Effects of suspension line on flow field around a supersonic parachute

Xue, Xiao; Koyama, Hiroto; Nakamura, Yoshiaki; Wen, Chih-Yung

doi:10.1016/j.ast.2015.02.014

Cited by 28 publications

(5 citation statements)

References 17 publications

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“…However, in case 2, suspension lines between the disk and band are omitted because they are extremely thin (please see Refs. [6,10] for their influences). Thus, the gap in case 2 is continuous.…”

Section: A Dgb Parachute Model Configurationmentioning

confidence: 99%

“…However, their conditions were limited to very low speed (0.6-1.2 m∕s). Xue and Nakamura [9] and Xue et al [10,11] conducted a series of studies on supersonic parachutes. In Refs.…”

mentioning

confidence: 99%

“…[10,11], they assumed the parachute canopy was rigid (i.e., no deformation was considered) and focused on its surrounding supersonic flow physics, such as shock interactions and oscillations: Particular attention was paid to the separation between the forebody and the canopy in Ref. [10], whereas the effects of the (rigid-body-modeled) suspension lines were discussed in Ref. [11].…”

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confidence: 99%

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Numerical Study of Surface Pressure Fluctuation on Rigid Disk-Gap-Band-Type Supersonic Parachutes

2020

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Section: A Dgb Parachute Model Configurationmentioning

confidence: 99%

“…However, their conditions were limited to very low speed (0.6-1.2 m∕s). Xue and Nakamura [9] and Xue et al [10,11] conducted a series of studies on supersonic parachutes. In Refs.…”

mentioning

confidence: 99%

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confidence: 99%

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Numerical Study of Surface Pressure Fluctuation on Rigid Disk-Gap-Band-Type Supersonic Parachutes

2020

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“…There are two approaches to gain the aerodynamic coefficients of a parachute, one is the numerical computation [5][6][7][8][9][10][11][12][13][14][15][16] and the other is the wind tunnel test [17,18]. Among the parachute's descent process of deployment, inflation and terminal, the aerodynamic performances are so complex that the numerical computation method is usually not correct.…”

Section: Introductionmentioning

confidence: 99%

Experimental Investigations on Aerodynamic Characteristics of Parachutes in Mars Probe Decelerator System

Dong¹,

Yang²,

Yu³

et al. 2018

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An experimental study is conducted to characterize the aerodynamic performances of two parachutes in the Mars probe decelerator system and the experiments are carried out in the 2.4 m×2.4 m transonic wind tunnel. The lift, drag and pitch moment coefficients versus the angle of attack from 0 to 25 degrees at Mach 0.4 and 0.8 are accurately measured and carefully analyzed. A novel mathematical model is proposed to express the aerodynamic characteristics of the parachutes. The obtained results show that the drag coefficient of the parachutes varies in a small range of 0.525~0.575 at Mach 0.4 and 0.8 as the angle of attack increases from 0 to 25 degrees. The simulated results of the propose model have a well agreement with the wind tunnel experimental data. The investigations in the present paper have a good significant to the engineering development of the parachutes in Mars probe decelerator system.

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“…Xue et al [8] conducted the simulations of three-dimensional (3-D) flexible supersonic parachute system and found that there are two key factors for the dynamics of the parachute system: the unsteady change in canopy shape and the aerodynamic interference between the capsule wake and the canopy shock. Xue et al [9] performed the simulations of supersonic parachute system with canopy shrouds, and shock waves are generated upon the canopy shrouds, which exacerbate the flow field instability. This is consistent with the experimental findings in the literature [6].…”

Section: Introductionmentioning

confidence: 99%