Józef Pietrucha

The Comparative Evaluation of Power Requirements for Fixed, Rotary, and Flapping Wings Micro Air Vehicles

In this paper we describe power requirements for micro air vehicles. We have researched three flight modes: fixed wing, rotary wing and flapping wing. We have calculated energy and power requirements for the three flight modes. As we can excepted, when there is no hover requirement, fixed wing flight is always most energy efficient for the micro air vehicle. However, if there is a hover requirement, the suitability of flapping or rotary wing flight is dependent on the mission profile and ambient windspeed.

Comparative Evaluation of Power Requirements for Fixed, Rotary, and Flapping Wings Micro Air Vehicles

In this paper we describe power requirements for micro air vehicles. We have researched three flight modes: fixed wing, rotary wing and flapping wing. We have calculated energy and power requirements for the three flight modes. As we can excepted, when there is no hover requirement, fixed wing flight is always most energy efficient for the micro air vehicle. However, if there is a hover requirement, the suitability of flapping or rotary wing flight is dependent on the mission profile and ambient windspeed.

Comparative Analysis of Wing Rock Control

In this paper the application of modern control theory to modification of nonlinear systems behaviour is described. The features of this approach are analysed on the example of wing rock (WR) phenomenon. The main objective of our investigations was modification of WR characteristcs by active control technique. The following methods are described and evaluated: Pontryagin maximum principle; Lyapunov function method; non-linear inverse dynamics. The WR model is numerically treated for the generic fighter aircraft data. The results indicate that it is sufficient to use a linear feedback of state variables to suppress the WR motion.

Analysis of the Sensitivity of Aircraft Flight Control at High Angles of Attack

This paper contains the results of numerical analysis of the sensitivity of aircraft flight control on the mathematical model chosen. The control is designed using the non linear inverse dynamics method. Non -linear contro l laws have been synthesised for wing rock stabilisation. As an example the numerical simulation of the controlled motion is carried out employing the aerodynamic and mass data of the F -16 aircraft.

Numerical analysis of continuous models of structures in non-linear wind flow using the time-marching approach

Abstract This paper deals with the aeroelastic behavior of a flexible chimney undergoing transverse lift forces due to the vortex shedding. The chimney is modeled as a continuous beam having non-uniform distribution of parameters. The standard wake-oscillator model is used as the model of the vortex-induced response. Three levels of generalization of this model are presented: point force, continuous force and supplied by spanwise correlation. Numerical analysis of the models is performed by the simulation (time-marching) approach. The obtained results indicate that the classical phenomena, such as the locking and peak amplitude, did not appear. Instead, new effects, e.g., the reverse locking and multiperiodic motion have been observed. Therefore, experimental work is strongly recommended to verify the obtained results.