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.

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

1992 ◽  
Vol 114 (3) ◽  
pp. 142-149 ◽  
Author(s):  
Jennifer L. Rhatigan ◽  
Eric L. Christiansen ◽  
Michael L. Fleming
Keyword(s):  
Space Debris ◽  
Particle Density ◽  
Space Station ◽  
Impact Angle ◽  
Hypervelocity Impact ◽  
Test Results ◽  
Environmental Threat ◽  
Extensive Test ◽  
Specific Configuration ◽  
Orbital Debris Environment

Recent progress to better understand the environmental threat of micrometeoroid and space debris to the solar dynamic radiator for the Space Station Freedom power system is reported. The objective was to define a design which would perform to survivability requirements over the expected lifetime of the radiator. A previous paper described the approach developed to assess on-orbit survivability of the solar dynamic radiator due to micrometeoroid and space debris impacts. Preliminary analyses were presented to quantify the solar dynamic radiator survivability. These included the type of particle and particle population expected to defeat the radiator bumpering. Results of preliminary hypervelocity impact (HVI) testing performed on radiator panel samples were also presented. This paper presents results of a more extensive test program undertaken to further define the response of the solar dynamic radiator to HVI. Tests were conducted on representative radiator panels (under ambient, nonoperating conditions) over a range of particle size, particle density, impact angle, and impact velocity. Target parameters were also varied. Data indicate that analytical penetration predictions are conservative (i.e., pessimistic) for the specific configuration of the solar dynamic radiator. Test results are used to define more rigorously the solar dynamic radiator reliability with respect to HVI. Test data, analyses, and survivability results are presented.

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.

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

Orbital debris environment as measured at the Mir space station

1996 ◽  
Author(s):  
Carl R. Maag ◽  
Sunil P. Deshpande ◽  
Tim J. Stevenson ◽  
Paul S. Mitzen
Keyword(s):  
Space Station ◽  
Orbital Debris ◽  
Orbital Debris Environment

scholarly journals The Self-Healing Capability of Carbon Fibre Composite Structures Subjected to Hypervelocity Impacts Simulating Orbital Space Debris

2012 ◽  
Vol 2012 ◽  
pp. 1-16 ◽  
Author(s):  
B. Aïssa ◽  
K. Tagziria ◽  
E. Haddad ◽  
W. Jamroz ◽  
J. Loiseau ◽  
...  
Keyword(s):  
Composite Structures ◽  
Space Debris ◽  
Fibre Composite ◽  
Space Station ◽  
Short Review ◽  
Hypervelocity Impact ◽  
The Self ◽  
Space Environment ◽  
Self Healing ◽  
Carbon Fibre Composite

The presence in the space of micrometeoroids and orbital debris, particularly in the lower earth orbit, presents a continuous hazard to orbiting satellites, spacecrafts, and the international space station. Space debris includes all nonfunctional, man-made objects and fragments. As the population of debris continues to grow, the probability of collisions that could lead to potential damage will consequently increase. This work addresses a short review of the space debris “challenge” and reports on our recent results obtained on the application of self-healing composite materials on impacted composite structures used in space. Self healing materials were blends of microcapsules containing mainly various combinations of a 5-ethylidene-2-norbornene (5E2N) and dicyclopentadiene (DCPD) monomers, reacted with ruthenium Grubbs' catalyst. The self healing materials were then mixed with a resin epoxy and single-walled carbon nanotubes (SWNTs) using vacuum centrifuging technique. The obtained nanocomposites were infused into the layers of woven carbon fibers reinforced polymer (CFRP). The CFRP specimens were then subjected to hypervelocity impact conditions—prevailing in the space environment—using a home-made implosion-driven hypervelocity launcher. The different self-healing capabilities were determined and the SWNT contribution was discussed with respect to the experimental parameters.

scholarly journals Optical Characterization of DebriSat Fragments in Support of Orbital Debris Environmental Models

2021 ◽  
Author(s):  
Heather M. Cowardin ◽  
John M. Hostetler ◽  
James I. Murray ◽  
Jacqueline A. Reyes ◽  
Corbin L. Cruz
Keyword(s):  
Optical Measurement ◽  
Low Earth Orbit ◽  
Hypervelocity Impact ◽  
Orbital Debris ◽  
Laboratory Research ◽  
Size Estimation ◽  
Material Density ◽  
Environmental Models ◽  
Research Activities

