Numerical Study of Magnetohydrodynamic Flow Control Along Superorbital Reentry Trajectories

Shimosawa, Yuta; Fujino, Takayasu

doi:10.2514/1.a33340

Cited by 34 publications

(1 citation statement)

References 21 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…In the past 20 years, magnetic control technology has been supplemented by experiments and simulations, and the research on magnetic control technology has also expanded to other aspects. The research contents include magnetic interaction model (Lineberry et al 2002, Bityurin et al 2004a, Shneider and Macheret 2005, Bityurin and Bocharov 2006, Nagata et al 2013, magnetic field type (Li et al 2017a, Yao et al 2018, re-entry orbit (Shimosawa andFujino 2016, Fujino andTakahashi 2022), simulation (Poggie and Gaitonde 2002, Fujino et al 2003, Bityurin et al 2005, Katsurayama et al 2008, Shimosawa and Fujino 2016, Li et al 2017b, experiment (Bityurin et al 2004b, Smith et al 2018, Lefevre et al 2021 and concept (Bisek et al 2013, Balasubramanian et al 2016. So far, many studies have proved that magnetic control technology has broad application prospects in many situations (Lineberry et al 2000, Batenin et al 2001.…”

Section: Introductionmentioning

confidence: 99%

Side plasma flow and stagnation of a conical blunt body vehicle under an axial dipole magnetic field

Wang,

Tian,

et al. 2023

Fluid Dyn. Res.

View full text Add to dashboard Cite

The study of plasma flow under the thermal protection magnetic field of reentry vehicle is helpful to verify the magnetic control thermal protection technology and further understand its flow law. By solving hypersonic magnetohydrodynamics equations and combining with dipole magnetic field conditions, the plasma flow mechanism of RAM-CII (Radio Attenuation Measurement Experiment) spacecraft at 61km altitude is analyzed and compared with OREX (Orbital Reentry Experiment) spacecraft under the same conditions. The results show that the plasma flow of RAM-CII is more complex than that of OREX, and there are several regions with different Lorentz force directions near the aircraft, which play the role of plasma ejection and adsorption. Under the action of Lorentz force, the side flow of the aircraft will be separated and reattached, and the fluid stagnation zone will be generated. The results show that for different shapes of aircraft, the flow laws caused by magnetic thermal protection technology are different, and the side flow may be greatly affected.

show abstract