3 edition of Empirical predictions of hypervelocity impact damage to the space station found in the catalog.
Empirical predictions of hypervelocity impact damage to the space station
by National Aeronautics and Space Administration, George C. Marshall Space Flight Center in [Marshall Space Flight Center, Ala.]
Written in English
|Statement||by W.K. Rule and K.B. Hayashida.|
|Series||NASA TM -- 103550, NASA technical memorandum -- 103550..|
|Contributions||Hayashida, K. B., George C. Marshall Space Flight Center.|
|The Physical Object|
As discussed in Chapter 2, the ISS program requires that both the Russian and the non-Russian (U.S./European/Japanese) segments have an overall PNP of or better (a maximum 10 percent probability of penetration) over 10 achieve this goal, the ISS will employ different shield designs to protect various critical components. In general, the approach aims to prevent internal damage. nasa technical note nasa tn d i*- hypervelocity impact damage characteristics in beryllium and graphite plates and tubes a by james h. diedricb, irvin jt loeffler, -and a. rtmcmilzan national aeronautics and space administration washington,Cited by: 5.
Generic module wall damage prediction equations for habitable spacecraft crew survivability evaluations Article in International Journal of Impact Engineering –80 June with 8 Reads. The most probable impact velocities are in the range from 0 to 15 km/s for space debris, and between 5 km/s and 30 km/s for meteoroids (denoted as hypervelocity impacts or HVI). At such speeds, the impact of an aluminum sphere of 1 cm diameter deploys the same energy as an exploding hand-grenade, with equally devastating consequences, unless Cited by: 1.
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. The NASA Hypervelocity Impact Technology (HVIT) team has analyzed many spacecraft and conducted thousands of hypervelocity impact tests since its inception almost four decades ago.
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A module of the program facilitates the creation of the data base of experimental results that are used by the damage prediction modules of the code. The user has the choice of three different prediction modules to predict damage to the bumper, Empirical predictions of hypervelocity impact damage to the space station book MLI, and the pressure wall.
Get this from a library. Empirical predictions of hypervelocity impact damage to the space station. [W K Rule; K B Hayashida; George C. Marshall Space Flight Center.]. based computer program to empirically predict hypervelocity impact damage to the Space Station Freedom from space debris.
The main goal was to predict damage to 'the multilayer insulation (MLI). However, to extend the usefulness of the program, damage to other copponents of the space station wall can be predicted as Size: 2MB. Prediction of damage to orbiting space craft due to collisions with hypervelocity space debris is an important issue in the design of Space Station Freedom.
Space station wall structures are designed to absorb impact energy during a : S. Guleyupoglu, R. Smith. Int. hnpact Engng Vol. 10, pp.X/90 $ + Printed in Great Britain Pergamon Press pie INVESTIGATION OF HYPERVELOCITY IMPACT DAMAGE TO SPACE STATION TRUSS TUBES Eric L.
Christiansen Space Science Branch (SN3), NASA Lyndon B. Johnson Space Center Houston, Texas ABSTRACT Fifty-eight hypervelocity impact data shots were used to Cited by: Pergamon Int.
ImpactEngng, Vol. 17, pp. 57~8, Elsevier Science Ltd Printed in Great Britain X/95 $+ HYPERVELOCITY IMPACT DAMAGE INTO SPACE SHUTTLE SURFACES Ronald P. Bernhard*, Erie L. Christiansen, James Hyde*, Jeanne L. Crews NASA Johnson Space Center, Houston, Texas *Lockheed ESC, NASA Rd. 1, Houston, Texas Summary- Cited by: Hypervelocity impact damage prediction in composites: Part I—material model and characterisation Article in International Journal of Impact Engineering 33(1) December with Reads.
brings you the latest images, videos and news from America's space agency. Get the latest updates on NASA missions, watch NASA TV live, and learn about our quest to reveal the unknown and benefit all : Judy Corbett.
