TEMPERATURE CALIBRATION OF NAVIGATIONAL ACCELEROMETER UNIT
Journal Title: Механіка гіроскопічних систем - Year 2016, Vol 0, Issue 31
Abstract
<p align="center"> </p><p>Temperature calibration method of navigational accelerometer unit, which excludes accelerometer unit reset in temperatures and allows performing calibration by one-time passage at all calibration temperatures, is considered. Special device – tilt, is used for accelerometer unit setting in test positions.</p><p>Model of absolute instrumental measurement error of accelerometer unit acceleration projections in measurement axes was obtained by known accelerometer unit metrology models. Polynomial and piecewise linear model of accelerometer unit temperature errors were obtained using appropriate expressions for two types of dependencies twelve passport constants of temperature change. In addition, simplified polynomial and piecewise linear models of accelerometer unit temperature errors were obtained.</p><p>Two methods of algorithmic compensation of accelerometer unit temperature errors are proposed: method 1 -mathematical method of correction accelerometer unit metrology model passport constants current values based on current temperature, method 2 - method of introducing amendments to accelerometer unit measurement results, values of which are equal to temperature errors values.</p><p>Experimentally temperature calibration of accelerometer unit using tilt was performed and its quality was checked, which performed by comparing measurement errors of gravity acceleration module at verification temperatures. Adequacy of the developed method of navigational accelerometer unit temperature calibration was confirmed. Two methods of temperature errors accelerometer unit algorithmic compensation were compared, each method gave almost the same result - reducing accelerometer unit temperature errors by three-four times. For increasing compensation accuracy it is recommended to use complex accelerometer unit temperature errors models and, or increase number of piecewise linear model subbands and polynomial model order.</p>
Authors and Affiliations
Mykola Chenyak, Kateryna Vidyakina
Keywords
Related Articles
- EP ID EP510773
- DOI 10.20535/0203-377131201678048
- Views 87
- Downloads 0
ШУМ ОТ РАКЕТНЫХ ДВИГАТЕЛЕЙ ПРИ ЗАПУСКАХ РАКЕТ-НОСИТЕЛЕЙ КОСМИЧЕСКОГО НАЗНАЧЕНИЯ
<p>Проблема гашения шумов при старте ракет космического назначении (РКН) приобрела в настоящее время особую актуальность.</p><p>Наиболее «шумящим» агрегатом стартующей РКН является ее двигательная установка (ДУ). Поэтому...
ВИЗНАЧЕННЯ ОПТИМАЛЬНОГО ПОЛОЖЕННЯ КРИЛА ДОЗВУКОВОГО ЛІТАЛЬНОГО АПАРАТА
<p>Запропонована методологія визначення оптимального положення крила дозвукового літального апарату проілюстрована на прикладі моделі літака, що містить крило заданого профілю та фюзеляж, побудований по круглим перерізам...
ЗМЕНШЕННЯ ОПОРУ ТЕРТЯ ЛІТАКА ШЛЯХОМ МІКРОВИДУВУ ЧЕРЕЗ ПРОНИКНІ ДІЛЯНКИ ПОВЕРХНІ КРИЛА
<strong><strong></strong></strong>На прикладі крила літака Ан-124 було досліджено переваги та особливості впливу на опір літака мікровидуву повітря через пористу ділянку обтічної поверхні. Проведено параметричний аналіз...
Features of influence of the gyroscopic system on oscillation of the vibration protection system of passive type
The paper examines the impact of gyroscopic system on vibration protection system. Object of research is adjustable gyro compass. It is shown that the horizontal vibration of base can cause hull angular oscillations of t...
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...