ПІДВИЩЕННЯ ТОЧНОСТІ НАВІГАЦІЙНОГО АКСЕЛЕРОМЕТРА В УМОВАХ РАКЕТНОГО ПОЛЬОТУ
Journal Title: Інформаційні системи, механіка та керування - Year 2018, Vol 0, Issue 19
Abstract
During the flight, the accelerometer, in addition to the aircraft accelerating, is influenced by vibration. This leads to additional static measurement errors of the accelerometer i.e. vibration error. This significantly reduces the accuracy of all INS, and, therefore, the accuracy of the navigation problem solution. A mathematical model of the instrumental vibration error of the navigation accelerometer is considered in the aircraft flight conditions. It is shown that the sources of this error are the nonlinear components of the static conversion function of navigation accelerometer. Formulas for calculating the vibration error of the navigation accelerometer are obtained depending on the apparent acceleration of the aircraft flight, the vibration parameters of the base on which the accelerometer is installed and the parameters of the nonlinear accelerometer conversion function. The mathematical model of instrumental vibration error of navigation 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 depends on the odd nonlinearity coefficients. If one knows the numeric value of these coefficients, resulting model allows us to calculate numerical assessment of vibration error for its further compensation. A method is proposed for identifying the mathematical model coefficients of the navigation accelerometer vibration error during its dynamic tests on a shake table. It is proposed to increase the navigation accelerometer accuracy in a rocket flight in two ways: at the production stage of the accelerometer is to match the accelerometer to the coefficients requirements of its conversion function formed in the article; in flight is to use algorithmic compensation of the main and additional vibration errors of the accelerometer according to the algorithm obtained in the article.
Authors and Affiliations
М. Г. Черняк
Keywords
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