scholarly journals Reentry of Space Debris from Low Earth Orbit by Pulsed Nd:YAG Laser

2020 ◽  
Vol 12 (02) ◽  
pp. 39-51
Author(s):  
H. K. Al-Zaidi ◽  
◽  
M. J. Al-Bermani ◽  
A.M. Taleb ◽  
Keyword(s):  
Numerical Analysis ◽  
Nd:Yag Laser ◽  
Space Debris ◽  
Peak Pressure ◽  
Interaction Model ◽  
Low Earth Orbit ◽  
Orbital Dynamics ◽  
Earth Orbit ◽  
Analysis Program ◽  
Momentum Coupling

This research studies the orbital dynamics of space debris in near earth orbit. The orbital dynamics of space debris is closely examined in near earth orbit whereby (apogee altitude ha=1200 km and perigee altitude hp=200 km). In addition, the lifetime of the space debris is calculated using the influence of the friction force exerted on the atmospheric particles with debris dimensions measuring between (1 and 10 cm). In this study, the Drag Thermospheric Models (DTM78 and DTM94) are used because of their dependence on solar and geomagnetic activities, and pulsed lasers are utilized to interact with Aluminum 2024 particles which are frequently employed in the structure of spacecraft and aerospace designs. A numerical analysis program (NaP1) was built to calculate the lifetime of space debris and its time of return to the atmosphere. It is then integrated with a second numerical analysis program (NaP2) developed using the Lax-Wendroff finite difference method to simulate the laser material interaction model. A high power Nd:YAG laser was applied to produce shock wave pressure in target. The results show that the maximum peak pressure occurs at 50 µm depth then slowly decays, the peak pressure increases with the increase of the laser intensity, and the optimum value of the momentum coupling coefficient (Cm) for the aluminum debris of size range (1and10 cm) is 6.5 dyn.s/j.

scholarly journals Optimum parameters for laser launching objects into low Earth orbit

2000 ◽  
Vol 18 (4) ◽  
pp. 661-695 ◽  
Author(s):  
CLAUDE R. PHIPPS ◽  
JAMES P. REILLY ◽  
JONATHAN W. CAMPBELL
Keyword(s):  
Low Earth Orbit ◽  
Laser Source ◽  
Sounding Rocket ◽  
Earth Orbit ◽  
Laser Propagation ◽  
Optimum Parameters ◽  
Ablation Plasma ◽  
Light Concentration ◽  
Momentum Coupling ◽  
Flight Simulations

We derive optimum values of parameters for laser-driven flights into low Earth orbit (LEO) using an Earth-based laser, as well as sensitivity to variations from the optima. These parameters are the ablation plasma exhaust velocity vE and specific ablation energy Q*, plus related quantities such as momentum coupling coefficient Cm and the pulsed or continuous laser intensity that must be delivered to the ablator to produce these values. Different optima are found depending upon whether it is desired to maximize mass m delivered to LEO, maximize the ratio m/M of orbit to ground mass, or minimize cost in energy per gram delivered. Although it is not within the scope of this report to provide an engineered flyer design, a notional, cone-shaped flyer is described to provide a substrate for the discussion and flight simulations. The flyer design emphasizes conceptually and physically separate functions of light collection at a distance from the laser source, light concentration on the ablator, and autonomous steering. Approximately ideal flight paths to LEO are illustrated beginning from an elevated platform. We believe LEO launch costs can be reduced 100-fold in this way. Sounding rocket cases, where the only goal is to momentarily reach a certain altitude starting from near sea level, are also discussed. Nonlinear optical constraints on laser propagation through the atmosphere to the flyer are briefly considered.

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

Orbit Control Manoeuvre Strategy for Post-Mission De-Orbiting of a Low-Earth-Orbit Satellite

2015 ◽  
Vol 781 ◽  
pp. 495-499
Author(s):  
Manop Aorpimai ◽  
Pornthep Navakitkanok
Keyword(s):  
Space Debris ◽  
Electronic Devices ◽  
Low Earth Orbit ◽  
Propulsion System ◽  
Passive State ◽  
Earth Orbit ◽  
Orbit Control ◽  
Practical Strategy ◽  
Chemical Propulsion ◽  
Debris Mitigation

In this paper, we investigate a practical strategy for de-orbiting the retired satellite in low-Earth orbit for the space debris mitigation. The only means available onboard the spacecraft for performing the task is the chemical propulsion system with limited propellant provided. It is proposed to reduce the orbital perigee to reach a certain level where the atmospheric drag can play its role in lowering the satellite altitude, and eventually bringing it to re-entry within a defined period of time. The required delta-V is divided into a series under the constraints on the propulsion system and orbit control manoeuvre implementation. The results from the flight dynamics simulator suggest that a fraction of the remaining propellant available on the demonstrating mission, the Thaichote satellite, would be sufficient to accomplish the task. The strategy implementation will be another vital step in transferring the spacecraft to a safe passive state, where the fuel tank is empty, all batteries are discharged and all electronic devices are deactivated.

scholarly journals An Overview of the Space Debris Issue

1991 ◽  
Vol 112 ◽  
pp. 113-114
Author(s):  
Donald J. Kessler
Keyword(s):  
Space Debris ◽  
Primary Source ◽  
Low Earth Orbit ◽  
Earth Orbit ◽  
Astronomical Observations

The amount of man-made debris in orbit is now sufficient to create a flux in some regions of low Earth orbit which exceeds the flux of natural meteoroids. The primary source for this debris is from the fragmentation, or disintegration, of spacecraft. Future debris can be expected to result from random collisions between orbiting objects. This debris will require additional shielding for some spacecraft, will contaminate some types of meteoroid experiments, and contaminate some types of astronomical observations. Steps are being taken to minimize the accumulation of future debris.

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