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1

Analysis of possible modification of transport aircraft to medevac in the Czech Republic

Kozuba Jarosław, Piła Jan, Martinec František

Zeszyty Naukowe. Transport / Politechnika Śląska

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2023

|

z. 118

109--121

EN

With a growing number of coronavirus patients worldwide, military and civilian transport aircraft are increasingly being used for civilian medical evacuation duties (MEDEVAC) on time-critical flights. This article deals with the possibility of converting an aircraft fleet in the Czech Republic to MEDEVAC. The indication for the analysis of the possibility of transforming transport aircraft was the past and current pandemic situation in the Czech Republic. The main research question is how to implement the modification of a selected airline of the Czech Republic to MEDEVAC. An analysis of the technical data of selected aircraft from Airbus and Boeing was used to investigate this problem. Further, an analysis of the medical equipment required for the MEDEVAC aircraft category was also performed using equipment manufactured in the Czech Republic. The results obtained by the analysis and spatial arrangement of the aircraft deck for the transport of patients with medical equipment confirmed the possibility of such a transformation within the Czech Republic. We consider it important to elaborate on a project that would solve, in detail, all the steps of the conversion of a transport aircraft to MEDEVAC.

2

Development of a flight simulator for conceptual aircraft design and sizing

Hon Kai San, Karpuk Stanislav, Yang Daqing, Elham Ali

Transactions on Aerospace Research

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2022

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Nr 2 (267)

31--61

EN

This article describes the development of a flight simulator module within the ADEMAO aircraft design framework to investigate the effects of novel airframe and propulsion technologies on new generations of aircraft. Methods used to develop and integrate the fight simulator into the overall design framework are described. The simulator is validated based on existing data from the Convair CV-880M and is then used to analyze an example case of a conceptual medium-range aircraft with advanced airframe technologies designed in the Sustainable and Energy-Efficient Aviation research cluster at the Institute of Aircraft Design and Lightweight Structures at the Technische Universität Braunschweig. Results show the deficiencies of the medium-range aircraft in short-period pitch and Dutch roll performance, and recommendations for modifications to the conceptual medium-range aircraft are drafted.

3

The KhAI-90 Light Civil Turboprop Airplane Pilot Project

Grebenikov Oleksandr, Loginov Vasyl, Humennyi Andrii, Buival Liliia, Chumak Anton

Transactions on Aerospace Research

|

2021

|

Nr 4 (265)

21--40

EN

The pilot project of new light civil turboprop aircraft, called the KhAI-90, featuring a cruising speed of 350km/h, payload of 600 kg at 500 km range, and equipped with two turboprop Rolls-Royce 250-B17F engines each with power of 420 hp (alternatively, two AI-450C engines each with power of 450 hp may be installed) is presented herein. Based on the developed technical task, the concept for creating the KhAI-90 new competitive light civil aircraft, and the analysis of prototypes’ aircraft parameters and characteristics, the main tactical and technical requirements are assigned. The take-off weight of the new aircraft is determined in three approximations at the preliminary design stage of light civil turboprop aircraft, using the iterative software “CLA-TOW”, studying the influence of the wing geometric parameters and lift devices on aerodynamic performance, the power-to-weight ratio and the airplane weight parameters. The following parameters are calculated for the design: minimum takeoff weight WTO min = 3,600 kg, optimal wing loading p0 opt = 130 daN/m2 , optimal aspect ratio 9.6, taper ratio 2.25, sweep angle at leading edge 3 degrees, airfoil relative thickness 10.6%. A general view and three-dimensional parametric models of the master-geometry and passenger cabin space distribution are constructed for the KhAI-90 by means of the SIEMENS NX computer integrated system. More broadly, this pilot project has also demonstrated the viability of the method we developed and previously reported for determining light civil turboprop airplane parameters.

