DSMC-SPARTA aerodynamic characterization of a deorbiting CubeSat

Marín, C Alberto; Sebastião, Israel B.; Tamrazian, Sebastian; Spencer, David A.; Alexeenko, Alina

doi:10.1063/1.5119578

Cited by 5 publications

(4 citation statements)

References 3 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…Therefore, DSMC is a statistical numerical approach. Nowadays, the method is widely applied to the analysis of re-entry spacecraft [29,30] and LEO satellites [31] and is favored by researchers and engineers [21,27].…”

Section: Methodology and Code Validationmentioning

confidence: 99%

“…Before simulating 3D cases with SPARTA, it is a conventional prerequisite to check its installation and performance by replicating a previous study; in this case, the ADE from Purdue University was used [27]. By setting the SPARTA input parameters to the same values in the literature, C D at a 185 km orbital altitude and zero incident angles (α = 0, β = 0) is found to be identical to the reference value.…”

Section: Methodology and Code Validationmentioning

confidence: 99%

“…ADE is a 1U CubeSat designed by Purdue University and is equipped with a drag sail with a 1.346 m 2 cross-sectional area [27]. The NUST-3 CubeSat reserves 1.5 U onboard space for a 7.84 m 2 sail.…”

Section: The Design Of the Drag Sailmentioning

confidence: 99%

See 2 more Smart Citations

Aerodynamic Analysis of Deorbit Drag Sail for CubeSat Using DSMC Method

Chen,

Qin

et al. 2024

Aerospace

View full text Add to dashboard Cite

Reducing space debris is a critical challenge in current space exploration. This study focuses on designing a drag sail for CubeSat models and examining their aerodynamic properties using the direct simulation Monte Carlo (DSMC) method. The analysis encompasses the aerodynamic performance of intricate three-dimensional shapes with varying sail dimensions at orbital altitudes of 125 km, 185 km, 300 km, and 450 km. Additionally, free molecular flow (FMF) theory is applied and compared with the DSMC findings for both a flat-plate model and the CubeSat. The results reveal that FMF accurately predicts the drag coefficient at altitudes of 185 km and above, while significant discrepancies occur at lower altitudes due to increased inter-molecular collisions. This study also suggests that the drag sail substantially enhances the CubeSat’s drag force, which effectively reduces its deorbiting time.

show abstract

Section: Methodology and Code Validationmentioning

confidence: 99%

Section: Methodology and Code Validationmentioning

confidence: 99%

See 1 more Smart Citation

Aerodynamic Analysis of Deorbit Drag Sail for CubeSat Using DSMC Method

Chen,

Qin

et al. 2024

Aerospace

View full text Add to dashboard Cite

show abstract

“…It is an open source tool which offers both two-dimensional and three-dimensional capability and has been tested on other spacecraft [30,31] The panel method used in this work was based on method developed by Sentman [14]. Both the DSMC and panel method simulations return the forces acting on the body, however the drag will be sampled as the drag coefficient C D .…”

Section: Methods For Determining Drag In Vleomentioning

confidence: 99%

Drag reduction through shape optimisation for satellites in Very Low Earth Orbit

2021

View full text Add to dashboard Cite

Operating satellites at altitudes in Very Low Earth Orbit (VLEO) has many advantages. However, due to the higher atmospheric density of this region, satellites encounter significantly higher atmospheric drag.Depending on the mission, this may require a propulsive system to maintain the orbit which costs both fuel mass and volume. It is therefore desirable to reduce the drag in order to either reduce these costs or to extend the operational life. In this paper a series of viable aeroshell profiles are identified for satellites operating in VLEO using a Radial Basis Function-based surrogate model with data generated using both Panel Methods and Discrete Simulation Monte Carlo simulations. It was demonstrated that a maximum drag reduction of between 21% and 35% was achievable for the profiles when optimizing a bi-conic profile for minimum drag based on Discreet Simulation Monte Carlo simulations with an energy accommodation coefficient of 0.95. Accounting for the loss of internal volume and assuming the reduction in fuel mass results in an equally proportioned reduction in fuel system volume it was observed that only a 13% to 27% reduction was achieved.

show abstract