Simulation of Fluid-Structure Interaction of the Mars Science Laboratory Parachute

Gidzak, Vladimyr M.; Barnhardt, Michael; Drayna, Travis; Nompelis, Ioannis; Candler, Graham V.; Garrard, William L.

doi:10.2514/6.2008-6910

Cited by 10 publications

(4 citation statements)

References 9 publications

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“…This suggests a pressurization and depressurization of the parachute interior determined by the bow shock. Testing and computational fluid dynamics simulations of a rigid DGB parachute configuration exhibited a similar bow-shock shape variation in a cyclical manner, suggesting that the physical mechanism driving the instability is aerodynamic [15,18,22]. The flowfield during an area oscillation is shown in Fig.…”

Section: Shadowgraphmentioning

confidence: 94%

“…Test conditions were chosen to match the Mach and Reynolds numbers of the MSL deployment envelope. CFD analyses suggest that the supersonic parachute instability under investigation is dependent on Reynolds number and Mach number [18]. To match the Reynolds number on Mars, the test dynamic pressure is significantly higher than the flight value.…”

Section: A Wind-tunnel Test Configurationmentioning

confidence: 98%

See 1 more Smart Citation

Supersonic Performance of Disk-Gap-Band Parachutes Constrained to a 0-Degree Trim Angle

Sengupta

Kelsch²,

Roeder³

et al. 2009

Journal of Spacecraft and Rockets

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Supersonic wind-tunnel tests of 0.813 m disk-gap-band parachutes were conducted in a 10 10 ft cross section of a closed-loop wind tunnel. Four-percent-scale parachutes were attached to a 4%-scale Mars Science Laboratory (Viking-type) entry vehicle to simulate the free-flight configuration. The parachutes were tested from Mach 2 to 2.5 over a Reynolds number Re range of 2 10 5 to 1:3 10 6 , representative of the Mars flight deployment envelope. A constrained parachute configuration was investigated to quantify the effect of parachute trim angle with respect to alignment with the entry-vehicle wake. In the constrained configuration, the parachutes were supported at the vent, using a rod that restricted parachute translation along a single axis. This was investigated for fixed trim angles of 0 and 10 degrees from the velocity vector. In the unconstrained configuration, the parachute was permitted to translate as well as trim and cone, in a manner similar to free flight. Nonintrusive test diagnostics were selected. An in-line load cell provided measurement of unsteady and mean parachute normal force. High-speed shadowgraph video of the upstream parachute flowfield was used to capture bow-shock motion and standoff distance. Stereo particle image velocimetry of the flowfield upstream of the parachute provided spatially resolved measurements of all three velocity components. Multiple high-speed-video views were used to document the supersonic inflation, parachute trim angle, projected area, and frequency of area oscillations. In addition, reflective targets placed in the interior of the canopy enabled photogrammetric reconstruction of the canopy-fabric motion (in both time and space) from the high-speedvideo data. Nomenclatureor constructed diameter D p = projected diameter d = entry-vehicle diameter F D = axial drag force F D;RMS = axial rms drag M = Mach number m p = parachute mass q = freestream dynamic pressure Re = Reynolds number t = time t FI = time to full inflation t = nondimensional inflation time x=d = nondimensional trailing distance v = freestream velocity p = mass ratio ! AO = area oscillation frequency

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Section: Shadowgraphmentioning

confidence: 94%

Section: A Wind-tunnel Test Configurationmentioning

confidence: 98%

Supersonic Performance of Disk-Gap-Band Parachutes Constrained to a 0-Degree Trim Angle

Sengupta

Kelsch²,

Roeder³

et al. 2009

Journal of Spacecraft and Rockets

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“…The test matrix for the flexible experiment is shown in Table 2. As simulations suggested area oscillations are turbulence dependent, test conditions were chosen to match the Mach and Reynolds numbers of the MSL deployment envelope, resulting in substantially higher dynamic pressures(Q~20 kPa) than flight 30,33 . These tests are referred to as "High" Q in the test matrix.…”

Section: Flexible Parachute Experimentsmentioning

confidence: 99%

Findings from the Supersonic Qualification Program of the Mars Science Laboratory Parachute System