post-impact damage are presented. The effects of ejecta channelling in the case of honeycomb shield is highlighted. Hydrocode calculations are proposed to analyse this geometrical effect. 1 INTRODUCTION Space debris represent a real threat to space structures like the International Space Station Author: Paul Deconinck, Pierre-louis Héreil, Jérôme Mespoulet, Hakim Abdulhamid, Christian Puillet.
was performed in the area of hypervelocity impact physics to analyze the damage that occurs when a space vehicle is impacted by a micro-meteoroid or a space debris particle. Specifically, an impact analysis of over test specimens was per-formed to generate a Hypervelocity Impact Damage Database.
The analysisFile Size: 8MB. To perform step (c) above, MSCSurv utilizes selected empirical and analytical ballistic limit relations to determine whether particles penetrate the spacecraft shields.
Step (d) requires use of hypervelocity impact damage prediction equations for hole size, crack length, and depth of Cited by: 1. The Johnson Space Center and the NASA White Sands Test Facility's Remote Hypervelocity Test Laboratory (RHTL) compose a team dedicated to evaluating the environmental effects from micrometeoroid and orbital debris (MMOD) impacts on orbiting spacecraft.
This team has the in-house ability to prepare and plan hypervelocity impact tests, perform. Damage to Spacecraft by Meteoroids and Orbital Debris. Chapter. Structural Damage Prediction and Analysis for Hypervelocity Impacts-Handbook, NASA CR Google Scholar.
Hayashida, K.B. and Tennyson, R.C., Shortliffe, G.,MOD Impact Damage on Composite Materials in Space, 7th International Symposium ‘Materials in Space.
The Hypervelocity Impact Society (HVIS) fosters the development and exchange of technical information in the discipline of hypervelocity impact phenomena by promoting technical excellence, encouraging peer review publications, and holding technical meetings on a periodic basis.
computer program to empirically predict hypervelocity impact damage to the Space Station from space debris. The main goal was to predict damage to the multilayer insulation (MLI).
However, to extend the usefulness of the program, damage to other components of the Space Station wall are predicted as well. Predictions are based on data sets of experimental results obtained from simulating debris impact on spacecraft. One module of MLIBlast facilitates creation of the data base of experimental results that is used by the damage prediction modules of the : William K.
Rule. The program first uses empirical equations to predict hypervelocity impact damage to spacecraft due to space debris in earth orbit. A Whipple  style of spacecraft wall configuration is assumed as is shown In Fig. Then, the program predicts the thermal effects associated with impact damage, including the amount of condensate that would form.
Hypervelocity impacts of space debris, represented by aluminium spheres, against typical shielding systems for the International Space Station (ISS) manned modules are simulated using the AUTODYN-2D hydrocode.
The considered shield type is the double bumper shield, i.e., two separate bumpers placed in front of the structure to be : David Palmieri, Michel Lambert.
To acquire the interference status of typical logic chips in spacecraft caused by plasma generated from a hypervelocity impact, the triple Langmuir probe system established by selfishness is used. of space debris impacts the satellite or space station at such a high velocity, the damage caused on the structure could lead to its scrapping.
As shown in Fig. 1, the amount of the space debris around earth grows rapidly from to [Johnson ()]. Many theoretical and experimental researches on damage of the thin plate induced by the Author: Z.
Zhang, T. Ma, D. Feng, M. Liu. The largest composite structure in space named Space Station Remote Manipulator System (SSRMS), its front face crater and the extensive damage to rear face after hypervelocity impact is.Meso-scale modeling of hypervelocity impact damage in composite laminates Article (PDF Available) in Composites Part B Engineering 74 June with Reads How we measure 'reads'.Impact damage predictions are based on data sets of experimental results obtained from simulating debris impacts on spacecraft using light gas guns on earth.
A module of the program facilitates the creation of the database of experimental results that is used by the damage prediction modules to predict damage to the bumper, the MLI, and the Author: W. K. Rule and V. Giridharan.