METEOROID AND ORBITAL DEBRIS

Jones, J., Meteoroid Engineering Model Final Report, SEE/CR-2004-400, George C. Marshall Space Flight Center, Marshall Space Flight Center, AL 35812, National Aeronautics and Space Administration, Washington, DC 20546-0001, Prepared for NASA’s Space Environments and Effects (SEE) Program by the University of Western Ontario; June 2004, pp. 48.

Keywords: sporadic, meteoroid, parametric, model, fluxes, spatial, distribution, comet, particle, source

Abstract: A parametric model of the spatial distribution of sporadic meteoroids has been developed by taking their primary source to be short-period comets with aphelia less than 7 AU, which shows to be the major source of dust released through the sublimation of cometary ices. The model is constrained to fit the observed distribution of particles deduced from the zodiacal light measurements of Helios I and II as well as Earth-based radio-meteor observations. Contributions to the sporadic meteor complex from long-period comets are also considered. An origin for the North and South Toroidal source of sporadic meteors is proposed and the results of calculations for the likely characteristics of asteroidal meteors are also presented. Predicted fluxes and radiant distributions of sporadic meteors in the region between Mercury and Mars are shown as well. The effects of the gravitational shielding and focusing of the planets are also included and show that flux enhancements of up to 70% are possible at some locations.

A.J. Piekutowski, A New Technique for Achieving Impact Velocities, NASA/CR-2001-210990, George C. Marshall Space Flight Center Marshall Space Flight Center, AL 35812, University of Dayton Research Institute, Dayton, OH 45469-0182, Prepared for NASA's Space Environments and Effects (SEE) Program Technical Monitor: Angie Nolen, May 2001, pp. 78. 

Keywords: hypervelocity launchers; two-stage, light-gas guns; three-stage, light-gas guns; high-pressure hydrogen; augmented acceleration

Abstract: This contractor Report describes and presents the results of work that was done in an attempt to develop an augmented acceleration technique that would launch small projectiles of known shape, mass, and state to velocities of 10 km/sec and higher. The higher velocities were to be achieved by adding a third stage to a conventional two-stage, light-gas gun and using a modified firing cycle for the third stage. the technique did not achieve the desired results and was modified for use during the development program. Since the design of the components used for the augmented-acceleration, three-stage launcher could be readily adapted for use as a three-stage launcher that used a single-stage acceleration cycle; the remainder of the contract period was spent performing test firings using the modified three-state launcher. Work with the modified three-stage launcher, although not complete, did produce test firings in which an 0.11-g cylindrical nylon projectile was launched to a velocity of 8.65 km/sec. 

W. P. Strong, Characterizing Secondary Debris Impact Ejecta, NASA/CR-1999-209561, NASA, Marshall Space Flight Center, Alabama 35812, pp. 90.

Keywords: Hypervelocity Impact, Meteroids, Orbital Debris

Abstract: All spacecraft in low-Earth orbit are subject to high-speed impacts by meteoroids and orbital debris particles. These impacts can damage flight-critical systems, which can in turn lead to catastrophic failure of the spacecraft. Therefore, the design of a spacecraft for an Earth-orbiting mission must take into account the possibility of such impacts and their effects on the spacecraft structure and on all of its exposed subsystem components. In addition to threatening the operation of the spacecraft itself, on-orbit impacts also generate a significant amount of ricochet particles. These high-speed particles can destroy critical external spacecraft subsystems and also increase the contamination of the orbital environment.

This report presents a summary of the work performed towards the development of an empirical model that Characterizes the secondary ejecta created by a high speed impacta on a typical aerospace structural surface.

Cynthia Belk*, Jennnifer Robinson, Margaret Alexander, William Cooke** and Steven Pavelitz***, Meteoroids and Orbital Debris: Effects on Spacecraft, NASA RP-1408, Electromagnetics and Aerospace Environments Branch, Systems Analysis and Integration Laboratory, Science and Engineering Directorate, NASA Marshall Space Flight Center, AL 35812 and *Universities Space Research Association, **Computer Sciences Corporation, ***Sverdrup Technology, Inc., August 1997, pp. 24.

Keywords: natural space environment; spacecraft environment; environmental effects and impacts; meteoroids and orbital debris; orbital debris source, size, lifetime, and mitigation source, size, lifetime and mitigation

Abstract: The natural space environment is characterized by many complex and subtle phenomena hostile to spacecraft. The effects of these phenomena impact spacecraft design, development, and operations. Space systems become increasingly susceptible to the space environment as use of composite materials and smaller, faster electronics increases. This trend makes an understanding of the natural space environment essential to accomplish overall mission objectives, especially in the current climate of better/cheaper/faster. Meteroids are naturally occurring phenomena in the natural space environment. Orbital debris is manmade space litter accumulated in Earth orbit from the exploration of space. Descriptions are presented of orbital debris source, distribution, size, lifetime, and mitigation measures. This primer is one in a series of NASA Reference Publications currently being developed by the Electromagnetics and Aerospace Environments Branch, Systems Analysis and Integration Laboratory, Marshall Space Flight Center, National Aeronautics and Space Administration.

Orbital Debris Document Repository

Single Wall Penetration Equations

Estimation of Meteoroid Flux for the Upcoming Leonid Storms

K.B. Hayashida and and J.H. Robinson, TSS Tether Cable Meteoroid/Orbital Debris Damage Analysis, NASA TM-108404 , Structures and Dynamics Laboratory, NASA Marshall Space Flight Center, AL 35812, April 1993, (N93-27023).

