Temat: take-off - Katalog OPAC zbiorów

Skocz do pozycji: 1.

Tytuł:: Impact of opening time of the take-off pneumatic launcher main valve on take-off pressure losses
Autorzy:: Jastrzębski, G.
Powiązania:: https://bibliotekanauki.pl/articles/243547.pdf
Data publikacji:: 2016
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: take-off launcher
pneumatic take-off systems
pressure losses
Opis:: This publication presents UAV rope and pneumatic launchers constructed and operated in the Air Force Institute of Technology. The construction and operating principle were presented, and functional properties of the UAV take-off pneumatic launcher were characterised. Furthermore, a detailed diagram of the take-off pneumatic launcher was shown, and an operating principle of the launcher take-off system and pneumatic control of the take-off procedure were discussed. The operation parameters of the most important operational elements (main ball valve, semi-rotary actuator, pneumatic valves controlling the flow) from the launcher pneumatic system were specified. On the basis of data sheets of pneumatic elements, a calculation model of the mass flow (volumetric flow rate) of compressed air flowing through the main valve (ball valve in the take-off cylinder supply line) of the take-off pneumatic launcher was designed. The possible cracks, through which compressed air leaks and the take-off cylinder dead sections during the main valve opening and shot, were characterised and discussed. The calculation model designed for individual leaks and total compressed air leaks in the take-off line of the pneumatic launcher was presented. Based on the mass flow model (volumetric flow rate) of compressed air flowing through the main valve, and total compressed air leaks, the relationship of compressed air energy losses depending on opening time of the main valve of the take-off pneumatic launcher was determined. In the paper, the results of simulation studies for the times shorter than data sheets of the main valve opening were presented. In addition, the change of the compressed air disposable energy losses was defined. Based on the results of simulation studies, the opening time of the take-off launcher main valve for the acceptable disposable energy loss level of the take-off pneumatic launcher was specified.
Źródło:: Journal of KONES; 2016, 23, 4; 175-182
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 2.

Tytuł:: Evaluation of the required ground power of a ground - based system for support of the aircraft safe take - off and landing
Autorzy:: Majka, A.
Powiązania:: https://bibliotekanauki.pl/articles/242165.pdf
Data publikacji:: 2012
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: air transport
take-off and landing
magnetic levitation
Opis:: Among the most important problems faced by the air transport today there can be mentioned some negative influences of aircraft and airports on the environment and the increasing costs of air transport. One of the possibilities to improve the situation is to work out innovative solutions aimed at decreasing of the aircraft pollution and improving the transport effectiveness. Among the most innovative ideas is the use of magnetic levitation to aid the take-off and landing of the transport aircraft. The use of the aiding system will bring a lot of benefits, however, regarding its innovative character and the problems connected with it, the idea can have been realized in a couple of years or even decades. The aim of this work was to carry out the analysis of the change to the required thrust of the transport aircraft in the take-off, landing and cruise using the system of magnetic levitation. Magnetic levitation or magnetic suspension is a method by which a body floats due to a special quality of magnets. The generated electromagnetic force is used to balance the weight of the object. The current work describes the ways of determining the weights of the main systems of the aircraft with classical construction solutions where the weight of the whole aircraft is estimated on the basis of the statistical methods. It allows determining the weights of all main systems of the aircraft and verifying the results using the known examples. Thanks to this approach, it could be possible to determine the modified aircraft weight more thoroughly, adding the changes in weights of the modified systems.
Źródło:: Journal of KONES; 2012, 19, 4; 411-418
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 3.

