3 edition of Hypervelocity particle penetration into spacecraft structures found in the catalog.
Hypervelocity particle penetration into spacecraft structures
Allen J. Richardson
|Statement||Allen J. Richardson.|
|LC Classifications||TL867 .R53 2006|
|The Physical Object|
|Pagination||1 v. (various pagings) :|
|LC Control Number||2007277875|
In the present study, the microspacecraft bulkhead was reduced to the double honeycomb panel, and the projectile oblique hypervelocity impact on the double honeycomb panel was simulated. The distribution of the debris cloud and the damage of a honeycomb sandwich panel were investigated when the incident angles were set to be 60°, 45°, and 30°. The results showed that as incident Cited by: 1. Overview "Hypervelocity" refers to velocities in the range from a few kilometers per second to some tens of kilometers per second. This is especially relevant in the field of space exploration and military use of space, where hypervelocity impacts (e.g. by space debris or an attacking projectile) can result in anything from minor component degradation to the complete destruction of a.
Abstract. Spacecraft that are launched to operate in Earth orbit are susceptible to impacts by meteoroids and pieces of orbital debris (MOD). The effect of a MOD particle impact on a spacecraft depends on where the impact occurs, the size, composition, and speed of the impacting object, the function of the impacted by: 3. SPIE Digital Library Proceedings. Proc. SPIE , Characteristics and Consequences of Orbital Debris and Natural Space Impactors, pg (31 October ); doi: /
The orbital debris hazard to the International Space Station (ISS) and other space structures has focused a significant research effort on the problem of spacecraft shielding design. To date shield design work has relied primarily on experimental hypervelocity impact researchFile Size: 1MB. Hypervelocity impacts generate extreme pressure and shock waves in impacted targets that undergo severe localized deformation within a few microseconds. These impact experiments pose unique challenges in terms of obtaining accurate measurements. Similarly, simulating these experiments is not straightforward. This study proposed an approach to experimentally measure the velocity of the back Cited by: 8.
Past, present, future
manual of equity jurisprudence
Surface areas of graphite regenerated from graphite oxide
I Gotta Be Me!
Bachelor of technology degree in agriculture. Year 3. 1999/2000.
call of the wild
Herring revision of the Binet-Simon test
Pacific-basin capital markets research
Whether the preserving the Protestant religion was the motive unto, or the end, that was designed in the late revolution
Social studies in the elementary school.
evolution of Australian foreign policy, 1938-1965.
Theoretical penetration mechanics of multisheet structures based on discrete debris particle modeling. RICHARDSON; Hypervelocity Impact Conference August Theoretical penetration of hypervelocity projectiles into finite targets /normal impact/ (Theoretical model of penetration process for design problems involving hypervelocity impacts Cited by: 1.
(f) Magnified view of (e) showing sputtered Ag/Inconel layer structure. PARTICLE PENETRATION Vol. 28, No. 3 while creating zones of reaction, also create a delamination zone as a result of the impedance mismatch between the multi-layer by: 4.
Discussion of “Hypervelocity Impact Penetration Phenomena in Aluminum Space Structures”; by William P. Schonberg (July,Vol. 3, No. 3) Journal of Aerospace Engineering April Transition from Nondeformable Projectile Penetration to Semihydrodynamic Penetration. Penetration and ricochet phenomena in oblique hypervelocity impact.
Response of space structures to orbital debris particle impact. International Journal of Impact Engineering, Vol. 14, No. Theoretical penetration of hypervelocity projectiles into finite targets /normal impact/ (Theoretical model of penetration process for design Cited by: The basic design of the STS Experiment suspended a thin film above an Hypervelocity penetration parameters of thin films impact plate.
Fig. shows an exploded diagram of the design which was flown. The thin film holders, machined by BUSSL workers, were made of aluminum (99% pure).Cited by: 5. This data indicates that at the time of STS the fluxes of particles in the size range less than ram have a greater proportion of orbital debris particles than the current environment models predict.
