Numerical prediction of deployment, initial fill, and inflation of parachute canopies

Purvis, James W.

doi:10.2514/6.1984-787

Cited by 9 publications

(5 citation statements)

References 2 publications

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“…where σ s is the Cauchy stress of the structure, ρ s is the density of the structure, f s is the force on the structure, e is the specific internal energy, d v → /dt is the acceleration, and D → and T → are the displacement vector and stress vector of the structure. e solution of equations (2) and (3) is subject to equations (4) and (5) corresponding to the displacement boundary condition on boundary zΩ s 1 and the traction boundary condition on the boundary zΩ s 2 , respectively. e traction boundary is the fluid-structure interaction surface, where the air pressure acts on the fabric canopy.…”

Section: Membrane Shell Of the Porous Canopymentioning

confidence: 99%

“…Purvis coupled the kinematic equation of the canopy with that of the fluid in a tight coupling manner, but both the canopy structure model and the flow field model were simplified [1]. en, Purvis improved the coupling model, in which the canopy was used as the MSD model and the two-dimensional Euler equation was used to calculate the flow field [2]. Later on, Stein and Benney used a simplified arbitrary Lagrangian-Eulerian (SALE) CFD program and the MSD model of the canopy to calculate the inflation process of the C-9 flat circular parachute in loose coupling manner [3,4].…”

Section: Introductionmentioning

confidence: 99%

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Study on Transient Dynamics and Aerodynamic Characteristics of a New Type of High-Damping Four-Winged Rotating Parachute Inflation Process

Jiang

Mao

et al. 2020

Mathematical Problems in Engineering

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To decrease the opening shock as well as improve the resistance coefficient and stability of the parachute of aviation weapon under subsonic conditions, a new kind of high-damping four-winged rotating (HFWR) parachute is investigated in this paper. e transient dynamic behavior and aerodynamic characteristics of the parachute during the inflation process are studied. Considering the permeability, the 3D folded finite element (FE) model of the HFWR parachute is established based on the direct folding modeling technique, and the inflation process of the parachute under subsonic flow is simulated using the multimaterial arbitrary Lagrange-Euler (ALE) method. A series of wind tunnel tests are conducted to verify the numerical results. Besides, the opening performances of the HFWR parachute and the round parachute, which includes the inflation process, the dynamic response of the swing angle, and the opening shock load varying with time, are compared under the same conditions. e results show that the opening performance of the HFWR parachute is superior to the round parachute under specific military background. e fluid-structure interaction (FSI) simulation results show good consistency with the wind tunnel tests, which indicates that the numerical modeling can effectively simulate and predict the opening performance and aerodynamic characteristics of the rotating parachute. e modeling method in this paper can help shorten the development cycle, improve the cost effectiveness, and optimize the design of the parachute.

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Section: Membrane Shell Of the Porous Canopymentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Study on Transient Dynamics and Aerodynamic Characteristics of a New Type of High-Damping Four-Winged Rotating Parachute Inflation Process

Jiang

Mao

et al. 2020

Mathematical Problems in Engineering

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“…1 Progress in parallel computing has enabled the simulation of large and complex problems, yet certain sacrifices have been made to make the problem tractable. Historically, finite element methods (FEM) have been popular, and most problems have been solved with tetrahedral grids and no model for the geometric porosity of the parachute.…”

Section: Introductionmentioning

confidence: 99%

Simulation of Drogue Parachute for the Multi-Purpose Crew Vehicle using Computational Fluid Dynamics

Dinzl

Gidzak

Candler³

2013

AIAA Aerodynamic Decelerator Systems (ADS) Conference

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Simulations of a 10% scale Multi-Purpose Crew Vehicle and its drogue parachute were carried out using US3D, a finite-volume computational fluid dynamics code, with capsule angles of attack at 0, 30 and 50 degrees. A model for the geometric porosity of the parachute is incorporated which locally varies the mass flux through the surface based on the instantaneous flowfield. These simulations were then compared to wind tunnel tests, including mean drag measurements and particle image velocimetry data. It was found that the simulations matched the wind tunnel drag within 4% for α = 0 and 30 • with the maximum drag deficit due to the capsule being 13.4% at α = 0 • . Pressure data from the simulations was used to deform a structural model of the parachute to the correct inflated shape, as a precursor to future fluid structural interaction work.

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“…As early as the 70s of last century Wolf [1], Moog [2] et al adopted the continuous straightening model and the simplified spring damping model to analyze the parachute straightening process, which can predict the straightening process to a certain extent. By the 1980s, Purvis [3][4][5] created a more complex linear straightening model that discrete the parachute into mass nodes interconnected by damped springs and consider the effects of aerodynamics, tension, gravity, and friction. Purvis used this model to analyze the process of parachute deployment and predict line sail.…”

Section: Introductionmentioning

confidence: 99%

Numerical Analysis of the Influence of the Wake Flow Field in the Process of Parachute Deployment

Zhang¹,

Gao²

2018

dtcse

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The wake flow field of the return cabin has an effect on the process of parachute deployment. In this paper CFD method is used to analyze the tail flow field and the flow field data are brought into the dynamic analysis by plane division and interpolation. The influence of the tail flow field on the deployment process is analyzed in the case of Mars and Earth. The result shows that the greater the separation speed or the angle of attack, the smaller the influence of tail flow field and it should be considered under low angle of attack in Mars environment. The influence is small enough that can be ignored in Earth environment.

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Numerical prediction of deployment, initial fill, and inflation of parachute canopies

Cited by 9 publications

References 2 publications

Study on Transient Dynamics and Aerodynamic Characteristics of a New Type of High-Damping Four-Winged Rotating Parachute Inflation Process

Study on Transient Dynamics and Aerodynamic Characteristics of a New Type of High-Damping Four-Winged Rotating Parachute Inflation Process

Simulation of Drogue Parachute for the Multi-Purpose Crew Vehicle using Computational Fluid Dynamics

Numerical Analysis of the Influence of the Wake Flow Field in the Process of Parachute Deployment

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