A computational study of supersonic disk-gap-band parachutes using Large-Eddy Simulation coupled to a structural membrane

Karagiozis, Kostas; Kamakoti, Ramji; Cirak, Fehmi; Pantano, Carlos

doi:10.1016/j.jfluidstructs.2010.11.007

Cited by 87 publications

(36 citation statements)

References 52 publications

(51 reference statements)

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“…1) However, in a full-scale experiment of the supersonic parachute system © 2013 The Japan Society for Aeronautical and Space Sciences * Present address: Mitsubishi Heavy Industries Ltd., Ama District, Aichi, 490-1445, Japan in flight situations, because of the interaction of the capsule wake with the canopy bow shock, the drag decreases and flow instability increases.…”

Section: Introductionmentioning

confidence: 99%

Numerical Simulation of Supersonic Aerodynamic Interaction of a Parachute System

Xue

Koyama

Nakamura

2013

AEROSPACE TECHNOLOGY JAPAN

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In the present study the supersonic flow over rigid parachute models is studied by numerically solving the three-dimensional compressible Navier-Stokes equations at a free stream Mach number of 2. The parachute system employed here consists of a capsule and a canopy. Two models are considered: model A and model B. The former is the same model as the experiment, where the canopy is connected with the capsule by a rod, and the whole system is supported by another rod, while the latter does not have these rods. The objective of the present study is to examine the flow field produced by these models, and analyze the effects of aerodynamic interaction such as shock/shock and wake/shock interactions on it. The numerical results show good agreement with the experimental data in the case of model A. In addition, it is found that the difference of flow features between models A and B is rather small. The unsteady flow pulsation phenomenon observed in this study can be demonstrated using three processes; the bow shock formed ahead of the capsule periodically inflates and laterally expands, which is caused by upstream propagation and lateral expansion of the complicated wake/rear shock and fore shock/rear shock interaction systems.

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Section: Introductionmentioning

confidence: 99%

Numerical Simulation of Supersonic Aerodynamic Interaction of a Parachute System

Xue

Koyama

Nakamura

2013

AEROSPACE TECHNOLOGY JAPAN

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“…In case C, the canopy shock moves upstream of the parachute mouth, and interacts with the capsule wake, which is a main source of the unsteadiness in the flow field. 6,7) This causes repetition of the pressure change inside the canopy, as seen in Fig. 12.…”

Section: Effect Of Parachute Trailing Distancementioning

confidence: 99%

“…21, which suggests that the interaction between the capsule wake and the canopy shock wave is a main source of the unsteadiness in the flow field, 6,7) leading to large pressure fluctuations inside the canopy with a consequential shape change. The time history of drag coefficient for cases F and G are shown in Fig.…”

Section: Canopy Sizementioning

confidence: 99%

“…Lingard et al 5) used the method of fluid structure interaction (FSI) to simulate a flexible supersonic parachute and examined the effects of Mach number and the trailing distance on the parachute. Karagiozis et al 6) performed a simulation of a large-scale flexible supersonic DGB parachute using large-eddy simulation coupled with a structural membrane based on the finite element model, and reproduced the area oscillations of the canopy, which were often observed in the experiment at higher Mach number. Recent subscale MSL parachute models were experimentally and numerically investigated at supersonic conditions.…”

Section: Introductionmentioning

confidence: 99%

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Numerical Simulation of a Three-Dimensional Flexible Parachute System under Supersonic Conditions

Xue

Nakamura

2013

AEROSPACE TECHNOLOGY JAPAN

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In the present study, the supersonic flow over a three-dimensional flexible parachute system is numerically simulated using a simple "immersed boundary method" together with the weak fluid-structure coupling scheme. The parachute system employed here consists of a capsule and a canopy. The mass-spring-damper model is applied to solve the structural dynamics of the flexible parachute system. The objective of this study is to analyze the effects of aerodynamic interaction such as wake/shock interaction on the dynamics of the canopy behavior, and clarify the performance of the flexible parachute system in terms of Mach number, the ratio of a capsule to a canopy diameter, and the trailing distance between the capsule and canopy. As a result, it is found that there are two key factors for the dynamics of the parachute system: one is the unsteady change in canopy shape and the other the aerodynamic interference between the capsule wake and the canopy shock. As the trailing distance increases reasonably, the area oscillation of the canopy shape is observed. However, by reducing the canopy size in the certain smaller trailing distance case, the canopy deformation is improved. Moreover, it is found that the free stream Mach number has a big impact on the canopy behavior in the smaller Mach number case, where the canopy undergoes smaller deformation, leading to a larger drag coefficient.

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“…Tutt et al applied the arbitrary Lagrangian-Eulerian method to solve the practical engineering problems [10,11]. Karagiozis et al used the large eddy simulation method to investigate the supersonic parachute [12]. Fan proposed the nonlinear finite element method based on the implicit algorithm to calculate the C9 parachute inflating process [13].…”

Section: Introductionmentioning

confidence: 99%

Numerical Study of Extra-Large Parachute’s Pre-Inflation in Finite Mass Situation

Sun

Cheng

Yang

2018

Autex Research Journal

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The extra-large parachutes were different from the common parachutes because of their size and opening process. Some undesirable inflation phenomena such as canopy winding and whipping usually appeared in their pre-inflation process. However, the mechanical mechanism of these phenomena was very difficult to be explained by experimental means. In this paper, the pre-inflation process in finite mass situation of an extra-large parachute was calculated by explicit finite elements. According to the results, the pre-inflation process can be subdivided into symmetric inflation stage, undesirable inflation stage, and stable inflation stage. The canopy winding and whipping mainly occurred in the second stage. With the continuous deceleration of parachute-payload system, the top of canopy without effective constraints would appear winding and whipping under the function of inertia force. The canopy winding and whipping increased the difficulty of canopy expanding and then caused asymmetric inflation. The above undesirable phenomena had a great influence on the deceleration effect and were easy to cause the recovery failure. The actual airdrop experiments also proved that the lack of effective constraints on the canopy top will cause undesirable inflation phenomena. The conclusions in this paper can also provide a reference for extra-large parachute design and research.

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A computational study of supersonic disk-gap-band parachutes using Large-Eddy Simulation coupled to a structural membrane

Cited by 87 publications

References 52 publications

Numerical Simulation of Supersonic Aerodynamic Interaction of a Parachute System

Numerical Simulation of Supersonic Aerodynamic Interaction of a Parachute System

Numerical Simulation of a Three-Dimensional Flexible Parachute System under Supersonic Conditions

Numerical Study of Extra-Large Parachute’s Pre-Inflation in Finite Mass Situation

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