Compensating Microaccelerations from a Temperature Shock

The problem of large elastic elements temperature shock is a serious problem of providing favorable conditions for the implementation of gravity-sensitive processes on board a small technological spacecraft. When a small spacecraft dives into and exits the Earth’s shadow, its large elastic elements, primarily solar panels, experience a significant change in the temperature regime. The purpose is to analyze the possibility of implementing algorithms for controlling an electrothermal micro-engine, developed to eliminate the influence of temperature shock on the level of micro-acceleration of the internal environment of a small technological spacecraft. The research is carried out using methods of mathematical modeling, spacecraft parameters analysis, technical justification and analysis of advantages, operating conditions analysis, test results analysis, experimental dependencies construction. The study confirms that it is necessary to take into account the real law of changes in the electrothermal micro-engine thrust for a correct assessment of the decrease in the micro-accelerations magnitude from a temperature shock. Since the temperature shock is an extremely dynamic phenomenon, a detailed study of a turned on executive body thrust change law is necessary. The results of the work can be used in the design of a small technological spacecraft to meet the micro-accelerations requirements.