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Annotation on the master dissertation of the student Terokhin

Master's thesis on "Instrumentation navigational error vibrating accelerometers and their identification with bench testing accelerometers" consists of 85 pages containing 16 figures, 10 tables and 25 references.

During the flight, the accelerometer in addition to accelerating the aircraft (LA), is influenced by vibration. This leads to additional static measurement errors of accelerometer - vibration error (VE). This significantly reduces the accuracy of all INS, and therefore the accuracy of the solution of the navigation problem.

The purpose of the master's thesis is to solve the following problems:

1. Get a mathematical model of instrumental VE NA, which is the dependence of the VE on own acceleration of the object, parameters of the vibration, and the parameters of nonlinear conversion function of accelerometer.

2. Develop testing methods for vibrational error mode’s coefficients identification.

3. Develop an algorithm for compensation of instrumental during the flight.

The subject of research is instrumental vibration error in terms of vibration influences on accelerometer, methods of identification of its components during the testing of accelerometers and ways to reduce this error to provide desired accuracy of measurements during the flight.

Obtained methods of identification of the coefficients of a mathematical model of instrumental VE were confirmed by experimentally. To test the adequacy of the proposed algorithm of VE compensation during the flight mathematical modeling using SAA tools included in the software package "Matlab" was done.

1. The mathematical model of instrumental VE of navigational accelerometer shows that this error includes both additive and multiplicative components. The first one depends on such parameters as asymmetry of scale factor, pair nonlinearity coefficient and cross-sensitivity coefficients, and the second one - un the odd nonlinearity coefficients. If one knows the numeric value of these coefficients, resulting model allows to calculate numerical assessment of VE for further compensation of it.

<p ">2. An improved method for accelerometers static test, unlike known, allows to find numerical values of ​conversion factors ​nonlinearity coefficients for further use for the evaluation of VE. <p ">3. The method of dynamic tests of accelerometer gives the opportunity for direct estimation of the VE if its conversion function coefficients are unknown.

The results were made public at the X International Scientific Conference "Gyro technologies, navigation, traffic control and design of aerospace vehicles", Kiev, 2015.

Also results were published or accepted for publication in professional journals: "Information Systems, Engineering and Control", Kyiv; «Transactions of the Institute of Aviation», Institute of Aviation, Warsaw.

<p ">Keywords: navigation accelerometer, vibration error, mathematical model, transfer function, identification of coefficients, the algorithm compensation. 

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