Temat: aircraft design - Katalog OPAC zbiorów

Skocz do pozycji: 1.

Tytuł:: Conceptual and aerodynamic study of a highlymanoeuvrable jet trainer
Autorzy:: Kubrynski, K.
Powiązania:: https://bibliotekanauki.pl/articles/245019.pdf
Data publikacji:: 2016
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: aerodynamics
aerodynamic project
high angle of attack
manoeuvrability
aircraft design
Opis:: The article discusses the initial study of the two-seat jet trainer with high manoeuvrability. The study included the concept of structural layout of the aircraft, as well as the development of its aerodynamics. The mail aim was to ensure the correct airplane characteristics (in particular control efficiency and dynamic properties) in the wide range of angles of attack. Another challenge was to ensure adequate aerodynamic characteristics at high transonic speed range. The geometry of the aircraft has been developed using CAD system (Simens NX). Initial aerodynamic study and aerodynamic design of the plane were performed using both: the low speed wind tunnel tests performed at Warsaw University of Technology using six-component internal balance and computational work performed using ANSYS CFX computer system. The first was used mainly to check characteristics at high angles of attack. Modifications of the wind tunnel model geometry at this stage were performed using the plastic mass (plasticine), or replacing some components of the model. An important problem with such approach was the lack of a precise definition of the revised geometry in the CAD system. Computational study was performed mainly to check high-speed characteristics. The final geometry of the modified wind tunnel model generally meets the requirements.
Źródło:: Journal of KONES; 2016, 23, 4; 245-252
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 2.

Tytuł:: Aerodynamic and mechanical design of micro class UAV for aerodesign international competition
Autorzy:: Figur, K.
Lorenc, W.
Powiązania:: https://bibliotekanauki.pl/articles/950097.pdf
Data publikacji:: 2017
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: unmanned aerial vehicles
drone
Aero Design
aircraft design
bezzałogowy statek powietrzny
dron
projekt samolotu
Opis:: Aero Design is an annual student competition held by Society of Automotive Engineers in which the goal is to design and build a flying UAV capable of lifting the highest payload while observing lowest payload weight and fitting in a specified carrying case. The most important aspect in aircraft design is choosing suitable aerodynamic and mechanical configurations for example: aircraft and wing layout, airfoil with the correct Reynolds (in this case low) number, airframe, and landing gear construction. The article presents airfoil selection, trade studies, tail aerodynamic design, tail sizing, drag analysis, calculations of stability, stress analysis, propulsion selection and manufacturing of UAV prototype. In particular, the comparison of different aircraft designs, effect of taper ratio on lift distribution, the design of wings, lift vs. angle of attack curves and. angle of attack curves, the aircraft tail surfaces, fuselage design are presented in the article. The aim of this study was to perform analysis of aerodynamic and mechanical of Micro Class UAV for Aerodesign International Competition. All projects will be doing in a prototype technology demonstrator was built to confirm our assumptions about airfoil's performance. Flight tests were successful. Analytical model was made and put into an excel spreadsheet. Maximum predicted payload was estimated to be 5.5 pounds.
Źródło:: Journal of KONES; 2017, 24, 1; 137-141
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 3.

Tytuł:: Analysis and conceptual design of micro class UAV for aerodesign international competition
Autorzy:: Figur, K.
Lorenc, W.
Nykaza, A.
Powiązania:: https://bibliotekanauki.pl/articles/242812.pdf
Data publikacji:: 2017
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: UAV
unmanned aerial vehicle
drone
analysis
aircraft design
bezzałogowy statek powietrzny
dron
analiza
projekt samolotu
Opis:: Aero Design is an annual student competition held by Society of Automotive Engineers in which the goal is to design and build a flying UAV capable of lifting the highest payload while observing lowest payload weight and fitting in a specified carrying case. To achieve that task teams have to choose between conflicting objectives that are lowest empty weight and highest lifting capacity. The rules state that design to enter the competition must be a fixed wing aircraft fitting in a box with inside dimensions of 24x18x8 inches. The payload bay has to be a rectangular block measuring 5x2x2 inches. There also is a limit of 55 pounds total weight with payload. The aircraft must take of either by hand launch or be propelled using a rubber tubing, than do a 360-degree circuit of the flying field and finally land within 200 feet landing zone. The article presents requirements analysis, weather research, design research, considered about launch method, wing layout and aircraft layout study (napkin sketches).
Źródło:: Journal of KONES; 2017, 24, 1; 129-135
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 4.

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: 5.