PL

Przedstawiono projekt pilotażowy nowego lekkiego cywilnego samolotu turbośmigłowego o nazwie KhAI-90, charakteryzującego się prędkością przelotową 350 km/h i ładownością 600 przy zasięgu 500 km, wyposażonego w dwa silniki turbośmigłowe Rolls-Royce 250-B17F, każdy o mocy 420 KM (alternatywnie w dwa silniki AI-450C, każdy o mocy 450 KM). Na podstawie ustalonego zadania technicznego, koncepcji stworzenia nowego wyczynowego lekkiego samolotu cywilnego KhAI-90 oraz analizy parametrów i charakterystyk prototypów samolotu określono główne wymagania taktyczno-techniczne. Masa startowa nowego samolotu określono w trzech przybliżeniach na etapie wstępnego projektowania lekkiego samolotu przy użyciu iteracyjnego oprogramowania „CLA-TOW” (analizując wpływ parametrów geometrycznych skrzydła i urządzeń nośnych na osiągi aerodynamiczne, stosunek mocy do masy i parametry masy samolotu). Obliczono następujące parametry projektu: minimalna masa startowa WTO min = 3600 kg, optymalne obciążenie skrzydła p0 opt = 130 daN/m2, optymalny współczynnik kształtu 9,6, współczynnik zbieżności 2,25, kąt natarcia na krawędzi natarcia 3 stopnie, grubość względna profilu 10,6%. Przedstawiono ogólny widok oraz trójwymiarowe modele parametryczne geometrii głównej i rozkładu przestrzeni kabiny pasażerskiej wygenerowane dla KhAI-90 za pomocą zintegrowanego systemu komputerowego SIEMENS NX. Niniejszy projekt pilotażowy wykazał również przydatność wcześniej opracowanej przez autorów metody określania parametrów lekkich cywilnych samolotów turbośmigłowych.

4

Analysis and conceptual design of micro class UAV for aerodesign international competition

Figur K., Lorenc W., Nykaza A.

Journal of KONES

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2017

|

Vol. 24, No. 1

129--135

EN

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).

5

Aerodynamic and mechanical design of micro class UAV for aerodesign international competition

Figur K., Lorenc W.

Journal of KONES

|

2017

|

Vol. 24, No. 1

137--141

EN

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.

6

Ocena wpływu zamontowanego silnika na obciążenia samolotu lekkiego

Cichocka E.

Prace Instytutu Lotnictwa

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2016

|

Nr 2 (243)

73--92

PL

W niniejszym artykule skupiono się na zbadaniu wpływu zamontowanego silnika na obciążenia statków powietrznych klasy General Aviation. Do analizy porównawczej wybrano samoloty różniące się jedynie typem zabudowanego zespołu napędowego, z których pierwszy jest certyfikowanym samolotem tłokowym, traktowanym jako obiekt odniesienia, natomiast drugi jest jego wersją rozwojową, wyposażoną w silnik turbośmigłowy. Dla każdego z płatowców rozważono łącznie ponad tysiąc przypadków obliczeniowych zgodnych z wymaganiami przepisów budowy samolotów lekkich. Założonym celem było zapewnienie, aby ekstremalne obciążenia konstrukcji turbośmigłowej zawierały się w obwiedni krytycznych przypadków obciążeń płatowca z napędem typu bokser, a w przypadku przekroczenia referencyjnego poziomu dopuszczalnych sił i momentów sił. zaproponowanie stosownych ograniczeń eksploatacyjnych. Wymóg ten podyktowany był celami i ograniczeniami projektu, w ramach którego zrealizowana została modernizacja konstrukcyjna wybranego statku powietrznego. Stąd. ustanowiono, że w zadanym reżimie czasowym i budżetowym samolot z nową jednostką napędową musi spehiić przepisy budowy lekkich samolotów i uzyskać dopuszczenie do lotu bez konieczności przeprowadzenia szeregu prób jako dowodu zgodności z wymaganiami przyjętej bazy certyfikacyjnej. Syntezę pracy stanowi ocena uzyskanych rezultatów i sformułowanie wniosków dotyczących skutków zamiany silnika tłokowego na turbinowy na lekkim samolocie celem poprawy jego osiągów i własności lotnych przy zachowaniu obciążeń.

EN

This paper focuses on examining the effects of the mounted engine type on General Aviation airplane loads. For comparative analysis two airplanes, different from each other only by the type of power unit, were selected. The first is certified piston engine powered airplane, treated as the reference object, whereas the other one is its turbopropeller version. For each of them, more than a thousand computational cases were considered to prove fulfilment of all the airworthiness requirements for light airplanes. The assumed goal was to ensure that extreme structural loads of turboprop airplane are contained within the envelope of critical loads of airplane powered by boxer engine, or to propose appropriate operational limitations in the case forces and torques exceed the permissible reference level. This requirement was dictated by the objectives and constraints of the project, under which modernization of the airplane nose section was realized. Hence, it was assumed that, within available time and budget, the airplane with a different type of engine have to meet the light aircraft regulations and gam permission to fly without the need to perform a number of experimental tests as a proof of compliance with the certification specifications. Summary of the work is the evaluation of the results and formulating conclusions of the effect of changing from piston engine to turbine engine in light airplane in order to improve in-flight performance and properties while keeping structural loads at the same level.