Tytuł:: Methods for determining the take-off speed of launchers for unmanned aerial vehicles
Autorzy:: Jastrzębski, G.
Ułanowicz, L.
Powiązania:: https://bibliotekanauki.pl/articles/243050.pdf
Data publikacji:: 2018
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: aviation
unmanned aerial vehicle
take-off launcher
take-off speed
acceleration recorder
lotnictwo
bezzałogowy statek powietrzny
prędkość startu
rejestrator przyspieszenia
Opis:: Unmanned aerial vehicles (UAV) are currently a very rapidly developing type of aviation. The problem of support during the take-off with the use of, i.e. take-off launchers arose along with their development, especially for UAVs with weights and dimensions preventing manual take-off. One of the major issues associated with UAV take-off launchers is for its UAV accelerating element to obtain its initial speed. The article presents three methods of determining launcher take-off speeds for unmanned aerial vehicles, i.e. the concentrated very oblique projection method, the high-speed camera methods, and the acceleration recorder method. The take-off launcher carriage speed in the oblique projection method is determined from a formula. This method involves “ejections” of concentrated masses from the UAV mass range and measuring the component values resulting from the used formula, which contains the range of the oblique projection, the elevation of the projection and its angle. The method using the high-speed camera involves recording the course of ejections of the concentrated mass from the launcher. The average take-off speed is determined on the basis of a take-off run length (section of the launcher race, where the unit accelerates) and defining the start and end frame of the carriage movement. The third method for the determination of the take-off speed utilizes an acceleration recorder. The method with the recorder involves registering a change in the accelerations when the take-off carriage is being accelerated by a system fixed on the carriage or the accelerated object. The article presents the methodology of dynamic tests of object acceleration on a launcher, necessary for the determination of speed with the mentioned methods. Selected results from actual tests with the use of the 01/WS/2015 launcher, which is an element of the ZOCP JET2 set, were presented. The test results are presented in a tabular form. The methods for the determination of the take-off speed were compared on the basis of performed tests. Based on the obtained results, the factors impacting the accuracy of each of the methods were identified.
Źródło:: Journal of KONES; 2018, 25, 1; 170-176
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 4.

Tytuł:: National policy and big-push theory of development in Nigeria: moving away from low-level economic equilibrium
Autorzy:: Umoru, D.
Onimavo, J. A.
Powiązania:: https://bibliotekanauki.pl/articles/321703.pdf
Data publikacji:: 2018
Wydawca:: Politechnika Śląska. Wydawnictwo Politechniki Śląskiej
Tematy:: development
infrastructure
Nigeria
big-push
take-off
rozwój
infrastruktura
Opis:: The paper analyzes the policy implications of the big-push model for development in Nigeria. The highlights of the analysis include existence of three inter-related perceptions namely, poverty trap, big push (BP) and takeoff. The basic idea is that poor countries are in poverty, hence needs BP linking amplified investment, leading to takeoff in national income and development. This indeed rationalizes necessity for overseas aid. In effect, minimum infrastructure and educational resources be apportioned to development programme to achieve success. However, nations that have implemented coordinated investment programs can achieve industrialization of each sector and thus be able push forward sequence of development.
Źródło:: Zeszyty Naukowe. Organizacja i Zarządzanie / Politechnika Śląska; 2018, 116; 177-187
1641-3466
Pojawia się w:: Zeszyty Naukowe. Organizacja i Zarządzanie / Politechnika Śląska
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 5.

Tytuł:: Optimal configurations of wave energy converter arrays with a floating body
Autorzy:: Zhang, W.
Liu, H.
Zhang, X.
Zhang, L.
Ashraf, M. A.
Powiązania:: https://bibliotekanauki.pl/articles/260084.pdf
Data publikacji:: 2016
Wydawca:: Politechnika Gdańska. Wydział Inżynierii Mechanicznej i Okrętownictwa
Tematy:: wave energy
cylinder array
power take-off
hydrodynamic analysis
Opis:: An array of floating point-absorbing wave energy converters (WECs) is usually employed for extracting efficiently ocean wave energy. For deep water environment, it is more feasible and convenient to connect the absorbers array with a floating body, such as a semi-submersible bottom-moored disk, whose function is to act as the virtual seabed. In the present work, an array of identical floating symmetrically distributed cylinders in a coaxial moored disk as a wave energy device is proposed The power take-off (PTO) system in the wave energy device is assumed to be composed of a linear/nonlinear damper activated by the buoys heaving motion. Hydrodynamic analysis of the examined floating system is implemented in frequency domain. Hydrodynamic interferences between the oscillating bodies are accounted for in the corresponding coupled equations. The array layouts under the constraint of the disk, incidence wave directions, separating distance between the absorbers and the PTO damping are considered to optimize this kind of WECs. Numerical results with regular waves are presented and discussed for the axisymmetric system utilizing heave mode with these interaction factors, in terms of a specific numbers of cylinders and expected power production.
Źródło:: Polish Maritime Research; 2016, S 1; 71-77
1233-2585
Pojawia się w:: Polish Maritime Research
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 6.

