Numerical simulation of hypervelocity impact problem for spacecraft shielding elements

2018 ◽  
Vol 150 ◽  
pp. 56-62 ◽  
Author(s):  
M.V. Silnikov ◽  
I.V. Guk ◽  
A.F. Nechunaev ◽  
N.N. Smirnov
Keyword(s):  
Numerical Simulation ◽  
Hypervelocity Impact ◽  
Impact Problem ◽  
Spacecraft Shielding

Experimental Investigation and Numerical Simulation of Porous Volcano Rock Hypervelocity Impact on Whipple Shield of Spacecrafts

2010 ◽  
Vol 452-453 ◽  
pp. 385-388
Author(s):  
Bin Jia ◽  
Gao Jian Liao ◽  
Hai Peng Gong ◽  
Bao Jun Pang
Keyword(s):  
Numerical Simulation ◽  
Space Debris ◽  
Geometrical Model ◽  
Hypervelocity Impact ◽  
Rear Wall ◽  
Projectile Impact ◽  
Gas Gun ◽  
Significant Damage ◽  
Speed Range ◽  
Whipple Shield

All spacecrafts in earth orbit are subject to hypervelocity impact by micro-meteoroids and space debris, which can in turn lead to significant damage and catastrophic failure of spacecraft. Porous volcano rock was adopted as one of micro-meteoroid material due to their similar physical and geometric features. Two-stage light gas gun experiments were carried out for a 6mm diameter volcano rock projectile impact on an Al-Whipple shield within the speed range from 1 km/s to 3 km/s. An ANSYS/LS-DYNA software was employed and justified by experimental results, in which a porous geometrical model was established for volcano rock projectile. The higher speed range was extended from 3 km/s to 10 km/s by numerical simulation. The results of experiments and numerical simulation indicated that major damage on rear wall of the Whipple shield impacted by volcano rock projectile is caused by the fragments of bumper of the shield, which is different from that of aluminum projectile. And 5.5km/s is the critical speed of a 6mm diameter volcano rock projectile impact on the Whipple shield investigated.

PARALLEL SIMULATION OF EXPLOSION IN AN UNLIMITED ATMOSPHERE

2010 ◽  
Vol 24 (13) ◽  
pp. 1349-1352 ◽  
Author(s):  
TIANBAO MA ◽  
CHENG WANG ◽  
GUANGLEI FEI ◽  
JIANGUO NING
Keyword(s):  
Numerical Simulation ◽  
Parallel Algorithm ◽  
Large Scale ◽  
Three Dimensional ◽  
Parallel Simulation ◽  
Data Dependency ◽  
Empirical Results ◽  
Parallel Speedup ◽  
Good Agreement ◽  
Impact Problem

In this paper, a parallel Eulerian hydrocode for the simulation of large scale complicated explosion and impact problem is developed. The data dependency in the parallel algorithm is studied in particular. As a test, the three dimensional numerical simulation of the explosion field in an unlimited atmosphere is performed. The numerical results are in good agreement with the empirical results, indicating that the proposed parallel algorithm in this paper is valid. Finally, the parallel speedup and parallel efficiency under different dividing domain areas are analyzed.

A New Concept for Material Fragmentation Simulation – Nodes Separation

2010 ◽  
Vol 160-162 ◽  
pp. 558-563
Author(s):  
Xiao Tian Zhang ◽  
Guang Hui Jia ◽  
Hai Huang
Keyword(s):  
Experimental Data ◽  
Energy Loss ◽  
High Efficiency ◽  
Hypervelocity Impact ◽  
Separation Method ◽  
Secondary Development ◽  
Separation Mechanism ◽  
Protective Structure ◽  
Aluminum Mesh ◽  
Impact Problem

A method for material fragmentation based on Lagrangian FEM with the concept of nodes separation is proposed. This method is consisted of nodes separation mechanism and elements distortion erosion. In the simulation the nodes of failure elements are separated to form crack and distorted elements are detected and eliminated to prevent singularity. Nodes separation method can greatly improve the energy loss disadvantage in the failure erosion method. Based on LS-dyna secondary development the method is implemented. Hypervelocity impact problem of satellite protective structure is simulated and compared to experimental data for calibration. The performance of multi layer aluminum mesh shield under hypervelocity impact is also evaluated. The results show the high efficiency and applicability of nodes separation method in practical problems.

A Study of Damage in Aluminum Dual-Wall Structure by Hypervelocity Impact of AL-Spheres

2006 ◽  
Vol 324-325 ◽  
pp. 197-200
Author(s):  
Gong Shun Guan ◽  
Bao Jun Pang ◽  
Run Qiang Chi ◽  
Yao Zhu
Keyword(s):  
Numerical Simulation ◽  
Space Debris ◽  
Simulation Method ◽  
Hypervelocity Impact ◽  
Wall Structure ◽  
Rear Wall ◽  
Back Wall ◽  
Projectile Velocity ◽  
Gas Gun ◽  
The Law

In order to simulate and study the hypervelocity impact of space debris on dual-wall structure of spacecrafts, firstly a non-powder two-stage light gas gun was used to launch AL-sphere projectiles. Damage modes in rear wall of dual-wall structure were obtained, and while the law of damage in rear wall depends on projectile diameter and impact velocity were proposed. Finally, numerical simulation method was used to study the law of damage in rear wall. By experiment and numerical simulation of hypervelocity impact on the dual-wall structure by Al-spheres, and it is found that AUTODYN-2D SPH is an effective method of predicting damage in rear wall from hypervelocity impact. By numerical simulation of projectile diameter, projectile velocity and the space between bumper and back wall effect on damage in rear wall by hypervelocity impact, and fitting curves with simulation results, the law of damage in rear wall and dominant factors effect damage in rear wall by hypervelocity impact were proposed.

Protection properties of stuffed corrugated sandwich structures under hypervelocity impact: Numerical simulation

2017 ◽  
Vol 21 (2) ◽  
pp. 532-551 ◽  
Author(s):  
Hao Zhou ◽  
Rui Guo ◽  
Rongzhong Liu
Keyword(s):  
Numerical Simulation ◽  
Sandwich Structure ◽  
Hypervelocity Impact ◽  
Orbital Debris ◽  
Protection Mechanism ◽  
Broad Application ◽  
Waves Propagation ◽  
Debris Cloud ◽  
Impact Characteristics ◽  
The Impact

The stuffed corrugated sandwich structure was proposed for the application in the protection of the spacecraft against orbital debris. In order to investigate the protection properties of the stuffed corrugated sandwich structure under hypervelocity impact, numerical simulations were carried out to analyze the impact characteristics. The hypervelocity impact process was presented and the properties such as shock waves propagation, energy absorption, and expansion of the debris cloud were discussed; corresponding properties of mass equal Whipple structure under impact were analyzed for comparison. The results illustrate the protection mechanism of the stuffed corrugated sandwich subject to hypervelocity impact and show that it has superior protection performance to monolithic plate, which prove that the stuffed corrugated sandwich structure has potentially broad application prospect in the field of spacecraft protection against the orbital debris. The research can provide reference for the design of protection shield of the spacecraft.

Sign in / Sign up

Export Citation Format

Share Document