7

Conceptual and aerodynamic study of a highlymanoeuvrable jet trainer

Kubrynski K.

Journal of KONES

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2016

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Vol. 23, No. 4

245--252

EN

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.

8

Design and Optimisation of Fuel Tanks for BWB Configurations

Goraj Z.

Archive of Mechanical Engineering

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2016

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Vol. LXIII, nr 4

605--617

EN

This paper describes assumptions, goals, methods, results and conclusions related to fuel tank arrangement of a flying wing passenger airplane configuration. A short overview of various fuel tank systems in use today of different types of aircraft is treated as a starting point for designing a fuel tank system to be used on very large passenger airplanes. These systems may be used to move fuel around the aircraft to keep the centre of gravity within acceptable limits, to maintain pitch and lateral balance and stability. With increasing aircraft speed, the centre of lift moves aft, and for trimming the elevator or trimmer must be used thereby increasing aircraft drag. To avoid this, the centre of gravity can be shifted by pumping fuel from forward to aft tanks. The lesson learnt from this is applied to minimise trim drag by moving the fuel along the airplane. Such a task can be done within coming days if we know the minimum drag versus CG position and weight value. The main part of the paper is devoted to wing bending moment distribution. A number of arrangements of fuel in airplane tanks are investigated and a scenario of refuelling – minimising the root bending moments – is presented. These results were obtained under the assumption that aircraft is in long range flight (14 hours), CL is constant and equal to 0.279, Specific Fuel Consumption is also constant and that overall fuel consumption is equal to 20 tons per 1 hour. It was found that the average stress level in wing structure is lower if refuelling starts from fuel tanks located closer to longitudinal plane of symmetry. It can influence the rate of fatigue.

PL

W pracy przedstawiono założenia, cele, metody, wyniki i wnioski dotyczące układu zbiorników paliwowych dla projektu samolotu pasażerskiego w konfiguracji BWB, t.j. kadłuba przechodzącego płynnie w skrzydło. Zamieszczono krótki przegląd współczesnych układów zbiorników paliwowych, które mogą stanowić punkt wyjściowy do projektu systemu paliwowego dla dużych samolotów pasażerskich. Takie systemy powinny umożliwiać przepompowywanie paliwa w celu zachowania położenia środka masy samolotu w akceptowalnych granicach, ze względu na warunki równowagi oraz stateczności samolotu. Wraz ze wzrostem prędkości środek parcia przesuwa się do tyłu samolotu i dla zachowania równowagi podłużnej zmianie ulega wychylenie sterów wysokości, trymera lub tzw. elewonów. Aby uniknąć nadmiernego wzrostu oporów wyważenia paliwo powinno być przepompowywane ze zbiorników położonych z przodu do zbiorników położonych w tylnej części samolotu. W tym celu obliczono zmianę oporu minimalnego w funkcji położenia środka masy i ciężaru samolotu. Główna część pracy jest poświęcona analizie rozkładu momentów gnących skrzydła w funkcji wypełnienia zbiorników paliwowych. Zbadano kilkanaście różnych wariantów wypompowywania paliwa ze zbiorników umieszczonych w skrzydle i zminimalizowano wartości momentów gnących u nasady skrzydła. Optymalizacje przeprowadzono przy założeniu, że samolot wykonuje długotrwały lot (14 godzin), ze współczynnikiem siły nośnej CL = 0:279 i przy stałym jednostkowym zużyciu paliwa (SFC = 20 ton na 1 godz = const). Stwierdzono, że średni poziom naprężeń w strukturze dźwigara głównego skrzydła jest najmniejszy jeżeli wypompowywanie paliwa rozpocznie się od zbiorników zlokalizowanych jak najbliżej pionowej płaszczyzny symetrii samolotu, czyli u nasady skrzydeł. Minimalizacja naprężeń może mieć istotny wpływ na zmniejszenie zmęczenia dźwigarów.

9

Zużycie zasobów w cyklu życia konstrukcji: samolot, samochód

Pokorski M.

