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The influence of the development of private air communication on the architecture and urban planning of the 21st century

Szczepański J., Szuta A. F.

Technical Transactions

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2018

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Vol. 115, iss. 7

61--73

EN

In the first part, the article describes the stages of the development of gyroplanes and the influence of wartime policy on the interest in light aircraft. Also presented are links and the possibilities of using gyroplanes in various sectors of the economy. The authors, based on source texts, present the current position of the aviation industry in the Polish economy and attempt to diagnose its development capabilities. As a result, factors responsible for the current condition of the light aviation industry and its links with architecture and urban planning are submitted. The question is posed: what consequences will the development of the aviation industry bring for architecture and urban planning, for the community and the image of 21st century cities?

PL

Niniejszy artykuł w pierwszej części przybliża etapy rozwoju wiatrakowców oraz ukazuje wpływ polityki czasów wojennych na zainteresowanie lekkimi statkami powietrznymi. Przedstawione zostają również powiązania oraz możliwości wykorzystywania wiatrakowców w różnych sektorach gospodarki. Autorzy, na podstawie tekstów źródłowych, ukazują aktualną pozycję przemysłu lotniczego w polskiej gospodarce i podejmują próbę diagnozy jego możliwości rozwojowych. W efekcie zidentyfikowane zostają czynniki oddziałujące na obecny stan przemysłu lotnictwa lekkiego oraz jego powiązania z architekturą i urbanistyką. Otwarte więc jest pytanie: jakie konsekwencje przyniesie rozwój przemysłu lotniczego dla architektury i urbanistyki, dla społeczności i obrazu miast XXI wieku?

2

The science of operating processes as the branch of knowledge dealing with operating the aeroplanes and helicopters

Lewitowicz J.

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

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2001

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nr 11

145-148

EN

Operating the technical objects has become inherent in life of modem societies. Therefore, there is no doubt that attention should be paid to this field as related to products of the theory of machines (TMM). The branch of knowledge called the science of operating processes deals with these matters, as opposed to engineering of operating processes, of aimed at putting this knowledge into practice. Papers shows the sequence of the so-called phases of life of a technical object (OT), locations of the science of operating processes, of engineering of operating processes and of some exemplary interrelations and requirements to be met. The paper has been prepared with the purpose of emphasising significance of the operational knowledge as the separate branch called the science of operating processes. Aiming at uniformity of applying theory, principles and laws to all forms of technical objects seems to be an inevitable necessity.

3

Development of modern comprehensive computer software for rotorcraft aeromechanical analysis

Narkiewicz J.

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

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2001

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nr 12

7-12

EN

A helicopter model developed by the Helicopter Mechanics Research Group at Warsaw University of Technology is presented. The model comprises main and tail rotors, fuselage and horizontal stabiliser. The model was used for investigating an influence of various factors on helicopter and rotors motion. The sample results of calculations may be used for explanation of aeromachanical phenomena in rotorcraft.

4

Helicopter flight envelope extending while performing manoeuvres at low flight velocities

Szumański K., Bereżański J., Szumański A.

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

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2000

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nr 10

203-210

EN

The paper deals with the problem of helicopter flight mechanics at low flight speeds. The purpose of performed analysis is to achieve possibility of helicopter angular position control within wide range of angular displacement. This is performed by linear and centrifugal acceleration control. Rotor thrust vector control makes those accelerations appear.

5

Optimization of aerodynamic design of human powered helicopter

Popela R.

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

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1999

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nr 9

207-210

EN

This paper deals with the application of genetic algorithm as an optimization technique to the aerodynamic design of helicopter rotor. A special kind of helicopter, human powered helicopter, is optimized as a test case. The main result of this work is a development of aerodynamic optimization tool for helicopter rotors and propellers.

6

Numerical design and optimization of new generation main and tail rotors blade airfoils

Kania W., Stalewski W., Godlewski J.

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

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1999

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nr 9

31-38

EN

A numerical study on the design of new generation main and tail rotors blade airfoils has been undertaken to develop advanced rotors for helicopters. Design criteria and objectives for the root and tip main rotor blade airfoils are discussed based on the mission requirements and today's state of the art. The tail rotor airfoil design was aimed specifically to obtain Cmax in the Mach number range up to 0.5 higher than conventional airfoils. Aerodynamic inverse, optimization and analysis methods used in the design process are described. The subsonic and transonic code (MSES) based on the Euler equations and the boundary layer with simulation of the separation effects was extensively used in the design procedure to satisfy the design criteria and to achieve the design goals. The - aerodynamic characteristics of the designed main rotor blade with 12%, 9% and 8% thickness are compared to the third generation advanced rotor blade airfoil family VR12-VR14 of Boeing. This comparison shows the benefits of the new airfoils. Presented effort led to a new tail rotor section design that offered a 38%-48% increase in Cimax in the Mach number range of 0.4-0.5.

7

Comparison of the ground and in-flight helicopter vibrations testing

Uhl T., Lisowski W., Wasilak A., Auweraer H., Hermans L.

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

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1999

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nr 9

157-162

EN

This paper presents an approach to aircraft airframe structural vibration testing in both the ground and the flight conditions. The main objective of the research was to investigate the applicability of the selected experimental method and the identification algorithm for the description of the operational conditions structural vibration. For comparison purpose a set of the reference modal models obtained for the ground conditions was The in-flight testing measurement of acceleration of the selected airframe points was for different flight conditions. Identification of the structural dynamics model was carried out with use of the Least Squares Complex Exponential applied for the correlation functions from the recorded tested object output In the paper an overview of the ground and the in-flight vibration testing of a helicopter airframe is given. Main results of the both experiments are and compared. It should be noted that not only the natural frequency values but also mode for flight conditions were identified. The obtained results indicated the difference between the identified modal model for the ground and the inflight conditions as well as the actual structural vibration contribution to the tested helicopter operational vibrations.