C2 + thrust of the rotor equal to the total mass of the helicopter, C4 = C2 + fixing the helicopter to the ground, C5 = C2 + helicopter with additional mass. At the beginning the modal analysis for all cases was done – natural frequencies and modes of the structure were identified. Next, for selected cases, harmonic analysis was performed – the structure of the helicopter was loaded with concentrated harmonic forces. Finally the dynamic analysis gave time courses of blades and the hub center motions in the case of structural damages. All phases of simulations were correlated with ground tests of the helicopter prototype. This allowed to compare results of theoretical investigations. These results also supported tests of the prototype.

3

Researches of the dynamic characteristics of the turbine jet engine in flight based on its ground tests

Golak K., Lindstedt P., Grądzki R.

Journal of KONES

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2016

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Vol. 23, No. 3

151--156

EN

Turbine jet engines maintenance (adjustment) actions are performed during standard ground tests, but they are used during the flight. It turns out that the characteristics of the engine determined during the ground tests from the input value "w" introduced by the engine control lever DSS are significantly different from those obtained from disturbance “z" operating in the engine during the aircraft flight. It is noticed, that improvement of the engine control state made by mechanic during aircraft ground tests may cause the deterioration of the engine performance, which is felt by the pilot. The article presents a method that allows determining the basic characteristics of the engine in flight based only on the signals measured during testing ground. This method is based on measurement the major engine signals n – engine rpm, p4 – turbine discharge total pressure, p2 – low pressure compressor inlet, mp – fuel usage, then the designation of synthetic signals y=n/p4 (which describes the engine output), u=mp/p2 (describes engine input) and further their own and cross correlation function. Next, the power spectral density functions of these synthetic signals were calculated. Power spectral density functions is a basis to determine the spectral transfer function HW(jω) (during the ground tests) and HZ(jω) (in flight) which are the basis to determine the characteristics (step response) of the turbine jet engine in flight and during ground tests.

4

Zagadnienia bezrozbiegowego startu wiatrakowca

Krzymień W.

Prace Instytutu Lotnictwa

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2015

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Nr 4 (241)

54--61

PL

Charakterystyczną cechą wiatrakowców, postrzeganą jako ich wadę, jest start z rozbiegiem - podobny do startu samolotu. W ramach realizowanego w Instytucie Lotnictwa Projektu POJG obejmującego zaprojektowanie i badania nowego typu wiatrakowca, wykonano także szereg analiz oraz pewne badania mające na celu zdobycie wiedzy w zakresie skrócenia rozbiegu przy starcie wiatrakowca. Jednym z elementów tego Projektu było zaprojektowanie i wykonanie wiatrakowca-demonstratora (nielotnego), na którym na ziemi wykonano wstępne badania podzespołów pod kątem możliwości bezpiecznego wykonania startu bezrozbiegowego. W artykule przedstawiono problemy związane z konstrukcją i badaniami przeprowadzonymi w celu realizacji bezrozbiegowego startu wiatrakowca (tzw. "jump takeoff").

EN

Gyroplanes have a specific quality similar to helicopters and airplanes - one of them is take-off typical for airplanes. The take-off without run, called "jump takeoff" of an ultra light gyroplane is already known. Within the framework of a project, which was realized in the Institute of Aviation in Warsaw, a new type of a gyroplane was designed and tested, some investigations and analyses were made about the take-off without run of the two-person gyroplane. For this purpose a special gyroplane for the ground tests was prepared with a new main rotor, construction of power system and stand for tests. In the paper are presented some problems with this kind of take-off: • requirements for take-off without run, • preparation of a demo of gyroplane for ground tests, • program of the tests and the requirements of civil air regulations.

5

Wytyczne do badań lotniskowych układu ABS

Tywoniuk A., Grygorcewicz P.

Logistyka

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2014

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nr 3

6486--6492

PL

Niezwykle istotne są badania lotniskowe, które wykonuje się w przypadku bardzo innowacyjnych konstrukcji lotniczych. Hamulce pojazdów mechanicznych ze względu na rolę, jaką spełniają podlegają restrykcyjnym badaniom. Badania te przeprowadzane są na poziomie wdrożenia nowej konstrukcji do użytkowania oraz w trakcie trwania eksploatacji. Szczególnie dokładne badania dotyczą hamulców o dużej energochłonności przeznaczonych do statków powietrznych, czasem do ciężkich samochodów mogących poruszać się ze znacznymi prędkościami. Hamulce lotnicze bada się według zasad oraz na urządzeniach niespotykanych dla innych rodzajów pojazdów. Jednocześnie niedopuszczalna jest sytuacja zmiany konstrukcji, bez uprzedniego przebadania hamulca. W artykule autorzy przedstawią wytyczne do badań hamulców lotniczych z ABS-em przeprowadzanych w warunkach terenowych na lotnisku.

EN

Ground tests of innovative aircraft structures are extremely important in order to prevent design errors. The vehicle brakes are subject to strict testing due to the their role. High energy brakes for aircraft as well as for heavy ground vehicles that could move at significant speeds are the subject for the strict test procedures. Aircraft brakes are tested for the compliance with aviation regulations using special designed test rigs. What is more brake design cannot be changed without verification tests. In this paper, the authors present guidelines for ground tests of aircraft brakes with antilock system.

6

Method of regulation condition assessment of turbine jet engine in flight basing on signals recorded during ground tests

Golak K.

Journal of KONES

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2012

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Vol. 19, No. 3

125-134

EN

During exploitation process operation quality differences may be observed between each particular machine and occurring in exploitation of one machine. These differences result from deviations of realized service process. Turbine jet engine regulation process was realized during ground tests. However, due to varying reactions of engines to external distortions, such as rocket launching, air swirl from another plane etc. as well as lack of possibility of simulation of in-flight conditions on ground (e.g. by partial choking of air intake), a situation may occur in which engine properly regulated on ground may not present sufficient efficiency in flight. Hence, the necessity to assess turbine jet engine regulation condition in flight basing on its ground tests. Research realized on computer models presenting engine operation both in flight and during ground tests indicated that real possibility of engine in flight regulation condition assessment based on its ground tests does exist. As was also noticed, with known input signal “w” and output signal “yW” recorded during engine ground tests as well as input “e” and output “u” signals from regulator during given test spectral powers and cross spectral powers of signals Swyw, Sww, See, Seu may be calculated and thus HW transfer function describing engine operation during ground test and GR transfer function describing regulator operation during given test and hence obtain transfer function HZ describing engine in flight. This grants possibility of regulation condition assessment of turbine jet engine in flight using signals recorded during ground tests.

7

Premises of Parametrical Assessment of Turbojet Engine in Flight Regulation Condition During Ground Test

Lindstedt P., Golak K.

Acta Mechanica et Automatica

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2012

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Vol. 6, no. 1

44-48

EN

The article presents the theoretical bases of method, engine technical condition is described by one (in other methods four are used) comprehensive model (binding engine input signals p2 and mp and engine output - n and p4 signals) with unique feature, that engine operation quality during ground tests will provide neccessary data on its performance in flight. The changes occurring in turbojet engine during its exploitation will be measure by comparision of standard model with parameters obtained from experiment (ground test).