Hypervelocity impact testing above 10 km/s of advanced orbital debris shields

1996 ◽  
Author(s):  
Eric L. Christiansen ◽  
Jeanne Lee Crews ◽  
Justin H. Kerr ◽  
Lalit C. Chhabildas
Keyword(s):  
Hypervelocity Impact ◽  
Orbital Debris ◽  
Impact Testing

On Protection of Freedom’s Solar Dynamic Radiator From the Orbital Debris Environment: Part I—Preliminary Analysis and Testing

1992 ◽  
Vol 114 (3) ◽  
pp. 135-141
Author(s):  
Jennifer L. Rhatigan ◽  
Eric L. Christiansen ◽  
Michael L. Fleming
Keyword(s):  
Space Debris ◽  
Complex Geometry ◽  
Space Station ◽  
Hypervelocity Impact ◽  
Orbital Debris ◽  
Impact Testing ◽  
Flow Tube ◽  
Material Density ◽  
Particle Population ◽  
Orbital Debris Environment

A great deal of experimentation and analysis has been performed to quantify penetration thresholds of components which will experience orbital debris impacts. Penetration has been found to depend upon mission-specific parameters such as orbital altitude, inclination, and orientation of the component; and upon component specific parameters such as material, density, and the geometry particular to its shielding. Experimental results are highly dependent upon shield configuration and cannot be extrapolated with confidence to alternate shield configurations. Also, current experimental capabilities are limited to velocities which only approach the lower limit of predicted orbital debris velocities. Therefore, prediction of the penetrating particle size for a particular component having a complex geometry remains highly uncertain. This paper describes the approach developed to assess on-orbit survivability of the solar dynamic radiator due to micrometeroid and space debris impacts. Preliminary analyses are presented to quantify the solar dynamic radiator survivability, and include the type of particle and particle population expected to defeat the radiator bumpering (i.e., penetrate a fluid flow tube). Results of preliminary hypervelocity impact testing performed on radiator panel samples (in the 6 to 7 km/sec velocity range) are also presented. Plans for further analyses and testing are discussed. These efforts are expected to lead to a radiator design which will perform to Space Station Freedom requirements over the expected lifetime.

Updates to the DebriSat Project in Support of Improving Breakup Models and Orbital Debris Risk Assessments

2019 ◽  
Author(s):  
Heather Cowardin ◽  
Phillip Anz-Meador ◽  
James Murray ◽  
J.-C. Liou ◽  
Eric Christiansen ◽  
...  
Keyword(s):  
Impact Test ◽  
Laboratory Data ◽  
Hypervelocity Impact ◽  
Orbital Debris ◽  
Impact Testing ◽  
Size Estimation ◽  
Estimation Model ◽  
Radar Sensors ◽  
Derived Properties ◽  
Upper Stage

Abstract Existing DOD and NASA satellite breakup models are based on a key laboratory test, the 1992 Satellite Orbital debris Characterization Impact Test (SOCIT), which has supported many applications and matched on-orbit events involving older satellite designs reasonably well over the years. To update and improve these models, the NASA Orbital Debris Program Office, in collaboration with the Air Force Space and Missile Systems Center, The Aerospace Corporation, and the University of Florida, conducted a hypervelocity impact test using a high-fidelity mock-up satellite, DebriSat, in controlled and instrumented laboratory conditions. DebriSat is representative of present-day LEO satellites, having been constructed with modern spacecraft materials and techniques. The DebriSat fragment ensemble provided a variety of shapes, bulk densities, and dimensions. Fragments down to 2 mm in size are being characterized by their physical and derived properties. A subset of fragments will be analyzed further in laboratory radar and optical facilities to update the existing radar-based NASA Size Estimation Model (SEM) and develop a comparable optical-based SEM. Thoroughly understanding size estimates from ground-based optical and radar sensors is one of the key parameters used in assessing the environment and the risks that debris present to operational spacecraft. The data will inform updates to the current NASA Standard Satellite Breakup Model (SSBM);, which was formulated using laboratory and ground-based measurements of on-orbit fragmentation events to describe an average breakup for spacecraft and upper stage collisions and explosions. DebriSat will extend the laboratory data ensemble. The DebriSat shape and density categories provide a baseline for non-spherical projectile hypervelocity impact testing for damage assessment. The data from these tests, simulations, and analyses will be used to update the NASA Orbital Debris Engineering Model (ORDEM) with more realistic simulations of catastrophic fragmentation events for modern satellites and to assess the risk posed by the orbital debris environment. This paper provides an overview of the project, updates on the characterization process, and the NASA analysis status.

