DOI: 10.14489/vkit.2014.11.pp.013-019

Козорез Д. А., Кружков Д. М.
ОЦЕНКА МОДУЛЯ И ОРИЕНТАЦИИ ТЯГИ ПЛАЗМЕННОГО ДВИГАТЕЛЯ ПРИ ВЫВЕДЕНИИ КОСМИЧЕСКОГО АППАРАТА НА ГЕОСТАЦИОНАРНУЮ ОРБИТУ
(с. 13-19)

Аннотация. Рассмотрено решение навигационной задачи, в том числе оценки компонент тяги двигательной установки плазменного типа при выведении полезной нагрузки на геостационарную орбиту. Разработаны архитектура системы, состав и алгоритмы функционирования, обеспечивающие решение навигационной задачи, в частности оценку компонент вектора тяги стационарного плазменного двигателя с точностью, требуемой для успешного выведения полезной нагрузки на орбиту. Получены оценки уровня точности, достаточного для обеспечения требований, предъявляемых алгоритмами управления при выведении КА на геостацио-нарную орбиту с использованием стационарного плазменного двигателя.

Ключевые слова: навигация; стационарный плазменный двигатель; фильтр Калмана; глобальные навигационные спутниковые системы; геостационарная орбита.

Kozorez D. A., Kruzhkov D. M.
ELECTRIC PROPULSION SYSTEM THRUST MODULE AND DIRECTION ON-LINE EVALUATION AT THE SPACECRAFT INSERTION INTO GEOSTATIONARY ORBIT
(pp. 13-19)

Abstract. The subject of this paper is the navigation problem solution including thrust vector components evaluation by a payload insertion into geostationary orbit. System architecture, components and algorithms developing is considered in order to provide required accuracy level of navigation problem solution. Particularly, electric population system thrust vector components evaluation providing required for successful payload insertion into GEO (Geostationary Orbit) accuracy level is considered. Thrust components evaluation was obtained using «residuals» between onboard measured trajectory and onboard predicted trajectory and Kalman’s filter on-line processing. Measured trajectory provided by estimating of the SC (SpaceCraft) state vector components according to a deeply integrated architecture, using both optical electric and GNSS (Global Navigation Satellites System) receiver data and the so-called «scalar» Kalman’s filtering algorithm. Predicted trajectory is the result of SC motion along reference trajectory without thrust. Mathematical modeling, optimal filtering, object-oriented programming and stochastic methods were used for discussed research. Standard linearized Kalman’s filtering algorithm is the main method providing navigation task solution including thrust vector components. The following restrictions of mathematical simulation were made, they are: SC position errors were not worse than 9 metres (3 RMS) and SC velocity errors were not worse than 1 meter per second (3 RMS). Simulation results were shown that SC thrust module error not worse 1 % (3 RMS) from nominal value and thrust direction estimation errors not worse 5 angular minutes (3 RMS) each other. Sufficient accuracy level which provides by control system for successful payload insertion into GEO using electric propulsion system was reached. This accuracy level allows to apply developed thrust vector estimation algorithm as a part of onboard SC navigation system by payload insertion into GEO using low-thrust engines.

Keywords: Navigation; Electric propulsion system; Kalman’s filter; GNSS; GEO.