Wszystkie pola: WINGS - Katalog OPAC zbiorów

Skocz do pozycji: 1.

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: 2.

Tytuł:: Experimental analysis of aerodynamic performance of flapping wings nano aerial vehicles
Autorzy:: Czekałowski, P.
Drewniak, T.
Sibilski, K.
Żyluk, A.
Powiązania:: https://bibliotekanauki.pl/articles/243431.pdf
Data publikacji:: 2014
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: aerodynamic performance
flapping wings micro aerial vehicles
water tunnel measurements
Opis:: The aerodynamics of flapping wings is ultimately concerned with the relation between motion kinematics and the time-history of aerodynamic forces and moments. However, an important intermediate quantity is the evolution of the flow field – and in particular of flow separation. Nature’s solution to large time-varying pressure gradients, for example those due to aggressive motions, is to form and eventually to shed vortices. We are interested in understanding and exploiting these vortices – for example, in delaying vortex shedding to promote lift in situations where flow separation is in any case inevitable. From the engineering viewpoint, the question is to what extent closedform models and conventional numerical/analytical tools can estimate the aerodynamic force history, with an eye to eventually running large parameter studies and optimizations. Our paper contains results of water tunnel experiments on flapping wings aeromechanics. The idea of investigation is to optimize the wing trajectories, and to find methods providing stability and control. In the paper, we present, also, conception and methodology of tests. The investigation is dividing into two parts: preliminary and principal tests. The aim of initial part is to extract quasi – state characteristic for wings of different platforms shapes. This characteristic will be used to generate initial kinematics of movement of wing. It will be initial point of further tests. The purpose of the main experiment is to find the best way of movement for wing taking account all of unsteady phenomena (interaction between vortices, wing – wing interference, etc.). Finally, we want to identify efficient way of controlling nano-microelectromechanical flying insect (entomopter).
Źródło:: Journal of KONES; 2014, 21, 3; 47-57
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 3.

Tytuł:: Experimental study and neural network modelling of aerodynamic and dynamic characteristics of flapping wings micro aerial vehicle
Autorzy:: Czekałowski, P.
Sibilski, K.
Żyluk, A.
Powiązania:: https://bibliotekanauki.pl/articles/242331.pdf
Data publikacji:: 2018
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: entomopter
flapping wings
aerodynamics
neural network
modelling
aerodynamika
sieć neuronowa
modelowanie
Opis:: The article is close connected with building flying object, that fly like an insect (entomopter). Present work concerns on concept of aerodynamic model using artificial neural networks. Model is used in simulations of flight of entomopter. Aerodynamic model based on experimental data. Necessary data are taken from experiment performed in water tunnel on entomopter model. For this case dynamic test are required. Measurements are ducted during sinusoidal motion of whole model. Modelled object is dipterous. Each wing can perform various spherical motions (wing is rotated around point). The motion of the wing in this case was two-dimensional; it was rotated around two axis. As a model, specially trained neural network is used. For training are used data from measurement. Presented in this article approach is based on artificial neural networks. In this article, innovative concept of model, describing unsteady aerodynamics of entomopter was proposed. It was shown that it could be easily implemented as mathematical model. Unsteady effects related to many state variables can be easily captured. Model can be easily adopted to predict different states of flight by networks training on appropriate data. Test has to reproduce real conditions as close, as it is possible. In reality, it is challenging to design test that will reproduce similar motion.
Źródło:: Journal of KONES; 2018, 25, 4; 49-57
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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