Temat: landing gear - Katalog OPAC zbiorów

Skocz do pozycji: 1.

Tytuł:: Numerical testing of landing gear system for different drop velocities
Autorzy:: Krasoń, W.
Małachowski, J.
Powiązania:: https://bibliotekanauki.pl/articles/245668.pdf
Data publikacji:: 2009
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: landing gear
numerical simulation
drop velocities
touchdown
Opis:: The FEM model of the landing gear was developed to determine efforts of individual structural members while simulating the landing-gear drop, and to investigate how the energy of such a system changes; also, to find what kinds of deformations occur in individual components, and to investigate into the effectiveness of the damping system. In the developed numerical model of the landing gear account was taken also of the support-wheel-related subassembly, which includes such elements as: the wheel pin, the wheel rim, and the tyre. All parts of this subassembly, belt in the tyre excluded, were represented with the flexible hexagonal elements. results of numerical analyses for some selected drop tests and results from experiments carried out on a real landing gear confirm high quality of results gained from the dynamic simulation in the model of a complete landing-gear configuration. The advantage of the presented numerical method is applicability there of to landing gear testing for the very wide range of drop velocities, what is impossible to be performed with other methods, including experimental testing work. Paper show the geometric model of the main landing gear, a discrete model with the shock-absorber model included, the fringe of the landing gear deformation at the flnal stage of touchdown phase respectively from experimental and numerical tests and the maps ofmaximum principal stresses and how they change within the area of the welded joint that connects the upper and lower levers of the main landing gear.
Źródło:: Journal of KONES; 2009, 16, 4; 241-246
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 2.

Tytuł:: Some selected examples of fem modelling of structure-affecting material and manufacturing faults
Autorzy:: Jachimowicz, J.
Małachowski, J.
Krasoń, W.
Kajka, R.
Powiązania:: https://bibliotekanauki.pl/articles/243333.pdf
Data publikacji:: 2008
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: FEM modelling
combustion engine
landing gear
imperfection
Opis:: In design practice, in most of cases, stresses and deformations of structures with nominal dimensions and average material properties were analyzed. It have been concluded that such procedure is most often sufficient. However, there are design solutions, especially in high-effort structures for example aircraft and turbine engines, where scatter of geometrical dimensions consistent with assumed tolerances cause significant scatter of stresses and strains, differ from values coming from nominal dimensions. Scatter of these values have essential influence on service life of presented structures. Example of such effect is described in the paper. There were used FEM analyses to determination of scatter of stresses and stres s concentration coefficient in herringbone lock joint of K-15 engine's turbine. Another example of fault impact on stresses in structure is analysis of undercarriage element with material fault. Both these examples indicate on great sensitivity of stress distribution on manufacturing imperfections. The impact of these faults and imperfections reaches hundreds of per cent, and in some cases could be serious menace of operating safety. In structures with the multiple 3D stress state, non-linear geometric and material phenomena, with contact between friction-affected elements, any geometric imperfections can cause considerable local changes in the stress and strain.
Źródło:: Journal of KONES; 2008, 15, 1; 97-107
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 3.

Tytuł:: Analysis of electric - drive applicability in mechanical brake for the commuter class airplane
Autorzy:: Grygorcewicz, P.
Powiązania:: https://bibliotekanauki.pl/articles/246340.pdf
Data publikacji:: 2013
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: transport
airplanes
brakes
landing gear
construction process
Opis:: This article presents selected issues related to the design methodology of the electric brakes during the construction process as well as other factors which are important in the design process. It is a very important issue due to affect on the airplane and automotive brake design. Nowadays when new solution of brakes is being designed there is a need to take into account various factors influencing the design such as: weight, compatibility and flexibility of use in various aircraft, reliability and durability, ease of installation and maintenance, low-cost operation and low cost components, braking efficiency, short braking distance. All of these factors are taken into account when designing a prototype of the electric brake as well as economical factor of the design. It is also necessary to verify the design during its creation using experimental and laboratory test data from other similar designs. The aim of the paper is to discuss design process from the very beginning (i.e. by comparing features of the electric brakes with other types of brakes in order to show advantages and disadvantages of chosen solution) to the creation of a working demonstrator in future. Author of the paper in his electric brake design bases on the experience of the Warsaw’s Institute of Aviation Landing Gear Department.
Źródło:: Journal of KONES; 2013, 20, 2; 143-148
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 4.