Tytuł:: Minimum emission unconventional MAGLEV assisted take-off
Autorzy:: Majka, A.
Powiązania:: https://bibliotekanauki.pl/articles/246124.pdf
Data publikacji:: 2014
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: air transport
green trajectory
take-off
aircraft emission
magnetic levitation
Opis:: Among the most important problems faced by the air transport today there can be mentioned some negative influences of aircraft and airports on the environment and the increasing costs of air transport. One of the possibilities to improve the situation is to work out innovative solutions aimed at decreasing of the aircraft pollution and improving the transport effectiveness. Among the most innovative ideas is the use of magnetic levitation (MAGLEV) to aid the take-off and landing of the transport aircraft. The “Integrated Ground and on-Board system for Support of the Aircraft Safe Take-off and Landing” – GABRIEL, deals with radically new integration of the MAGLEV technology into the air transportation system that contains aircraft, airport, air traffic control, authority, logistic and operational support, maintenance, etc. GABRIEL idea includes operation of the aircraft without the conventional undercarriage system and using the ground based power and supporting systems for take-offs and landings. In case of using the GABRIEL system as a catapult, the aircraft on the track must be accelerated to the speed permitting to reach the altitude of 300 m or more. Such take-off and climb results in minimum noise and minimal emission of substances harmful for the environment. After reaching the altitude of 300 m, the aircraft may follow its flight with using different flight strategies. Different conditions of the unconventional take-off needs to shape other way the trajectory of the initial stage of the aircraft flight after the lift-off. The aim of the present work was to determine the optimal conditions of the lift-off and the optimal trajectory of the initial climb minimizing the emission. Simplified realization of the Ritz- Galerkin method was used in this work, which uses an approximate solution to boundary value problems for determining the optimal flight trajectory.
Źródło:: Journal of KONES; 2014, 21, 4; 335-342
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 7.

Tytuł:: A conception of vertical take-off air vehicle with self-aligning moving wings
Autorzy:: Lichoń, D.
Powiązania:: https://bibliotekanauki.pl/articles/242818.pdf
Data publikacji:: 2014
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: vertical take-off
air vehicle conception
self-aligning wings
flapping wings
Opis:: The possibility of vertical take-off of an aircraft is a valuable feature in air transport. It allows to increase operational characteristics of an air vehicle and requires less field and low cost ground infrastructure. Currently the vertical take-off feature is practically reserved to helicopters and tilt-rotor aircrafts. Both types of air vehicles have their advantages and also have some important limitations. Regarding the helicopters their construction provides natural vertical take-off features and makes them useful in low altitude flight tasks. However the power required for flight and main rotor kinematics results in low cruising speed and short range performance. The tilt-rotor aircraft is an answer which provides good cruise characteristics saving the vertical take-off feature. The construction of tiltrotor aircraft consists of rotors with adjustable position of tip-path plane. The main technical problem of tilt-rotors is necessity of change aerodynamic configuration from vertical mode to cruise mode at low flight altitude and very low flight speed. A proposed conception of a vertical take-off air vehicle using self-aligning moving wings is focused on producing aerodynamic force always on wings without participation of rotors or propellers. The self-aligning or semirotating wing movement enables to produce aerodynamic force in each flight speed. During take-off lift force is generated by means of power unit driving the wings. The transition from hovering to progressive flight is a smooth phase without aerodynamic configuration changes. It occur as a result of change in wing kinematics or gravity center position. As the flight speed increases the lift force is generated like in classic airplane wing and the power unit load decreases. The conception of presented air vehicle assume to join best features of airplanes and helicopters i.e. vertical take-off, good flight performances and lack of strict border between both phases of flight.
Źródło:: Journal of KONES; 2014, 21, 4; 311-317
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 8.

Tytuł:: The influence of ship rolling motion on take-off aerodynamic characteristics of aircraft
Autorzy:: He, Z.
Sun, X.
Gu, X.
Powiązania:: https://bibliotekanauki.pl/articles/259257.pdf
Data publikacji:: 2018
Wydawca:: Politechnika Gdańska. Wydział Inżynierii Mechanicznej i Okrętownictwa
Tematy:: ship rolling motion
ski-jump take-off
Meshless method
WALE turbulence model
aerodynamic characteristics
Opis:: Ship motion is an important factor affecting on the safety of ski-jump take-off. The simplified frigate ship SFS1 was numerically simulated, and the results were compared with the experimental data, the feasibility of the calculation method was verified; Meshless method and WALE turbulence model were used to simulate the process of aircraft skijump take-off, aerodynamic characteristics under different rolling conditions during the aircraft ski-jump take-off process were presented. The results showed that: the influence of ship rolling motion on lift coefficient, drag coefficient and pitching moment was small, side force and rolling moment were greatly affected by rolling motion; the region of downwash with the maximum speed was about 10 m from the bow; the safety of ski-jump take-off was greatly affected when aircraft was close to the bow within 20 m.
Źródło:: Polish Maritime Research; 2018, S 2; 23-29
1233-2585
Pojawia się w:: Polish Maritime Research
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 9.

