Abstract
Introduction.Precision elements of the target equipment and sensitive elements of the stabilization and orientation system of the advanced spacecraft are considered in the framework of this research. A method and software for modeling the dynamic characteristics of these elements are developed and validated. At that, the processing data results from the experimental studies on active and passive oscillators are taken into account.Materials and Methods. It is shown how the method of weightlessness provides simulation of the conditions that as much as possible conform to the real-time use of advanced space vehicles, precision structural elements, target equipment and their drives. Schemes of the corresponding experimental facilities are presented. Mathematical modeling methods, techniques of machine mechanics and dynamics are applied. Basic parameters of the proposed design dynamics, which are governing parameters in terms of the implementation of the target functions of the spacecraft, are calculated. Rational versions of layout and approximate cycle patterns of the operation of advanced space vehicles are formed to reduce microperturbations from driving gear with rotating masses.Research Results. A simulation technique for the dynamic characteristics of the drives of advanced space vehicles considering the regular oscillator operation is developed and validated. A complex of methods is presented for solving the problems of identifying dynamic parameters of a mathematical model of an advanced spacecraft based on the processing data results obtained through the experimental testing of active and passive oscillators. Two types of vibration from flywheel engines are noted. The first type is according to the commands of the position control and stabilization control system. The second type is due to residual imbalance from the solar constant meter. It is shown how these vibrations affect the dynamic characteristics of the gyro mounting seats and of the multispectral scanner for hydrometeorological support of the spacecraft. The data obtained are meant to solve the problems of assurance of the dynamic accuracy of advanced space vehicles.Discussion and Conclusions. A technique for modeling the dynamic characteristics of advanced space vehicles when operating in the precision orientation mode is proposed. The solution is based on the results of theoretical and experimental studies presented in the paper, and it considers the operation of standard oscillators. The implementation of this method is brought to software and algorithmic support for assessing the dynamic characteristics of standard oscillators of an advanced space vehicle. Recommendations to reduce the effect of active oscillators are established. Initial data are selected to determine the dynamics of advanced space vehicles from the point of view of fulfilling their target functions. The layout and approximate cycle patterns of the operation of advanced space vehicles to identify the driving gear with rotating masses as sources of micro-perturbations are proposed.
Highlights
Precision elements of the target equipment and sensitive elements of the stabilization and orientation system of the advanced spacecraft are considered in the framework of this research
The processing data results from the experimental studies on active and passive oscillators are taken into account
A complex of methods is presented for solving the problems of identifying dynamic parameters of a mathematical model of an advanced spacecraft based on the processing data results obtained through the experimental testing of active and passive oscillators
Summary
Теоретические основы моделирования динамических характеристик приводов перспективных космических аппаратов с учетом функционирования осцилляторов*. 1, 2 Московский автомобильно-дорожный государственный технический университет, Москва, Российская Федерация 3 Московский государственный технический университет имени Н. Э. Баумана, Москва, Российская Федерация 4 Научно-производственное объединение имени С. В рамках данного исследования рассмотрены прецизионные элементы целевой аппаратуры и чувствительные элементы системы стабилизации и ориентации перспективных космических аппаратов. Обоснованы и разработаны метод и программно-алгоритмическое обеспечение моделирования динамических характеристик указанных элементов. Как метод обезвешивания позволяет воссоздать условия, максимально соответствующие реальной эксплуатации перспективных космических аппаратов, прецизионных элементов конструкции, целевой аппаратуры и их приводов. Обоснован и разработан метод моделирования динамических характеристик приводов перспективных космических аппаратов с учетом функционирования штатных осцилляторов. Представлен комплекс методик решения проблем идентификации динамических параметров математической модели перспективных космических аппаратов с учетом результатов обработки данных, получаемых при экспериментальной отработке активных и пассивных осцилляторов.
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