scholarly journals Multifunctional load-bearing aerostructures with integrated space debris protection

2019 ◽  
Vol 304 ◽  
pp. 07003
Author(s):  
Martin Schubert ◽  
Anthanasios Dafnis
Keyword(s):  
Composite Structures ◽  
High Performance ◽  
Space Debris ◽  
Sandwich Panels ◽  
Thermal Control ◽  
Hypervelocity Impact ◽  
Radiation Shielding ◽  
Impact Testing ◽  
Load Bearing ◽  
Protection Capability

In the project multiSat multifunctional composite structures for satellite application have been developed. Functions such as protection against space debris, radiation shielding and passive thermal control have been integrated into the load-bearing composite spacecraft structure by use of suitable materials and components. Sandwich panels have been studied as representative structural parts of a conventional satellite structure. Measures for increased space debris protection include the substitution of the conventional honeycomb core by 3D-printed aluminum cellular structures and the reinforcement of the sandwich panel by integration of high performance fabrics which effectively break up and catch impacting debris particles. This paper describes the development and design of multifunctional sandwich concepts with increased impact protection capability and presents the experimental results of hypervelocity impact testing with different types of CFRP sandwich panels.

Fluidic Deformation Under Hypervelocity Impacts

2014 ◽  
Author(s):  
Andrew Thurber ◽  
Javid Bayandor
Keyword(s):  
Hypervelocity Impact ◽  
Orbital Debris ◽  
Inertial Forces ◽  
Impact Event ◽  
Aerospace Materials ◽  
Computational Framework ◽  
Hypervelocity Impacts ◽  
Dramatic Rise ◽  
Impact Risk

The increased frequency of exploration into space has caused a dramatic rise in the density of debris in orbit. Orbital debris, both natural and man-made, poses an extreme impact risk to satellites and spacecraft. The relative velocities between orbital components and debris can exceed thousands of meters per second, giving rise to immense kinetic energies even for small objects. In such a hypervelocity impact event, the shock pressures exceed the strength of common aerospace materials, and brief shock-induced temperature rises cause melting and vaporization of most structural bodies. Under these extreme conditions, the failure and deformation of solids can resemble fluid flow. By using meshless Lagrangian models in an explicit computational framework, this work identifies analogous fluidic interactions and further quantifies the role of shear and inertial forces in hypervelocity impacts (HVI).

scholarly journals Hypervelocity impact performance of 3D printed aluminum panels

2019 ◽  
Author(s):  
Bruce A. Davis ◽  
Richard A. Hagen ◽  
Robert J. McCandless ◽  
Eric L. Christiansen ◽  
Dana M. Lear
Keyword(s):  
Lattice Structure ◽  
Cell Structure ◽  
Hypervelocity Impact ◽  
Orbital Debris ◽  
Metallic Foam ◽  
Back Side ◽  
Foam Core ◽  
Deep Space ◽  
3D Printed ◽  
Aluminum Panels

Abstract NASA, JSC has been developing a light-weight, multi-functional sandwich core for habitable structure over the last several years. Typically honeycomb-based structures have been and still are a common structural component for many applications in the aerospace industry, unfortunately, honeycomb structures with an ordered, open path through the thickness have served to channel the micro-meteoroid or orbital debris into the pressure wall (instead of disassociating and decelerating). The development of a metallic open cell foam core has been explored to enhance the micro-meteoroid or orbital debris protection, which is heavier than comparable honeycomb-based structures when non-structural requirements for deep space environments (vacuum, micro-meteoroids/orbital debris, and radiation) have not been considered. While the metallic foam core represents a notable improvement in this area, there is an overwhelming need to further reduce the weight of space vehicles; especially when deep space (beyond low earth orbit, or LEO) is considered. NASA, JSC is currently developing a multi-functional sandwich panel using additive machining (3D printing), this effort evaluated the material response of a limited amount of 3D printed aluminum panels under hypervelocity impact conditions. The four 3D printed aluminum panels provided for this effort consisted of three body centric cubic lattice structure core and one kelvin cell structure core. Each panel was impacted once with nominally the same impact conditions (0.34cm diameter aluminum sphere impacting at 6.8 km/s at 0 degrees to surface normal). All tests were impacted successfully, with the aforementioned impact conditions. Each of the test panels maintained their structural integrity from the hypervelocity impact event with no damage present on the back side of the panel for any of the tests. These tests and future tests will be used to enhance development of 3D printed structural panels.

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