Tytuł:: Different defuzzification methods in Guimbal Cabri G2 helicopter takeoff possibility evaluation
Autorzy:: Mendrek, M.
Grzesik, N.
Krzyżak, A.
Kuźma, K.
Powiązania:: https://bibliotekanauki.pl/articles/374121.pdf
Data publikacji:: 2018
Wydawca:: Politechnika Śląska. Wydawnictwo Politechniki Śląskiej
Tematy:: fuzzy logic
fuzzy expert system
helicopter take off
logika rozmyta
regułowe systemy ekspertowe
start helikoptera
Opis:: The article discusses the aerodynamic properties of the Guimbal Cabri G2 helicopter. The main considerations concern the helicopters ascending to the altitude under initial conditions, which were assumed in the project and how the change of the defuzzification method affects the work of the fuzzy controller. The authors analyzed the following: the aircraft, the crew and the payload. The authors assessed the altitude and the minimum time of the helicopter climb. In designing and the work simulation process, the authors used Matlab and Simulink software. A comparison of the influence of selected defuzzification methods on the work of the fuzzy controller was made.
Źródło:: Transport Problems; 2018, 13, 2; 27-38
1896-0596
2300-861X
Pojawia się w:: Transport Problems
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 10.

Tytuł:: Nonlinear PTO effect on performance of vertical axisymmetric wave energy converter using semi-analytical method
Autorzy:: Liu, M.
Liu, H.
Zheng, X.
Chen, H.
Wang, L.
Zhang, L.
Powiązania:: https://bibliotekanauki.pl/articles/258878.pdf
Data publikacji:: 2017
Wydawca:: Politechnika Gdańska. Wydział Inżynierii Mechanicznej i Okrętownictwa
Tematy:: wave energy converter (WEC)
power take-off (PTO)
capture width ratios
analytical method
eigen function
Opis:: The wave energy, as a clean and non-pollution renewable energy sources, has become a hot research topic at home and abroad and is likely to become a new industry in the future. In this article, to effectively extract and maximize the energy from ocean waves, a vertical axisymmetric wave energy converter (WEC) was presented according to investigating of the advantages and disadvantages of the current WEC. The linear and quadratic equations in frequency-domain for the reactive controlled single-point converter property under regular waves condition are proposed for an efficient power take-off (PTO). A method of damping coefficients, theoretical added mass and exciting force are calculated with the analytical method which is in use of the series expansion of eigen functions. The loads of optimal reactive and resistive, the amplitudes of corresponding oscillation, and the width ratios of energy capture are determined approximately and discussed in numerical results.
Źródło:: Polish Maritime Research; 2017, S 3; 49-57
1233-2585
Pojawia się w:: Polish Maritime Research
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 11.

Tytuł:: Probabilistic model for airport runway safety areas
Autorzy:: Szabo, S.
Vittek, P.
Kraus, J.
Plos, V.
Lališ, A.
Štumper, M.
Vajdova, I.
Powiązania:: https://bibliotekanauki.pl/articles/374515.pdf
Data publikacji:: 2017
Wydawca:: Politechnika Śląska. Wydawnictwo Politechniki Śląskiej
Tematy:: take-off
landing
runway
safety area
probability
distance
start
lądowanie
pas startowy
obszary bezpieczeństwa
prawdopodobieństwo
odległość
Opis:: The Laboratory of Aviation Safety and Security at CTU in Prague has recently started a project aimed at runway protection zones. The probability of exceeding by a certain distance from the runway in common incident/accident scenarios (take-off/landing overrun/veer-off, landing undershoot) is being identified relative to the runway for any airport. As a result, the size and position of safety areas around runways are defined for the chosen probability. The basis for probability calculation is a probabilistic model using statistics from more than 1400 real-world cases where jet airplanes have been involved over the last few decades. Other scientific studies have contributed to understanding the issue and supported the model’s application to different conditions.
Źródło:: Transport Problems; 2017, 12, 2; 89-97
1896-0596
2300-861X
Pojawia się w:: Transport Problems
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 12.

