SPACE VEHICLE WITH AN ELECTRIC THRUSTER FOR GATHERING FINE SPACE DEBRIS

Paper number

IAC-08.A6.5.8

Author

Dr. Anatoliy Alpatov, Institute of Technical Mechanics of the National Academy of Science and National Space Agency of Ukraine, Ukraine

Coauthor

Dr. Vjacheslav Gusynin, National Space Agency of Ukraine (NSAU), Ukraine

Coauthor

Dr. Mykola M. Slyunyaev, Yuzhnoye State Design Office, Ukraine

Coauthor

Mr. Andrey Khitko, Dniepropetrovsk National University, Ukraine

Year

2008

Abstract

Fine space debris presents essential danger since its quantity and hence the probability of collisions with it considerably surpasses that of collisions with large fragments. Its diagnostics and maneuvers for withdrawal of a space vehicle (SV) from a collision are complicated also.
In the paper the research results for SV for gathering fine space debris and burying it in dense layers of the atmosphere are presented. The basic feature of SV is use of electric thrusters and receiver-store of fine debris.
The vehicle maneuvers in the range of heights 1000 - 200 km. Use of an electric propulsion (EP) of small thrust allows to increase maneuver opportunities and to carry out the maneuver on a helicoids trajectory that considerably increases the probability of collisions and efficiency of gathering space debris. Using EP with a higher value of specific impulse than that of chemical propulsion allows reducing a necessary stock of a working propellant.
Structures with an elastic force frame are supposed to be used as a receiver-store of fine space debris. Multilayered units of a "trap" intended especially for the prevention of additional fragment formation in the process of interaction with space debris are fixed on the frame. 
The evaluation of the quantity of turns of a spiral orbit and of the decrease in height during each turn for a set time of maneuver and calculated change of  SV speed at the maneuver is carried out. Acceleration of braking and SV mass are determined for the set propulsion thrust. The EP type and parameters are chosen. The assessment of the propulsion plant mass with working propellant stock for the maneuver, of the solar array power, and of the receiver-store mass is carried out.

Abstract document

IAC-08.A6.5.8.pdf

Manuscript document

IAC-08.A6.5.8.pdf (🔒 authorized access only).

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