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Usage of micromechanical angular rate measurement device as an antenna stabilization system sensitive element is considered. Namely-collecting data of orientation for holding direction at an object within referenced accuracy limits and during certain period of time.
The paper presents realization variants of fundamental new technology rebuilding of sensitivity which based on coherence effect. Principles of construction and work peculiarities of Laser Doppler Velocimeter differential schemes.
This paper deals with autonomous precision attitude and heading reference system. Usage of the dynamically tuned gyros and two-axis gimbals that allows to reduce mass and dimensions of the studied system is suggested. The model of the studied system is given. Forming of the control moments is considered.
The paper presents results of researching the influence of the monitor type on the human-operator's work in the process of tracking stochastic signal with the help of structure identification.
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.
Synthesis of a feedback control system for Coriolis vibratory gyroscopes that implements whole angle force rebalance mode of operation is presented in this paper. Feedback controller is derived in terms of demodulated signals. Successful operation of the control system is demonstrated using numerical simulation of realistic Coriolis vibratory gyroscopes model in modulated signals.
The model of hypothetic biotechnical 2D natural neuron system for images recognition is presented. Results of real biophysical experiments with transmembrane electrical current registration and fluorescent neuronal markers usage were put on the base of this model.
This work presents investigation of differential Coriolis vibratory gyroscope ability to external shock suppression. First of all pulse amplitude in voltage caused by external mechanical shock of 100 g is estimated for the two sensor designs. Then, using differential CVG Simulink model, output signals of two channels are analyzed. It is shown that differential CVG damps amplitude of erroneous angle...
The paper deals with the two-step hybrid asymptotic method based on perturbation methods and phase integrals. Approximate analytical solution of the nonlinear problem of the vibrations of the aircraft near the rough surface was obtained. Comparison with the data of direct numerical integration of the equations of the original problem was done.
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...
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.
In this paper the application of the wideband radar ambiguity function and its nonparametric variant in radar and navigation systems is considered. The new nonparametric variant of the ambiguity function, which is based on the copula notion, is discussed. The suggested function can be used for the signal synthesis and detection in different electronic systems for signals with an unknown spectrum and...
The problem of design of the robust combined systems for stabilization and control by orientation of lines-of-sight of devices mounted at vehicles in difficult conditions of real operation is considered. The optimization criterion of the solved problem taking into consideration the functions of sensitivity by the coordinate disturbances and noise measurements is obtained.
The problem of optimal state feedback controller design in terms of quadratic performance index is considered. The problem is formulated in the form of linear matrix inequalities (LMIs). The obtained solution guarantees stabilization of the aircraft during flight mission. During flight envelope the aircraft is subjected to the external stochastic disturbances. The efficiency of the proposed approach...
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