Abstract
The article is devoted to an actual problem of clearing of low earth orbits from space objects of a technogenic origin. Existing versions of struggle against space debris, in particular, removal of technogenic objects with help of the special means for deorbiting delivered into a target orbit by launch vehicles that are especially actual for bulky space debris are considered. Recognizing that the ascent of such means for deorbiting by orbital launch vehicles demands large financial expenses, for an increase of efficiency of delivery the means for deorbiting on a low earth orbit widely known sub-orbital launch vehicles are offered: MAXUS, TEXUS (VSB-30), REXUS (Improved Orion), SS-520, MH-300, Black Brant 12А and the estimation of a capability of their application also is conducted. Are considered the use of sub-orbital launch vehicles for the ascent the means for deorbiting on altitudes of a concentration of space debris on a low earth orbit on a trajectory, close to vertical, with the subsequent operations of interception of demanded space objects, and also modernization of launch vehicles by addition of an additional stage. Results of calculations of an injection trajectory of the means for deorbiting in weight in a layer of space debris in altitude 600 … 1200 km showed of 150 kg that sub-orbital launch vehicles MAXUS, SS-520, Black Brant 12A allow executing delivery the means for deorbiting to altitudes from 770 km to 1200 km and to supply time of its presence in a layer of space debris 420 … 850 s. The most perspective sub-orbital rocket is MAXUS. It possesses higher power and a capability of installation of an additional stage by a decrease in weight of a payload with small losses the power of the first stage. It is shown that the given configuration of the rocket with engine thrust specific impulse in vacuum 300 s and engine thrust in vacuum 16 кН is capable to inject into an elliptical orbit with an altitude of apogee 600 km and altitude of a perigee 130 km with a corner of an inclination 5,5 degrees payload in weight of 55 kg. For orbit short circuit in apogee at the altitude, the upper stage should supply 600 km increase the speeds, equal 133 m/s. Mass characteristics of the second stage are induced.
Sign-in/Register to access full text options 
Talk to us
Join us for a 30 min session where you can share your feedback and ask us any queries you have
Schedule a callDisclaimer: All third-party content on this website/platform is and will remain the property of their respective owners and is provided on "as is" basis without any warranties, express or implied. Use of third-party content does not indicate any affiliation, sponsorship with or endorsement by them. Any references to third-party content is to identify the corresponding services and shall be considered fair use under The CopyrightLaw.
