Simulation of the orbital decay of a spacecraft in low Earth orbit due to aerodynamic drag

2021 ◽  
pp. 1-19
Author(s):  
R. Kumar ◽  
R. Singh ◽  
A.K. Chinnappan ◽  
A. Appar
Keyword(s):  
Space Debris ◽  
Aerodynamic Drag ◽  
Direct Simulation Monte Carlo ◽  
Low Earth Orbit ◽  
Earth Orbit ◽  
Aerodynamic Coefficients ◽  
Orbital Perturbations ◽  
Orbital Decay ◽  
Simulation Monte Carlo ◽  
Tumbling Motion

Abstract Orbiting objects in space are exposed to the risk of collision with space debris over their lifetime. Space debris orbiting in space experiences orbital decay due to various orbital perturbations. This work considers only orbital perturbations due to aerodynamic forces, which spacecraft experience due to the presence of a rarefied atmosphere, causing tumbling motion and orbital decay. Analysis of the orbital decay of a spacecraft is carried out by considering the variation of the drag coefficient as a function of its shape, motion and angle-of-attack. An in-house Direct Simulation Monte Carlo (DSMC) solver is modified for aerodynamic analysis of a spacecraft orbiting in the free molecular regime in low Earth orbit. In addition, an orbital dynamics model is developed to simulate the tumbling motion of a spacecraft and its orbital decay. The orbital decay trajectory is predicted for two sample spacecrafts using the aerodynamic coefficients obtained from the in-house DSMC solver as inputs to the orbital decay model. This study analyses and explores in detail the effects of the aerodynamic coefficients and shape of a spacecraft on its orbital decay.

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

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.

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.

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