The Infona portal uses cookies, i.e. strings of text saved by a browser on the user's device. The portal can access those files and use them to remember the user's data, such as their chosen settings (screen view, interface language, etc.), or their login data. By using the Infona portal the user accepts automatic saving and using this information for portal operation purposes. More information on the subject can be found in the Privacy Policy and Terms of Service. By closing this window the user confirms that they have read the information on cookie usage, and they accept the privacy policy and the way cookies are used by the portal. You can change the cookie settings in your browser.
Computer aided-design problems of unmanned aerial vehicles integrated navigation complexes are considered. The design algorithm of unmanned aerial vehicles integrated navigation complexes is proposed.
National Technical University of Ukraine “Kyiv Polytechnic Institute” develops and offers unmanned aerial vehicles for using in many areas of civil and military applications.
The problem of the UAV path planning for given set of the waypoints avoiding requirements of differentiability of the program signal is considered. This problem is solved by the methods of non-holonomic mechanics via usage of decomposition, spatial lead and optimization of the quadratic performance index. Efficiency of this approach is illustrated by example.
The algorithms of the synthesis of optimal structures and parameters of the matrix of transfer functions of the filter which enables to assess the vector of useful signals with the noise correction as well as without it according to the data on sensor dynamics, electromagnetic interference characteristics and vector characteristics of the measured signals were developed.
This paper presents results of development and implementation of Ukrainian Coriolis vibratory gyroscopes (CVG). The main achievement of this development is that low-cost metallic alloy resonator CVG can reach high accuracy to compete with larger size higher cost fiber optic gyroscopes (FOG) and at the same time has higher reliability. Main parameters comparison with one of the FOG is presented. New...
Unmanned aerial vehicles (UAV) are successfully exploited in different applications for the last years. To perform successfully the specified tasks they have to rely on navigation and automatic flight control systems. Development of such systems is a complex task that requires comprehensive testing throughout the whole process. This paper presents some recommendations regarding UAV navigation system...
This paper deals with a problem of aircraft navigation systems components condition change forecasting, which is connected with lack of admissible approaches and methods. The solution of the problem lies in development of models taking into account the unit condition change, caused by either operating time, or service period. The goal of the paper is determination of requirements to aircraft maintenance...
The new method of a modernized Wiener optimal filter synthesis is proposed in the article. A main characteristic feature of the method is connected with the achievement of the high-precision selection of the useful stationary random signals vector on a background of a controlled multidimensional stationary noise.
Improvement of unmanned aerial vehicle navigation reliability in rough air and gusts provides by aerodynamic characteristics of Unmanned aerial vehicle. Investigation of leading edge vortex generators effectiveness in subsonic wind tunnels and on RC airplane was presented. Leading edge vortex generators, which form vortex slat can influence on flow separation, therefore increasing critical angle of...
Problem of correlation-extremal navigation for several geophysical fields is considered. Optimal estimation for highly non-linear measurement equation is realized using particle filtering. Simulation for relief and anomalous magnetic fields is done by sequential importance sampling based on Monte Carlo method.
Are given principles of the combined sensor which measures the angular parameters and is used in inertial-satellite systems constructed by the method of compensation or based on the reduced Kalman filter. Measurement errors of angular orientation parameters are investigated by the proposed method with aircraft performing various maneuvers and with changing the acceleration and attitude.
Set the date range to filter the displayed results. You can set a starting date, ending date or both. You can enter the dates manually or choose them from the calendar.