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Hypervelocity impact simulations on space structures using various shielding systems

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Abstract

In this study, hypervelocity impact (HVI) simulations between a space object and space structure using various shielding systems are conducted. A nonlinear structural dynamics analysis code, LS-DYNA, is used. The space object at 6.910 km/s is modeled as an Al2017-T4 sphere with a diameter of 2 mm. The four types of space sandwich structures with the same mass of 0.0121 kg are considered to investigate the shielding performances and are modeled as honeycomb core sandwich panel (HCSP), lattice core sandwich panel (LCSP), LC/HCSP, and HC/LCSP. The shielding performances and final failure shapes of the space structures are studied through the HVI simulations on the space structure using various shielding systems. The HCSP fails to protect due to the channeling effect, resulting in failure to the rear wall. The three types of the shielding systems using the LC successfully protect the space structure from the HVI with the space object as the debris cloud is distributed by the multishock effect.

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Abbreviations

ρ :

Density, kg/m3

v :

Velocity, m/s

t :

Time, s

σ :

Stress, Pa

e :

Internal energy, J

NP :

Number of particles

ρ 0 :

Initial density, kg/m3

C 0 :

Speed of sound in material, m/s

μ :

Condition of compression (or expansion)

y :

Grüneisen gamma

a :

First-order volume correction of y0

V s :

Shock velocity, m/s

V p :

Particle velocity, m/s

S 1−3 :

Dimensionless coefficients of the slope vs = f(vp) curve

E :

Internal energy, J

G :

Shear modulus, Pa

A :

Initial yield strength, Pa

B :

Hardening constant, Pa

n :

Hardening exponent

C :

Strain rate constant

ε :

Effective plastic strain

\(\dot{\varepsilon}^{\star}\) :

Dimensionless plastic strain rate, \(\dot{\varepsilon}/\dot{\varepsilon}_{0}\)

\(\dot{\varepsilon}^{0}\) :

Reference strain rate, s−1

T ⋆ :

Homogeneous temperature, (T-Tref)/(Tmelt-Tref)

m :

Thermal softening exponent

ε p :

Plastic strain

ε f :

Equivalent strain to fracture

σ ⋆ :

Dimensionless pressure-stress ratio, σm/σ

D 1−5 :

Material constants of damage in material

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Acknowledgments

The work was supported by the National Research Foundation of Korea (NRF) grant funded by the Korea government (MSIT) (NRF-2022M1A3B8076744). Part of this paper was presented at the 2022 Korean Society for Aeronautical and Space Sciences Fall Conference, Korea, November 16–18, 2022.

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Authors and Affiliations

  1. Satellite System 5 Team, Hanwha Systems, Yongin, 17121, Korea

    Hyun-Cheol Shin

  2. Department Aerospace Engineering, Chungnam National University, Daejeon, 34134, Korea

    Mi Jang & Jae-Sang Park

Authors
  1. Hyun-Cheol Shin
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  2. Mi Jang
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  3. Jae-Sang Park
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Correspondence to Jae-Sang Park.

Additional information

Jae-Sang Park received Ph.D. degree in Mechanical and Aerospace engineering, from Seoul National University, Seoul, Korea in 2006. From 2006 to 2007, he worked as a post doctor at Flight Vehicle Research Center, Seoul National University. From 2008 to 2013, he worked as a research professor at Konkuk University, Seoul, Korea. Dr. Park is currently a Professor, Department of Aerospace engineering, Chungnam National University, Daejeon, Korea. His research interests include aerospace structural analyses and rotorcraft aeromechanics analyses.

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Shin, HC., Jang, M. & Park, JS. Hypervelocity impact simulations on space structures using various shielding systems. J Mech Sci Technol 38, 401–410 (2024). https://doi.org/10.1007/s12206-023-1233-8

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  • DOI: https://doi.org/10.1007/s12206-023-1233-8

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