Providing accuracy in measuring linear acceleration of a missile’s flight

1Chernyak, MG
1Interdisciplinary Research Institute for Problems in Mechanics Rhythm, National Technical University of Ukraine «Igor Sikorsky Kyiv polytechnic institute», Kyiv, Ukraine
Space Sci. & Technol. 2018, 24 ;(6):03-15
Publication Language: Ukrainian
The problem of providing a given accuracy in measuring the linear acceleration of a rocket flight with the help of a navigation accelerometer in conditions of acting on it of deterministic and broadband random vibrations from the rocket body side is considered. It is shown that in these conditions, the accelerometer has a systematic additional vibration error, which is a source of significant (more than an order of magnitude) reduction in the accuracy of measuring the acceleration of the flight of a rocket. The source of this error is the nonlinearity of the static function of accelerometer conversion. A mathematical model of this error is obtained. The model allows you to calculate the value of this error in flight for a specific accelerometer (direct problem) and select an accelerometer based on the values of the coefficients of its conversion function, starting from the provision of a specified accuracy in measuring the linear acceleration of the flight of a specific rocket using this accelerometer (inverse problem).
               Two examples of solving the inverse problem are considered: for a transport three-stage «Cyclone-4» carrier rocket and for a hypothetical single-stage combat tactical missile. The proposed accuracy in measuring the acceleration of rocket flight using a navigation accelerometer is proposed to be implemented in two ways: at the stage of accelerometer selection - by matching the accelerometer with the requirements formulated in the article to the coefficients of its conversion function; in flight - by algorithmic compensation of the main and additional vibrational errors of the accelerometer according to the algorithm obtained in the article. The adequacy of all mathematical models and algorithms obtained in the article is confirmed by experimental studies of the vibration error and the efficiency of its algorithmic compensation for the modern navigation accelerometer AKS-05 produced by the State Enterprise of Special Instrumentation «Arsenal» (Kiev), which corresponds to all presented in the article the requirements to the coefficients of its nonlinear static transformation function.
Keywords: algorithmic error compensation, flight acceleration, mathematical model, navigation accelerometer, nonlinear transformation function, vibration, vibration error
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