Determining the regions for efficient use of electrojet lowthrust engines
Journal Title: Восточно-Европейский журнал передовых технологий - Year 2019, Vol 3, Issue 5
Abstract
<p>This work addresses the issues on determining the optimal regions for using propulsion system for spacecraft at low near-Earth orbits. An analysis of spacecraft launches over the past 5 years has been performed. The result of analyzing the launches is the type of spacecraft, selected for subsequent calculations, specifically a remote sensing satellite at low near-Earth orbit. We have solved the problem on determining parameters for the trajectory of a spacecraft motion, exposed to external non-permanent forces. Based on an analysis of the external influence, the scope of possible future application of spacecraft propulsion systems has been defined. A comparative analysis has been performed for the mass criterion of efficiency of using propulsion systems based on the chemical mono-component and electro-jet engines in order to solve tasks on maintaining the circular orbit parameters over a long time.</p><p>For orbit altitudes below 300 km, as was established based on the calculation results, the application of a propulsion system proved to be inefficient due to the need for a large reserve of fuel aboard and a large required engine thrust. For satellites at circular orbits from 350 to 450 km, a propulsion system that includes the Hall-effect- based engine ST-25, manufactured by SETS, proved to be more effective than the chemical propulsion unit. Application of chemical engines to maintain the orbit parameters at altitude above 500 km would be preferable to electro-jet ones due to a relatively small mass of the chemical propulsion system and a sufficient resource of engines operation in order to maintain the orbit.</p><p>We have obtained parameters for the propulsion system that uses the Hall-effect-based engine ST-25 in order to maintain orbital parameters within different ranges of altitudes, solar activity, and geometrical parameters for a satellite. The result of calculation is the determined necessary resource of operation and the fuel stock to maintain parameters of the orbit.</p><p>The calculation results obtained could be used to design new satellites and to modify satellite platforms.</p>
Authors and Affiliations
Aleksey Sidorov, Viktor Pererva
Keywords
Related Articles
- EP ID EP666410
- DOI 10.15587/1729-4061.2019.168446
- Views 67
- Downloads 0
Using the intensity of absorbed gamma radiation to control the content of iron in ore
<p>The paper reports results of mathematical modeling of the intensity of absorbed gamma radiation for determining the iron content in IOR. It was shown that to enhance the accuracy of rapid control of the iron content i...
Development and investigation of methods of graphic-functional modeling of distributed systems
<p>During the research, the method of geometric modeling of distributed systems and related technological objects was developed. The method is based on the use of functional graphs. In the context of the research, the ma...
Identification of the state of an object under conditions of fuzzy input data
The modernization of the methods for identification of the state of objects under conditions of fuzzy input data, described by their membership functions, was performed. The selected direction of improvement of tradition...
Investigation of the process of fermentation of recovered whey-malt mixtures
<p>We report a study into the fermentation of the recovered whey-malt mixtures using the lactose-fermenting yeast and saccharomyces. The use of such mixtures for production of fermentation beverages using the appropriate...
Development of the formulation and quality assessment of immunostimulating fresh-mixes with a balanced potassium-protein composition
<p>Using the methods of mathematical modeling, we developed formulations for the immunostimulating fresh-mixes. We determined the percentage of plant raw materials, which corresponds to maximum potassium content in the f...