Autor: Wojtas, M. - Katalog OPAC zbiorów

Skocz do pozycji: 1.

Tytuł:: Gyroplane rotors vibration tests
Autorzy:: Wojtas, M.
Trendak, M.
Powiązania:: https://bibliotekanauki.pl/articles/246317.pdf
Data publikacji:: 2017
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: rotor vibration
rotor blades
teetering rotor
hub connector
rotor imbalance
Opis:: The article presents vibration test of three different types of gyroplane main rotors. The test was carried out on a specially prepared test bench using a Red Led Tacho Sensor measuring system. Tests were conducted for the project „Research and development works on innovative construction of aircrafts of weight over 560 kilograms at the company Trendak Aviation”. The work outlines the basic properties of the gyroplane vibration and gives their sources. The research focused on the gyroplane main rotor vibration related inter alia to the rotor imbalance as well as rotor hub connector construction. Tested rotors consisted of three different types of gyroplane rotor blades and innovative universal hub connector with positive coning angle of 2.8º. The article summarized the basic properties of three types of gyroplane the rotor blade, marks advantages of use hub connector witch constructional dihedral angle. Discusses the principle of operation of measuring device, tests methodology starting from instrument calibration. The results of the measurements are shown in the graphs in polar coordinates. The vibration measurement is carried out in two axes, in x-axis, longitudinal, along the rotor radius and in y-axis, perpendicular to the x-axis, in the direction of the chord of the rotor blades.
Źródło:: Journal of KONES; 2017, 24, 4; 349-354
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 2.

Tytuł:: New gyroplane hub connector with positive coning angle
Autorzy:: Wojtas, M.
Trendak, M.
Powiązania:: https://bibliotekanauki.pl/articles/244662.pdf
Data publikacji:: 2017
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: blade dihedral angle
waving
rotor instability
teetering rotor
Opis:: The article presents advantages and disadvantages of two blade teetering rotors with constructional dihedral angle greater than 0o . Several structural design solutions of rotor hub connector are shown in this work. However, the main attention is focused on innovative hub connector design and manufactured by Trendak Aviation Company during the project “Research and development works on innovative construction of aircrafts of weight over 560 kilograms”. Discusses structural advantages of the new rotor hub connector according to other construction. Also were raised issues related to the load of the gyroplane rotor during the flight, in particular the load of rotor blades root, during a gyroplane break manoeuvre, according to conning angle of rotor hub connector. The disadvantages of using the structural dihedral angle in teetering rotors are also presented, focusing on the rotor aeroelastic instability so-called waving, which from the literature analysed is concerned only with two blades teetering rotors. Performed a coarse analysis in SMOG program, prepared at the Institute of Aviation for the analysis of helicopter and gyroplanes rotors. The stability analysis of the rotor for a number of structural dihedral angle and blades setting pitch was performed. Basis of this analysis the stability boundary were determined for the analysed gyroplane rotor with connector hub with positive coning angle of 2.8o. .
Źródło:: Journal of KONES; 2017, 24, 3; 325-330
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 3.

Tytuł:: Composite rotor blades tests essential before mounting on gyroplane
Autorzy:: Sobieszek, A.
Wojtas, M.
Powiązania:: https://bibliotekanauki.pl/articles/242636.pdf
Data publikacji:: 2016
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: gyroplane
strength test
blades properties
composites
Opis:: The article presents the course of the composite rotor blades tests. Object of study was designed in Institute of Aviation, new airfoil for gyroplane rotors and technology of manufacturing carbon rotor blades were made. When the test program was developed, we focused for special test to check not only typical rotor blades properties but also composite structures thereby technology of manufacturing. One of the basic rotor blades test is to determine the breaking force, which, taking into account the safety factor, cannot exceed the maximum centrifugal force occurring on the rotor blades during flight. The first step of rotor blades tests was static test, which gave us answer about stiffness in plane of low stiffness and torsional stiffness, it’s very important properties related to vibrations. Another mechanical properties measured during tests were centre of gravity and mass moment of inertia in rotor blade. Next step was dynamic test – tracking and balancing verification. After static and dynamics, which has proper results – good balance and no vibration on the entire range of rotational speed – rotor blades can be use on fly object. After getting proper results of static and dynamic test next step was a specially prepared test, which defined the time needed for delamination to take place. During the delamination tests, the rotor blade was subjected to adequate loads that occur in horizontal flight. That kind of test is basis to determine service life of rotor blades.
Źródło:: Journal of KONES; 2016, 23, 4; 487-494
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 4.