AbstractThe NASA Orbital Debris Program Office (ODPO) develops, maintains, and updates orbital debris environmental models, such as the NASA Orbital Debris Engineering Model (ORDEM), to support satellite designers and operators by estimating the risk from orbital debris impacts on their vehicles in orbit. Updates to ORDEM utilize the most recent validated datasets from radar, optical, and in situ sources to provide estimates of the debris flux as a function of size, material density, impact speed, and direction along a mission orbit. On-going efforts within the NASA ODPO to update the next version of ORDEM include a new parameter that highly affects the damage risk – shape. Shape can be binned by material density and size to better understand the damage assessments on spacecraft. The in situ and laboratory research activities at the NASA ODPO are focused on cataloging and characterizing fragments from a laboratory hypervelocity-impact test using a high-fidelity, mock-up satellite, DebriSat, in controlled and instrumented laboratory conditions. DebriSat is representative of present-day, low Earth orbit satellites, having been constructed with modern spacecraft materials and techniques. The DebriSat fragment ensemble provides 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 is being analyzed further in NASA’s Optical Measurement Center (OMC) using broadband, bidirectional reflectance measurements to provide insight into the optical-based NASA Size Estimation Model. Additionally, pre-impact spectral measurements on a subset of DebriSat materials were acquired for baseline material characterization. This paper provides an overview of DebriSat, the status of the project, and ongoing fragment characterization efforts within the OMC.

Study of Burst Conditions of Thin-Walled Pressure Vessels Subjected to Hypervelocity Impact

2003 ◽  
Author(s):  
Igor Ye. Telitchev
Keyword(s):  
Space Debris ◽  
Space Station ◽  
Pressure Vessels ◽  
Hypervelocity Impact ◽  
Unstable Crack ◽  
Linear Fracture ◽  
Debris Particles ◽  
Thin Walled ◽  
Catastrophic Fracture ◽  
Onboard System

The present paper is devoted to analysis of burst conditions of thin-walled cylindrical pressure vessels subjected to hypervelocity impact of space debris particles. Two types of gas-filled pressure vessels onboard the International Space Station were considered: inhabited or laboratory pressurized modules and onboard system vessels with a gas under high pressure. The central concern of this study is to determine the border between simple perforation and catastrophic fracture of gas-filled pressure vessels of both types under hypervelocity impact. Non-linear fracture mechanics techniques were used to analyze and predict whether a vessel perforation will lead to mere leakage of gas, or whether unstable crack propagation will occur that could lead to catastrophic fracture of the vessel. Damage patterns and mechanisms leading to unstable crack growth are discussed. A model of fracture of an impact damaged pressure vessel is presented. A developed model was successfully applied to the simulation of experimental results obtained at Ernst-Mach-Institute (Germany).

Simulation of Small-Size Space Debris Impact on the Protective Shield of a Transformable Trap

2021 ◽  
pp. 99-111
Author(s):  
P.V. Prosuntsov ◽  
A.A. Alekseev ◽  
E.O. Zherebtsova
Keyword(s):  
Space Debris ◽  
Effective Means ◽  
Reaction Force ◽  
Space Station ◽  
Time History ◽  
Hypervelocity Impact ◽  
Design Parameters ◽  
Load Bearing ◽  
Protective Shield ◽  
The Impact

The growth in the number of space debris, especially small-size debris undetectable by radars, urges the development of protective equipment for the crucial satellites and space station. Passive multilayer shields are the most effective means of protection. As the shields are big, it makes sense to make them out of flexible composite materials that allow them to be deployed in orbit. The article determines the loads acting on the composite load-bearing frame of the trap for small-size debris during impact. For a rational choice of the structural trap layout and optimization of its design parameters it is critical to know these loads. The hypervelocity impact of the projectile on the shield was modeled in the Altair Radioss software package using a combined model based on the Smoothed Particle Hydrodynamic (SPH) method and mesh finite elements. The simulation of the shield penetration at various locations was carried out. For each simulation case, a time history of the reaction force in the attachment point of the protective shield to the load-bearing frame was determined. It was shown that the maximum load of about 2000 N acts for around 6 milliseconds on the joint closest to the impact point for the debris projectile size of 10 mm and velocity of 2 km/s.

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