Advanced Supersonic Parachute Inflation Research Experiment Preflight Trajectory Modeling and Postflight Reconstruction

Dutta, Soumyo; Karlgaard, Christopher D.; Tynis, Jake A.; O’Farrell, Clara; Sonneveldt, Bryan; Queen, Eric M.; Bowes, Angela; Leylek, Emily A.; Ivanov, Mark C.

doi:10.2514/1.a34706

Cited by 10 publications

(4 citation statements)

References 20 publications

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“…Dutta et al [6] presented a graphical representation of the correlation between the axial force coefficient ( )…”

Section: Combined External Force and Combined External Momentmentioning

confidence: 99%

“…Moreover, the parameters remain unaffected by the 6 predetermined interval, highlighting the genetic algorithm's ability to solve and calculate implicit parameters presented through mathematical modeling. Subsequently, this paper compares the drag coefficient and stable equilibrium angle of attack obtained from the aforementioned experiment with the measured values from a wind tunnel test conducted on a similar scaled parachute [6] . The contracted parachute inflated in the wind tunnel test has a nominal area of 0.588 m 2 , with an inflation condition of Ma0.4.…”

Section: Parameters Numerical Preset Interval 70% Confidence Probabil...mentioning

confidence: 99%

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Parameter identification of disk-gap-band parachute during steady descent

Jiang,

2024

J. Phys.: Conf. Ser.

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In light of the challenges associated with acquiring the display model for identifying parachute aerodynamic parameters, this study aims to establish a correlation model for the aerodynamic parameters of a specific type of disk-gap-band parachute during the steady drop stage of transonic and subsonic speeds. This will be achieved by employing the genetic algorithm and utilizing observed data from airdrop experiments. The findings indicate that the genetic algorithm can accurately calculate the aerodynamic parameters in dynamic simulation with a high level of precision. Additionally, the numerical distribution state of the parameters to be identified exhibits similarity in the multiple disk-gap-band parachute airdrop experiments, thereby confirming the accuracy of the model and methodology. Finally, the numerical ranges for the drag coefficient and the stable equilibrium angle of attack of this particular type of disk-gap-band parachute are provided. The results are compared with both the airdrop experiments and the wind tunnel experiment. The errors in question satisfy the criteria of engineering precision, and the verification process confirms the accuracy of the identification outcomes.

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“…Dutta et al [6] presented a graphical representation of the correlation between the axial force coefficient ( )…”

Section: Combined External Force and Combined External Momentmentioning

confidence: 99%

Section: Parameters Numerical Preset Interval 70% Confidence Probabil...mentioning

confidence: 99%

Parameter identification of disk-gap-band parachute during steady descent

Jiang,

2024

J. Phys.: Conf. Ser.

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“…3 Meanwhile, similar models were also used for trajectory analysis of other types of parachute systems, 4,5 and even for parachute dropping prediction in Mars environment. 6 Compared to multi-body dynamics model, the discrete models are mainly based on fluid structure coupling methods, such as Computational Fluid Dynamics/Mass spring Damper (CFD/MSD) models. The fabric is discretized into a series of mass points connected by springs and dampers.…”

Section: Introductionmentioning

confidence: 99%

Research on the influence of length-width ratio on cruciform parachute airdropping performance

Cheng

Ouyang

Zhang

et al. 2022

Journal of Industrial Textiles

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Different from the other design parameters in general drogues, there are few studies about the parameter of Length-Width Ratio (LWR). Therefore, the fluid structure coupling model based on the Finite Element Method was used to study the deceleration characteristics and terminal trajectory stability of parachute system in this work. And the graphic transformation technology commonly used in Computer Graphics was used to realize the following of flow field with the trajectory movement. In this work, the cruciform parachutes with different LWR were taken as the research objects, and the above method was used to obtain the trajectory curves, deceleration characteristic curves, and stability curves of the cruciform parachutes under different external conditions. It was found that the deceleration performance was negatively correlated with the LWR when the other design parameters and working conditions remained unchanged, and the trajectory stability and the stability of the parachute were positively correlated with the LWR. Subsequently, the cruciform parachute with the LWR of 4.5 was used for airdropping test, and the accuracy of numerical method used in this work was verified. Then the deceleration processes of cruciform parachute (LWR: 4.5) under different dropping conditions were calculated. It could be found that the external launching conditions had a limited impact on the deceleration performance. The LWR was another design parameter that had a greater impact on the deceleration performance after the parameter of canopy area. Finally, the drag coefficient correction equation representing the deceleration performance was proposed for the first time.

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“…Recently, the Low-Density Supersonic Decelerator (LDSD) supersonic flight tests were conducted to develop the supersonic disk-sail (SSDS) and the supersonic ring-sail (SSRS) parachutes based on the MSL parachute [20,21]; however, the newly developed parachutes failed in each flight test. 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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Advanced Supersonic Parachute Inflation Research Experiment Preflight Trajectory Modeling and Postflight Reconstruction

Cited by 10 publications

References 20 publications

Parameter identification of disk-gap-band parachute during steady descent

Parameter identification of disk-gap-band parachute during steady descent

Research on the influence of length-width ratio on cruciform parachute airdropping performance

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

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