Abstract: This report summarizes the damage analysis performed on the tether cable used for the tethered satellite system (TSS), for the damage that could be caused by meteoroid or orbital debris impacts. The TSS consists of a tethered satellite deployer and a tethered satellite. The analytical studies were performed at Marshall Space Flight Center (MSFC) with the results from the following tests: (1) hypervelocity impact tests to determine the "critical" meteoroid particle diameter, i.e., the maximum size of a meteoroid particle which can impact the tether cable without causing "failure"; (2) electrical resistance tests on the damaged and undamaged tether cable to determine if degradation of current flow occurred through the damaged tether cables; and (3) tensile load tests to verify the load carrying capability of the damaged tether cables. Finally, the HULL hydrodynamic computer code was used to simulate the hypervelocity impact of the tether cable by particles at velocities higher than can be tested, to determine the extent of the expected tether damage.

The National Science and Technology Council Committee on Transportation Research and Development, Interagency Report on Orbital Debris

Abstract: Taking into consideration the results of the National Research Council orbital debris technical assessment study funded by the National Aeronautics and Space Administration, an Interagency Working Group under the direction of the Office of Science and Technology Policy and the National Security Council revised and updated the 1989 Report on Orbital Debris. This 1995 Report contains an up-to-date portrait of our measurement, modeling, and mitigation efforts and a set of recommendations outlining specific steps we should pursue, both domestically and internationally, to minimize the potential hazards posed by orbital debris.

N. C. Elfer, User's Manual for Space Debris Surfaces (SD_SURF), NASA CR-4705, Prepared for Structures and Dynamics Laboratory, Science and Engineering Directorate, NASA Marshall Space Flight Center, AL 35812, Contract NAS8-38856, by Lockheed Martin Marietta Manned Space Systems New Orleans, LA 70189, February 1996, pp. 208.

Keywords: bumpers, debris shields, hypervelocity impacts, impact, meteoroids, orbital debris, probability of no penetration, space debris

Abstract: A unique collection of computer codes, Space Debris Surfaces (SD_SURF), have been developed to assist in the design and analysis of space debris protection systems. SD_SURF calculates and summarizes a vehicle's vulnerability to space debris as a function of impact velocity and obliquity. An SD_SURF analysis will show which velocities and obliquities are the most probable to cause a penetration. This determination can help the analyst select a shield design which is best suited to the predominant penetration mechanism. The analysis also indicates the most suitable parameters for development or verification testing. The SD_SURF programs offer the option of either FORTRAN programs and Microsoft EXCEL spreadsheets and macros. The FORTRAN programs work with BUMPERII version 1.2a or 1.3 (COSMIC released). The EXCEL spreadsheets and macros can be used independently or with selected output from the SD_SURF FORTRAN programs.

N. C. Elfer, Structural Damage Prediction and Analysis for Hypervelocity Impacts - Handbook, NASA CR-4706, Prepared for Structures and Dynamics Laboratory, Science and Engineering Directorate, NASA Marshall Space Flight Center, AL 35812, Contract NAS8-38856, by Lockheed Martin Marietta Manned Space Systems, New Orleans, LA 70189, February 1996, pp. 320.

Keywords: aluminum alloys, bumpers, debris shields, fracture mechanics, hypervocity impacts, impact, meteoroids, orbital debris

Abstract: This handbook reviews the analysis of structural damage on spacecraft due to hypervelocity impacts by meteoroid and space debris. These impacts can potentially cause structural damage to a Space Station module wall. This damage ranges from craters, bulges, minor penetrations, and spall to critical damage associated with a large hole, or even rupture. The analysis of damage depends on a variety of assumptions and the area of most concern is at a velocity beyond well controlled laboratory capability. In the analysis of critical damage, one of the key questions is how much momentum can actually be transfered to the pressure vessel wall. When penetration occurs without maximum bulging at high velocity and obliquities (if less momentum is deposited in the rear wall), then large tears and rupture may be avoided. In analysis of rupture effects of cylindrical geometry, biaxial loading, bending of the crack, a central hole strain rate and R-curve effects are discussed.

A. J. Piekutowski, Formation and Description of Debris Clouds Produced by Hypervelocity Impact, NASA CR-4707, Prepared for Structures and Dynamics Laboratory, Science and Engineering Directorate NASA Marshall Space Flight Center, AL 35812, Contract NAS8-38856, by University of Dayton Research Institute, Dayton, Ohio 45469-0182, February 1996, pp. 266.

Keywords: bumper shield, debris cloud, fragmentation, fragment-size, hole size, hypervelocity impact, meteoroids, multicomponent shield

Abstract: Forty-one light gas gun tests were performed to examine the formation of debris clouds produced by the hypervelocity impact of aluminum spheres with thin aluminum sheets at normal incidence. Two tests were performed with the bumper sheet at an oblique angle. All tests provided multiple-exposure, orthogonal-pair flash radiographs of the debris clouds produced by the impacts. The failure and fragmentation of the aluminum sphere was observed to be an orderly process. Measurements taken from the flash radiographs were used to determine: (1) the velocity of a number of characteristic points in the debris clouds; (2) fragment sizes; and (3) fragment-size distributions. Sphere diameter, bumper-sheet thickness, and impact velocity were the primary test variables. The effects of bumper-thickness-to-projectile-diameter ratio, impact velocity, and material on the debris-cloud formation process were evaluated. A collection of models was developed and used to describe the formation of various debris-cloud elements. A method for estimating the state of the material in a debris cloud was developed. Features observed in the radiographs of the debris clouds indicated that the estimation procedure was reasonable. Analyses of the holes formed in the bumper sheets and damage patterns produced on witness plates behind the bumpers complemented the analyses of the flash radiographs.
 

    
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