Sengupta

Steltzner

Witkowski

et al. 2009

20th AIAA Aerodynamic Decelerator Systems Technology Conference and Seminar

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In 2012, the Mars Science Laboratory Mission (MSL) will deploy NASA's largest extra-terrestrial parachute, a technology integral to the safe landing of its advanced robotic explorer on the surface. The supersonic parachute system is a mortar deployed 21.5 m disk-gap-band (DGB) parachute, identical in geometric scaling to the Viking era DGB parachutes of the 1970's. The MSL parachute deployment conditions are Mach 2.3 at a dynamic pressure of 750 Pa. The Viking Balloon Launched Decelerator Test (BLDT) successfully demonstrated a maximum of 700 Pa at Mach 2.2 for a 16.1 m DGB parachute in its AV4 flight. All previous Mars deployments have derived their supersonic qualification from the Viking BLDT test series, preventing the need for full scale high altitude supersonic testing. The qualification programs for Mars Pathfinder, Mars Exploration Rover, and Phoenix Scout Missions were all limited to subsonic structural qualification, with supersonic performance and survivability bounded by the BLDT qualification. The MSL parachute, at the edge of the supersonic heritage deployment space and 33% larger than the Viking parachute, accepts a certain degree of risk without addressing the supersonic environment in which it will deploy. In addition, MSL will spend up to 10 seconds above Mach 1.5, an aerodynamic regime that is associated with a known parachute instability characterized by significant canopy projected area fluctuation and dynamic drag variation. This aerodynamic instability, referred to as "area oscillations" by the parachute community has drag performance, inflation stability, and structural implications, introducing risk to mission success if not quantified for the MSL parachute system. To minimize this risk and as an alternative to a prohibitively expensive high altitude test program, a multi-phase qualification program using computation simulation validated by subscale test was developed and implemented for MSL. The first phase consisted of 2% of fullscale supersonic wind tunnel testing of a rigid DGB parachute with entry-vehicle to validate two high fidelity computational fluid dynamics (CFD) tools. The computer codes utilized Large Eddy Simulation and Detached Eddy Simulation numerical approaches to accurately capture the turbulent wake of the entry vehicle and its coupling to the parachute bow-shock. The second phase was the development of fluid structure interaction (FSI) computational tools to predict parachute response to the supersonic flow field. The FSI development included the integration of the CFD from the first phase with a finite element structural model of the parachute membrane and cable elements. In this phase, a 4% of full-scale supersonic flexible parachute test program was conducted to provide validation data to the FSI code and an empirical dataset of the MSL parachute in a flight-like environment. The final phase is FSI simulations of the full-scale MSL parachute in a Mars type deployment. Findings from this program will be presented in terms of code development and validation, empirica...

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“…Barnhardt et al [3] used the detached-eddy simulation (DES) method to investigate the flow field around a rigid supersonic parachute system, and showed that the time-dependent deficit in the wake interacts with the canopy shock. Gidzak et al [4,5] further compared the simulation results obtained using the DES method with the experimental results and revealed that the instability coming from the capsule wake leads to a pressurization cycle in the canopy. Recent studies using subscale Mars Science Laboratory parachute models have shown that the flow instability of the parachute system originates from the aerodynamic interference between the canopy shock and the capsule wake, and that it depends on the Mach number, the Reynolds number, the capsule shape, and proximity to a forebody [6].…”

Section: Introductionmentioning

confidence: 99%

Parametric Study on Aerodynamic Interaction of Supersonic Parachute System

et al. 2015

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Simulation of Fluid-Structure Interaction of the Mars Science Laboratory Parachute

Cited by 10 publications

References 9 publications

Supersonic Performance of Disk-Gap-Band Parachutes Constrained to a 0-Degree Trim Angle

Supersonic Performance of Disk-Gap-Band Parachutes Constrained to a 0-Degree Trim Angle

Findings from the Supersonic Qualification Program of the Mars Science Laboratory Parachute System

Parametric Study on Aerodynamic Interaction of Supersonic Parachute System

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