Prace Instytutu Lotnictwa

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2010

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Nr 4 (206)

124-135

PL

W pracy przedstawiono analizę zużycia zasobów w cyklu życia konstrukcji, dla samolotu i samochodu, takich jak: energia, materiały, woda. Analiza uwzględnia głównie fazy produkcji i eksploatacji. A także emisję powstających zanieczyszczeń: odpady wyrzucane, ścieki, dwutlenek węgla (CO2) i lotne pochodne węglowodorów (VOC). Wyniki prezentowane są w formie porównania samolotu do samochodu w przeliczeniu na pasażero-kilometr.

EN

The elaboration presents analysis of resources consumption within life cycle for an airplane and a car, such as: energy, materials and water. The analysis takes under account production and operating phases, mainly. Also pollution emission of wastes to landfill, water discharge, Carbon Dioxide (CO2) and Volatile Organic Compounds (VOC). Results are presented as comparison airplane to car recalculated per passenger-kilometer.

10

Metody prognozowania rozwoju obiektu na etapie projektowania statków powietrznych

Kachel S., Kozakiewicz A.

Prace Instytutu Lotnictwa

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2010

|

Nr 4 (206)

72-83

PL

W artykule zaprezentowano podstawy metodyki prognozowania rozwoju, zmiany kluczowych parametrów eksploatowanych samolotów i zespołów napędowych, których techniczny i technologiczny rozwój wskazuje nowe drogi w procesie projektowania i optymalizacji konstrukcji lotniczych. Przedstawiono metodyczne podejście do tworzenia dynamicznych szeregów rozwoju obiektów, ich głównych parametrów niosących niezbędne informacje eliminujące błędne kierunki w procesie projektowania i modernizacji struktur lotniczych.

EN

In the article one presented bases of the methodologies of prognosings of the development, the change of key-parameters of exploited aircrafts and propulsive complexes whose the technical and technological development indicates new ways in the process of the designing and the optimization of air-constructions. One introduced the methodical approach to the creation of dynamic row of the development of objects, their main parameters carrying the necessary information eliminating incorrect directions in the process of the designing and the modernization of air-structures.

11

Zastosowanie inżynierii odwrotnej do procesu optymalizacji projektowania łopatek turbinowych

Kachel S., Kozakiewicz A.

Biuletyn Wojskowej Akademii Technicznej

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2010

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Vol. 59, nr 3

171-200

PL

W artykule zaprezentowano metodykę optymalizacji projektowania elementów lotniczego silnika turbinowego na przykładzie łopatki turbinowej silnika RD-33. Przedstawiono osobliwości projektowania lotniczego silnika turbinowego i jego zespołów. Opracowano algorytmy w języku GRIP (Graphics Interactive Programming) dla systemu CAD/CAM/CAE Unigraphics. Przeprowadzono dyskusję na temat doboru krzywych do parametrycznego modelowania z uwzględnieniem wejść do wielokryterialnej optymalizacji odtwarzania powierzchni, bazując na technice inżynierii odwrotnej. Przedstawiono proces odwzorowania geometrii od etapu wykonania precyzyjnych pomiarów, identyfikacji danych, weryfikacji krzywych, aż do utworzenia bryły modelowanego obiektu. W pracy zawarto założenia opracowanych przez autorów i zastosowanych algorytmów modelowania elementów struktur lotniczych.

EN

In the work, a method for facilitation of the jet turbine engine design in the CAD/CAMCAE environment was presented (the jet RD-33 was selected as an example). The recommended method utilizes, specially elaborated by the authors, algorithms written in the GRIP (Graphics Interactive Programming) language exclusively for the CAD/CAM/CAE Unigraphics system needs. Evaluation of the curves and surfaces for the parametric modeling, including the entrances into multi criterion optimisation of the curves for airfoils recreation on the base of the reverse engineering techniques, was done. Process of the geometry elaboration from early stage of the precise measurements, through data verification, and curves validation to the final stage of the wane body faces creation was presented as well as the algorithms elaborated by the authors.

12

Structural weight estimation of a flying wing with a pressurized wing box

Rodriquez C., Martinez-Val R., Gutierrez L.

Research Bulletin / Warsaw University of Technology, Institute of Aeronautics and Applied Mechanics

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2000

|

nr 10

177-182

EN

The present paper will introduce a prediction method that will allow for estimation of the structural weight of a transport flying with an approximate capacity of 300 passengers. The flying wing payload will be located between the front and rear spars, and up to half the span approximately, which implies that the study of the wing structure will have two different parts; i.e., the external structure that will be of conventional architecture apart from its dimensions that will be bigger and the internal structure, no conventional, where the torsion box will be pressurized and with all the equipment required for passenger and, cargo transportation.

