Mathematical model of navigation accelerometer instrumental vibration error and its identification at accelerometer dynamic tests
Journal Title: Механіка гіроскопічних систем - Year 2018, Vol 0, Issue 36
Abstract
During the flight, in addition to an aircraft accelerating the accelerometer is influenced by vibration. This leads to additional static measurement errors of 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 vibrational error of the navigation accelerometer is considered in an aircraft flight conditions. It is shown that the sources of this error are the nonlinear components of the static conversion function of accelerometer. Formulas for calculating the vibrational error of the 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 the navigational accelerometer instrumental vibrational error shows that this error includes both additive and multiplicative components. The first one depends on such parameters as scale factor asymmetry, pair nonlinearity coefficient and cross-sensitivity coefficients, and the second one is the odd nonlinearity coefficient. If the numeric value of these coefficients is known, the resulting model allows the calculating of the vibrational error numerical assessment for its further compensation. A method for identifying the mathematical model coefficients of the navigation accelerometer vibrational error during its dynamic tests on a shake table is proposed. The method of the accelerometer dynamic tests gives the opportunity for direct estimation of the vibrational error if its conversion function coefficients are unknown. Obtained methods of the mathematical model coefficients identification of an instrumental vibrational error were confirmed experimentally.
Authors and Affiliations
M. G. Chernyak
Keywords
Related Articles
- EP ID EP508751
- DOI -
- Views 93
- Downloads 0
Влияние температурно-деформационных параметров ТМКО на изменение структуры аустенита и механических свойств микролегированных сталей
В процессе ТМКО микролегированных сталей в широком диапазоне варьировали параметры чистовой прокатки и охлаждения, изменяя степени горячего обжатия при моделировании плоской горячей деформации на стане. Оценивая кривые т...
Mathematical model of navigation accelerometer instrumental vibration error and its identification at accelerometer dynamic tests
During the flight, in addition to an aircraft accelerating the accelerometer is influenced by vibration. This leads to additional static measurement errors of accelerometer i.e. vibration error. This significantly reduce...
Improving the accuracy of the inertial navigation system by means of technical vision
The development of the inertial navigation system (INS) errors correction method by means and methods of technical vision(MTV) is an actual and effective application problem. Having the values of the UAV distance and di...
Estimation of state of flight simulator motion system
Solution of problem of status analyzing of motion systems, deficiency identification of both motion systems and their hydraulic actuators, and suitability assessment of motion systems for use in aircraft flight simulator...
Method of determining the geographic meridian plane by ground-based pendulum gyrocompass in exponential acceleration mode of its rotor
A method of determining the position of the geographic meridian by threefold pendulum gyrocompass during the process of exponential acceleration of its rotor. Obtained an algorithm identifying the initial position of the...