Tytuł:: The influence of the blades leading edge anti-erosion protection on main rotor performances
Autorzy:: Wojtas, M.
Czajkowski, Ł.
Sobieszek, A.
Powiązania:: https://bibliotekanauki.pl/articles/243585.pdf
Data publikacji:: 2018
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: airfoil
rotor blades
flight tests
light rotorcrafts
ultra-light rotorcrafts
Opis:: This article presents the influence of rotor blade airfoil shape on main rotor performances. In this case, we analysed the influence of anti-erosion tape, which is applied to the leading edge of the blade to protect the blades from environmental conditions. In Gyro-Tech Innovation an Aviation Company and Institute of Aviation the independent tests of helicopter and gyroplane main rotors were performed. Research includes: bench tests, on the test stand for dynamic testing of insulated rotors and tests on two flying constructions, gyroplane Cavalon produced by AutoGyro GmbH Company and ultralight helicopter Dynali H3. On the test bench, a two-blade rotor, used in ultralight and unmanned helicopters, was tested. In article, the authors present importance of the proper selection and application of anti-erosion coatings on rotor blades. Discuss the behaviour of the above-mentioned constructions with main rotor blades leading edge covered anti-erosion tape, during flight tests. The results of bench tests, including the comparison of polar curves of the main rotor with anti-erosion coating and without were also presented and discussed. In the summary of this article among others the solution of technological pocked introduced in the rotor blade, corresponding to the thickness of the anti-erosion tapes, in such way that after tape is applied it does not change the contour of the blade airfoil were presented.
Źródło:: Journal of KONES; 2018, 25, 2; 409-414
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 5.

Tytuł:: Strength analysis of the magnesium alloy control system lever of the ILX-27 unmanned helicopter
Autorzy:: Wojtas, M.
Sobieszek, A.
Żurawski, R.
Powiązania:: https://bibliotekanauki.pl/articles/246896.pdf
Data publikacji:: 2017
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: magnesium alloys
FEM
strain gauges
geometry verification
strength test
Opis:: The article presents the potential use of magnesium alloys in the aerospace industry. In this project the static strength analysis of magnesium alloy AZ31 of the control – system lever of the ILX-27 unmanned helicopter was carried out. Control-system levers are located between the swash plate and an actuator. The aim of the tests was to confirm the strength properties of the magnesium alloy control-system lever for their implementation on the ILX-27 unmanned helicopter. Strain gauge sensor was used during the tests. Strain gauges installation on easily corrodes surface requires special method. The laboratory tests were proceeded by the lever static strength calculations in the computing environment ANSYS Inc. Additionally, a geometry measurement of the control-system lever at CMM equipped with a laser scanner head was made to compare with the lever CAD model to assess the quality and method of conformance. Unmanned helicopter ILX-27 is being developed through the introduction new materials and technologies. Tests of control system lever have shown if it is possible to use lighter materials than aluminum alloy to provide sufficient strength properties while reducing the mass of the object. Analysis of the available materials used in aerospace engineering allowed selecting the best of magnesium alloy.
Źródło:: Journal of KONES; 2017, 24, 2; 293-300
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 6.

Tytuł:: Innovative composite gyroplane rotor blades : fatigue tests
Autorzy:: Wojtas, M.
Sobieszek, A.
Szczepanik, T.
Powiązania:: https://bibliotekanauki.pl/articles/241581.pdf
Data publikacji:: 2018
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: rotor blades
fatigue tests
NDT
composite
Opis:: The paper presents test bench method for verifying the fatigue life of the rotor blades, working in operating conditions in a position steady flight (autorotation), on the aviation construction called the gyroplane. One of the critical elements of this design is the main rotor, which in its modern versions takes the form of advanced composite structures subjected to loads in flight complex variable, the nature of which differs from the well-known operating conditions of helicopter rotors. The article includes a description of the test object, which are composite rotor blades designed specifically to work in autorotation, the specificity of loads of autorotation rotor, and method of implementation of the gyroplane rotor work cycles in the test bench. The main aim of this research is to evaluate the sustainability of the composite blades under the gyroplane operating loads with the goal to allow the rotor to operate in the air. The tests were carried out for 100 hours of gyroplane flight at loads do not exceed the maximum operating loads, and for several hours under a load higher than operating. During test for the evaluation of composite structure, the infrared camera with dedicated software IRNDT was used. The reached showed structural integrity in critical mounting section of the blade.
Źródło:: Journal of KONES; 2018, 25, 4; 447-453
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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