Tytuł:: Designing process of landing gear in 3D CAD program
Autorzy:: Grygorcewicz, P.
Powiązania:: https://bibliotekanauki.pl/articles/244762.pdf
Data publikacji:: 2016
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: transport
airplanes
designing
main landing gear
CAD
Opis:: This article presents selected issues related to the design methodology of the landing gear during the construction process. The 3D modelling of the landing gear nowadays is very popular method, which simplifies the process and reduces the costs of the prototype. The author used the designing program Solid Edge ST 7. The concepts and phases of designing will be shown in this elaboration. Readers can see the problems resolved by designers and this is showing the scale of designing challenges. The landing gear consist of many parts and every of this parts needs to be design to meet the requirements of construction. Only experienced designers can effort to design landing gear because they have to acquire specific knowledge. The aim of the paper is to discuss design process from the very beginning first steps to the final version of the landing gear. All of different factors like weight, durability, resistance of the weather are taken into account when designing a prototype of the landing gear as well as economical factor of the design. It is also necessary to verify the design during its creation using experimental and laboratory test data from other similar designs. The article also subscribes some methods, which help designer to find the proper solution. The presented landing gear was designed by Landing Gear Laboratory team Institute of Aviation.
Źródło:: Journal of KONES; 2016, 23, 3; 165-170
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 5.

Tytuł:: The analysis of chosen technological parameters in the process of manufacturing components of landing gear of structural post aircraft
Autorzy:: Boś, P.
Hakim, M.
Budzik, G.
Rybak, M.
Powiązania:: https://bibliotekanauki.pl/articles/950100.pdf
Data publikacji:: 2013
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: transport
aviation
landing gear
measuring method
engineering
Opis:: High quality of components used in constructions of Landing Gears forces the manufacturers to choose appropriate technologies in order to manufacture and control dimensions of particular details. It is especially difficult to predict how the elements of huge dimensions will act during heat treat and chemical processing. The changes in size and. shape of the elements of suspension of STRUCTURAL POST aircraft are connected with hardening stresses. This requires accurate determining of allowance of final machining. The analysis of processing parameters and manufacturing of a precise component is possible with the use of high-tech coordinate measuring techniques based on touch and untouched measurements . The highest quality of machines used in manufacturing and measuring as well as innovative technologies used during the process of manufacturing STRUCTURAL POST components result in effects assumed by the designing engineer. The aim of this article is to present issues connected with technological process of manufacturing STRUCTURAL POST components as well as the analysis of particular parameters of manufacturing process which have an impact on the accuracy of dimensions and shape of the final product. These parameters are also responsible for functionality, operational reliability and safety of the Landing Gear.
Źródło:: Journal of KONES; 2013, 20, 1; 23-28
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 6.

Tytuł:: Crack Growth Analysis of the Landing Gear Pull Rod of the Fighter Jet Aircraft
Autorzy:: Kurdelski, M.
Leski, A.
Powiązania:: https://bibliotekanauki.pl/articles/97773.pdf
Data publikacji:: 2011
Wydawca:: Sieć Badawcza Łukasiewicz - Instytut Lotnictwa
Tematy:: crack growth
fatigue
flight tests
landing gear
Opis:: This paper describes the problem of searching for the causes of damage in the form of rupture of a strength member of the main landing gear. There have been two incidents noted which both occurred during hangar storage. It should be pointed out that the two occurrences mentioned concern a particular aircraft currently in operation, and that these incidents occurred a few days after the last flight. This article presents part of the investigation process needed to determine the causes of cracks in the test item. The crack growth analysis of the pull rod was performed using the NASGRO software. In order to perform the calculations, the information was gathered during previously conducted material studies and flight tests.
Źródło:: Fatigue of Aircraft Structures; 2011, 3; 64-73
2081-7738
2300-7591
Pojawia się w:: Fatigue of Aircraft Structures
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 7.

