Wyniki wyszukiwania - BazTech

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Układ automatycznego wykonywania manewru korkociągu

Pruchniak M., Rogalski T., Nowak D., Prusik J.

Autobusy : technika, eksploatacja, systemy transportowe

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2017

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R. 18, nr 12

1245--1251, CD

PL

W artykule przedstawiono koncepcję systemu automatycznego sterowania przeznaczonego dla małych samolotów załogowych i bezzałogowych, realizującego manewry inne, niż niezbędne do wykonywania tzw. normalnego lotu [3], których proces syntezy przedstawiono na przykład w pozycji [1, 4]. Charakter tych manewrów, zakres zmian parametrów lotu samolotu podczas ich wykonywania ograniczają zastosowanie klasycznych algorytmów sterowania. Niejednokrotnie, również ograniczają możliwość pozyskania pełnej informacji o parametrach lotu samolotu. W pracy przedstawiono alternatywne rozwiązanie, które w takich przypadkach, może zostać zastosowane [2, 9, 11]. Zaprezentowano strukturę algorytmów sterowania oraz metodę doboru współczynników regulatorów w nich występujących. Jako przykład wybrano manewr korkociągu, będący elementem akrobacji lotniczej Weryfikacja przyjętych założeń i otrzymanych wyników obliczeń została przeprowadzona w symulowanych lotach testowych a otrzymane przykładowe rezultaty zostały zamieszczone w końcowej części artykułu.

EN

The paper presents a concept of automatic control laws for unmanned aircraft control system. There is a general structure of algorithms controlling aircraft at nonconventional flight state presented in the paper. Authors apply their semi closed loop control algorithm for automatic flight during selected aerobatic maneuver (spin maneuver is selected). Moreover there are methods of control laws adjustment and tuning discussed in this paper. Theoretical discussion is supported by results achieved during simulated test flights.

2

Modal control approach to the test maneuver design for aircraft flight tests

Brusov V., Ovcharenko V.

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

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2001

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nr 11

25-28

EN

A problem of test maneuver design is discussed in the case of statically unstable aircraft. The results obtained can be applied to formulation of the control laws for an aircraft within a predetermined frequency range. There appears a kind of duality for such control laws, namely, an input signal stabilizes and disturbs the dynamic system states at the same time.

3

Dynamics of an aircraft augmented by direct control of aerodynamic forces and moments

Gouskov Y., Palyonov Y.

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

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2001

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nr 11

87-94

EN

In this paper the novel forms of aircraft motion are demonstrated, using the simultaneous control over the aerodynamic forces and moments. These forms are similar to the well known old forms, in which the phase coordinates are kept constant, using traditional central control stick and pedals. The maneuvering capabilities of these old forms of motion can be increased, if parallel to the abovementioned controls the additional command devices are used. Using these additional command devices, pilot can generate additional signals to improve the longitudinal and lateral control of motion. By such a control the maneuvers can be separated into pure translation and pure rotation. This paper discusses the control systems for these maneuvers. It is shown that by the coordinated deflection of all aerodynamic control surfaces the pure (force-less) torque and the pure (torque-less) force can be provided.

4

Application of the non-linear filtering method to determination an optimal control of aircraft manoeuvres

Goetzendorf-Grabowski T.

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

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2001

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nr 11

95-98

EN

The paper presents an application of the non-linear filtering method to determination the optimal control function of the aircraft manoeuvres. Theoretical grounds of the filtering problem and the main idea of its application for the identification problem were shown. The method, originally applied to a parametrical identification was adapted to determination a control function. A mathematical model of an aircraft flight was developed for considered case. Paper shows the results of a numerical example for a fire fighting aircraft. The calculation results concern control function determination and parametrical identification as well.

5

Application of the coupled Euler / flight dynamics model into analysisof a rapid pull-up manoeuvre

Goraj Z., Iglewski T.

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

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2000

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nr 10

113-120

EN

The Eater flow model for in viscid, compressible gas and the aircraft flight dynamics model were coupled to analyse rapid pull-up manoeuvre. The Euler flow equations were used to obtain aerodynamic forces and moments acting on a simplified aircraft configuration, considered as a rigid body. The McCormack predictor-corrector scheme for a finite differences representation was used as a numerical method for solving the Euler flow equations. The second order artificial viscosity was introduced to improve convergence of the scheme. Far field boundary conditions in the Euler model were determined from the steady state conditions of in the horizontal flight. Aircraft components in the body frame of were computed having known the of attack of the aircraft and its speed. The air density and pressure correspond to the height. From the boundary condition on the wing surface it follows that local flow vector is tangent to the local surface. 225200 grid points in five connected structural grid blocks in computations. The flight dynamics equations of motion were used to describe the aiecraft dynamics. No additional aerodynamic derivatives were considered. Some dynamic phenomena and damping effects (including hysteresis) were taken into account. In the simulation process both models were used and coupled by means of the mutual data transfer process. Any change of flight conditions immediately influences on the flow. Initial conditions for the flight dynamics equations of motion were settled up coming from the solutionof the Euler flow model for several cases of stationary flow. Only symmetrical motion and symmetrical airflow were examined. This makes it possible to use a grid for half of the aircraft only. The influence of the horizontal tailplane and fuselage on the main wing flow was neglected. The results of simulation (including flight path history, surface loading, aerodynamic forces and moments) were compared to those of classical approach, obtained from pure flight dynamics equations of motion.