On a possibility of using domestic low-thrust engines in the ultra-low-orbit spacecraft
Authors: Sobolev I.A.
Published in issue: #2(158)/2025
DOI: 10.18698/2308-6033-2025-2-2423
Category: Aviation and Rocket-Space Engineering | Chapter: Design, Construction, Production, Testing, and Operation of Aircraft
The paper considers an approach to determining the minimum orbital altitude, where operation of an ultra-low-orbit spacecraft for the Earth remote sensing is possible. It analyzes the influence of limitations imposed by the engine activation duration, relative mass of the working fluid, and engine service life in terms of the number of activations. The study is conducted for spacecraft with different mass and ballistic coefficient values. The range of orbits within the altitudes of 200...250 km is selected for consideration. Spacecraft position in these orbits makes it possible to improve significantly resolution of the existing optical systems, reduce the mass and dimensions, as well as the cost of those being developed. Propulsion system for the ultra-low-orbit spacecraft is created based on the SPD-70, SPD-100V and SPD-140D domestic plasma engines having experience in the flight operation, and the ID-200 ion engine, which passed the ground testing.
EDN UXFFXC
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