Tytuł:: State of the art in landing gear shock absorbers
Amortyzatory podwozi lotniczych
Autorzy:: Wolejsza, Z.
Kowalski, W.
Lafitte, A.
Mikulowski, G.
Remmers, L
Powiązania:: https://bibliotekanauki.pl/articles/213657.pdf
Data publikacji:: 2005
Wydawca:: Sieć Badawcza Łukasiewicz - Instytut Lotnictwa
Tematy:: state of art in landing gear shock absorbers
Opis:: This report describes the state of the art inlanding gear design with a particular focus on shock absorbes. It gives an overview on the general design solutions and installation of landing gears into the airframe. An emphasis is placed on the function and calculation of loads acting on oleopneumatic shock absorbers, which are the main type of shock absorber considered within ADLAND. One part of this dokument covers the requirements which are the basis of the shock absorber design, materials used and related future developments within aerospace industry. A brief summary is given on research performed on active shock absorber so far.
Opracowanie przedstawia zagadnienia związane z konstrukcjami podwozi lotniczych, ze szczególnym uwzględnieniem problematyki amortyzatorów cieczowo-gazowych. Podano ogólne wskazówki dotyczące rozwiązań konstrukcyjnych różnych rodzajów amortyzatorów i ich adaptacji do pozostałej struktury samolotu. Szczególny nacisk położono na analizę obciążeń generowanych w amortyzatorach cieczowo-gazowych, które aktualnie są przedmiotem szczegółowych badań w ramach programu UE ADLAND. W opracowaniu opisano także wymagania stawiane obecnie nowo projektowanym konstrukcjom amortyzatorów lotniczych, a także wymieniono materiały z których są one wykonane. Przedstawiono zakres dotychczas zrealizowanych badań w obszarze podwozi adaptacyjnych oraz kierunki dalszego rozwoju i zastosowań amortyzatorów w lotnictwie.
Źródło:: Prace Instytutu Lotnictwa; 2005, 2(181); 1-54
0509-6669
2300-5408
Pojawia się w:: Prace Instytutu Lotnictwa
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 8.

Tytuł:: Adaptive landing gear control system assumptions
Autorzy:: Skorupka, Z.
Powiązania:: https://bibliotekanauki.pl/articles/247705.pdf
Data publikacji:: 2018
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: laboratory testing
landing gear
adaptive control
control system
Opis:: In the present time, landing energy dissipation process in aviation shock absorber design is optimized for the most demanding, but still safe, landing scenario (reserve energy landing conditions). Most of the current solutions are based on a fixed hole (orifice) or a set of holes regulating hydraulic fluid flow in the shock absorber. This approach although safe provides no optimization of the forces acting on the fuselage in different (less energetic than limit energy) conditions. Due to the progress in hydraulic flow control, it is possible to design and control a proper system for extended optimization of the landing process energy dissipation. The complete system contains two parts, one of which is a direct flow executive electro-mechanical system and second of which is an electronic control system. The electronic control system directly manages executive system via a set of inputs, thus creating proper output signals for the optimal flow control. In this article, the author presents the idea of the computer control part of the adaptive hydraulic flow control system. The author describes a set of possible control input and output signals both external and internal, from the landing gear reference system, characterizing their role in the landing process. The author also defines possible control algorithms selected to fit the assumptions of the adaptive landing gear system. Finally, the author presents a proposal for the laboratory grade control system for future testing of the assumptions described in this article.
Źródło:: Journal of KONES; 2018, 25, 2; 329-333
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 9.