Impact damage into space shuttle surfaces 65 Table by: National Aeronautrcs and Space Administration associated with the oblique hypervelocity impact of spherical projectiles onto multi- damaging ricochet debris particle can be as large as A spacecraft developed for a mission into the meteoroid and space debris environment must include adequate protection against penetration of habitable spacecraft components by such impacts.
Traditional penetration-resistant wall design for long-duration spacecraft consists of a bumperFile Size: 8MB. With regard to hypervelocity impact detection, a sensor network that can be applied on typical spacecraft structures is under development at Fraunhofer EMI (Ernst-Mach-Institut), supported by OHB.
Response of space structures to orbital debris particle impact International Journal of Impact Engineering, Vol. 14, No. Aluminum T87 and H A comparative study of spacecraft wall materials in dual-wall structures under hypervelocity impactCited by: • The Capacitance underneath the cells through the Kapton.
This is the common mode capacitance measured between the. (+) and the (-) wire of the string on one hand and the solar. panel structure on. Composite Structures 19 () Use of Composite Materials in Multi-wall Structures to Prevent Perforation by Hypervelocity Particle Impact William P.
Schonberg & Eve J. Walker Mechanical Engineering Department, University of Alabama in Huntsville, Huntsville, AlabamaUSA ABSTRACT All earth-orbiting spacecraft are susceptible to impacts by meteoroids and pieces of Cited by: Hazards of Hypervelocity Impacts on Spacecraft.
(Meteoroid hazard to spacecraft materials and structures, using particle-projection techniques) Spacecraft wall design for increased protection against penetration by space debris impacts. WILLIAM SCHONBERG and Cited by: A representative carbon fiber reinforced plastic/aluminum honeycomb sandwich panel (CFRP/Al HC SP) spacecraft structure has been modeled in the hydrocode AUTODYN using the state-of-the-art ADAMMO material model [Riedel W, Harwick W, White D, Clegg R.
Advanced material damage models for numerical simulation by: Spacecraft structures are exposed to hypervelocity impact derived from space debris and micro-meteoroids. The effect of the flyer material properties impacting upon different targets at hypervelocity was carried out using a laser driven flyer (LDF) system for simulating hypervelocity impact.
At hypervelocity impact both the. Hypervelocity impact on long duration and large size spacecraft by meteoroid and space debris is a threat to its safety operation that can in turn lead to significant damage and catastrophic failure. The ionization produced by a.
particle penetrating the thin films is measured and also serves to initiate the "start" and "stop" pulses for the time-of-flight determination, The amount af ionization is indicative of the particle energy and composikion but the quantitative relationship is, as yet, not fully Size: 1MB.
Evaluation of craters formation in hypervelocity impact of debris particles on solid structures Article (PDF Available) in Acta Astronautica 65(11) December with 83 Reads. ABSTRACT: Damage due to hypervelocity impact (HVI) of micrometeoroid and space debris (MMOD) is a common threat in the current space environment for any spacecraft orbiting the Earth and for future launches of new spacecraft.
For this reason, the choice of structure and protection materials is an important issue during the design and. SCREENING TESTS FOR ENHANCED SHIELDING AGAINST HYPERVELOCITY PARTICLE IMPACTS FOR FUTURE UNMANNED SPACECRAFT Robin Putzar (1), Jan Hupfer, Gwenaëlle Aridon(2), Bernard Gergonne (2), Matthieu.
The Solution. Engineers and technicians design, test, and analyze spacecraft systems to reduce the risk from MMOD particle impact. The team has performed thousands of hypervelocity impact tests that have yielded numerous efficient and effective shielding designs, as well as detailed data on the effect of MMOD impact on various spacecraft.
Material Phase Transformation Effects upon Performance of Spaced Bumper Systems. Analysis of Space Structures Subject to Hypervelocity Impact. Review of hypervelocity penetration theories. International Journal of Impact Engineering, Vol. 5, No. Cited by: The average velocity is fre.
quently assumed to be 30 km/sec. The velocity of the spacecraft (7 km/sec) should be added vectorially to this value, but it produces little change in the result. 30 km/sec shall be adopted in the present study as the average velocity of particles rela- tive to the Size: KB.