Tytuł:: Design and optimisation of exhaust system of light turboprop airplane
Autorzy:: Stalewski, W.
Powiązania:: https://bibliotekanauki.pl/articles/247804.pdf
Data publikacji:: 2016
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: turboprop aircraft
exhaust system
ejector
computer-aided design
optimisation
Opis:: Innovative exhaust system for light turboprop airplane has been developed and optimised. Apart from the basic function of removing exhaust from turboprop engine, the system supports cooling of the engine bay. To do this, the system removes hot air from the engine bay, utilising the ejector-pump effect, where the exhaust stream generates under-pressure, sucking the hot air through the ejector slot and removes the air together with the exhaust gases. The design and optimisation of the exhaust system has been conducted based on computational methods of Computer-Aided Design and Optimisation and Computational Fluid Dynamic. Three-dimensional analysis of flow around the airplane (including effect of propeller) and inside the exhaust system was conducted by application of URANS solver ANSYS FLUENT. Using these software the trajectories of exhaust particles, both inside the exhaust ducts and outside the airplane, have been determined. Parametric model of the designed exhaust system has been developed using the in-house software PARADES. As design parameters the diameter, length and direction of exhaust ducts as well as few parameters describing a shape of the ejector, have been established. The optimisation process aimed at designing of the exhaust system, which removes the exhaust gases possibly far away from the airframe, especially during a descent flight of the airplane. Additional objectives were maximisation of the mass flow rate of hot air sucked through the ejector and minimisation of the drag force generated by external part of the exhaust system. The optimised exhaust system should have also fulfilled requirements of permissible total-pressure losses inside the exhaust ducts. The optimised exhaust system has been implemented on the light turboprop airplane and validated during flight tests.
Źródło:: Journal of KONES; 2016, 23, 2; 341-348
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 6.

Tytuł:: Conceptual design of blended wing body business jet aircraft
Autorzy:: Mulyanto, T.
Luthfi Imam Nurhakim, M.
Powiązania:: https://bibliotekanauki.pl/articles/242317.pdf
Data publikacji:: 2013
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: transport
business jet aircraft
blended wing body
conceptual design
Opis:: Blended Wing Body concept offers several advantages compared to traditional aircraft tube and wing concept. The advantages mainly come from the distributed aerodynamic and structural loads, which leads to better aerodynamic performance as well as lighter structural weight. Most of the existing studies were focused on big transport aircraft carrying 400 to 800 passenger. In this study, a conceptual design of a business jet aircraft applying blended wing body concept is carried out. The market forecast for this category of aircraft can reach up to 24000 aircraft in the next 20 years. The possibility of having larger cross section is one of the competitive advantages, notably in a long-range flight. The requirement stated was to fly a trans-atlantic flight and carrying up to 18 passengers. It has to have a low floor height permitting easy passenger access. The design process consists of initial weight estimation, initial sizing, and preliminary aerodynamics, weight and balance and performance analysis. Some design consideration specially related with Blended Wing Body concept will be discussed, i.e. take-off and landing aerodynamics, structural concept, stability and control. The final design resulted in twin-engine aircraft, a Maximum Take-off Weight of 44 ton, cabin floor area of 6.9 x 10 m, winglet and split rudder for directional stability and control, and elevons for longitudinal and lateral control.
Źródło:: Journal of KONES; 2013, 20, 4; 299-306
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 7.

Tytuł:: The influence of multi - role aircraft mission type on the low bypass engine performance parameters
Autorzy:: Wygonik, P.
Powiązania:: https://bibliotekanauki.pl/articles/242065.pdf
Data publikacji:: 2013
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: gas turbine engine design
airplane-engine integration
aircraft mission optimization
Opis:: The aim of the article is to find the relationship and dependencies between the mission parameters of the multi-role aircraft (altitude, flight velocity, thrust load) and the parameters that define the flow of the turbofan engine. The conclusions of these studies are relevant at the stage of preliminary engine design. There was built the model of thermal cycle of low bypass. The model of an airplane was simplified to its aerodynamic characteristics. The mission was divided into air tasks (stages) such as a take-off, a climb at a certain velocity, sub and supersonic flight and maneuvers (i.e. turn). Dimensionless energy criteria binding both the engine and aircraft parameters were introduced. There were conducted the simulation studies of the model airplane-engine mission to show the part of the mission that "dimensions " the engine. The results were limited to the presentation of the impact of circuit parameters such as T3, π, μ on the defined criteria. The calculations were carried out for a number of selected missions defined in the literature as Loll, HiLoHi and HiHiHi. The comparison of the energy requirements of these missions was done. There were pointed out these criteria of the mission evaluation that may affect making decisions at early design stages. There were designated the areas of design variability in an engine meeting the criteria for energy mission. The advantage of this model is universal character of dimensionless criteria, whereas the disadvantage is the need to build complex models of the engine and the assumption at the outset aerodynamic characteristics of the aircraft. The originality of the presented solution is to show an alternative, unconventional approach to the design process (not as so far) the engine itself but the entire aviation system.
Źródło:: Journal of KONES; 2013, 20, 3; 435-442
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 8.

