Overview of the ASPIRE Project's Supersonic Flight Tests of a Strengthened DGB Parachute

O’Farrell, Clara; Sonneveldt, Bryan; Karhgaard, Chris; Tynis, Jake A.; Clark, Ian G.

doi:10.1109/aero.2019.8741611

Cited by 22 publications

(6 citation statements)

References 9 publications

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“…Figure 16(left) reports the predicted time‐histories of the total drag generated by the parachute system using the two different material models described above and contrasts them with their counterpart measured during the flight test 38 . The reader can observe that both considered fabric material models lead to simulated total drag time‐histories that match reasonably well their counterpart measured during the SR03 flight test, particularly during the inflation process (

t < 0.4

s).…”

Section: Applications and Performance Assessmentsmentioning

confidence: 71%

“…The viscous flow is modeled using AERO‐F's LES turbulence modeling capability. The free‐stream conditions are set to those of the SR03 flight test at the instance of line‐stretch 38 —that is, the free‐stream Mach number is set to

M_{\infty} = 1.88

, the free‐stream density is set to

ρ_{\infty} = 6.01 \times 1 0^{- 3} kg m^{- 3}

, and the free‐stream pressure is set to

P_{\infty} = 414 Pa

. While the supersonic FSI simulation was performed in dimensional mode, it is noted here that the corresponding Reynolds number based on the parachute diameter is

R e_{D} = 3.3 \times 1 0^{6}

.…”

Section: Applications and Performance Assessmentsmentioning

confidence: 99%

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A mechanics‐informed artificial neural network approach in data‐driven constitutive modeling

Asad

Avery

Farhat

2022

Numerical Meth Engineering

105

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A mechanics‐informed artificial neural network approach for learning constitutive laws governing complex, nonlinear, elastic materials from strain–stress data is proposed. The approach features a robust and accurate method for training a regression‐based model capable of capturing highly nonlinear strain–stress mappings, while preserving some fundamental principles of solid mechanics. In this sense, it is a structure‐preserving approach for constructing a data‐driven model featuring both the form‐agnostic advantage of purely phenomenological data‐driven regressions and the physical soundness of mechanistic models. The proposed methodology enforces desirable mathematical properties on the network architecture to guarantee the satisfaction of physical constraints such as objectivity, consistency (preservation of rigid body modes), dynamic stability, and material stability, which are important for successfully exploiting the resulting model in numerical simulations. Indeed, embedding such notions in a learning approach reduces a model's sensitivity to noise and promotes its robustness to inputs outside the training domain. The merits of the proposed learning approach are highlighted using several finite element analysis examples. Its potential for ensuring the computational tractability of multi‐scale applications is demonstrated with the acceleration of the nonlinear, dynamic, multi‐scale, fluid‐structure simulation of the supersonic inflation dynamics of a parachute system with a canopy made of a woven fabric.

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t < 0.4

s).…”

Section: Applications and Performance Assessmentsmentioning

confidence: 71%

M_{\infty} = 1.88

, the free‐stream density is set to

ρ_{\infty} = 6.01 \times 1 0^{- 3} kg m^{- 3}

, and the free‐stream pressure is set to

P_{\infty} = 414 Pa

. While the supersonic FSI simulation was performed in dimensional mode, it is noted here that the corresponding Reynolds number based on the parachute diameter is

R e_{D} = 3.3 \times 1 0^{6}

.…”

Section: Applications and Performance Assessmentsmentioning

confidence: 99%

A mechanics‐informed artificial neural network approach in data‐driven constitutive modeling

Asad

Avery

Farhat

2022

Numerical Meth Engineering

105

View full text Add to dashboard Cite

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“…The second flight test (SR02) occurred on March 31 2018 14 . Here, the payload separated from the Black Brant second stage at an altitude of 53.0 km and reached an apogee of 54.8 km before accelerating back towards the surface of the Earth.…”

Section: Figure 4 Trajectory During the First Flight Test (Sr01) Figures Show The Variation Of Mach Number Altitude Attitude And Dynamicmentioning

confidence: 99%

ASPIRE Aerodynamic Models and Flight Performance

Muppidi

O’Farrell

Norman

et al. 2019

AIAA Aviation 2019 Forum

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Experiments (ASPIRE) project was established to test full-scale supersonic parachutes at Mars-relevant conditions, as a risk-reduction activity for NASA's upcoming Mars2020 mission. Deployment and inflation of Disk-Gap-Band (DGB) parachutes were examined at Mach number and dynamic pressure conditions relevant to Mars2020, using a sounding rocket platform. The flight tests examined two parachutes: a build-to-print version of the parachute used by the Mars Science Laboratory and a strengthened version of this parachute that has the same geometry but differs in materials and construction. The first flight test (SR01) of the built-to-print parachute took place on October 4, 2017, followed by the first test of the strengthened parachute during flight SR02 on March 31, 2018. A second test of the strengthened parachute with a higher target load, SR03, took place on September 7, 2018. Over the sequence of the three tests, the parachute was exposed to increasing aerodynamic loads with the peak load during SR03 being significantly larger than is expected during a Martian descent. All three tests were successful: the parachute deployment and inflation occurred at the intended conditions, the measurement systems performed as designed and provided the data, and the parachutes survived the aerodynamic loads they were exposed to. The flight tests yielded valuable data on parachute forces and high-speed imagery of the deployment and inflation process.The final paper will provide details of the aerodynamic behavior and performance of the parachute over the three tests, along with comparisons to pre-flight predictions.

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“…Subsequently, the Advanced Supersonic Parachute Inflation Research Experiments (ASPIRE) project was conducted as a risk reduction activity for the Mars 2020 mission [22][23][24]. This leads to a critical need to better understand the dynamics of the supersonic parachute inflation in a Mars-like environment [25].…”

Section: Introductionmentioning

confidence: 99%

Analysis and Verification of Aerodynamic Characteristics of Tianwen-1 Mars Parachute

Huang

Wang

2022

Space Sci Technol

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The Mars parachute flight environment is supersonic, low-density, and low dynamic pressures. To ensure the operating performance and reliability, the design optimization and verification of the Tianwen-1 Mars parachute have been carried out. Firstly, through supersonic and subsonic wind tunnel tests, the design optimization of the parachute structure is realized. Subsequently, the high-altitude flight tests of four parachutes were conducted, the drag coefficient and the oscillation angle of the parachute from supersonic to subsonic speed were gained, and the aerodynamic characteristics and reliable opening of the parachutes were thoroughly tested and verified. This article presents the design, development, and qualification of the Tianwen-1 Mars parachute, which can provide a reference for the creation of future Mars exploration parachutes.

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Overview of the ASPIRE Project's Supersonic Flight Tests of a Strengthened DGB Parachute

Cited by 22 publications

References 9 publications

A mechanics‐informed artificial neural network approach in data‐driven constitutive modeling

A mechanics‐informed artificial neural network approach in data‐driven constitutive modeling

ASPIRE Aerodynamic Models and Flight Performance

Analysis and Verification of Aerodynamic Characteristics of Tianwen-1 Mars Parachute

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