TY  - JOUR
T1  - Fuel and Energy Analysis of a Space Vehicle Aimed at De-orbiting Large-size
Objects from Low Orbits Using Thruster De-orbiting Kits
AU - Grishko, Dmitriy A. AU - Baranov, Andrey A. AU - Chen, Danhe 
JO  - Journal of Engineering and Applied Sciences
VL  - 14
IS  - 4
SP  - 1312
EP  - 1317
PY  - 2019
DA  - 2001/08/19
SN  - 1816-949x
DO  - jeasci.2019.1312.1317
UR  - https://makhillpublications.co/view-article.php?doi=jeasci.2019.1312.1317
KW  - Large-size space debris
KW  -SV-collector
KW  -thruster de-orbiting kit
KW  -mass and energy
KW  -parameters
KW  -disposal orbit
AB  - The study focuses on analysis of mass and energy parameters of an advanced SV-collector (SV)
designed for fly-pasts between Large-Size Space Debris (LSSD) in low orbits with the aim at their de-orbiting.
De-orbiting is supposed to be carried out using Thruster De-orbiting Kits (TDK) installed onboard the
SV-collector. The SV and TDKs dry masses are estimated as well as the masses of LSSD objects to
be de-orbited with the help of TDKs, the required fuel reserves for TDKs and SV are estimated, the optimal
number of TDKs per one SV is evaluated. Earlier the authors of the present study determined 5 compact groups
of LSSD in low orbits formed by launch vehicle stages. From the known mass of such objects it is possible to
assess the fuel mass required to de-orbit any object of a given group to a disposal orbit. The dry mass of an
active SV can be estimated from the mass characteristics of a modern cargo space vehicle. To assess the
required fuel reserves of an SV it is necessary to simulate SV’s fly-bys between objects of a concrete group of
LSSD. Simulation results show that it is expedient to accommodate 8-12 TDKs on one SV, the total initial mass
of an SV is estimated to be 7-8 metric tons (at most 10 tons in the limit case).
ER  -