Tytuł:: A simulation model for computing the loads generated at landing site during helicopter take-off or landing operation
Symulacyjny model do wyznaczania obciążeń powierzchni lądowiska w trakcie startu lub lądowania śmigłowca
Autorzy:: Stanisławski, Jarosław
Powiązania:: https://bibliotekanauki.pl/articles/36401017.pdf
Data publikacji:: 2019
Wydawca:: Sieć Badawcza Łukasiewicz - Instytut Lotnictwa
Tematy:: helicopter
landing site
landing gear loads
śmigłowiec
lądowisko
obciążenia podwozia
Opis:: The paper presents simulation method and results of calculations determining behavior of helicopter and landing site loads which are generated during phase of the helicopter take-off and landing. For helicopter with whirling rotor standing on ground or touching it, the loads of landing gear depend on the parameters of helicopter movement, occurrence of wind gusts and control of pitch angle of the rotor blades . The considered model of helicopter consists of the fuselage and main transmission treated as rigid bodies connected with elastic elements. The fuselage is supported by landing gear modeled by units of spring and damping elements. The rotor blades are modeled as elastic axes with sets of lumped masses of blade segments distributed along them. The Runge-Kutta method was used to solve the equations of motion of the helicopter model. According to the Galerkin method, it was assumed that the parameters of the elastic blade motion can be treated as a combination of its bending and torsion eigen modes. For calculations, data of a hypothetical light helicopter were applied. Simulation results were presented for the cases of landing helicopter touching ground with different vertical speed and for phase of take-off including influence of rotor speed changes, wind gust and control of blade pitch. The simulation method may help to define the limits of helicopter safe operation on the landing surfaces.
W pracy przedstawiono metodę symulacyjną wyznaczania obciążeń lądowiska generowanych przez podwozie śmigłowca w fazie startu lub lądowania. Przy wirującym wirniku wielkość obciążenia podwozia śmigłowca może zmieniać się w zależności od parametrów ruchu śmigłowca w momencie zetknięcia podwozia z podłożem, sterowaniem kątem nastawienia łopat, wystąpieniem podmuchów. Rozważany model fizyczny śmigłowca składa się z kadłuba i przekładni głównej traktowanych jako ciała sztywne połączone elementami sprężystymi. Kadłub podparty jest na podwoziu modelowanym przez układ elementów sprężystych i tłumiących. Łopaty wirnika nośnego zastąpiono osiami elastycznymi z rozmieszczonymi wzdłuż nich masami skupionymi segmentów łopat. Do rozwiązania równań ruchu modelu śmigłowca zastosowano metodę Runge-Kutta. Zgodnie z metodą Galerkina przyjęto, że parametry ruchu odkształcalnych łopat można traktować jako złożenie uwzględnianych giętnych i skrętnych postaci własnych. Do obliczeń symulacyjnych wykorzystano dane hypotetycznego śmigłowca lekkiego. Przedstawiono symulacyjne wyniki dotyczące zachowania się śmigłowca w trakcie zetknięcia się z podłożem oraz dotyczące zmian obciążeń wirnika i podwozia przy wystąpieniu podmuchów lub wprowadzeniu sterowaniu skokiem łopat wirnika nośnego. Metoda symulacyjna może być przydatna przy określeniu granic bezpiecznej eksploatacji śmigłowca.
Źródło:: Transactions on Aerospace Research; 2019, 2 (255); 65-81
0509-6669
2545-2835
Pojawia się w:: Transactions on Aerospace Research
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 10.

Tytuł:: Strain gauge pin based force measurement
Autorzy:: Skorupka, Z.
Sobieszek, A.
Powiązania:: https://bibliotekanauki.pl/articles/247743.pdf
Data publikacji:: 2018
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: strain gauges
landing gear
test stand
measuring system
Opis:: In this article authors present force measurement method based on strain gauge measuring system installed inside pin, which is a part of light helicopter Main Landing Gear Shock Absorber. Strain gauges in full bridge configuration were installed inside the mounting pin (upper one – fuselage side). Placement and type of strain gauges were selected during the preliminary tests, which verified the validity and conditions of the force measurement. Preliminary tests allowed verification and selection of an optimal measurement system by testing two types of them. The impact on force according to the angle of force vector direction was also verified. Preliminary tests of the strain gauges equipped pin were performed using quasistatic tests stand – 40 T hydraulic press for applying force acting on shock absorber and pin. Whole measuring system is planned to be used in real time analysis of shock absorber force acting on fuselage mounting node. The strain gauges allows measurement of force in any place of the structure, the article presents the advantages of the system located inside pin. Additionally, the installation technologies of strain gauges in hard-to-reach places are presented. The article is summed up with an analysis of the problems, which arise during the installation and measurement process using strain gauges installed in such a specific place.
Źródło:: Journal of KONES; 2018, 25, 2; 335-340
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 11.