13

Advanced flow simulation methods in aircraft design

Sillen M.

Research Bulletin / Warsaw University of Technology, Institute of Aeronautics and Applied Mechanics

|

2000

|

nr 10

183-190

EN

Computational Fluid Dynamics is an important tool in the aerodynamic design and analysis process. The continuous increase in computer speed and algorithm efficiency offers the aerospace industry a possibility to deploy increasingly more advanced numerical methods early in the design process. The flow modelling methods at Saab Aerospace have been developed to meet the requirements of short tum'around'time problem and advanced physical of viscous flow for applications in the aerospace field. The presented improvements focus on two main aspects, the efficient use of parallel computers and turbulence modelling. A load balancing method is described how to partition a structured multi-block grid for efficient use of parallel computers. The prevailing turbulence models employed In the design process in the aerospace industry today range from simple algebraic models through to linear eddy viscosity models. Initial at Saab Aerospace using an Explicit Algebraic Reynolds Stress Model (EARSM) on the k-o) transport equations is presented. A non-linear stress/strain relationship in the EARSM offers improved physical modelling of turbulent flow. A number of viscous flow examples on complex configurations, including a complete aircraft are presented in the paper.

14

Vortex wake safety - the problem of encountering aircraft

Mikhailov Y., Vyshinsky V.

Research Bulletin / Warsaw University of Technology, Institute of Aeronautics and Applied Mechanics

|

1999

|

nr 9

91-100

EN

When flying through the atmosphere an aircraft generates a stable vortex wake posing a hazard for other aircraft. A sudden path disturbance caused by the trailing turbulence is most dangerous at low altitudes due to a possible collision with the ground. Encountering an intensive wake may lead to a strctural failure. Maintaining safe-separation distances reduces airport capacity and eventually results in economic losses. To solve this problem on a rational basis, it is necessary to create an adequate aerodynamic vortex wake model and determine wake characteristics as well as create a flight-dynamic and structural-strength models for the trailing turbulence conditions, determine, aircraft response, and work out on this basis concrete measures aimed at enhancing airport capacity. All tree issues and especially means for increasing aircraft controllability are briefly considered in the present paper.

15

Preliminary design of an ASTOVL strike-fighter

Serghides V.

Research Bulletin / Warsaw University of Technology, Institute of Aeronautics and Applied Mechanics

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1999

|

nr 9

127-134

EN

The paper presents the Imperial ASF-94A, an advanced short take-off, vertical landing (ASTOVL) strike-fighter design concept. This was originally developed by the author in September 1994, at Imperial College and then became the subject of an eight-month preliminary design study, by a large group of students in the department of Aeronautics. The aircraft was designed primarily for the air superiority role, but with also a good offensive support capability. It is a single-seat, single-engine design, featuring a low-observables configuration with an arrowwing and an all-moving close-coupled foreplane, V-tail, twin diamond intakes and internal weapon bays. Clean configuration aerodynamics and lightweight structural design together with thrust from a powerful, advanced, low bypass ratio, reheated turbofan with a limited single-axis thrust vectoring nozzle and a remote lift-fan, produced a highly effective and manoeuvrable combat with short take-off, vertical landing and high angle-of-attack capabilities. Low ground support, rapid turnaround and enhanced maintainability features where also incorporated in the ASF-94A, from the earliest stages of its design in order to develop a configuration with high overall operational effectiveness. This paper aims to provide a technical description of the ASF-94A and its operational performance and to discuss the design challenges encountered in the development of this innovative concept.

16

Functional approach to the general scheme synthesis

Malchevky V.

Research Bulletin / Warsaw University of Technology, Institute of Aeronautics and Applied Mechanics

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1999

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nr 9

85-90

EN

Two making processes of an aircraft design - stages of structural and parametric synthesis are investigated. It is indicated that structural synthesis and it's milestone - synthesis of an aircraft scheme are principal for reaching effective operation of the vehicle. Instead of the conventional structurally modular approach to a classification of elements of an aircraft the new functional approach is offered which more full to use internal resources of a created technical system and to increase efficiency of an airplane by a combination and adjustment of element's functions. It's shown, that in the basis of new effective aircraft schemes creation is the process of the sanction of technical contradictions; the formal ways of the sanction of these contradictions and, in particular, method of supplying of an 'intellectual supports' to the designer with the help of specialized consulting models are offered.