Simulation of the Mars Science Laboratory Parachute Performance and Dynamics

Lingard, J. Stephen; Darley, Matt; Underwood, John; Brown, Glen

doi:10.2514/6.2007-2507

Cited by 23 publications

(15 citation statements)

References 5 publications

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“…2) Lingard et al 3) have used the fluid structure interaction (FSI) to simulate a flexible supersonic parachute and examined the effects of Mach number and the trailing distance on the parachute. Barnhardt et al 4) presented a numerical simulation of a rigid parachute model using the detached-eddy simulation method, and found that the time-dependent deficit in the wake interacts with the canopy bow shock, causing the flow field around the parachute to become highly unsteady.…”

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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“…Tutt et al built the airflow model based on Eulerian algorithm and obtained the inflation characteristics of parachute through ALE algorithm [4][5][6]. Lingard et al demonstrated the stimulation and analysis of parachute performance in supersonic flow, highlighting the numerical modeling of parachute and airflow and airflow mesh generation [7][8]. Jia He et al and Cheng Han et al studied the kinematics of parachute inflation process and surrounding flow field, providing parameters of parachute and flow field variations during parachute inflation process [9][10][11][12].…”

Section: Introductionmentioning

confidence: 99%

Simulation and Experimental Analysis of the Wind Field inside the Air Deflector of a Sugarcane Leaf Cutting and Returning to Field Machine

Xu¹,

Wang²,

Zhen³

et al. 2016

Proceedings of the 2016 International Conference on Civil, Structure and Environmental Engineering

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This work investigated the self-excited wind field caused by rotating knife rollers inside the air deflector during the operation of the sugarcane leaf cutting and returning to field machine. Based on the arbitrary Lagrangian-Eulerian (ALE) method, a fluid-structure interaction simulation of wind field inside the air deflector was carried out under the condition of two clockwise rotating knife rollers, exploiting the finite element software LS-DYNA．The simulation results revealed an airflow confluence surface generated during the process of the airflow interaction, accompanied by formation of vortices. The wind field in the left and right outlets of the air deflector and regions near the ground between the two knife rollers is regular and stable. Airflow velocities below the deflector near the ground were measured. With both simulation and experimental evidences, we demonstrate that the horizontal wind velocity decreases with an increasing elevation above the ground, with a simulation deviation of velocity decreasing rate no more than 12%. In contrast, the vertical wind velocity shows an opposite correlation with height, and the simulation deviation of velocity increasing rate is no more than 26%. Our simulation and experimental data indicate a consistent variation trend of wind velocity. Insights from this study can be useful in designing and optimization of relevant structures and mechanisms involving air deflectors and knife rollers.

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“…Basically, the canopies of cases F and G are less deformed compared with those of cases B and C; in particular it is pronounced in case F. However, the trend in change is similar in the small and large canopies, and the "area oscillation" can be observed in both cases. Lingard 5) has suggested that the trailing distance should be X/d > 6+D/d, which can avoid the phenomenon observed in cases A or B. Therefore, we need to pay attention to the following.…”

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.…”

Section: Introductionmentioning

confidence: 99%

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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Simulation of the Mars Science Laboratory Parachute Performance and Dynamics

Cited by 23 publications

References 5 publications

Numerical Simulation of Supersonic Aerodynamic Interaction of a Parachute System

Numerical Simulation of Supersonic Aerodynamic Interaction of a Parachute System

Simulation and Experimental Analysis of the Wind Field inside the Air Deflector of a Sugarcane Leaf Cutting and Returning to Field Machine

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

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