Tytuł:: Environmental threats around airports and possibilities limiting them
Zagrożenia ekologiczne wokół lotnisk i możliwości ich ograniczania
Autorzy:: Głowacki, P.
Szczeciński, S.
Powiązania:: https://bibliotekanauki.pl/articles/212476.pdf
Data publikacji:: 2011
Wydawca:: Sieć Badawcza Łukasiewicz - Instytut Lotnictwa
Tematy:: zagrożenie środowiskowe lotniska
mozliwości ograniczania zagrożeń ekologicnych
environmental threats of aviation
ecology
toxins
airport traffic
aircraft take- off
turbofan engine
Opis:: The article has presented some of the most important reasons for and sources of main factors causing interferences with the natural ecosystem within the airport zone- resulting from particularly heavy traffic and from the functioning of various devices on small limited areas of surface and the ground-level layer of the atmosphere. These operations are accompanied by intensive noise and heat emitted in large quantities- which are caused by the work of jet engines of taking off and landing aircraft. The jet engines work contributes to the ‘production’ of not only CO2 and H2O, but also numerous harmful chemical compounds such as CO, HC as well as NOx.
W artykule przedstawiono najważniejsze przyczyny i źródła głównych czynników powodujących zakłócenia „normalnego” systemu ekologicznego w strefie lotnisk–a wynikające ze szczególnie intensywnego ruchu i działania różnych urządzeń na niewielkim obszarze powierzchni ziemi i przyziemnej warstwie atmosfery. Działaniom tym towarzyszą skoncentrowany hałas i wydzielanie ciepła w ogromnych ilościach–których przyczyną jest praca turbinowych silników odrzutowych startujących i lądujących samolotów. Z pracą tych silników wiąże się „produkowanie” nie tylko CO2 i H2O ale także wiele szkodliwych związków chemicznych jak CO, niespalone HC oraz NOx w dużych ilościach.
Źródło:: Prace Instytutu Lotnictwa; 2011, 8 (217); 35-38
0509-6669
2300-5408
Pojawia się w:: Prace Instytutu Lotnictwa
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 13.

Tytuł:: Dynamic load indicators for take-off–landing sequence in blocks and attacks of elite female volleyball players
Autorzy:: Kabaciński, J.
Dworak, L. B.
Murawa, M.
Rzepnicka, A.
Powiązania:: https://bibliotekanauki.pl/articles/307295.pdf
Data publikacji:: 2016
Wydawca:: Politechnika Wrocławska. Oficyna Wydawnicza Politechniki Wrocławskiej
Tematy:: siła reakcji podłoża
obciążenie dynamiczne
start
atak
biomechanika
ground reaction forces
take-off–landing
dynamic loads
blocks
attacks
volleyball
biomechanics
Opis:: Purpose: Dynamic loads during landings determined by the ground reaction forces (GRFs) may elaborate internal loads and increase the risk of overload knee injuries as a result of performing volleyball jumps many times. The study dealt with a biomechanical assessment of dynamic load indicators in female volleyball players for the motion sequence of take-off–landing in blocks and attacks. Methods: Twelve professional female volleyball players participated in the study. Blocks and attacks were filmed by two cameras. GRFs vs. time graphs were recorded with the use of a force platform. Values of dynamic load indicators in terms of the relations of peak of vertical component of GRF, build-up index of this force (BIF), and power output (P) during landing to the vGRF, BIF and P during take-off (L/T) were calculated. Results: The statistically significant ( p < 0.05) highest values of L/T indicators were found for back row attack spikes: 2.4 (vGRF), 12.2 (BIF) and 3.1 (P). In the case of blocks, slide attack spikes and attack line spikes, results of these variables were in range: 1.8÷2.1, 5.9÷7.6 and 2.1÷2.9, respectively. Conclusions: The reduction of GRFs during landings contributes to decreasing the level of the load indicators L/T which should minimize the incidence of anterior cruciate ligament and patellar tendon injuries in female volleyball players.
Źródło:: Acta of Bioengineering and Biomechanics; 2016, 18, 1; 41-46
1509-409X
2450-6303
Pojawia się w:: Acta of Bioengineering and Biomechanics
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 14.

