Author:
Bogatyi A V,Dyakonov G A,Kashirin D A,Popov G A,Semenikhin S A
Abstract
Abstract
The paper presents the appearance of a low-power electric propulsion system for a small remote sensing satellites based on an ablative pulsed plasma thruster. Preliminary analysis for the purpose and fields of application of ablative pulsed plasma thrusters (APPT) was carried out. The design appearance of a thruster for small remote sensing satellites was identified, and the main directions of APPT further development were defined. Methods for calculating the APPT propulsion characteristics were developed. The breadboard model of APPT for small remote sensing satellites was developed and made (APPT-350). Research tests of the breadboard model of APPT for Earth remote sensing small spacecrafts were carried out.
Subject
General Physics and Astronomy
Reference10 articles.
1. Some features of a small spacecraft application as a technique for the world ocean exploration;Sedelnikov;IOP Conf. Ser.: Earth Environ. Sci.,2019
2. Mathematical models of station keeping for low orbit spacecraft with electric propulsion and limited power supply;Anshakov;J. Phys.: Conf. Ser.,2018
3. Electric propulsion for small satellites;Keidar;Plasma Phys. Controlled Fusion.,2015
4. New stage in the development of ablative pulsed plasma thrusters at RIAME MAI;Antropov;Sol. Syst. Res.,2012
5. The current state of work on the development the APPT-based electric propulsion systems at RIAME MAI;Bogatyi;Bulletin of the Russian Academy of Sciences. Energetic.,2019