Tytuł:: A design and numerical optimization of a landing gear for 1400 kg (AT-6) take-off mass aircraft
Autorzy:: Tywoniuk, A.
Jakubowski, R.
Powiązania:: https://bibliotekanauki.pl/articles/243599.pdf
Data publikacji:: 2016
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: landing gear
aircraft
design
finite element method
undercarriage
Opis:: One of the most important systems responsible for safe take-off and landing of aircraft is a landing gear system. Regardless of the configuration and the type of landing gear, its main function is to absorb energy from landing. The aim of this paper is to describe design and numerical optimization of modern tricycle-type, retractable landing gear system equipped with oleo-pneumatic amortization and mechanical emergency release. The landing gear was designed for a new prototype of 4 seats 1400 kg (AT-6) take-off mass aircraft in accordance with Certification Specifications for Normal, Utility, Aerobatic and Commuter Category Aeroplanes – CS-23. A complete design process from concept to final version was performed in Warsaw Institute of Aviation’s Landing Gear Laboratory. Proposed retractable landing gear concept substantially reduces aerodynamic drag of aircraft. Although application of one retraction system for the left and right gear make the system more complicated, this solution significantly reduces weight. The authors, because of the project complexity, focused on most important aspects of the main landing gear design and described numerical optimization of chosen components like composite leg with main and upper aluminium fittings. Engineers involved in the project used SolidEdge software for 3D modelling, kinematics optimization and 2D documentation preparation. Strength and stiffness analysis was carried out using hand and numerical calculation methods – FEMAP with NX Nastran and Hyperworks software.
Źródło:: Journal of KONES; 2016, 23, 3; 541-547
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 12.

Tytuł:: An energy absorption dynamic test of landing gear for 1400 kg general aviation aircraft
Autorzy:: Jakubowski, R.
Tywoniuk, A.
Powiązania:: https://bibliotekanauki.pl/articles/245048.pdf
Data publikacji:: 2016
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: landing gear
energy absorption
drop test
shock absorber
Opis:: Landing gear as one of the most crucial systems ensuring safe take-off and landing must be rigorously tested before first flight of each newborn aeroplane. In the static and dynamic tests strength, functionality and energy absorption capability of landing gear components (wheel, brake, shock absorber, support structure and retraction system) are verified. One of the most important is an energy absorption dynamic test. During drop, test campaign a landing gear damping system is not only verified but also optimized by changing parameters like: damping orifice diameter, geometry of gas and oil chambers and shock absorber and tire inflation pressures. This process often takes substantial amount of time because of influence of the mentioned parameters on landing gear energy absorption efficiency. Other factors like landing configuration spin up and spring back effects generated during wheel contact with the ground [1] also have to be considered in the energy absorption optimization process. The paper describes the landing gear drop test campaign and main challenges, which have to be overcome to achieve optimal dynamic characteristics of the system. The tested object was the main landing gear of the 1400 kg General Aviation aircraft certified in accordance with EASA CS-23 regulations. The drop test campaign was carried out in Warsaw Institute of Aviation Landing Gear Laboratory.
Źródło:: Journal of KONES; 2016, 23, 4; 159-165
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 13.

