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Research Papers

Multidirection Validation of a Finite Element 50th Percentile Male Hybrid III Anthropomorphic Test Device for Spaceflight Applications

[+] Author and Article Information
Derek A. Jones

Wake Forest University School of Medicine,
Virginia-Tech Wake Forest University Center for
Injury Biomechanics,
575 N. Patterson Avenue, Suite 120,
Winston-Salem, NC 27101
e-mail: derek.alexander.jones@gmail.com

James P. Gaewsky

Wake Forest University School of Medicine,
Virginia-Tech Wake Forest University Center for
Injury Biomechanics,
575 N. Patterson Avenue, Suite 120,
Winston-Salem, NC 27101
e-mail: jgaewsky@wakehealth.edu

Mona Saffarzadeh

Wake Forest University School of Medicine,
Virginia-Tech Wake Forest University Center for
Injury Biomechanics,
575 N. Patterson Avenue, Suite 120,
Winston-Salem, NC 27101
e-mail: msaffarz@wakehealth.edu

Jacob B. Putnam

KBRWyle,
2400 NASA Parkway,
Houston, TX 77058
e-mail: jacob.putnam@wyle.com

Ashley A. Weaver

Wake Forest University School of Medicine,
Virginia-Tech Wake Forest University Center for
Injury Biomechanics,
575 N. Patterson Avenue, Suite 120,
Winston-Salem, NC 27101
e-mail: asweaver@wakehealth.edu

Jeffrey T. Somers

KBRWyle,
2400 NASA Parkway,
Houston, TX 77058
e-mail: jeffrey.somers@wyle.com

Joel D. Stitzel

Wake Forest University School of Medicine,
Virginia-Tech Wake Forest University Center for
Injury Biomechanics,
575 N. Patterson Avenue, Suite 120,
Winston-Salem, NC 27101
e-mail: jstitzel@wakehealth.edu

1Corresponding author.

Manuscript received May 22, 2018; final manuscript received October 12, 2018; published online January 18, 2019. Editor: Beth A. Winkelstein. The United States Government retains, and by accepting the article for publication, the publisher acknowledges that the United States Government retains, a nonexclusive, paid-up, irrevocable, worldwide license to publish or reproduce the published form of this work, or allow others to do so, for United States government purposes.

J Biomech Eng 141(3), 031004 (Jan 18, 2019) (9 pages) Paper No: BIO-18-1243; doi: 10.1115/1.4041906 History: Received May 22, 2018; Revised October 12, 2018

The use of anthropomorphic test devices (ATDs) for calculating injury risk of occupants in spaceflight scenarios is crucial for ensuring the safety of crewmembers. Finite element (FE) modeling of ATDs reduces cost and time in the design process. The objective of this study was to validate a Hybrid III ATD FE model using a multidirection test matrix for future spaceflight configurations. Twenty-five Hybrid III physical tests were simulated using a 50th percentile male Hybrid III FE model. The sled acceleration pulses were approximately half-sine shaped, and can be described as a combination of peak acceleration and time to reach peak (rise time). The range of peak accelerations was 10–20 G, and the rise times were 30–110 ms. Test directions were frontal (−GX), rear (GX), vertical (GZ), and lateral (GY). Simulation responses were compared to physical tests using the correlation and analysis (CORA) method. Correlations were very good to excellent and the order of best average response by direction was −GX (0.916±0.054), GZ (0.841±0.117), GX (0.792±0.145), and finally GY (0.775±0.078). Qualitative and quantitative results demonstrated the model replicated the physical ATD well and can be used for future spaceflight configuration modeling and simulation.

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Figures

Grahic Jump Location
Fig. 1

Hybrid III positioned in the 90–90–90 deg seat with head, shoulder, hip, and leg guards in the simulation (left) and physical test (right). Foam padding shown in white.

Grahic Jump Location
Fig. 2

Maximum excursion comparisons between physical and FE models for 10-G, 70 ms sled acceleration pulses. (a) frontal, (b) rear, (c) lateral 10-G configuration, and (d) vertical directions displayed.

Grahic Jump Location
Fig. 3

Comparison of FE and physical Hybrid III results from a +GX (rear) impulse with a 10 G peak acceleration and 110 ms rise time. Resultant linear acceleration of the head (a), y-rotational velocity of the head (b), neck y-moment (c), upper neck resultant force (d), T6 resultant linear acceleration (e) and pelvis resultant linear acceleration (f).

Grahic Jump Location
Fig. 4

Stress–strain curve for foam material in compression

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