scholarly journals ОЦЕНКА ВОЗМОЖНОСТЕЙ ПРИМЕНЕНИЯ СУБОРБИТАЛЬНЫХ РАКЕТ-НОСИТЕЛЕЙ ДЛЯ ВЫВЕДЕНИЯ СРЕДСТВ УВОДА ОБЪЕКТОВ КОСМИЧЕСКОГО МУСОРА С НИЗКИХ ОКОЛОЗЕМНЫХ ОРБИТ

2020 ◽  
pp. 60-65
Author(s):  
Николай Михайлович Дронь ◽  
Кирилл Валерьевич Коростюк ◽  
Александр Вячеславович Голубек ◽  
Людмила Григорьевна Дубовик ◽  
Алексей Владимирович Кулик
Keyword(s):  
Space Debris ◽  
Short Circuit ◽  
Specific Impulse ◽  
Low Earth Orbit ◽  
Earth Orbit ◽  
Launch Vehicles ◽  
Actual Problem ◽  
Black Brant ◽  
Engine Thrust ◽  
Space Objects

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.

The conception of a launch vehicles with ramjet and rocket-ramjet engines for a small payload injection into Low Earth Orbit

2006 ◽  
Author(s):  
Valeriy I. Timoshenko ◽  
Vjacheslav P. Gusinin ◽  
Valeriy P. Galinsky ◽  
Igor S. Belotserkovets
Keyword(s):  
Low Earth Orbit ◽  
Earth Orbit ◽  
Launch Vehicles ◽  
Ramjet Engines

scholarly journals The Ad Hoc Back-End of the BIRALET Radar to Measure Slant-Range and Doppler Shift of Resident Space Objects

Electronics ◽  
2021 ◽  
Vol 10 (5) ◽  
pp. 577
Author(s):  
Luca Schirru ◽  
Tonino Pisanu ◽  
Angelo Podda
Keyword(s):  
Doppler Shift ◽  
Space Debris ◽  
Ad Hoc ◽  
Low Earth Orbit ◽  
Slant Range ◽  
Radar Systems ◽  
The Earth ◽  
Space Objects ◽  
Resident Space Objects ◽  
Potential Issue

Space debris is a term for all human-made objects orbiting the Earth or reentering the atmosphere. The population of space debris is continuously growing and it represents a potential issue for active satellites and spacecraft. New collisions and fragmentation could exponentially increase the amount of debris and so the level of risk represented by these objects. The principal technique used for the debris monitoring, in the Low Earth Orbit (LEO) between 200 km and 2000 km of altitude, is based on radar systems. The BIRALET system represents one of the main Italian radars involved in resident space objects observations. It is a bi-static radar, which operates in the P-band at 410–415 MHz, that uses the Sardinia Radio Telescope as receiver. In this paper, a detailed description of the new ad hoc back-end developed for the BIRALET radar, with the aim to perform slant-range and Doppler shift measurements, is presented. The new system was successfully tested in several validation measurement campaigns, the results of which are reported and discussed.

scholarly journals Dynamic Modelling Transformations for the Low Earth Orbit Satellite Particulate Environment

1991 ◽  
Vol 126 ◽  
pp. 37-40
Author(s):  
J.A.M. McDonnell ◽  
K. Sullivan ◽  
S.F. Green ◽  
T.J. Stevenson ◽  
D.H. Niblett
Keyword(s):  
Dynamic Model ◽  
Space Debris ◽  
Residue Analysis ◽  
Dynamic Modelling ◽  
Low Earth Orbit ◽  
Earth Orbit ◽  
Natural Orbital ◽  
Low Earth Orbit Satellite ◽  
Chemical Residue ◽  
Particle Velocities

AbstractA simple dynamic model to investigate the relative fluxes and particle velocities on a spacecraft’s different faces is presented. The results for LDEF are consistent with a predominantly interplanetary origin for the larger particulates, but a sizable population of orbital particles with sizes capable of penetrating foils of thickness <30μm. Data from experiments over the last 30 years do not show the rise in flux expected if these were space debris. The possibility of a population of natural orbital particulates awaits confirmation from chemical residue analysis.

