Special Refill Spacecraft Debris Collector, Equipped with Electro Rocket Engine of Low-thrust, Design Parameters Optimization. (2017)

• Record Type: Journal Article
• Authors: Ishkov, Sergey A.; Filippov, Gregory A.
• Is Part Of: Procedia engineering. Volume 185(2017)
• Page Start: 396
• Page End: 403
• Publication Date: 2017
• Subjects: space debris -- special spacecraft debris collector -- criteria function -- characteristic velocity gains -- design parameters -- total resource; Engineering -- Congresses; Engineering -- Periodicals; Engineering; Conference proceedings; Periodicals; 620.005
• DOI: 10.1016/j.proeng.2017.03.321
• Languages: English
• ISSNs: 1877-7058

Abstract

Abstract: The problem of near Earth space debris is studied in this article. A special spacecraft debris collector, equipped with electro rocket engine of low-thrust, for large space debris disposal is introduced. The mass model of spacecraft debris collector, one-off or reusable, is obtained. Ballistic scheme, spacecraft debris collector orbital transfer from parking orbit to space debris orbit, its disposal in Earth atmosphere and reusable spacecraft return to the parking orbit are studied. For the introduced criteria of transport transfer efficiency and assumption about consistency of acceleration from thrust, analytical relations for spacecraft design parameters calculation are obtained. The design parameters calculation results are shown in a generalized form.