Tytuł:: Strength and fatigue numerical analysis of jointed-telescopic power take-off shaft
Wytrzymałościowa i zmęczeniowa analiza numeryczna wału przegubowo-teleskopowego
Autorzy:: Kukiełka, K.
Patyk, R.
Kukiełka, L.
Bohdal, Ł.
Powiązania:: https://bibliotekanauki.pl/articles/334737.pdf
Data publikacji:: 2014
Wydawca:: Sieć Badawcza Łukasiewicz - Przemysłowy Instytut Maszyn Rolniczych
Tematy:: power take-off shaft
strength analysis
fatigue wear analysis
numerical analysis
wał przegubowo-teleskopowy
analiza wytrzymałościowa
analiza zmęczeniowa
analiza numeryczna
Opis:: The aim of this work is to develop a numerical application to strength and fatigue numerical analysis of jointed-telescopic Power Take-Off shaft. Exemplary results for equivalent of stress in whole shaft and in a part of stress concentration are shown. Presented chart of changing of the number of the correct cycles operation of the PTO shaft depending on the torsional angle allows to predict a shaft life. From numerical analyses of process it follows that the numerically tested system can withstand the load associated with the vibration phenomena and is properly designed. Furthermore, it was found that the shaft at the maximum rotational operating speeds, is working at frequencies under resonance.
Celem niniejszej pracy jest opracowanie aplikacji numerycznej do wytrzymałościowej i zmęczeniowej analizy numerycznej wału przegubowo-teleskopowego. Zamieszczono przykładowe wyniki dla naprężeń zredukowanych dla całego wałka oraz w miejscach ich koncentracji. Zaprezentowany wykres zależności liczby cykli pracy od kąta odchylenia widłaków pozwala na prognozowanie trwałości WPM. Z przeprowadzonych analiz numerycznych procesu wynika, że badany numerycznie układ wytrzymuje obciążenia związane ze zjawiskami drganiowymi i jest prawidłowo zaprojektowany. Ponadto, stwierdzono, że wał przy maksymalnych obrotowych prędkościach roboczych pracuje w częstotliwościach podrezonansowych.
Źródło:: Journal of Research and Applications in Agricultural Engineering; 2014, 59, 1; 77-82
1642-686X
2719-423X
Pojawia się w:: Journal of Research and Applications in Agricultural Engineering
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 15.

Tytuł:: Preliminary design for a jet training aircraft
Wstępny projekt odrzutowego samolotu szkoleniowego
Autorzy:: Loginov, Vasyl
Grebenikov, Oleksandr
Humennyi, Andrii
Eremenko, Serhii
Soboliev, Oleksandr
Powiązania:: https://bibliotekanauki.pl/articles/36440680.pdf
Data publikacji:: 2021
Wydawca:: Sieć Badawcza Łukasiewicz - Instytut Lotnictwa
Tematy:: jet trainer plane
performance
take-off mass
scheme
master geometry
odrzutowy samolot szkolno-treningowy
osiągi
masa startowa
schemat
geometria samolotu
Opis:: This paper present the results of our project to develop the preliminary design of a jet trainer plane (JTP) with a two-person crew, the base version of which is intended for cadet training. We first consider the assumptions and requirements for the new aircraft, and review the parameters of existing aircraft designs in the similarly-purposed class. Next we argue for certain design choices, regarding the aircraft layout, cockpit configuration, wing location and wingform, tail scheme, and powerplant. The resulting aircraft design is calculated to have a maximum flight speed of 940 km/h, a ground-level rate of climb of 100 m/s, and a range of 1130 km. The plane’s take-off mass is calculated, in three approximations, at 2264 kg. Lastly we present the training plane’s geometrical parameters, general view, and master geometry.
W pracy przedstawiono wyniki projektu opracowania wstępnej konstrukcji odrzutowego samolotu szkoleniowego (JTP) z dwuosobową załogą, z podstawową wersją przeznaczoną do szkolenia kadetów. Rozważono założenia i wymagania stawiane nowemu samolotowi oraz dokonano przeglądu parametrów istniejących konstrukcji samolotów w klasie o podobnym przeznaczeniu. Podano argumenty przemawiające za określonymi wyborami konstrukcyjnymi, dotyczącymi układu samolotu, konfiguracji kabiny pilota, położenia i kształtu skrzydeł, schematu ogona oraz zespołu napędowego. Obliczono, że projektowany samolot będzie miał maksymalną prędkość lotu 940 km/h, prędkość wznoszenia na poziomie ziemi 100 m/s i zasięg 1130 km. Masę startową samolotu obliczono, w trzech przybliżeniach, na 2264 kg. Na zakończenie przedstawiono parametry geometryczne opracowanego samolotu treningowego, widok ogólny oraz geometrię.
Źródło:: Transactions on Aerospace Research; 2021, 2 (263); 30-45
0509-6669
2545-2835
Pojawia się w:: Transactions on Aerospace Research
Dostawca treści:: Biblioteka Nauki

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