scholarly journals Lisk-Broom: A laser concept for clearing space debris

1995 ◽  
Vol 13 (1) ◽  
pp. 33-41 ◽  
Author(s):  
Claude Phipps
Keyword(s):  
Plasma Physics ◽  
Atmospheric Turbulence ◽  
Space Debris ◽  
Laser System ◽  
Average Power ◽  
Low Earth Orbit ◽  
Earth Orbit ◽  
Interaction Theory ◽  
Space Propulsion ◽  
Laser Impulse

So-called “space junk” forced a change of plan for a recent Shuttle mission. However, ground-based lasers with atmospheric-turbulence-compensating beam directors represent a singularly effective method of de-orbiting space junk, because they use cheap Earth-based power, and because they lend themselves to rapid retargeting. Plasma physics and lasertarget interaction theory dictate the laser parameters for a particular mission. We will discuss a practical laser system and beam director with 20-kW average power at 0.5-µm wavelength that is capable of clearing most low-Earth-orbit objects with mass less than 100 kg in about 4 years. This is a special application of the Laser Impulse Space Propulsion (LISP) concept, by which objects are propelled in space by the ablation jet produced on their surface by a remote laser.

scholarly journals Innovative observing strategy and orbit determination for Low Earth Orbit space debris

2012 ◽  
Vol 62 (1) ◽  
pp. 10-22 ◽  
Author(s):  
A. Milani ◽  
D. Farnocchia ◽  
L. Dimare ◽  
A. Rossi ◽  
F. Bernardi
Keyword(s):  
Orbit Determination ◽  
Space Debris ◽  
Orbit Space ◽  
Low Earth Orbit ◽  
Earth Orbit

Space Debris in Low-Earth Orbit

Space 98 ◽  
1998 ◽  
Author(s):  
Terri L. Nelson
Keyword(s):  
Space Debris ◽  
Low Earth Orbit ◽  
Earth Orbit

Investigation on Sustained Discharge of Satellite’s Power Harness Due to Plasma from Space Debris Impact

2019 ◽  
Author(s):  
Yuki Mando ◽  
Koji Tanaka ◽  
Takayuki Hirai ◽  
Shirou Kawakita ◽  
Masumi Higashide ◽  
...  
Keyword(s):  
Space Debris ◽  
Internal Resistance ◽  
Low Earth Orbit ◽  
Hypervelocity Impact ◽  
Space Environment ◽  
Earth Orbit ◽  
Large Area ◽  
Solar Arrays ◽  
Sustained Discharge ◽  
Circuit Configuration

Abstract Space debris travels at a velocity of 7-8 km/s in low Earth orbit (LEO) and at 3 km/s in geostationary Earth orbit (GEO). An impact between space debris and spacecraft will result in tremendous damage. In particular, particles less than 1mm in diameter pose a risk of causing permanent sustained discharge (PSD). PSD may affect a satellite’s power system. The effect on solar arrays has been well-studied given their large area, but the effect on the bundle of a satellite’s wire harness (called the power harness) has yet to be clarified, even though the power harness is usually exposed to the space environment without protection. We conducted hypervelocity impact experiments using a two-stage light gas gun, and investigated the risk resulting in PSD from hypervelocity impacts of particles less than 1mm in size. In addition, we compared two kinds of circuit configurations: a more realistic circuit configuration with internal resistance and a circuit configuration without it, so as to investigate whether internal resistance affects the occurrence of PSD. Stainless steel and aluminum oxide projectiles measuring from 0.3 to 1 mm in diameter were gun-accelerated up to 7.16 km/s. Targets entailed a three-layered power harness under a simulated power condition of typical satellites operating in LEO or GEO. As a result, 11 of 28 shots resulted in PSD. With the more realistic circuit configuration we could not confirm any results regarding PSD. We thus found that PSD is less likely to occur in a more realistic circuit configuration.

Space debris and micrometeorite events experienced by WL Experiment 701 in prolonged low Earth orbit

1991 ◽  
Vol 96 (A6) ◽  
pp. 9829 ◽  
Author(s):  
D. S. McKnight ◽  
R. E. Dueber ◽  
E. W. Taylor
Keyword(s):  
Space Debris ◽  
Low Earth Orbit ◽  
Earth Orbit
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