Wyniki wyszukiwania - BazTech

1

Studies and tests of micro aerial vehicle during flight

Kowalski M., Zyluk A., Sibilski K.

Journal of KONES

|

2015

|

Vol. 22, No. 4

155--162

EN

The article presents the results of flight tests of an unmanned flying device based on a model Micro Air Vehicle (MAV). The airplane was used during experimental studies. In the article, on-board equipment of micro-plane used in the study has been shown. Furthermore, the process of integrating all of the avionics equipment with MAV has been described. During the flight test, all parameters of microaircraft flight such as air and cruising speeds, altitude, air route, angles of tilt, slope angle, deviation angle, tilting speed, slope speed, deviation speed, etc. were recorded. During the study, the behaviour of micro-aircraft in various phases of flight such as autonomous take off, landing, programmable flight to the specific points of the air route was checked. In addition, the action of specified fail safe features of micro airplane operating in the case of a failure (e.g. in the case of low voltage of power package, loss of GPS signal, loss of communication with the ground station, etc.) is determined. The graphs of some flight parameters and figures of flight routes as well as flight profiles during the programmable flight have been presented. The researches allow for the verification of the integration process of micro-aircraft with on-board systems and they also allow for evaluation of its functional characteristics in further studies such as formation flights and bypassing the obstacles.

2

Simulation studies of micro air vehicle

Sibilski K., Zyluk A., Kowalski M.

Journal of KONES

|

2015

|

Vol. 22, No. 4

243--252

EN

In the paper, we presented results of analysis of Micro Air Vehicle MAV stability on high Angle of Attack (AOA) by application continuation methods and bifurcation theory. Moreover, it presented two main tasks accomplished – performance analysis carried out, as well as numerical studies in order to find possible simplifications drive model, suitable for further design and analysis. This paper shows the typical MAV construction and their characteristics. Then presented results of calculations of necessary and required power (for CR3516 motor). The results shown in the Figure. The next step of MAV performance examination was calculations of dynamics stability and controllability of open loop system. Also shown state, and control matrixes for the longitudinal motion. Roots loci and open loop dynamics analysis for longitudinal motion are shown in the Figures. The next shown few function such as transfer function for the input (longitudinal velocity), transfer function for the pitch angular rate q input and for the lateral motion, state, and control matrices, etc. At the end shown results of simulations for dynamic response of MAV flight disturbance is shown in the Figure. The paper concluded short motions.

3

Aerodynamic measurements micro air vehicle

Zyluk A., Sibilski K., Kowalski M., Wiśniowski W.

Journal of KONES

|

2015

|

Vol. 22, No. 4

343--353

EN

In present times, constructions of micro air vehicles arouse more and more interest researchers and manufacturers. Air turbulence is perceived as a major problem for Micro Air Vehicles (MAV) in outdoor applications. According to the literature, short duration vertical gusts may have velocity comparable to MAV airspeed, so brief periods of flight at very large angles of attack have to be considered. In these circumstances, it seems reasonable to apply the design with as high stall angle of attack as possible. In particular, the flow has to be attached to control surfaces to perform effective control in order to damp air turbulence effect. Therefore, an aircraft configuration was developed with cranked delta wing and propeller located inside the wing contour. To prove the value of the concept, wind tunnel experiment was undertaken. The prototype demonstrated ability to fly controllably at extremely high angles of attack. Moreover we present few disadvantages of these construction for example it was very sensitive to the motor settings, since every rpm change required immediate airplane trimming to maintain straight path of flight. This drawback can be eliminated by application of counter-rotating propeller. The status of the program is presented in the paper, including the most recent results, as well as currently undertaken experiments and plans for the nearest future.