Tytuł:: Analysis of links positions in landing gear mechanism
Autorzy:: Brewczyński, D.
Tora, G.
Powiązania:: https://bibliotekanauki.pl/articles/955121.pdf
Data publikacji:: 2014
Wydawca:: Uniwersytet Zielonogórski. Oficyna Wydawnicza
Tematy:: samolot
podwozie samolotu
kinematyka
aircrafts
landing gear
mechanics
kinematics
Opis:: This article contains a kinematic analysis of an aircraft chassis mechanism in a range of positions. The mechanism of the chassis is made up of several smaller subsystems with different functions. The first mechanism is used to eject the chassis before landing (touchdown) and fold it to hatchway after the lift off. The second mechanism is designed to perform rotation of the crossover with the wheel, in order to adjust the position of the wheel to fit it in the limited space in the hold. The third mechanism allows movement of the chassis resulting from the change in length of the damper. To determine the position of the following links of the mechanism calculus of vectors was applied in which unit vectors were used to represent the angular position of the links. The aim of the analysis is to determine the angle of convergence and the angle of heel wheels as a function of the variable length of hydraulic cylinder, length of the shock absorber, length of the regulations rods.
Źródło:: International Journal of Applied Mechanics and Engineering; 2014, 19, 3; 503-512
1734-4492
2353-9003
Pojawia się w:: International Journal of Applied Mechanics and Engineering
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 14.

Tytuł:: Health monitoring in landing gears
Autorzy:: Skorupka, Zbigniew
Tywoniuk, Andrzej
Powiązania:: https://bibliotekanauki.pl/articles/242829.pdf
Data publikacji:: 2019
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: health monitoring
landing gear
load measurement
pressure measurement
strain gauges
Opis:: Every mechanical construction loses its properties in time due to the usage wear that leads to malfunctions and, in the end, to failure. Widely used method of failure time prediction base on extended laboratory tests where a device is tested against fatigue and wear. This method is well established but is expensive, time-consuming, and costly. Another way of failure prediction is to calculate it using advanced algorithms what is faster and cheaper but less accurate than actual tests. Furthermore, both methods are not optimal due to the principle of operation based on simplified assumptions. In such cases, it is common to make the lifespan of the safety wise devices for example landing gears much less than real in case of fatal failure not covered by the predictions. This can lead to much higher price and maintenance costs of the landing gear. Nowadays the worldwide trend is to monitor the behaviour of the devices in real time and predict failure using actual state. There are several methods of health monitoring, most of them including sensors, acquisition systems and computer software for analysis. In this article, authors describe possible landing gears health monitoring methods based on authors’ laboratory experience in sensor appliance and test data analysis. The authors also present their idea of adding health monitoring to existing landing gears where no dedicated infrastructure was initially designed.
Źródło:: Journal of KONES; 2019, 26, 1; 167-174
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 15.

Tytuł:: Laboratory investigations on landing gear ground reactions (load) measurement
Autorzy:: Skorupka, Z.
Powiązania:: https://bibliotekanauki.pl/articles/243799.pdf
Data publikacji:: 2017
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: laboratory-testing
landing gear
load measurement
direct measurement
indirect measurement
Opis:: Ground reaction measurement in landing gear laboratory tests is used in order to gain knowledge about loads transferred to the aircraft structure. Ground reaction level is defined during aircraft design phase and it is required not to exceed limit value in real construction. Load from landing affect directly strength of aircraft structure especially mounting points what translates both strength of aircraft structure especially mounting points what translates both on safety and weight of the final design. Meeting the safety requirements is crucial in aviation regulations conformity. Landing gear ground reactions evaluation is performed during laboratory tests in order to meet the compliance with the ground load requirements assumed in design phase. Proper test method is crucial to prove the actual load. One of the methods is landing gear dynamic drop test where landing forces are measured. Force measurement is made in several ways according to test stand construction and test object specifics. In this article, three methods are described due to author’s experience in landing gear tests. Proposed techniques cover two direct and one indirect force measurements. Direct approach is based on strain gauge measurement principle. One is a strain gauge plate fixed to the ground while the second one is based on strain gauges attached to landing gear mounting nodes. Indirect approach is based on the acceleration of the tested object, which by definition is correlated with the force applied to the structure. Obtained test results allow determining the kinetic energy absorbed by landing gear during drop test. In this article author also presented numerical integration of the time history data and compared them with simulation results in order to show equivalence of all three of the test methods and to prove correctness of the test initial conditions determination.
Źródło:: Journal of KONES; 2017, 24, 2; 225-230
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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