Tytuł:: Influence of the gas turbine engine design parameters on the energy consumption of the multirole aircraft missions
Autorzy:: Wygonik, P.
Powiązania:: https://bibliotekanauki.pl/articles/246706.pdf
Data publikacji:: 2012
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: gas turbine engine design
simulation
airplane-engine integration
aircraft mission optimization
Opis:: In the article the analysis of the influence of design parameters of the engine on the performed by the multirole aircraft mission was performed. The problem is complex as a result of performing a series of manoeuvres in various conditions of flight. A special feature of multi-role aircraft mission is a sudden (even pulse) weight change and exactly its reduction as a result of the discharge of cargo bomb, rocket or due to the consumption of ammunition during air combat manoeuvring. Reducing the airplane mass by the weight of the fuel consumed (continuously) and the used weapons radically differ the demands on the energy required to overcome gravity and drag forces. The article shows how the reduction of the aircraft mass influences on the change of the thrust load factor. It was built the mathematical model of the system engine-aircraft-air job (taking into account the flight conditions, elements of the mission - subsonic and supersonic flight, flight time, the heat-and-gasdynamic and mass model of the engine). The model enables for the simulation research of the complex flight missions and their evaluation on the basis of the constructed criteria. The model includes a parametric description of physical processes in the turbofan engine, thus provides a direct assessment of the impact of selection of engine parameters on the effectiveness of the mission. The results of calculations according to classical criteria (e.g. kilometre fuel consumption, specific fuel consumption) were presented. The paper presents new criteria, which enable to analyze the energy consumption of the complex mission of the aircraft (e.g. energy consumption: the unit range, the degree of utilization of energy resources and the carried out the mission engine). Criteria were built in by combining the parameters necessary for the flight with disposable ones. On the basis of these parameters there was done an assessment of the "quantitative" adjustment of a power unit to various missions such as subsonic, supersonic and mixed (for different their proportion), for different levels and the plane range. The results were presented in a pictorial way on numerous charts.
Źródło:: Journal of KONES; 2012, 19, 2; 569-576
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 9.

Tytuł:: Potencjalne źródła zagrożeń w procesie projektowania i konstruowania statków powietrznych
Potential sources of threats in the designing and constructing process of aircrafts
Autorzy:: Uchman, Zbigniew
Powiązania:: https://bibliotekanauki.pl/articles/38952432.pdf
Data publikacji:: 2023
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: statek powietrzny
bezpieczeństwo
projektowanie
wypadek lotniczy
aircraft
safety
design
aviation accident
Opis:: Najwyższym priorytetem w lotnictwie jest bezpieczeństwo. Przewozy lotnicze należą do najbardziej bezpiecznych środków transportu. Jest to efekt nieustannych działań mających na celu eliminację źródeł potencjalnych zagrożeń we wszystkich obszarach związanych z wykonywaniem operacji lotniczych. Kluczowa rola w tej mierze przypada producentowi statku powietrznego (SP). To on odpowiada za projekt i konstrukcję nowo budowanego samolotu lub śmigłowca oraz za proces jego produkcji. Na nim spoczywa obowiązek prowadzenia nadzoru nad przebiegiem eksploatacji. W artykule zdefiniowano źródła potencjalnych zagrożeń dla bezpieczeństwa operacji lotniczych, które leżą w zakresie kompetencji producenta SP. Należą do nich m.in. błędy w projektowaniu i konstruowaniu, wady produkcyjne, niewłaściwe prowadzenie badań i prób dowodowych, błędy i braki w dokumentacji opisowo-eksploatacyjnej i programach szkolenia, a także niedostateczny nadzór nad procesem eksploatacji. W artykule omówiono potencjalne źródła zagrożeń związanych z fazą projektowania i konstruowania statku powietrznego, a także przedstawiono przykłady błędów i zaniedbań w tej dziedzinie. Zawarte w artykule wnioski są wynikiem autorskiej analizy ponad 250 niebezpiecznych zdarzeń we współczesnym lotnictwie komunikacyjnym. Materiałami źródłowymi były protokoły z badania przyczyn analizowanych wypadków.
Safety is the top priority in aviation. Air transport is one of the safest means of transport. This is the result of continuous activities aimed at eliminating sources of potential threats in all areas related to the performance of aviation operations. The key role in this respect belongs to the aircraft manufacturer. He is responsible for the design and construction of a newly built aircraft or helicopter and for its production process. He is responsible for supervising the operation. The article defines the sources of potential threats to the safety of air operations that lie within the manufacturer's competence. They include e.g. errors in design and construction, manufacturing defects, improper conduct of tests and proof tests, errors and deficiencies in the descriptive and operational documentation and training programs, as well as insufficient supervision over the operation process. The article discusses the potential sources of threats related to the design and construction phase of the aircraft, and also presents examples of errors and omissions in this field. The conclusions contained in the article are the result of the author's analysis of over 250 dangerous events that have taken place in modern commercial aviation. The source materials were protocols from the investigation of the causes of the analyzed accidents.
Źródło:: Journal of KONBiN; 2023, 53, 4; 43-59
1895-8281
2083-4608
Pojawia się w:: Journal of KONBiN
Dostawca treści:: Biblioteka Nauki

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